WorldWideScience

Sample records for model rocket curriculum

  1. Model Rockets and Microchips.

    Science.gov (United States)

    Fitzsimmons, Charles P.

    1986-01-01

    Points out the instructional applications and program possibilities of a unit on model rocketry. Describes the ways that microcomputers can assist in model rocket design and in problem calculations. Provides a descriptive listing of model rocket software for the Apple II microcomputer. (ML)

  2. Measuring Model Rocket Engine Thrust Curves

    Science.gov (United States)

    Penn, Kim; Slaton, William V.

    2010-01-01

    This paper describes a method and setup to quickly and easily measure a model rocket engine's thrust curve using a computer data logger and force probe. Horst describes using Vernier's LabPro and force probe to measure the rocket engine's thrust curve; however, the method of attaching the rocket to the force probe is not discussed. We show how a…

  3. Measuring Model Rocket Engine Thrust Curves

    Science.gov (United States)

    Penn, Kim; Slaton, William V.

    2010-01-01

    This paper describes a method and setup to quickly and easily measure a model rocket engine's thrust curve using a computer data logger and force probe. Horst describes using Vernier's LabPro and force probe to measure the rocket engine's thrust curve; however, the method of attaching the rocket to the force probe is not discussed. We show how a…

  4. Computational modeling of nuclear thermal rockets

    Science.gov (United States)

    Peery, Steven D.

    1993-01-01

    The topics are presented in viewgraph form and include the following: rocket engine transient simulation (ROCETS) system; ROCETS performance simulations composed of integrated component models; ROCETS system architecture significant features; ROCETS engineering nuclear thermal rocket (NTR) modules; ROCETS system easily adapts Fortran engineering modules; ROCETS NTR reactor module; ROCETS NTR turbomachinery module; detailed reactor analysis; predicted reactor power profiles; turbine bypass impact on system; and ROCETS NTR engine simulation summary.

  5. Rocket

    Directory of Open Access Journals (Sweden)

    K. Karmarkar

    1952-09-01

    Full Text Available The rockets of World War II represented, not the invention of a new weapon, but the modernization of a very old one. As early as 1232 A.D, the Chinese launched rockets against the Mongols. About a hundred years later the knowledge of ledge of rockets was quite widespread and they were used to set fire to buildings and to terrorize the enemy. But as cannon developed, rockets declined in warfare. However rockets were used occasionally as weapons till about 1530 A.D. About this time improvements in artillery-rifled gun barrel and mechanism to absorb recoil-established a standard of efficiency with which rockets could not compare until World War II brought pew conditions

  6. The Chameleon Solid Rocket Propulsion Model

    Science.gov (United States)

    Robertson, Glen A.

    2010-01-01

    The Khoury and Weltman (2004a and 2004b) Chameleon Model presents an addition to the gravitation force and was shown by the author (Robertson, 2009a and 2009b) to present a new means by which one can view other forces in the Universe. The Chameleon Model is basically a density-dependent model and while the idea is not new, this model is novel in that densities in the Universe to include the vacuum of space are viewed as scalar fields. Such an analogy gives the Chameleon scalar field, dark energy/dark matter like characteristics; fitting well within cosmological expansion theories. In respect to this forum, in this paper, it is shown how the Chameleon Model can be used to derive the thrust of a solid rocket motor. This presents a first step toward the development of new propulsion models using density variations verse mass ejection as the mechanism for thrust. Further, through the Chameleon Model connection, these new propulsion models can be tied to dark energy/dark matter toward new space propulsion systems utilizing the vacuum scalar field in a way understandable by engineers, the key toward the development of such systems. This paper provides corrections to the Chameleon rocket model in Robertson (2009b).

  7. Combining Undergraduate Student Curriculum, Research, and Outreach: High-altitude Balloon and Rockets

    Science.gov (United States)

    Davis, E. J.; Nielsen, K.

    2015-12-01

    The Society of Physics Students chapter at Utah Valley University (UVU) recently established a high altitude balloon project to provide students with research opportunities. This highly successful program involves students not only from physics but also from other STEM fields and non-STEM subjects, and as such acts as a unique outreach program for the department of physics. Examples of experiments performed with the balloon project are: 3D-acceleration measurements, altitude/pressure/temperature measurements, ozone monitoring, bio-aerosol collection, and solar panel performance output. All these experiment are designed and build by groups of students either as part of research projects or through class participation as the projects link with the curriculum in several courses. Most recently, a group of UVU students have initiated the implementation of small rockets capable of carrying payloads to this high-altitude program. Both balloon and rocket platforms are fundamental in-situ measuring techniques for numerous geoscience subjects, and are arguably best illustrated by the NASA balloon and sounding rocket programs. In this presentation, we give an overview of the program and how it is 1) being implemented into the curriculum, 2) provide unique research opportunities for students, and 3) specific outreach activities.

  8. Integrated model of a composite propellant rocket

    Science.gov (United States)

    Miccio, Francesco

    2016-12-01

    The combustion of composite solid propellants was investigated and an available numerical model was improved for taking into account the change of pressure, when the process occurs in a confined environment, as inside a rocket. The pressure increase upon ignition is correctly described by the improved model for both sandwich and dispersed particles propellants. In the latter case, self-induced fluctuations in the pressure and in all other computed variables occur, as consequence of the periodic rise and depletion of oxidizer particles from the binder matrix. The comparison with the results of the constant pressure model shows a different fluctuating profile of gas velocity, with a possible second order effect induced by the pressure fluctuations.

  9. Assumed PDF modeling in rocket combustor simulations

    Science.gov (United States)

    Lempke, M.; Gerlinger, P.; Aigner, M.

    2013-03-01

    In order to account for the interaction between turbulence and chemistry, a multivariate assumed PDF (Probability Density Function) approach is used to simulate a model rocket combustor with finite-rate chemistry. The reported test case is the PennState preburner combustor with a single shear coaxial injector. Experimental data for the wall heat flux is available for this configuration. Unsteady RANS (Reynolds-averaged Navier-Stokes) simulation results with and without the assumed PDF approach are analyzed and compared with the experimental data. Both calculations show a good agreement with the experimental wall heat flux data. Significant changes due to the utilization of the assumed PDF approach can be observed in the radicals, e. g., the OH mass fraction distribution, while the effect on the wall heat flux is insignificant.

  10. Ablative Rocket Deflector Testing and Computational Modeling

    Science.gov (United States)

    Allgood, Daniel C.; Lott, Jeffrey W.; Raines, Nickey

    2010-01-01

    A deflector risk mitigation program was recently conducted at the NASA Stennis Space Center. The primary objective was to develop a database that characterizes the behavior of industry-grade refractory materials subjected to rocket plume impingement conditions commonly experienced on static test stands. The program consisted of short and long duration engine tests where the supersonic exhaust flow from the engine impinged on an ablative panel. Quasi time-dependent erosion depths and patterns generated by the plume impingement were recorded for a variety of different ablative materials. The erosion behavior was found to be highly dependent on the material s composition and corresponding thermal properties. For example, in the case of the HP CAST 93Z ablative material, the erosion rate actually decreased under continued thermal heating conditions due to the formation of a low thermal conductivity "crystallization" layer. The "crystallization" layer produced near the surface of the material provided an effective insulation from the hot rocket exhaust plume. To gain further insight into the complex interaction of the plume with the ablative deflector, computational fluid dynamic modeling was performed in parallel to the ablative panel testing. The results from the current study demonstrated that locally high heating occurred due to shock reflections. These localized regions of shock-induced heat flux resulted in non-uniform erosion of the ablative panels. In turn, it was observed that the non-uniform erosion exacerbated the localized shock heating causing eventual plume separation and reversed flow for long duration tests under certain conditions. Overall, the flow simulations compared very well with the available experimental data obtained during this project.

  11. Rocketdyne/Westinghouse nuclear thermal rocket engine modeling

    Science.gov (United States)

    Glass, James F.

    1993-01-01

    The topics are presented in viewgraph form and include the following: systems approach needed for nuclear thermal rocket (NTR) design optimization; generic NTR engine power balance codes; rocketdyne nuclear thermal system code; software capabilities; steady state model; NTR engine optimizer code-logic; reactor power calculation logic; sample multi-component configuration; NTR design code output; generic NTR code at Rocketdyne; Rocketdyne NTR model; and nuclear thermal rocket modeling directions.

  12. ACTIVE MODEL ROCKET STABILIZATION VIA COLD GAS THRUSTERS

    OpenAIRE

    Malyuta, Danylo; Collaud, Xavier; Martins Gaspar, Mikael; Rouaze, Gautier Marie Pierre; Pictet, Raimondo; Ivanov, Anton; Mullin, Nickolay

    2015-01-01

    This paper describes the development and testing of a reaction control system (RCS) for a model rocket named FALCO-4. The rocket uses cold gas jets to keep itself perfectly vertical at low speeds. We first describe the mechanical layout of FALCO-4 and the characteristics of the cold gas propulsion system. We then propose a dynamical model of the rocket and a control scheme based on decoupled PID regulators for roll, pitch and yaw. The control scheme is then evaluated based on MATLAB simulatio...

  13. Dynamical Model of Rocket Propellant Loading with Liquid Hydrogen

    Data.gov (United States)

    National Aeronautics and Space Administration — A dynamical model describing the multi-stage process of rocket propellant loading has been developed. It accounts for both the nominal and faulty regimes of...

  14. Burn Rate Modelling of Solid Rocket Propellants (Short Communication

    Directory of Open Access Journals (Sweden)

    A.R. Kulkarni

    1998-01-01

    Full Text Available A generalised model of burning of a solid rocket propellant based on kinetics of propellant hasbeen developed. A complete set of variables has been formed after examining the existing models.Buckingham theorem provides the functional form of the model, such that the existing models are thesubcases of this generalised model. This proposed model has been validated by an experimental data.

  15. This "Is" Rocket Science!

    Science.gov (United States)

    Keith, Wayne; Martin, Cynthia; Veltkamp, Pamela

    2013-01-01

    Using model rockets to teach physics can be an effective way to engage students in learning. In this paper, we present a curriculum developed in response to an expressed need for helping high school students review physics equations in preparation for a state-mandated exam. This required a mode of teaching that was more advanced and analytical…

  16. Application of Chaboche Model in Rocket Thrust Chamber Analysis

    Science.gov (United States)

    Asraff, Ahmedul Kabir; Suresh Babu, Sheela; Babu, Aneena; Eapen, Reeba

    2017-06-01

    Liquid Propellant Rocket Engines are commonly used in space technology. Thrust chamber is one of the most important subsystems of a rocket engine. The thrust chamber generates propulsive thrust force for flight of the rocket by ejection of combustion products at supersonic speeds. Often double walled construction is employed for these chambers. The thrust chamber investigated here has its hot inner wall fabricated out of a high thermal conductive material like copper alloy and outer wall made of stainless steel. Inner wall is subjected to high thermal and pressure loads during operation of engine due to which it will be in the plastic regime. Main reasons for the failure of such chambers are fatigue in the plastic range (called as low cycle fatigue since the number of cycles to failure will be low in plastic range), creep and thermal ratcheting. Elasto plastic material models are required to simulate the above effects through a cyclic stress analysis. This paper gives the details of cyclic stress analysis carried out for the thrust chamber using different plasticity model combinations available in ANSYS (Version 15) FE code. The best model among the above is applied in the cyclic stress analysis of two dimensional (plane strain and axisymmetric) and three dimensional finite element models of thrust chamber. Cyclic life of the chamber is calculated from stress-strain graph obtained from above analyses.

  17. SRM (Solid Rocket Motor) propellant and polymer materials structural modeling

    Science.gov (United States)

    Moore, Carleton J.

    1988-01-01

    The following investigation reviews and evaluates the use of stress relaxation test data for the structural analysis of Solid Rocket Motor (SRM) propellants and other polymer materials used for liners, insulators, inhibitors, and seals. The stress relaxation data is examined and a new mathematical structural model is proposed. This model has potentially wide application to structural analysis of polymer materials and other materials generally characterized as being made of viscoelastic materials. A dynamic modulus is derived from the new model for stress relaxation modulus and is compared to the old viscoelastic model and experimental data.

  18. Facility for cold flow testing of solid rocket motor models

    Science.gov (United States)

    Bacchus, D. L.; Hill, O. E.; Whitesides, R. Harold

    1992-02-01

    A new cold flow test facility was designed and constructed at NASA Marshall Space Flight Center for the purpose of characterizing the flow field in the port and nozzle of solid propellant rocket motors (SRM's). A National Advisory Committee was established to include representatives from industry, government agencies, and universities to guide the establishment of design and instrumentation requirements for the new facility. This facility design includes the basic components of air storage tanks, heater, submicron filter, quiet control valve, venturi, model inlet plenum chamber, solid rocket motor (SRM) model, exhaust diffuser, and exhaust silencer. The facility was designed to accommodate a wide range of motor types and sizes from small tactical motors to large space launch boosters. This facility has the unique capability of testing ten percent scale models of large boosters such as the new Advanced Solid Rocket Motor (ASRM), at full scale motor Reynolds numbers. Previous investigators have established the validity of studying basic features of solid rocket motor development programs include the acquisition of data to (1) directly evaluate and optimize the design configuration of the propellant grain, insulation, and nozzle; and (2) provide data for validation of the computational fluid dynamics, (CFD), analysis codes and the performance analysis codes. A facility checkout model was designed, constructed, and utilized to evaluate the performance characteristics of the new facility. This model consists of a cylindrical chamber and converging/diverging nozzle with appropriate manifolding to connect it to the facility air supply. It was designed using chamber and nozzle dimensions to simulate the flow in a 10 percent scale model of the ASRM. The checkout model was recently tested over the entire range of facility flow conditions which include flow rates from 9.07 to 145 kg/sec (20 to 320 Ibm/sec) and supply pressure from 5.17 x 10 exp 5 to 8.27 x 10 exp 6 Pa. The

  19. Axisymmetric Numerical Modeling of Pulse Detonation Rocket Engines

    Science.gov (United States)

    Morris, Christopher I.

    2005-01-01

    Pulse detonation rocket engines (PDREs) have generated research interest in recent years as a chemical propulsion system potentially offering improved performance and reduced complexity compared to conventional rocket engines. The detonative mode of combustion employed by these devices offers a thermodynamic advantage over the constant-pressure deflagrative combustion mode used in conventional rocket engines and gas turbines. However, while this theoretical advantage has spurred considerable interest in building PDRE devices, the unsteady blowdown process intrinsic to the PDRE has made realistic estimates of the actual propulsive performance problematic. The recent review article by Kailasanath highlights some of the progress that has been made in comparing the available experimental measurements with analytical and numerical models. In recent work by the author, a quasi-one-dimensional, finite rate chemistry CFD model was utilized to study the gasdynamics and performance characteristics of PDREs over a range of blowdown pressure ratios from 1-1000. Models of this type are computationally inexpensive, and enable first-order parametric studies of the effect of several nozzle and extension geometries on PDRE performance over a wide range of conditions. However, the quasi-one-dimensional approach is limited in that it cannot properly capture the multidimensional blast wave and flow expansion downstream of the PDRE, nor can it resolve nozzle flow separation if present. Moreover, the previous work was limited to single-pulse calculations. In this paper, an axisymmetric finite rate chemistry model is described and utilized to study these issues in greater detail. Example Mach number contour plots showing the multidimensional blast wave and nozzle exhaust plume are shown. The performance results are compared with the quasi-one-dimensional results from the previous paper. Both Euler and Navier-Stokes solutions are calculated in order to determine the effect of viscous

  20. More-Accurate Model of Flows in Rocket Injectors

    Science.gov (United States)

    Hosangadi, Ashvin; Chenoweth, James; Brinckman, Kevin; Dash, Sanford

    2011-01-01

    An improved computational model for simulating flows in liquid-propellant injectors in rocket engines has been developed. Models like this one are needed for predicting fluxes of heat in, and performances of, the engines. An important part of predicting performance is predicting fluctuations of temperature, fluctuations of concentrations of chemical species, and effects of turbulence on diffusion of heat and chemical species. Customarily, diffusion effects are represented by parameters known in the art as the Prandtl and Schmidt numbers. Prior formulations include ad hoc assumptions of constant values of these parameters, but these assumptions and, hence, the formulations, are inaccurate for complex flows. In the improved model, these parameters are neither constant nor specified in advance: instead, they are variables obtained as part of the solution. Consequently, this model represents the effects of turbulence on diffusion of heat and chemical species more accurately than prior formulations do, and may enable more-accurate prediction of mixing and flows of heat in rocket-engine combustion chambers. The model has been implemented within CRUNCH CFD, a proprietary computational fluid dynamics (CFD) computer program, and has been tested within that program. The model could also be implemented within other CFD programs.

  1. Viscoelastic Modelling of Solid Rocket Propellants using Maxwell Fluid Model

    Directory of Open Access Journals (Sweden)

    Himanshu Shekhar

    2010-07-01

    Full Text Available Maxwell fluid model consisting of a spring and a dashpot in series is applied for viscoelastic characterisation of solid rocket propellants. Suitable values of spring constant and damping coefficient wereemployed by least square variation of errors for generation of complete stress-strain curve in uniaxial tensile mode for case-bonded solid propellant formulations. Propellants from the same lot were tested at different strain rates. It was observed that change in spring constant, representing elastic part was very small with strain rate but damping constant varies significantly with variation in strain rate. For a typical propellant formulation, when strain rate was raised from 0.00037/s to 0.185/s, spring constant K changed from 5.5 MPato 7.9 MPa, but damping coefficient D was reduced from 1400 MPa-s to 4 MPa-s. For all strain rates, stress-strain curve was generated using Maxwell model and close matching with actual test curve was observed.This indicates validity of Maxwell fluid model for uniaxial tensile testing curves of case-bonded solid propellant formulations. It was established that at higher strain rate, damping coefficient becomes negligible as compared to spring constant. It was also observed that variation of spring constant is logarithmic with strain rate and that of damping coefficient follows power law. The correlation coefficients were introduced to ascertain spring constants and damping coefficients at any strain rate from that at a reference strain rate. Correlationfor spring constant needs a coefficient H, which is function of propellant formulation alone and not of test conditions and the equation developeds K2 = K1 + H ´ ln{(de2/dt/(de1/dt}. Similarly for damping coefficient D also another constant S is introduced and prediction formula is given by D2 = D1 ´ {(de2/dt/(de1/dt}S.Evaluating constants H and S at different strain rates validate this mathematical formulation for differentpropellant formulations

  2. On the Elastic Vibration Model for High Length-Diameter Ratio Rocket with Attitude Control System

    Institute of Scientific and Technical Information of China (English)

    朱伯立; 杨树兴

    2003-01-01

    An elastic vibration model for high length-diameter ratio spinning rocket with attitude control system which can be used for trajectory simulation is established. The basic theory of elastic dynamics and vibration dynamics were both used to set up the elastic vibration model of rocket body. In order to study the problem more conveniently, the rocket's body was simplified to be an even beam with two free ends. The model was validated by simulation results and the test data.

  3. The critical thinking curriculum model

    Science.gov (United States)

    Robertson, William Haviland

    The Critical Thinking Curriculum Model (CTCM) utilizes a multidisciplinary approach that integrates effective learning and teaching practices with computer technology. The model is designed to be flexible within a curriculum, an example for teachers to follow, where they can plug in their own critical issue. This process engages students in collaborative research that can be shared in the classroom, across the country or around the globe. The CTCM features open-ended and collaborative activities that deal with current, real world issues which leaders are attempting to solve. As implemented in the Critical Issues Forum (CIF), an educational program administered by Los Alamos National Laboratory (LANL), the CTCM encompasses the political, social/cultural, economic, and scientific realms in the context of a current global issue. In this way, students realize the importance of their schooling by applying their efforts to an endeavor that ultimately will affect their future. This study measures student attitudes toward science and technology and the changes that result from immersion in the CTCM. It also assesses the differences in student learning in science content and problem solving for students involved in the CTCM. A sample of 24 students participated in classrooms at two separate high schools in New Mexico. The evaluation results were analyzed using SPSS in a MANOVA format in order to determine the significance of the between and within-subjects effects. A comparison ANOVA was done for each two-way MANOVA to see if the comparison groups were equal. Significant findings were validated using the Scheffe test in a Post Hoc analysis. Demographic information for the sample population was recorded and tracked, including self-assessments of computer use and availability. Overall, the results indicated that the CTCM did help to increase science content understanding and problem-solving skills for students, thereby positively effecting critical thinking. No matter if the

  4. Modeling and Diagnostic Software for Liquefying-Fuel Rockets

    Science.gov (United States)

    Poll, Scott; Iverson, David; Ou, Jeremy; Sanderfer, Dwight; Patterson-Hine, Ann

    2005-01-01

    A report presents a study of five modeling and diagnostic computer programs considered for use in an integrated vehicle health management (IVHM) system during testing of liquefying-fuel hybrid rocket engines in the Hybrid Combustion Facility (HCF) at NASA Ames Research Center. Three of the programs -- TEAMS, L2, and RODON -- are model-based reasoning (or diagnostic) programs. The other two programs -- ICS and IMS -- do not attempt to isolate the causes of failures but can be used for detecting faults. In the study, qualitative models (in TEAMS and L2) and quantitative models (in RODON) having varying scope and completeness were created. Each of the models captured the structure and behavior of the HCF as a physical system. It was noted that in the cases of the qualitative models, the temporal aspects of the behavior of the HCF and the abstraction of sensor data are handled outside of the models, and it is necessary to develop additional code for this purpose. A need for additional code was also noted in the case of the quantitative model, though the amount of development effort needed was found to be less than that for the qualitative models.

  5. Tie Tube Heat Transfer Modeling for Bimodal Nuclear Thermal Rockets

    Science.gov (United States)

    Clough, Joshua A.; Starkey, Ryan P.; Lewis, Mark J.; Lavelle, Thomas M.

    2007-01-01

    Bimodal nuclear thermal rocket systems have been shown to reduce the weight and cost of space vehicles to Mars and beyond by utilizing the reactor for power generation in the relatively long duration between burns in an interplanetary trajectory. No information, however, is available regarding engine and reactor-level operation of such bimodal systems. The purpose of this project is to generate engine and reactor models with sufficient fidelity and flexibility to accurately study the component-level effects of operating a propulsion-designed reactor at power generation levels. Previous development of a 1-D reactor and tie tube model found that ignoring heat generation inside of the tie tube leads to under-prediction of the temperature change and over-prediction of pressure change across the tie tube. This paper will present the development and results of a tie tube model that has been extended to account for heat generation, specifically in the moderator layer. This model is based on a 1-D distribution of power in the fuel elements and tie tubes, as a precursor to an eventual neutron-driven reactor model.

  6. An Eight-Parameter Function for Simulating Model Rocket Engine Thrust Curves

    Science.gov (United States)

    Dooling, Thomas A.

    2007-01-01

    The toy model rocket is used extensively as an example of a realistic physical system. Teachers from grade school to the university level use them. Many teachers and students write computer programs to investigate rocket physics since the problem involves nonlinear functions related to air resistance and mass loss. This paper describes a nonlinear…

  7. Integrated propulsion and power modeling for bimodal nuclear thermal rockets

    Science.gov (United States)

    Clough, Joshua

    Bimodal nuclear thermal rocket (BNTR) engines have been shown to reduce the weight of space vehicles to the Moon, Mars, and beyond by utilizing a common reactor for propulsion and power generation. These savings lead to reduced launch vehicle costs and/or increased mission safety and capability. Experimental work of the Rover/NERVA program demonstrated the feasibility of NTR systems for trajectories to Mars. Numerous recent studies have demonstrated the economic and performance benefits of BNTR operation. Relatively little, however, is known about the reactor-level operation of a BNTR engine. The objective of this dissertation is to develop a numerical BNTR engine model in order to study the feasibility and component-level impact of utilizing a NERVA-derived reactor as a heat source for both propulsion and power. The primary contribution is to provide the first-of-its-kind model and analysis of a NERVA-derived BNTR engine. Numerical component models have been modified and created for the NERVA reactor fuel elements and tie tubes, including 1-D coolant thermodynamics and radial thermal conduction with heat generation. A BNTR engine system model has been created in order to design and analyze an engine employing an expander-cycle nuclear rocket and Brayton cycle power generator using the same reactor. Design point results show that a 316 MWt reactor produces a thrust and specific impulse of 66.6 kN and 917 s, respectively. The same reactor can be run at 73.8 kWt to produce the necessary 16.7 kW electric power with a Brayton cycle generator. This demonstrates the feasibility of BNTR operation with a NERVA-derived reactor but also indicates that the reactor control system must be able to operate with precision across a wide power range, and that the transient analysis of reactor decay heat merits future investigation. Results also identify a significant reactor pressure-drop limitation during propulsion and power-generation operation that is caused by poor tie tube

  8. Internal Flow Simulation of High-Performance Solid Rockets using a k-ωTurbulence Model

    Institute of Scientific and Technical Information of China (English)

    V.R. SANAL KUMAR; H.D. KIM; B.N. RAGHUNANDAN; T. SETOGUCHI; S. RAGHUNATHAN

    2005-01-01

    @@ For technological reasons many high-performance solid rocket motors are made from segmented propellant grains with non-uniform port geometry. In this paper parametric studies have been carried out to examine the geometric dependence of transient flow features in solid rockets with non-uniform ports. Numerical computations have been carried out in an inert simulator of solid propellant rocket motor with the aid of a standard k-ω turbulence model. It was seen that the damping of the temperature fluctuation is faster in solid rocket with convergent port than with divergent port geometry. We inferred that the damping of the flow fluctuations using the port geometry is a meaningful objective for the suppression and control of the instability and/or pressure/thrust oscillations during the starting transient of solid rockets.

  9. Ultrasonic inspection of rocket fuel model using laminated transducer and multi-channel step pulser

    Science.gov (United States)

    Mihara, T.; Hamajima, T.; Tashiro, H.; Sato, A.

    2013-01-01

    For the ultrasonic inspection for the packing of solid fuel in a rocket booster, an industrial inspection is difficult. Because the signal to noise ratio in ultrasonic inspection of rocket fuel become worse due to the large attenuation even using lower frequency ultrasound. For the improvement of this problem, we tried to applied the two techniques in ultrasonic inspection, one was the step function pulser system with the super wideband frequency properties and the other was the laminated element transducer. By combining these two techniques, we developed the new ultrasonic measurement system and demonstrated the advantages in ultrasonic inspection of rocket fuel model specimen.

  10. Two phase flow combustion modelling of a ducted rocket

    NARCIS (Netherlands)

    Stowe, R.A.; Dubois, C.; Harris, P.G.; Mayer, A.E.H.J.; Champlain, A. de; Ringuette, S.

    2001-01-01

    Under a co-operative program, the Defence Research Establishment Valcartier and Université Laval in Canada and the TNO Prins Maurits Laboratory in the Netherlands have studied the use of a ducted rocket for missile propulsion. Hot-flow direct-connect combustion experiments using both simulated and s

  11. Infrared signature modelling of a rocket jet plume - comparison with flight measurements

    Science.gov (United States)

    Rialland, V.; Guy, A.; Gueyffier, D.; Perez, P.; Roblin, A.; Smithson, T.

    2016-01-01

    The infrared signature modelling of rocket plumes is a challenging problem involving rocket geometry, propellant composition, combustion modelling, trajectory calculations, fluid mechanics, atmosphere modelling, calculation of gas and particles radiative properties and of radiative transfer through the atmosphere. This paper presents ONERA simulation tools chained together to achieve infrared signature prediction, and the comparison of the estimated and measured signatures of an in-flight rocket plume. We consider the case of a solid rocket motor with aluminized propellant, the Black Brant sounding rocket. The calculation case reproduces the conditions of an experimental rocket launch, performed at White Sands in 1997, for which we obtained high quality infrared signature data sets from DRDC Valcartier. The jet plume is calculated using an in-house CFD software called CEDRE. The plume infrared signature is then computed on the spectral interval 1900-5000 cm-1 with a step of 5 cm-1. The models and their hypotheses are presented and discussed. Then the resulting plume properties, radiance and spectra are detailed. Finally, the estimated infrared signature is compared with the spectral imaging measurements. The discrepancies are analyzed and discussed.

  12. The PIC [Process Individualization Curriculum] Model: Structure with Humanistic Goals.

    Science.gov (United States)

    Gow, Doris T.

    This paper describes a curriculum design model to train research and development personnel under USOE-NIE funding. This design model, called PIC (Process Individualization Curriculum), was chosen for coverting on-campus courses to extra-mural self-instructional courses. The curriculum specialists who work with professors to individualize their…

  13. Curriculum Development: A Philosophical Model.

    Science.gov (United States)

    Bruening, William H.

    Presenting models based on the philosophies of Carl Rogers, John Dewey, Erich Fromm, and Jean-Paul Sartre, this paper proposes a philosophical approach to education and concludes with pragmatic suggestions concerning teaching based on a fully-functioning-person model. The fully-functioning person is characterized as being open to experience,…

  14. The Humanistic Approach: A Model For Dental Health Curriculums.

    Science.gov (United States)

    Beall, Sue; Hurley, Robert S.

    1982-01-01

    A special dental health curriculum, called the Tattletooth Curriculum, demonstrates the use of the humanistic model in health education and its concern for the learner as a total person. The main concept in the development of this curriculum is that the prospect for changing behavior is unlikely unless the health information is personally…

  15. Mathematical Modelling of In-Chamber Processes in Hydrocombined Propellant Solid Rocket Motors

    Directory of Open Access Journals (Sweden)

    Nikolai A. Obukhov

    1998-10-01

    Full Text Available The special conditions of employment of commercial rockets in the sea environment has opened up new possibilities of improving motor performance. The interesting method suggests supplying water into the running motor. This paper reports the calculations and experiments carried out with solid propellant model setups. The results prove the validity of the proposed method and allow the refinement of calculation techniques for the prediction of solid rocket motor performance characteristics. The serviceability of the solid propellant charges working in combination with water is demonstrated. A mathematical model is proposed for the operation of a hydrocombined propellant motor with water and powdered additives applied to the combustion chamber."

  16. Integrating Numerical Computation into the Modeling Instruction Curriculum

    CERN Document Server

    Caballero, Marcos D; Aiken, John M; Douglas, Scott S; Scanlon, Erin M; Thoms, Brian; Schatz, Michael F

    2012-01-01

    We describe a way to introduce physics high school students with no background in programming to computational problem-solving experiences. Our approach builds on the great strides made by the Modeling Instruction reform curriculum. This approach emphasizes the practices of "Developing and using models" and "Computational thinking" highlighted by the NRC K-12 science standards framework. We taught 9th-grade students in a Modeling-Instruction-based physics course to construct computational models using the VPython programming environment. Numerical computation within the Modeling Instruction curriculum provides coherence among the curriculum's different force and motion models, links the various representations which the curriculum employs, and extends the curriculum to include real-world problems that are inaccessible to a purely analytic approach.

  17. Verification of Model of Calculation of Intra-Chamber Parameters In Hybrid Solid-Propellant Rocket Engines

    Directory of Open Access Journals (Sweden)

    Zhukov Ilya S.

    2016-01-01

    Full Text Available On the basis of obtained analytical estimate of characteristics of hybrid solid-propellant rocket engine verification of earlier developed physical and mathematical model of processes in a hybrid solid-propellant rocket engine for quasi-steady-state flow regime was performed. Comparative analysis of calculated and analytical data indicated satisfactory comparability of simulation results.

  18. Verification of Model of Calculation of Intra-Chamber Parameters In Hybrid Solid-Propellant Rocket Engines

    OpenAIRE

    Zhukov Ilya S.; Borisov Boris V.; Bondarchuk Sergey S.; Zhukov Alexander S.

    2016-01-01

    On the basis of obtained analytical estimate of characteristics of hybrid solid-propellant rocket engine verification of earlier developed physical and mathematical model of processes in a hybrid solid-propellant rocket engine for quasi-steady-state flow regime was performed. Comparative analysis of calculated and analytical data indicated satisfactory comparability of simulation results.

  19. A DYNAMIC MODEL FOR ROCKET LAUNCHER WITH COUPLED RIGID AND FLEXIBLW MOTION

    Institute of Scientific and Technical Information of China (English)

    ZHANG Ding-guo; XIAO Jian-qiang

    2005-01-01

    The dynamics of a coupled rigid-flexible rocket launcher is reported. The coupled rigid-flexible rocket launcher is divided into two subsystems, one is a system of rigid bodies,the other a flexible launch tube which can undergo large overall motions spatially. First, the mathematical models for these two subsystems were established respectively. Then the dynamic model for the whole system was obtained by considering the coupling effect between these two subsystems. The approach, which divides a complex system into several simple subsystems first and then obtains the dynamic model for the whole system via combining the existing dynamic models for simple subsystems, can make the modeling procedure efficient and convenient.

  20. State Machine Modeling of the Space Launch System Solid Rocket Boosters

    Science.gov (United States)

    Harris, Joshua A.; Patterson-Hine, Ann

    2013-01-01

    The Space Launch System is a Shuttle-derived heavy-lift vehicle currently in development to serve as NASA's premiere launch vehicle for space exploration. The Space Launch System is a multistage rocket with two Solid Rocket Boosters and multiple payloads, including the Multi-Purpose Crew Vehicle. Planned Space Launch System destinations include near-Earth asteroids, the Moon, Mars, and Lagrange points. The Space Launch System is a complex system with many subsystems, requiring considerable systems engineering and integration. To this end, state machine analysis offers a method to support engineering and operational e orts, identify and avert undesirable or potentially hazardous system states, and evaluate system requirements. Finite State Machines model a system as a finite number of states, with transitions between states controlled by state-based and event-based logic. State machines are a useful tool for understanding complex system behaviors and evaluating "what-if" scenarios. This work contributes to a state machine model of the Space Launch System developed at NASA Ames Research Center. The Space Launch System Solid Rocket Booster avionics and ignition subsystems are modeled using MATLAB/Stateflow software. This model is integrated into a larger model of Space Launch System avionics used for verification and validation of Space Launch System operating procedures and design requirements. This includes testing both nominal and o -nominal system states and command sequences.

  1. Mechanical Slosh Models for Rocket-Propelled Spacecraft

    Science.gov (United States)

    Jang, Jiann-Woei; Alaniz, Abram; Yang, Lee; Powers. Joseph; Hall, Charles

    2013-01-01

    Several analytical mechanical slosh models for a cylindrical tank with flat bottom are reviewed. Even though spacecrafts use cylinder shaped tanks, most of those tanks usually have elliptical domes. To extend the application of the analytical models for a cylindrical tank with elliptical domes, the modified slosh parameter models are proposed in this report by mapping an elliptical dome cylindrical tank to a flat top/bottom cylindrical tank while maintaining the equivalent liquid volume. For the low Bond number case, the low-g slosh models were also studied. Those low-g models can be used for Bond number > 10. The current low-g slosh models were also modified to extend their applications for the case that liquid height is smaller than the tank radius. All modified slosh models are implemented in MATLAB m-functions and are collected in the developed MST (Mechanical Slosh Toolbox).

  2. Double time lag combustion instability model for bipropellant rocket engines

    Science.gov (United States)

    Liu, C. K.

    1973-01-01

    A bipropellant stability model is presented in which feed system inertance and capacitance are treated along with injection pressure drop and distinctly different propellant time lags. The model is essentially an extension of Crocco's and Cheng's monopropellant model to the bipropellant case assuming that the feed system inertance and capacitance along with the resistance are located at the injector. The neutral stability boundaries are computed in terms of these parameters to demonstrate the interaction among them.

  3. Validation of a Solid Rocket Motor Internal Environment Model

    Science.gov (United States)

    Martin, Heath T.

    2017-01-01

    In a prior effort, a thermal/fluid model of the interior of Penn State University's laboratory-scale Insulation Test Motor (ITM) was constructed to predict both the convective and radiative heat transfer to the interior walls of the ITM with a minimum of empiricism. These predictions were then compared to values of total and radiative heat flux measured in a previous series of ITM test firings to assess the capabilities and shortcomings of the chosen modeling approach. Though the calculated fluxes reasonably agreed with those measured during testing, this exercise revealed means of improving the fidelity of the model to, in the case of the thermal radiation, enable direct comparison of the measured and calculated fluxes and, for the total heat flux, compute a value indicative of the average measured condition. By replacing the P1-Approximation with the discrete ordinates (DO) model for the solution of the gray radiative transfer equation, the radiation intensity field in the optically thin region near the radiometer is accurately estimated, allowing the thermal radiation flux to be calculated on the heat-flux sensor itself, which was then compared directly to the measured values. Though the fully coupling the wall thermal response with the flow model was not attempted due to the excessive computational time required, a separate wall thermal response model was used to better estimate the average temperature of the graphite surfaces upstream of the heat flux gauges and improve the accuracy of both the total and radiative heat flux computations. The success of this modeling approach increases confidence in the ability of state-of-the-art thermal and fluid modeling to accurately predict SRM internal environments, offers corrections to older methods, and supplies a tool for further studies of the dynamics of SRM interiors.

  4. System Modeling and Diagnostics for Liquefying-Fuel Hybrid Rockets

    Science.gov (United States)

    Poll, Scott; Iverson, David; Ou, Jeremy; Sanderfer, Dwight; Patterson-Hine, Ann

    2003-01-01

    A Hybrid Combustion Facility (HCF) was recently built at NASA Ames Research Center to study the combustion properties of a new fuel formulation that burns approximately three times faster than conventional hybrid fuels. Researchers at Ames working in the area of Integrated Vehicle Health Management recognized a good opportunity to apply IVHM techniques to a candidate technology for next generation launch systems. Five tools were selected to examine various IVHM techniques for the HCF. Three of the tools, TEAMS (Testability Engineering and Maintenance System), L2 (Livingstone2), and RODON, are model-based reasoning (or diagnostic) systems. Two other tools in this study, ICS (Interval Constraint Simulator) and IMS (Inductive Monitoring System) do not attempt to isolate the cause of the failure but may be used for fault detection. Models of varying scope and completeness were created, both qualitative and quantitative. In each of the models, the structure and behavior of the physical system are captured. In the qualitative models, the temporal aspects of the system behavior and the abstraction of sensor data are handled outside of the model and require the development of additional code. In the quantitative model, less extensive processing code is also necessary. Examples of fault diagnoses are given.

  5. Development of Detonation Modeling Capabilities for Rocket Test Facilities: Hydrogen-Oxygen-Nitrogen Mixtures

    Science.gov (United States)

    Allgood, Daniel C.

    2016-01-01

    The objective of the presented work was to develop validated computational fluid dynamics (CFD) based methodologies for predicting propellant detonations and their associated blast environments. Applications of interest were scenarios relevant to rocket propulsion test and launch facilities. All model development was conducted within the framework of the Loci/CHEM CFD tool due to its reliability and robustness in predicting high-speed combusting flow-fields associated with rocket engines and plumes. During the course of the project, verification and validation studies were completed for hydrogen-fueled detonation phenomena such as shock-induced combustion, confined detonation waves, vapor cloud explosions, and deflagration-to-detonation transition (DDT) processes. The DDT validation cases included predicting flame acceleration mechanisms associated with turbulent flame-jets and flow-obstacles. Excellent comparison between test data and model predictions were observed. The proposed CFD methodology was then successfully applied to model a detonation event that occurred during liquid oxygen/gaseous hydrogen rocket diffuser testing at NASA Stennis Space Center.

  6. Experimental Investigation on Performance of Pulse Detonation Rocket Engine Model

    Institute of Scientific and Technical Information of China (English)

    LI Qiang; FAN Wei; YAN Chuan-jun; HU Cheng-qi; YE Bin

    2007-01-01

    The PDRE test model used in these experiments utilized kerosene as the fuel, oxygen as oxidizer, and nitrogen as purge gas. The solenoid valves were employed to control intermittent supplies of kerosene, oxygen and purge gas. PDRE test model was 50 mm in inner diameter by 1.2 m long. The DDT (defiagration to detonation transition) enhancement device Shchelkin spiral was used in the test model.The effects of detonation frequency on its time-averaged thrust and specific impulse were experimentally investigated. The obtained results showes that the time-averaged thrust of PDRE test model was approximately proportional to the detonation frequency. For the detonation frequency 20 Hz, the time-averaged thrust was around 107 N, and the specific impulse was around 125 s. The nozzle experiments were conducted using PDRE test model with three traditional nozzles. The experimental results obtained demonstrated that all of those nozzles could augment the thrust and specific impulse. Among those three nozzles, the convergent nozzle had the largest increased augmentation, which was approximately 18%, under the specific condition of the experiment.

  7. Rocket University at KSC

    Science.gov (United States)

    Sullivan, Steven J.

    2014-01-01

    "Rocket University" is an exciting new initiative at Kennedy Space Center led by NASA's Engineering and Technology Directorate. This hands-on experience has been established to develop, refine & maintain targeted flight engineering skills to enable the Agency and KSC strategic goals. Through "RocketU", KSC is developing a nimble, rapid flight engineering life cycle systems knowledge base. Ongoing activities in RocketU develop and test new technologies and potential customer systems through small scale vehicles, build and maintain flight experience through balloon and small-scale rocket missions, and enable a revolving fresh perspective of engineers with hands on expertise back into the large scale NASA programs, providing a more experienced multi-disciplined set of systems engineers. This overview will define the Program, highlight aspects of the training curriculum, and identify recent accomplishments and activities.

  8. High-Fidelity Gas and Granular Flow Physics Models for Rocket Exhaust Interaction with Lunar Soil Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Current modeling of Lunar and Martian soil erosion and debris transport caused by rocket plume impingement lacks essential physics from the peculiar granular...

  9. Analytical model for liquid rocket propellant feedline dynamics

    Science.gov (United States)

    Holster, J. L.; Astleford, W. J.

    1974-01-01

    A generalized analytical model and computer program have been developed to predict the frequency response of arbitrary liquid propellant feedline designs. The analytical model is based on an extension of an existing distributed parameter representation of a viscous fluid transmission line with laminar flow which was modified to include the effects of a turbulent mean flow. The effects of dissolved ullage gases, wall elasticity, localized gas or vapor bubbles, bellows, forced changes in length due to structural excitation, complex side branches, and structural mounting stiffness are also included. Each line component is written as a four-terminal, pressure-flow relationship in matrix form in the Laplace domain; the transfer function relating the pressure response at the line terminal (inducer inlet) to the external excitation is obtained in the computer program by sequential matrix substitution.

  10. Coupled Lagrangian impingement spray model for doublet impinging injectors under liquid rocket engine operating conditions

    Directory of Open Access Journals (Sweden)

    Qiang WEI

    2017-08-01

    Full Text Available To predict the effect of the liquid rocket engine combustion chamber conditions on the impingement spray, the conventional uncoupled spray model for impinging injectors is extended by considering the coupling of the jet impingement process and the ambient gas field. The new coupled model consists of the plain-orifice sub-model, the jet-jet impingement sub-model and the droplet collision sub-model. The parameters of the child droplet are determined with the jet-jet impingement sub-model using correlations about the liquid jet parameters and the chamber conditions. The overall model is benchmarked under various impingement angles, jet momentum and off-center ratios. Agreement with the published experimental data validates the ability of the model to predict the key spray characteristics, such as the mass flux and mixture ratio distributions in quiescent air. Besides, impinging sprays under changing ambient pressure and non-uniform gas flow are investigated to explore the effect of liquid rocket engine chamber conditions. First, a transient impingement spray during engine start-up phase is simulated with prescribed pressure profile. The minimum average droplet diameter is achieved when the orifices work in cavitation state, and is about 30% smaller than the steady single phase state. Second, the effect of non-uniform gas flow produces off-center impingement and the rotated spray fan by 38°. The proposed model suggests more reasonable impingement spray characteristics than the uncoupled one and can be used as the first step in the complex simulation of coupling impingement spray and combustion in liquid rocket engines.

  11. Coupled simulation of CFD-flight-mechanics with a two-species-gas-model for the hot rocket staging

    Science.gov (United States)

    Li, Yi; Reimann, Bodo; Eggers, Thino

    2016-11-01

    The hot rocket staging is to separate the lowest stage by directly ignite the continuing-stage-motor. During the hot staging, the rocket stages move in a harsh dynamic environment. In this work, the hot staging dynamics of a multistage rocket is studied using the coupled simulation of Computational Fluid Dynamics and Flight Mechanics. Plume modeling is crucial for a coupled simulation with high fidelity. A 2-species-gas model is proposed to simulate the flow system of the rocket during the staging: the free-stream is modeled as "cold air" and the exhausted plume from the continuing-stage-motor is modeled with an equivalent calorically-perfect-gas that approximates the properties of the plume at the nozzle exit. This gas model can well comprise between the computation accuracy and efficiency. In the coupled simulations, the Navier-Stokes equations are time-accurately solved in moving system, with which the Flight Mechanics equations can be fully coupled. The Chimera mesh technique is utilized to deal with the relative motions of the separated stages. A few representative staging cases with different initial flight conditions of the rocket are studied with the coupled simulation. The torque led by the plume-induced-flow-separation at the aft-wall of the continuing-stage is captured during the staging, which can assist the design of the controller of the rocket. With the increasing of the initial angle-of-attack of the rocket, the staging quality becomes evidently poorer, but the separated stages are generally stable when the initial angle-of-attack of the rocket is small.

  12. An injector design model for predicting rocket engine performance and heat transfer

    Science.gov (United States)

    Calhoon, D. F.; Kors, D. L.; Gordon, L. H.

    1973-01-01

    A model is formulated for estimating the performance and chamber heat transfer in rocket injectors/chambers operating with gaseous H2-O2 propellants. The model quantifies the combustion performance and chamber heat flux for variables such as chamber length, element type, element area ratio, impingement angle, thrust/element, mixture ratio, moment ratio, element spacing, and physical size. Design equations are given and curves are plotted for evaluation of combustion performance in injectors comprised of F-O-F triplet, premix, coaxial and swirl coaxial element types. Curve plots and equations are also included for estimation of the chamber wall heat fluxes generated by these element types.

  13. Analysis and modeling of infrasound from a four-stage rocket launch.

    Science.gov (United States)

    Blom, Philip; Marcillo, Omar; Arrowsmith, Stephen

    2016-06-01

    Infrasound from a four-stage sounding rocket was recorded by several arrays within 100 km of the launch pad. Propagation modeling methods have been applied to the known trajectory to predict infrasonic signals at the ground in order to identify what information might be obtained from such observations. There is good agreement between modeled and observed back azimuths, and predicted arrival times for motor ignition signals match those observed. The signal due to the high-altitude stage ignition is found to be low amplitude, despite predictions of weak attenuation. This lack of signal is possibly due to inefficient aeroacoustic coupling in the rarefied upper atmosphere.

  14. ADDITIVE-MULTIPLICATIVE MODEL FOR RISK ESTIMATION IN THE PRODUCTION OF ROCKET AND SPACE TECHNICS

    Directory of Open Access Journals (Sweden)

    Orlov A. I.

    2014-10-01

    Full Text Available For the first time we have developed a general additive-multiplicative model of the risk estimation (to estimate the probabilities of risk events. In the two-level system in the lower level the risk estimates are combined additively, on the top – in a multiplicative way. Additive-multiplicative model was used for risk estimation for (1 implementation of innovative projects at universities (with external partners, (2 the production of new innovative products, (3 the projects for creation of rocket and space equipmen

  15. Development of Efficient Real-Fluid Model in Simulating Liquid Rocket Injector Flows

    Science.gov (United States)

    Cheng, Gary; Farmer, Richard

    2003-01-01

    The characteristics of propellant mixing near the injector have a profound effect on the liquid rocket engine performance. However, the flow features near the injector of liquid rocket engines are extremely complicated, for example supercritical-pressure spray, turbulent mixing, and chemical reactions are present. Previously, a homogeneous spray approach with a real-fluid property model was developed to account for the compressibility and evaporation effects such that thermodynamics properties of a mixture at a wide range of pressures and temperatures can be properly calculated, including liquid-phase, gas- phase, two-phase, and dense fluid regions. The developed homogeneous spray model demonstrated a good success in simulating uni- element shear coaxial injector spray combustion flows. However, the real-fluid model suffered a computational deficiency when applied to a pressure-based computational fluid dynamics (CFD) code. The deficiency is caused by the pressure and enthalpy being the independent variables in the solution procedure of a pressure-based code, whereas the real-fluid model utilizes density and temperature as independent variables. The objective of the present research work is to improve the computational efficiency of the real-fluid property model in computing thermal properties. The proposed approach is called an efficient real-fluid model, and the improvement of computational efficiency is achieved by using a combination of a liquid species and a gaseous species to represent a real-fluid species.

  16. Rocket Flight.

    Science.gov (United States)

    Van Evera, Bill; Sterling, Donna R.

    2002-01-01

    Describes an activity for designing, building, and launching rockets that provides students with an intrinsically motivating and real-life application of what could have been classroom-only concepts. Includes rocket design guidelines and a sample grading rubric. (KHR)

  17. Thermohydraulic Design Analysis Modeling for Korea Advanced NUclear Thermal Engine Rocket for Space Application

    Energy Technology Data Exchange (ETDEWEB)

    Nam, Seung Hyun; Choi, Jae Young; Venneria, Paolo F.; Jeong, Yong Hoon; Chang, Soon Heung [KAIST, Daejeon (Korea, Republic of)

    2015-05-15

    NTR engines have continued as a main stream based on the mature technology. The typical core design of the NERVA derived engines uses hexagonal shaped fuel elements with circular cooling channels and structural tie-tube elements for supporting the fuel elements, housing moderator and regeneratively cooling the moderator. The state-of-the-art NTR designs mostly use a fast or epithermal neutron spectrum core utilizing a HEU fuel to make a high power reactor with small and simple core geometry. Nuclear propulsion is the most promising and viable option to achieve challenging deep space missions. Particularly, the attractions of a NTR include excellent thrust and propellant efficiency, bimodal capability, proven technology, and safe and reliable performance. The KANUTER-HEU and -LEU are the innovative and futuristic NTR engines to reduce the reactor size and to implement a LEU fuel in the reactor by using thermal neutron spectrum. The KANUTERs have some features in the reactor design such as the integrated fuel element and the regeneratively cooling channels to increase room for moderator and heat transfer in the core, and ensuing rocket performance. To study feasible design points in terms of thermo-hydraulics and to estimate rocket performance of the KANUTERs, the NSES is under development. The model of the NSES currently focuses on thermo-hydraulic analysis of the peculiar and complex EHTGR design during the propulsion mode in steady-state. The results indicate comparable performance for future applications, even though it uses the heavier LEU fuel. In future, the NSES will be modified to obtain temperature distribution of the entire reactor components and then more extensive design analysis of neutronics, thermohydraulics and their coupling will be conducted to validate design feasibility and to optimize the reactor design enhancing the rocket performance.

  18. Integrating Surface Modeling into the Engineering Design Graphics Curriculum

    Science.gov (United States)

    Hartman, Nathan W.

    2006-01-01

    It has been suggested there is a knowledge base that surrounds the use of 3D modeling within the engineering design process and correspondingly within engineering design graphics education. While solid modeling receives a great deal of attention and discussion relative to curriculum efforts, and rightly so, surface modeling is an equally viable 3D…

  19. Integrating Surface Modeling into the Engineering Design Graphics Curriculum

    Science.gov (United States)

    Hartman, Nathan W.

    2006-01-01

    It has been suggested there is a knowledge base that surrounds the use of 3D modeling within the engineering design process and correspondingly within engineering design graphics education. While solid modeling receives a great deal of attention and discussion relative to curriculum efforts, and rightly so, surface modeling is an equally viable 3D…

  20. Rocket exhaust effluent modeling for tropospheric air quality and environmental assessments

    Science.gov (United States)

    Stephens, J. B.; Stewart, R. B.

    1977-01-01

    The various techniques for diffusion predictions to support air quality predictions and environmental assessments for aerospace applications are discussed in terms of limitations imposed by atmospheric data. This affords an introduction to the rationale behind the selection of the National Aeronautics and Space Administration (NASA)/Marshall Space Flight Center (MSFC) Rocket Exhaust Effluent Diffusion (REED) program. The models utilized in the NASA/MSFC REED program are explained. This program is then evaluated in terms of some results from a joint MSFC/Langley Research Center/Kennedy Space Center Titan Exhaust Effluent Prediction and Monitoring Program.

  1. Computer Modeling of a Rotating Detonation Engine in a Rocket Configuration

    Science.gov (United States)

    2015-03-01

    coefficient CP Specific heat capacity at constant pressure ( J kg−K ) CS Nozzle stream thrust coefficient D Detonation wave speed in laboratory frame-of...greater than the detonation fuel-to-air ratio, the ratio of specific heats and gas constant at station c3.4 are calculated using Eq. 75 and Eq. 76...COMPUTER MODELING OF A ROTATING DETONATION ENGINE IN A ROCKET CONFIGURATION THESIS Nihar N. Shah, 1st Lt, USAF AFIT-ENY-MS-15-M-230 DEPARTMENT OF THE

  2. How High? How Fast? How Long? Modeling Water Rocket Flight with Calculus

    Science.gov (United States)

    Ashline, George; Ellis-Monaghan, Joanna

    2006-01-01

    We describe an easy and fun project using water rockets to demonstrate applications of single variable calculus concepts. We provide procedures and a supplies list for launching and videotaping a water rocket flight to provide the experimental data. Because of factors such as fuel expulsion and wind effects, the water rocket does not follow the…

  3. How High? How Fast? How Long? Modeling Water Rocket Flight with Calculus

    Science.gov (United States)

    Ashline, George; Ellis-Monaghan, Joanna

    2006-01-01

    We describe an easy and fun project using water rockets to demonstrate applications of single variable calculus concepts. We provide procedures and a supplies list for launching and videotaping a water rocket flight to provide the experimental data. Because of factors such as fuel expulsion and wind effects, the water rocket does not follow the…

  4. Models and automation technologies for the curriculum development

    Directory of Open Access Journals (Sweden)

    V. N. Volkova

    2016-01-01

    Full Text Available The aim of the research was to determine the sequence of the curriculum development stages on the basis of the system analysis, as well as to create models and information technologies for the implementation of thesestages.The methods and the models of the systems’ theory and the system analysis, including methods and automated procedures for structuring organizational aims, models and automated procedures for organizing complex expertise.On the basis of the analysis of existing studies in the field of curriculum modeling, using formal mathematical language, including optimization models, that help to make distribution of disciplines by years and semesters in accordance with the relevant restrictions, it is shown, that the complexity and dimension of these tasks require the development of special software; the problem of defining the input data and restrictions requires a large time investment, that seems to be difficult to provide in real conditions of plans’ developing, thus it is almost impossible to verify the objectivity of the input data and the restrictions in such models. For a complete analysis of the process of curriculum development it is proposed to use the system definition, based on the system-targeted approach. On the basis of this definition the reasonable sequence of the integrated stages for the development of the curriculum was justified: 1 definition (specification of the requirements for the educational content; 2 determining the number of subjects, included in the curriculum; 3 definition of the sequence of the subjects; 4 distribution of subjects by semesters. The models and technologies for the implementation of these stages of curriculum development were given in the article: 1 models, based on the information approach of A.Denisov and the modified degree of compliance with objectives based on Denisov’s evaluation index (in the article the idea of evaluating the degree of the impact of disciplines for realization

  5. Advanced Multi-Phase Flow CFD Model Development for Solid Rocket Motor Flowfield Analysis

    Science.gov (United States)

    Liaw, Paul; Chen, Y. S.; Shang, H. M.; Doran, Denise

    1993-01-01

    It is known that the simulations of solid rocket motor internal flow field with AL-based propellants require complex multi-phase turbulent flow model. The objective of this study is to develop an advanced particulate multi-phase flow model which includes the effects of particle dynamics, chemical reaction and hot gas flow turbulence. The inclusion of particle agglomeration, particle/gas reaction and mass transfer, particle collision, coalescence and breakup mechanisms in modeling the particle dynamics will allow the proposed model to realistically simulate the flowfield inside a solid rocket motor. The Finite Difference Navier-Stokes numerical code FDNS is used to simulate the steady-state multi-phase particulate flow field for a 3-zone 2-D axisymmetric ASRM model and a 6-zone 3-D ASRM model at launch conditions. The 2-D model includes aft-end cavity and submerged nozzle. The 3-D model represents the whole ASRM geometry, including additional grain port area in the gas cavity and two inhibitors. FDNS is a pressure based finite difference Navier-Stokes flow solver with time-accurate adaptive second-order upwind schemes, standard and extended k-epsilon models with compressibility corrections, multi zone body-fitted formulations, and turbulence particle interaction model. Eulerian/Lagrangian multi-phase solution method is applied for multi-zone mesh. To simulate the chemical reaction, penalty function corrected efficient finite-rate chemistry integration method is used in FDNS. For the AL particle combustion rate, the Hermsen correlation is employed. To simulate the turbulent dispersion of particles, the Gaussian probability distribution with standard deviation equal to (2k/3)(exp 1/2) is used for the random turbulent velocity components. The computational results reveal that the flow field near the juncture of aft-end cavity and the submerged nozzle is very complex. The effects of the turbulent particles affect the flow field significantly and provide better

  6. Thermal radiation of heterogeneous combustion products in the model rocket engine plume

    Science.gov (United States)

    Kuzmin, V. A.; Maratkanova, E. I.; Zagray, I. A.; Rukavishnikova, R. V.

    2015-05-01

    The work presents a method of complex investigation of thermal radiation emitted by heterogeneous combustion products in the model rocket engine plume. Realization of the method has allowed us to obtain full information on the results in all stages of calculations. Dependence of the optical properties (complex refractive index), the radiation characteristics (coefficients and cross sections) and emission characteristics (flux densities, emissivity factors) of the main determining factors and parameters was analyzed. It was found by the method of computational experiment that the presence of the gaseous phase in the combustion products causes a strongly marked selectivity of emission, due to which the use of gray approximation in the calculation of thermal radiation is unnecessary. The influence of the optical properties, mass fraction, the function of particle size distribution, and the temperature of combustion products on thermal radiation in the model rocket engine plume was investigated. The role of "spotlight" effect-increasing the amount of energy of emission exhaust combustion products due to scattering by condensate particles radiation from the combustion chamber-was established quantitatively.

  7. Extensions to the time lag models for practical application to rocket engine stability design

    Science.gov (United States)

    Casiano, Matthew J.

    The combustion instability problem in liquid-propellant rocket engines (LREs) has remained a tremendous challenge since their discovery in the 1930s. Improvements are usually made in solving the combustion instability problem primarily using computational fluid dynamics (CFD) and also by testing demonstrator engines. Another approach is to use analytical models. Analytical models can be used such that design, redesign, or improvement of an engine system is feasible in a relatively short period of time. Improvements to the analytical models can greatly aid in design efforts. A thorough literature review is first conducted on liquid-propellant rocket engine (LRE) throttling. Throttling is usually studied in terms of vehicle descent or ballistic missile control however there are many other cases where throttling is important. It was found that combustion instabilities are one of a few major issues that occur during deep throttling (other major issues are heat transfer concerns, performance loss, and pump dynamics). In the past and again recently, gas injected into liquid propellants has shown to be a viable solution to throttle engines and to eliminate some forms of combustion instability. This review uncovered a clever solution that was used to eliminate a chug instability in the Common Extensible Cryogenic Engine (CECE), a modified RL10 engine. A separate review was also conducted on classic time lag combustion instability models. Several new stability models are developed by incorporating important features to the classic and contemporary models, which are commonly used in the aerospace rocket industry. The first two models are extensions of the original Crocco and Cheng concentrated combustion model with feed system contributions. A third new model is an extension to the Wenzel and Szuch double-time lag model also with feed system contributions. The first new model incorporates the appropriate injector acoustic boundary condition which is neglected in contemporary

  8. Voices of innovation: building a model for curriculum transformation.

    Science.gov (United States)

    Phillips, Janet M; Resnick, Jerelyn; Boni, Mary Sharon; Bradley, Patricia; Grady, Janet L; Ruland, Judith P; Stuever, Nancy L

    2013-05-07

    Innovation in nursing education curriculum is critically needed to meet the demands of nursing leadership and practice while facing the complexities of today's health care environment. International nursing organizations, the Institute of Medicine, and; our health care practice partners have called for curriculum reform to ensure the quality and safety of patient care. While innovation is occurring in schools of nursing, little is being researched or disseminated. The purposes of this qualitative study were to (a) describe what innovative curricula were being implemented, (b) identify challenges faced by the faculty, and (c) explore how the curricula were evaluated. Interviews were conducted with 15 exemplar schools from a variety of nursing programs throughout the United States. Exemplar innovative curricula were identified, and a model for approaching innovation was developed based on the findings related to conceptualizing, designing, delivering, evaluating, and supporting the curriculum. The results suggest implications for nursing education, research, and practice.

  9. Dental Hygiene Curriculum Model for Transition to Future Roles.

    Science.gov (United States)

    Paarmann, Carlene S.; And Others

    1990-01-01

    The establishment of the baccalaureate degree as the minimum entry level for dental hygiene practice centers around three main concerns: changes in health care delivery, awarding of a degree commensurate with students' educational background, and the credibility of dental hygiene as a profession. A curriculum model is discussed. (MLW)

  10. Cesar Chavez--Grade Seven Model Curriculum and Resources.

    Science.gov (United States)

    California State Dept. of Education, Sacramento.

    In this California state curriculum model for grade 7, "World History and Geography: Medieval Society," students study the life, work, and philosophy of Cesar Chavez. They learn about the ideas and philosophies that have withstood the test of time and emerged in Chavez's work and actions. Students examine Chavez's ancestral heritage link to early…

  11. Cesar Chavez--Grade Six Model Curriculum and Resources.

    Science.gov (United States)

    California State Dept. of Education, Sacramento.

    In this California state curriculum model for grade 6, "World History and Geography: Ancient Civilization," students learn that religious ideas have inspired and influenced the lives and actions of men and women, including Cesar Chavez. They see how his unselfishness, compassion for others, tolerance, and nonviolence have roots reaching back…

  12. An Alumni Oriented Approach to Sport Management Curriculum Design Using Performance Ratings and a Regression Model.

    Science.gov (United States)

    Ulrich, David; Parkhouse, Bonnie L.

    1982-01-01

    An alumni-based model is proposed as an alternative to sports management curriculum design procedures. The model relies on the assessment of curriculum by sport management alumni and uses performance ratings of employers and measures of satisfaction by alumni in a regression model to identify curriculum leading to increased work performance and…

  13. Thermo-mechanical concepts applied to modeling liquid propellant rocket engine stability

    Science.gov (United States)

    Kassoy, David R.; Norris, Adam

    2016-11-01

    The response of a gas to transient, spatially distributed energy addition can be quantified mathematically using thermo-mechanical concepts available in the literature. The modeling demonstrates that the ratio of the energy addition time scale to the acoustic time scale of the affected volume, and the quantity of energy added to that volume during the former determine the whether the responses to heating can be described as occurring at nearly constant volume, fully compressible or nearly constant pressure. Each of these categories is characterized by significantly different mechanical responses. Application to idealized configurations of liquid propellant rocket engines provides an opportunity to identify physical conditions compatible with gasdynamic disturbances that are sources of engine instability. Air Force Office of Scientific Research.

  14. Coupled Solid Rocket Motor Ballistics and Trajectory Modeling for Higher Fidelity Launch Vehicle Design

    Science.gov (United States)

    Ables, Brett

    2014-01-01

    Multi-stage launch vehicles with solid rocket motors (SRMs) face design optimization challenges, especially when the mission scope changes frequently. Significant performance benefits can be realized if the solid rocket motors are optimized to the changing requirements. While SRMs represent a fixed performance at launch, rapid design iterations enable flexibility at design time, yielding significant performance gains. The streamlining and integration of SRM design and analysis can be achieved with improved analysis tools. While powerful and versatile, the Solid Performance Program (SPP) is not conducive to rapid design iteration. Performing a design iteration with SPP and a trajectory solver is a labor intensive process. To enable a better workflow, SPP, the Program to Optimize Simulated Trajectories (POST), and the interfaces between them have been improved and automated, and a graphical user interface (GUI) has been developed. The GUI enables real-time visual feedback of grain and nozzle design inputs, enforces parameter dependencies, removes redundancies, and simplifies manipulation of SPP and POST's numerous options. Automating the analysis also simplifies batch analyses and trade studies. Finally, the GUI provides post-processing, visualization, and comparison of results. Wrapping legacy high-fidelity analysis codes with modern software provides the improved interface necessary to enable rapid coupled SRM ballistics and vehicle trajectory analysis. Low cost trade studies demonstrate the sensitivities of flight performance metrics to propulsion characteristics. Incorporating high fidelity analysis from SPP into vehicle design reduces performance margins and improves reliability. By flying an SRM designed with the same assumptions as the rest of the vehicle, accurate comparisons can be made between competing architectures. In summary, this flexible workflow is a critical component to designing a versatile launch vehicle model that can accommodate a volatile

  15. A Mathematical and Numerical Model for the Analysis of Hybrid Rocket Motors

    Directory of Open Access Journals (Sweden)

    Florin MINGIREANU

    2011-12-01

    Full Text Available The hybrid rocket motors (HRM use a two-phase propellant system. This offers some remarkable advantages but also arises some difficulties like the neutralization of their instabilities. The non-acoustic combustion instabilities are high-amplitude pressure oscillations that have too low frequencies to be associated with acoustics. Acoustic type combustion instabilities are self-excited oscillations generated by the interaction between acoustic waves and combustion. The goal of the present work is to develop a simplified model of the coupling of the hybrid combustion process with the complete unsteady flow, starting from the combustion port and ending with the nozzle. This model must be useful for transient and stability analysis and also for scaling of HRMs. The numerical results obtained with our model show a good agreement with published experimental and numerical results. The computational and stability analysis models developed in this work are simple, computationally efficient and offer the advantage of taking into account a large number of functional and constructive parameters that are used by the engineers.

  16. A model curriculum vitae: what are the trainers looking for?

    Science.gov (United States)

    Chambler, A F; Chapman-Sheath, P J; Pearse, M F

    1998-04-01

    In this new era of Calman, the curriculum vitae (CV) still remains the most important document in furthering the careers of doctors. A survey of postgraduate deans and college regional training advisors opinions on CVs was undertaken. The results have allowed a model CV to be compiled expressing the layout and most of the features which senior trainers feel are important when producing a CV.

  17. Curriculum inventory: Modeling, sharing and comparing medical education programs.

    Science.gov (United States)

    Ellaway, Rachel H; Albright, Susan; Smothers, Valerie; Cameron, Terri; Willett, Timothy

    2014-03-01

    Abstract descriptions of how curricula are structured and run. The American National Standards Institute (ANSI) MedBiquitous Curriculum Inventory Standard provides a technical syntax through which a wide range of different curricula can be expressed and subsequently compared and analyzed. This standard has the potential to shift curriculum mapping and reporting from a somewhat disjointed and institution-specific undertaking to something that is shared among multiple medical schools and across whole medical education systems. Given the current explosion of different models of curricula (time-free, competency-based, socially accountable, distributed, accelerated, etc.), the ability to consider this diversity using a common model has particular value in medical education management and scholarship. This article describes the development and structure of the Curriculum Inventory Standard as a way of standardizing the modeling of different curricula for audit, evaluation and research purposes. It also considers the strengths and limitations of the current standard and the implications for a medical education world in which this level of commonality, precision, and accountability for curricular practice is the norm rather than the exception.

  18. Slip-model Performance for Underexpanded Micro-scale Rocket Nozzle Flows

    Institute of Scientific and Technical Information of China (English)

    José A. Morí(n)igo; José Hermida Quesada; Francisco Caballero Requena

    2007-01-01

    In aerospace Micro-ElectroMechanical Systems (MEMS), the characteristic length scale of the flow approaches the molecular mean free path, thus invalidating the continuum description and enforcing the use of particle methods, like the Direct Simulation Monte Carlo (DSMC), to deal with the non-equilibrium regions. Within the slip-regime (0.01<Kn<~0.1) both approaches, continuum and particle-based, seem to behave well in terms of accuracy. The present study summarizes the implementation and results obtained with a 2nd-order slip boundary condition in a Navier-Stokes solver to address the rarefaction near the nozzle walls. Its assessment and application to a cold-gas micro-scale conical nozzle of 300μm throat diameter, discharging into the low-pressure freestream,constitutes the major aim of the work. The slip-model incorporates the velocity slip with thermal creep and temperature jump, thus permitting to deal with non-isothermal flows as well. Results show that the gas experiences an intense rarefaction in the lip vicinity, pointing to the limits of model validity. Furthermore, a strong Mach deceleration is observed, attributed to the rather thick subsonic boundary layer and supersonic bulk heating caused by the viscous dissipation, in contrast with the expansion to occur in large rocket nozzles during underexpanded operation.

  19. Quark Model in the Quantum Mechanics Curriculum.

    Science.gov (United States)

    Hussar, P. E.; And Others

    1980-01-01

    This article discusses in detail the totally symmetric three-quark karyonic wave functions. The two-body mesonic states are also discussed. A brief review of the experimental efforts to identify the quark model multiplets is given. (Author/SK)

  20. Quark Model in the Quantum Mechanics Curriculum.

    Science.gov (United States)

    Hussar, P. E.; And Others

    1980-01-01

    This article discusses in detail the totally symmetric three-quark karyonic wave functions. The two-body mesonic states are also discussed. A brief review of the experimental efforts to identify the quark model multiplets is given. (Author/SK)

  1. Numerically Modeling the Erosion of Lunar Soil by Rocket Exhaust Plumes

    Science.gov (United States)

    2008-01-01

    In preparation for the Apollo program, Leonard Roberts of the NASA Langley Research Center developed a remarkable analytical theory that predicts the blowing of lunar soil and dust beneath a rocket exhaust plume. Roberts assumed that the erosion rate was determined by the excess shear stress in the gas (the amount of shear stress greater than what causes grains to roll). The acceleration of particles to their final velocity in the gas consumes a portion of the shear stress. The erosion rate continues to increase until the excess shear stress is exactly consumed, thus determining the erosion rate. Roberts calculated the largest and smallest particles that could be eroded based on forces at the particle scale, but the erosion rate equation assumed that only one particle size existed in the soil. He assumed that particle ejection angles were determined entirely by the shape of the terrain, which acts like a ballistic ramp, with the particle aerodynamics being negligible. The predicted erosion rate and the upper limit of particle size appeared to be within an order of magnitude of small-scale terrestrial experiments but could not be tested more quantitatively at the time. The lower limit of particle size and the predictions of ejection angle were not tested. We observed in the Apollo landing videos that the ejection angles of particles streaming out from individual craters were time-varying and correlated to the Lunar Module thrust, thus implying that particle aerodynamics dominate. We modified Roberts theory in two ways. First, we used ad hoc the ejection angles measured in the Apollo landing videos, in lieu of developing a more sophisticated method. Second, we integrated Roberts equations over the lunar-particle size distribution and obtained a compact expression that could be implemented in a numerical code. We also added a material damage model that predicts the number and size of divots which the impinging particles will cause in hardware surrounding the landing

  2. Reusable Solid Rocket Motor - V(RSRMV)Nozzle Forward Nose Ring Thermo-Structural Modeling

    Science.gov (United States)

    Clayton, J. Louie

    2012-01-01

    During the developmental static fire program for NASAs Reusable Solid Rocket Motor-V (RSRMV), an anomalous erosion condition appeared on the nozzle Carbon Cloth Phenolic nose ring that had not been observed in the space shuttle RSRM program. There were regions of augmented erosion located on the bottom of the forward nose ring (FNR) that measured nine tenths of an inch deeper than the surrounding material. Estimates of heating conditions for the RSRMV nozzle based on limited char and erosion data indicate that the total heat loading into the FNR, for the new five segment motor, is about 40-50% higher than the baseline shuttle RSRM nozzle FNR. Fault tree analysis of the augmented erosion condition has lead to a focus on a thermomechanical response of the material that is outside the existing experience base of shuttle CCP materials for this application. This paper provides a sensitivity study of the CCP material thermo-structural response subject to the design constraints and heating conditions unique to the RSRMV Forward Nose Ring application. Modeling techniques are based on 1-D thermal and porous media calculations where in-depth interlaminar loading conditions are calculated and compared to known capabilities at elevated temperatures. Parameters such as heat rate, in-depth pressures and temperature, degree of char, associated with initiation of the mechanical removal process are quantified and compared to a baseline thermo-chemical material removal mode. Conclusions regarding postulated material loss mechanisms are offered.

  3. Modeling the Thermal Rocket Fuel Preparation Processes in the Launch Complex Fueling System

    Directory of Open Access Journals (Sweden)

    A. V. Zolin

    2015-01-01

    Full Text Available It is necessary to carry out fuel temperature preparation for space launch vehicles using hydrocarbon propellant components. A required temperature is reached with cooling or heating hydrocarbon fuel in ground facilities fuel storages. Fuel temperature preparing processes are among the most energy-intensive and lengthy processes that require the optimal technologies and regimes of cooling (heating fuel, which can be defined using the simulation of heat exchange processes for preparing the rocket fuel.The issues of research of different technologies and simulation of cooling processes of rocket fuel with liquid nitrogen are given in [1-10]. Diagrams of temperature preparation of hydrocarbon fuel, mathematical models and characteristics of cooling fuel with its direct contact with liquid nitrogen dispersed are considered, using the numerical solution of a system of heat transfer equations, in publications [3,9].Analytical models, allowing to determine the necessary flow rate and the mass of liquid nitrogen and the cooling (heating time fuel in specific conditions and requirements, are preferred for determining design and operational characteristics of the hydrocarbon fuel cooling system.A mathematical model of the temperature preparation processes is developed. Considered characteristics of these processes are based on the analytical solutions of the equations of heat transfer and allow to define operating parameters of temperature preparation of hydrocarbon fuel in the design and operation of the filling system of launch vehicles.The paper considers a technological system to fill the launch vehicles providing the temperature preparation of hydrocarbon gases at the launch site. In this system cooling the fuel in the storage tank before filling the launch vehicle is provided by hydrocarbon fuel bubbling with liquid nitrogen. Hydrocarbon fuel is heated with a pumping station, which provides fuel circulation through the heat exchanger-heater, with

  4. Rocket Flight Path

    Directory of Open Access Journals (Sweden)

    Jamie Waters

    2014-09-01

    Full Text Available This project uses Newton’s Second Law of Motion, Euler’s method, basic physics, and basic calculus to model the flight path of a rocket. From this, one can find the height and velocity at any point from launch to the maximum altitude, or apogee. This can then be compared to the actual values to see if the method of estimation is a plausible. The rocket used for this project is modeled after Bullistic-1 which was launched by the Society of Aeronautics and Rocketry at the University of South Florida.

  5. A Replicable, Zero-Based Model for Marketing Curriculum Innovation

    Science.gov (United States)

    Borin, Norm; Metcalf, Lynn E.; Tietje, Brian C.

    2007-01-01

    As university curriculums inevitably change, their evolution typically occurs through a series of minor incremental adjustments to individual courses that cause the curriculum to lose strategic consistency and focus. This article demonstrates a zero-based approach to marketing curriculum innovation. The authors describe forces of change that led…

  6. Modeling of the filling and cooling processes of hot fuel mains in Liquid Fuel Rocket Power Plant (LFRPP)

    Science.gov (United States)

    Prisnyakov, V. F.; Pokrishkin, V. V.; Serebryansky, V. N.

    A mathematical model of heat and mass exchange processes during filling and cooling of hot fuel mains of the Liquid Fuel Rocket Power Plant (LFRPP), which allows to define a mass consumption and distribution of two-phase flow parameters by the length of pipeline. Results of calculations are compared with experimental data, taken during filling of the main with a supply of liquid oxygen from the tank into the combustion chamber. Also, the results of modeling of hydrogen main dynamic characteristics of LFRPP in the same conditions are given.

  7. Rocket Tablet,

    Science.gov (United States)

    1984-09-12

    is a vast and desolate world, this is a strip of mir- aculous land! How many struggling dramas full of power and * grandeur were cheered, resisted and...rocket officers and men, a group enormous and powerful , marched into this land soaked with the fresh blood of our ancestors. This place is about to...and tough pestering said he wanted an American aircraft ob- tained on the battlefield to transport goods from Lanzhou, Xian, Beijing, Guangzhou and

  8. Rocket launchers as passive controllers

    Science.gov (United States)

    Cochran, J. E., Jr.; Gunnels, R. T.; McCutchen, R. K., Jr.

    1981-12-01

    A concept is advanced for using the motion of launchers of a free-flight launcher/rocket system which is caused by random imperfections of the rockets launched from it to reduce the total error caused by the imperfections. This concept is called 'passive launcher control' because no feedback is generated by an active energy source after an error is sensed; only the feedback inherent in the launcher/rocket interaction is used. Relatively simple launcher models with two degrees of freedom, pitch and yaw, were used in conjunction with a more detailed, variable-mass model in a digital simulation code to obtain rocket trajectories with and without thrust misalignment and dynamic imbalance. Angular deviations of rocket velocities and linear deviations of the positions of rocket centers of mass at burnout were computed for cases in which the launcher was allowed to move ('flexible' launcher) and was constrained so that it did not rotate ('rigid' launcher) and ratios of flexible to rigid deviations were determined. Curves of these error ratios versus launcher frequency are presented. These show that a launcher which has a transverse moment of inertia about its pivot point of the same magnitude as that of the centroidal transverse moments of inertia of the rockets launched from it can be tuned to passively reduce the errors caused by rocket imperfections.

  9. Final Progress Report for the NASA Inductrack Model Rocket Launcher at the Lawrence Livermore National Laboratory

    Energy Technology Data Exchange (ETDEWEB)

    Tung, L S; Post, R F; Martinez-Frias, J

    2001-06-27

    The Inductrack magnetic levitation system, developed at the Lawrence Livermore National Laboratory, was studied for its possible use for launching rockets. Under NASA sponsorship, a small model system was constructed at the Laboratory to pursue key technical aspects of this proposed application. The Inductrack is a passive magnetic levitation system employing special arrays of high-field permanent magnets (Halbach arrays) on the levitating cradle, moving above a ''track'' consisting of a close-packed array of shorted coils with which are interleaved with special drive coils. Halbach arrays produce a strong spatially periodic magnetic field on the front surface of the arrays, while canceling the field on their back surface. Relative motion between the Halbach arrays and the track coils induces currents in those coils. These currents levitate the cradle by interacting with the horizontal component of the magnetic field. Pulsed currents in the drive coils, synchronized with the motion of the carrier, interact with the vertical component of the magnetic field to provide acceleration forces. Motional stability, including resistance to both vertical and lateral aerodynamic forces, is provided by having Halbach arrays that interact with both the upper and the lower sides of the track coils. At present, a 7.8 meter track composed of drive and levitation coils has been built and the electronic drive circuitry performs as designed. A 9 kg cradle that carries the Halbach array of permanent magnets has been built. A mechanical launcher is nearly complete which will provide an initial cradle velocity of 9 m/s into the electronic drive section. We have found that the drag forces from the levitation coils were higher than in our original design. However, measurements of drag force at velocities less than 1 m/s are exactly as predicted by theory. Provided here are recommended design changes to improve the track's performance so that a final velocity of 40

  10. A model for communication skills assessment across the undergraduate curriculum.

    Science.gov (United States)

    Rider, Elizabeth A; Hinrichs, Margaret M; Lown, Beth A

    2006-08-01

    Physicians' interpersonal and communication skills have a significant impact on patient care and correlate with improved healthcare outcomes. Some studies suggest, however, that communication skills decline during the four years of medical school. Regulatory and other medical organizations, recognizing the importance of interpersonal and communication skills in the practice of medicine, now require competence in communication skills. Two challenges exist: to select a framework of interpersonal and communication skills to teach across undergraduate medical education, and to develop and implement a uniform model for the assessment of these skills. The authors describe a process and model for developing and institutionalizing the assessment of communication skills across the undergraduate curriculum. Consensus was built regarding communication skill competencies by working with course leaders and examination directors, a uniform framework of competencies was selected to both teach and assess communication skills, and the framework was implemented across the Harvard Medical School undergraduate curriculum. The authors adapted an assessment framework based on the Bayer-Fetzer Kalamazoo Consensus Statement adapted a patient and added and satisfaction tool to bring patients' perspectives into the assessment of the learners. The core communication competencies and evaluation instruments were implemented in school-wide courses and assessment exercises including the first-year Patient-Doctor I Clinical Assessment, second-year Objective Structured Clinical Exam (OSCE), third-year Patient-Doctor III Clinical Assessment, fourth-year Comprehensive Clinical Practice Examination and the Core Medicine Clerkships. Faculty were offered workshops and interactive web-based teaching to become familiar with the framework, and students used the framework with repeated opportunities for faculty feedback on these skills. A model is offered for educational leaders and others who are involved

  11. Merging curriculum design with chemical epistemology: A case of teaching and learning chemistry through modeling

    Science.gov (United States)

    Erduran, Sibel

    The central problem underlying this dissertation is the design of learning environments that enable the teaching and learning of chemistry through modeling. Significant role of models in chemistry knowledge is highlighted with a shift in emphasis from conceptual to epistemological accounts of models. Research context is the design and implementation of student centered Acids & Bases Curriculum, developed as part of Project SEPIA. Qualitative study focused on 3 curriculum activities conducted in one 7th grade class of 19 students in an urban, public middle school in eastern United States. Questions guiding the study were: (a) How can learning environments be designed to promote growth of chemistry knowledge through modeling? (b) What epistemological criteria facilitate learning of growth of chemistry knowledge through modeling? Curriculum materials, and verbal data from whole class conversations and student group interviews were analyzed. Group interviews consisted of same 4 students, selected randomly before curriculum implementation, and were conducted following each activity to investigate students' developing understandings of models. Theoretical categories concerning definition, properties and kinds of models as well as educational and chemical models informed curriculum design, and were redefined as codes in the analysis of verbal data. Results indicate more diversity of codes in student than teacher talk across all activities. Teacher concentrated on educational and chemical models. A significant finding is that model properties such as 'compositionality' and 'projectability' were not present in teacher talk as expected by curriculum design. Students did make reference to model properties. Another finding is that students demonstrate an understanding of models characterized by the seventeenth century Lemery model of acids and bases. Two students' developing understandings of models across curriculum implementation suggest that curriculum bears some change in

  12. One Dimensional Analysis Model of a Condensing Spray Chamber Including Rocket Exhaust Using SINDA/FLUINT and CEA

    Science.gov (United States)

    Sakowski, Barbara; Edwards, Daryl; Dickens, Kevin

    2014-01-01

    Modeling droplet condensation via CFD codes can be very tedious, time consuming, and inaccurate. CFD codes may be tedious and time consuming in terms of using Lagrangian particle tracking approaches or particle sizing bins. Also since many codes ignore conduction through the droplet and or the degradating effect of heat and mass transfer if noncondensible species are present, the solutions may be inaccurate. The modeling of a condensing spray chamber where the significant size of the water droplets and the time and distance these droplets take to fall, can make the effect of droplet conduction a physical factor that needs to be considered in the model. Furthermore the presence of even a relatively small amount of noncondensible has been shown to reduce the amount of condensation [Ref 1]. It is desirable then to create a modeling tool that addresses these issues. The path taken to create such a tool is illustrated. The application of this tool and subsequent results are based on the spray chamber in the Spacecraft Propulsion Research Facility (B2) located at NASA's Plum Brook Station that tested an RL-10 engine. The platform upon which the condensation physics is modeled is SINDAFLUINT. The use of SINDAFLUINT enables the ability to model various aspects of the entire testing facility, including the rocket exhaust duct flow and heat transfer to the exhaust duct wall. The ejector pumping system of the spray chamber is also easily implemented via SINDAFLUINT. The goal is to create a transient one dimensional flow and heat transfer model beginning at the rocket, continuing through the condensing spray chamber, and finally ending with the ejector pumping system. However the model of the condensing spray chamber may be run independently of the rocket and ejector systems detail, with only appropriate mass flow boundary conditions placed at the entrance and exit of the condensing spray chamber model. The model of the condensing spray chamber takes into account droplet

  13. A Model for the Development of a CDIO Based Curriculum in Electrical Engineering

    DEFF Research Database (Denmark)

    Bruun, Erik; Kjærgaard, Claus

    2011-01-01

    at the Technical University of Denmark and this gives a strong direct impact of the university environment on the resulting curriculum in electrical engineering. The resulting Bachelor of Engineering curriculum is presented and it is discussed how it complies with the model for curriculum development. The main...... environment, the university environment, and the teachers and students. Each of them and their influence on the curriculum is described and the sources of information about the influencers are discussed. The CDIO syllabus has been defined as part of the basis for the Bachelor of Engineering programs...

  14. Arctic Climate Connections Curriculum: A Model for Bringing Authentic Data into the Classroom

    Science.gov (United States)

    Gold, Anne U.; Kirk, Karin; Morrison, Deb; Lynds, Susan; Sullivan, Susan Buhr; Grachev, Andrey; Persson, Ola

    2015-01-01

    Science education can build a bridge between research carried out by scientists and relevant learning opportunities for students. The Broader Impact requirements for scientists by funding agencies facilitate this connection. We propose and test a model curriculum development process in which scientists, curriculum developers, and classroom…

  15. Empirical Test of the Know, See, Plan, Do Model for Curriculum Design in Leadership Education

    Science.gov (United States)

    Martin, Beth Ann; Allen, Scott J.

    2016-01-01

    This research assesses the Know, See, Plan, portions of the Know, See, Plan, Do (KSPD) model for curriculum design in leadership education. There were 3 graduate student groups, each taught using 1 of 3 different curriculum designs (KSPD and 2 control groups). Based on a pretest, post-test design, students' performance was measured to assess their…

  16. Towards a Multi-Stakeholder-Driven Model for Excellence in Higher Education Curriculum Development

    Science.gov (United States)

    Meyer, M. H.; Bushney, M. J.

    2008-01-01

    A multi-stakeholder-driven model for excellence in higher education curriculum development has been developed. It is based on the assumption that current efforts to curriculum development take place within a framework of limited stakeholder consultation. A total of 18 multiple stakeholders are identified, including learners, alumni, government,…

  17. Towards a Multi-Stakeholder-Driven Model for Excellence in Higher Education Curriculum Development

    Science.gov (United States)

    Meyer, M. H.; Bushney, M. J.

    2008-01-01

    A multi-stakeholder-driven model for excellence in higher education curriculum development has been developed. It is based on the assumption that current efforts to curriculum development take place within a framework of limited stakeholder consultation. A total of 18 multiple stakeholders are identified, including learners, alumni, government,…

  18. Curriculum Guidelines for a Distance Education Course in Urban Agriculture Based on an Eclectic Model.

    Science.gov (United States)

    Gaum, Wilma G.; van Rooyen, Hugo G.

    1997-01-01

    Describes research to develop curriculum guidelines for a distance education course in urban agriculture. The course, designed to train the teacher, is based on an eclectic curriculum design model. The course is aimed at the socioeconomic empowerment of urban farmers and is based on sustainable ecological-agricultural principles, an…

  19. Rocket injector anomalies study. Volume 1: Description of the mathematical model and solution procedure

    Science.gov (United States)

    Przekwas, A. J.; Singhal, A. K.; Tam, L. T.

    1984-01-01

    The capability of simulating three dimensional two phase reactive flows with combustion in the liquid fuelled rocket engines is demonstrated. This was accomplished by modifying an existing three dimensional computer program (REFLAN3D) with Eulerian Lagrangian approach to simulate two phase spray flow, evaporation and combustion. The modified code is referred as REFLAN3D-SPRAY. The mathematical formulation of the fluid flow, heat transfer, combustion and two phase flow interaction of the numerical solution procedure, boundary conditions and their treatment are described.

  20. A project-centered undergraduate geoscience curriculum model

    Science.gov (United States)

    Kelso, P.; Brown, L.

    2003-04-01

    Lake Superior State University, a comprehensive rural public university with approximately 10% Native-Americans enrolled, located in Michigan's eastern Upper Peninsula, U.S.A., has redesigned it's undergraduate geology major by developing an entire curriculum around a project-centered integration of geoscience sub-disciplines. Our model, adapted from modern educational theory, advocates sub-discipline integration by implementing problem-based learning through coursework that develops students' intellectual skills and engages them in using complex reasoning in real-world contexts. Students in this new curriculum will actively discover how to learn about a new geologic province, what questions to ask in approaching problems, where and how to find answers, and how to apply knowledge to solving problems. To accomplish our goals, we redesigned our pedagogy for all courses by creating active learning environments including cooperative learning, jigsaw methodologies, debates, investigation oriented laboratories, use of case studies, writing and communication intensive exercises, and research experiences. Fundamental sub-discipline concepts were identified by our national survey and are presented in the context of sequentially ordered problems that reflect increasing geological complexity. All courses above first year incorporate significant field experience. Our lower division courses include a two semester sequence of physical and historical geology in which physical processes are discussed in the context of their historical extension and one semester of structure/tectonics and mineralogy/petrology. The lower division culminates with a three week introductory field geology course. Our upper division courses include hydrologic systems, environmental systems, geochemical systems, tectonic systems, geophysical systems, clastic systems, carbonate systems, two seminar courses, and advanced field geology. The two field courses, offered in different geologic provinces, provide

  1. Simple-1: Development stage of the data transmission system for a solid propellant mid-power rocket model

    Science.gov (United States)

    Yarce, Andrés; Sebastián Rodríguez, Juan; Galvez, Julián; Gómez, Alejandro; García, Manuel J.

    2017-06-01

    This paper presents the development stage of a communication module for a solid propellant mid-power rocket model. The communication module was named. Simple-1 and this work considers its design, construction and testing. A rocket model Estes Ventris Series Pro II® was modified to introduce, on the top of the payload, several sensors in a CanSat form factor. The Printed Circuit Board (PCB) was designed and fabricated from Commercial Off The Shelf (COTS) components and assembled in a cylindrical rack structure similar to this small format satellite concept. The sensors data was processed using one Arduino Mini and transmitted using a radio module to a Software Defined Radio (SDR) HackRF based platform on the ground station. The Simple-1 was tested using a drone in successive releases, reaching altitudes from 200 to 300 meters. Different kind of data, in terms of altitude, position, atmospheric pressure and vehicle temperature were successfully measured, making possible the progress to a next stage of launching and analysis.

  2. Parametric studies with an atmospheric diffusion model that assesses toxic fuel hazards due to the ground clouds generated by rocket launches

    Science.gov (United States)

    Stewart, R. B.; Grose, W. L.

    1975-01-01

    Parametric studies were made with a multilayer atmospheric diffusion model to place quantitative limits on the uncertainty of predicting ground-level toxic rocket-fuel concentrations. Exhaust distributions in the ground cloud, cloud stabilized geometry, atmospheric coefficients, the effects of exhaust plume afterburning of carbon monoxide CO, assumed surface mixing-layer division in the model, and model sensitivity to different meteorological regimes were studied. Large-scale differences in ground-level predictions are quantitatively described. Cloud alongwind growth for several meteorological conditions is shown to be in error because of incorrect application of previous diffusion theory. In addition, rocket-plume calculations indicate that almost all of the rocket-motor carbon monoxide is afterburned to carbon dioxide CO2, thus reducing toxic hazards due to CO. The afterburning is also shown to have a significant effect on cloud stabilization height and on ground-level concentrations of exhaust products.

  3. Designing a Curriculum Model for the Teaching of the Bible in UK Jewish Secondary Schools: A Case Study

    Science.gov (United States)

    Kohn, Eli

    2012-01-01

    This paper describes the process of designing a curriculum model for Bible teaching in UK Jewish secondary schools. This model was designed over the period 2008-2010 by a team of curriculum specialists from the Jewish Curriculum Partnership UK in collaboration with a group of teachers from Jewish secondary schools. The paper first outlines the…

  4. CFD Modelling of a Quadrupole Vortex Inside a Cylindrical Channel for Research into Advanced Hybrid Rocket Designs

    Science.gov (United States)

    Godfrey, B.; Majdalani, J.

    2014-11-01

    This study relies on computational fluid dynamics (CFD) tools to analyse a possible method for creating a stable quadrupole vortex within a simulated, circular-port, cylindrical rocket chamber. A model of the vortex generator is created in a SolidWorks CAD program and then the grid is generated using the Pointwise mesh generation software. The non-reactive flowfield is simulated using an open source computational program, Stanford University Unstructured (SU2). Subsequent analysis and visualization are performed using ParaView. The vortex generation approach that we employ consists of four tangentially injected monopole vortex generators that are arranged symmetrically with respect to the center of the chamber in such a way to produce a quadrupole vortex with a common downwash. The present investigation focuses on characterizing the flow dynamics so that future investigations can be undertaken with increasing levels of complexity. Our CFD simulations help to elucidate the onset of vortex filaments within the monopole tubes, and the evolution of quadrupole vortices downstream of the injection faceplate. Our results indicate that the quadrupole vortices produced using the present injection pattern can become quickly unstable to the extent of dissipating soon after being introduced into simulated rocket chamber. We conclude that a change in the geometrical configuration will be necessary to produce more stable quadrupoles.

  5. Curriculum information models in health professions education in Australia: an innovative approach to efficient curriculum design, development, and maintenance.

    Science.gov (United States)

    Kruger, Estie; Tennant, Marc

    2012-03-01

    Over the last decade, there has been a significant increase in attention to the overall accountability of higher education in Australia, and this is expected to continue. Increased accountability has led to the need for more explicitly documented curricula. The curricula from ten health-related disciplines developed over the last five years in Australia were the basis of this study. Curriculum information modeling is an approach that allows for the dynamic nature of curricula since elements and their linkages can be moved about and reconnected into meaningful patterns. In addition, the models give disciplines and institutions the ability to effectively monitor curricula and draw comparisons in a more unified manner. Curriculum information models are an efficient innovation in the design and management of curricula in higher education and particularly in the health care disciplines. They rest on the principles of reusable elements and linkages independent of content that were first used in the design, construction, and maintenance of buildings. The translation of this approach to the higher education sector provides a higher level of interoperability of resources and a clearer pathway for content design within a curriculum.

  6. Modeling of Uneven Flow and Electromagnetic Field Parameters in the Combustion Chamber of Liquid Rocket Engine with a Near-wall Layer Available

    Directory of Open Access Journals (Sweden)

    A. V. Rudinskii

    2015-01-01

    Full Text Available The paper concerns modeling of an uneven flow and electromagnetic field parameters in the combustion chamber of the liquid rocket engine with a near-wall layer available.The research objective was to evaluate quantitatively influence of changing model chamber mode of the liquid rocket engine on the electro-physical characteristics of the hydrocarbon fuel combustion by-products.The main method of research was based on development of a final element model of the flowing path of the rocket engine chamber and its adaptation to the boundary conditions.The paper presents a developed two-dimensional non-stationary mathematical model of electro-physical processes in the liquid rocket engine chamber using hydrocarbon fuel. The model takes into consideration the features of a gas-dynamic contour of the engine chamber and property of thermo-gas-dynamic characteristics of the ionized products of combustion of hydrocarbonic fuel. Distributions of magnetic field intensity and electric conductivity received and analyzed taking into account a low-temperature near-wall layer. Special attention is paid to comparison of obtained calculation values of the electric current, which is taken out from intrachamber space of the engine with earlier published data of other authors.

  7. Modeling and Testing of Non-Nuclear, Highpower Simulated Nuclear Thermal Rocket Reactor Elements

    Science.gov (United States)

    Kirk, Daniel R.

    2005-01-01

    When the President offered his new vision for space exploration in January of 2004, he said, "Our third goal is to return to the moon by 2020, as the launching point for missions beyond," and, "With the experience and knowledge gained on the moon, we will then be ready to take the next steps of space exploration: human missions to Mars and to worlds beyond." A human mission to Mars implies the need to move large payloads as rapidly as possible, in an efficient and cost-effective manner. Furthermore, with the scientific advancements possible with Project Prometheus and its Jupiter Icy Moons Orbiter (JIMO), (these use electric propulsion), there is a renewed interest in deep space exploration propulsion systems. According to many mission analyses, nuclear thermal propulsion (NTP), with its relatively high thrust and high specific impulse, is a serious candidate for such missions. Nuclear rockets utilize fission energy to heat a reactor core to very high temperatures. Hydrogen gas flowing through the core then becomes superheated and exits the engine at very high exhaust velocities. The combination of temperature and low molecular weight results in an engine with specific impulses above 900 seconds. This is almost twice the performance of the LOX/LH2 space shuttle engines, and the impact of this performance would be to reduce the trip time of a manned Mars mission from the 2.5 years, possible with chemical engines, to about 12-14 months.

  8. Models of Non-Stationary Thermodynamic Processes in Rocket Engines Taking into Account a Chemical Equilibrium of Combustion Products

    Directory of Open Access Journals (Sweden)

    A. V. Aliev

    2015-01-01

    Full Text Available The paper considers the two approach-based techniques for calculating the non-stationary intra-chamber processes in solid-propellant rocket engine (SPRE. The first approach assumes that the combustion products are a mechanical mix while the other one supposes it to be the mix, which is in chemical equilibrium. To enhance reliability of solution of the intra ballistic tasks, which assume a chemical equilibrium of combustion products, the computing algorithms to calculate a structure of the combustion products are changed. The algorithm for solving a system of the nonlinear equations of chemical equilibrium, when determining the iterative amendments, uses the orthogonal QR method instead of a method of Gauss. Besides, a possibility to apply genetic algorithms in a task about a structure of combustion products is considered.It is shown that in the tasks concerning the prediction of non-stationary intra ballistic characteristics in a solid propellant rocket engine, application of models of mechanical mix and chemically equilibrium structure of combustion products leads to qualitatively and quantitatively coinciding results. The maximum difference in parameters is 5-10%, at most. In tasks concerning the starting operation of a solid sustainer engine with high-temperature products of combustion difference in results is more essential, and can reach 20% and more.A technique to calculate the intra ballistic parameters, in which flotation of combustion products is considered in the light of a spatial statement, requires using the high-performance computer facilities. For these tasks it is offered to define structure of products of combustion and its thermo-physical characteristics, using the polynoms coefficients of which should be predefined.

  9. A model marine-science curriculum for fourth-grade pupils in Florida

    Science.gov (United States)

    Schulte, Philip James

    This dissertation focused on the development of a model marine-science curriculum for fourth-grade pupils in the State of Florida. The curriculum was developed using grounded theory research method, including a component of data collected from an on-line survey administered to 106 professional educators and marine biologists. The results of the data collection and analysis showed a definitive necessity for teacher preparedness, multidisciplinary content, and inquiry-based science instruction. Further, three important factors emerged: (a) collaborative grouping increases achievement; (b) field excursions significantly impact student motivation; (c) standardized testing influences curriculum development. The curriculum is organized as an 11-day unit, with detailed lesson plans presented in standard curricular format and with all components correlated to the Florida State Educational Standards. The curriculum incorporates teacher preparation, multimedia presentations, computer-assisted instruction, scientific art appreciation, and replication as well as assessment factors. The curriculum addresses topics of ichthyology, marine animal identification, environmental conservation and protection, marine animal anatomy, water safety, environmental stewardship, and responsible angling techniques. The components of the curriculum were discussed with reference to the literature on which it was based and recommendations for future research were addressed.

  10. PLA-Based Curriculum: Humanistic Model of Higher Education

    Science.gov (United States)

    Popova-Gonci, Viktoria; Tobol, Amy Ruth

    2011-01-01

    The authors believe that there is no inherent academic validity or lack of thereof in the notion of prior learning assessment (PLA)-based curriculum. If mishandled, it can become the tool for carrying out diploma mill practices. Conversely, if implemented and facilitated appropriately, PLA-based curricula can offer humanistic educational values…

  11. Homology Modeling and Molecular Docking for the Science Curriculum

    Science.gov (United States)

    McDougal, Owen M.; Cornia, Nic; Sambasivarao, S. V.; Remm, Andrew; Mallory, Chris; Oxford, Julia Thom; Maupin, C. Mark; Andersen, Tim

    2014-01-01

    DockoMatic 2.0 is a powerful open source software program (downloadable from sourceforge.net) that allows users to utilize a readily accessible computational tool to explore biomolecules and their interactions. This manuscript describes a practical tutorial for use in the undergraduate curriculum that introduces students to macromolecular…

  12. Modeling of Rocket Fuel Heating and Cooling Processes in the Interior Receptacle Space of Ground-Based Systems

    Directory of Open Access Journals (Sweden)

    K. I. Denisova

    2016-01-01

    Full Text Available The propellant to fill the fuel tanks of the spacecraft, upper stages, and space rockets on technical and ground-based launch sites before fueling should be prepared to ensure many of its parameters, including temperature, in appropriate condition. Preparation of fuel temperature is arranged through heating and cooling the rocket propellants (RP in the tanks of fueling equipment. Processes of RP temperature preparation are the most energy-intensive and timeconsuming ones, which require that a choice of sustainable technologies and modes of cooling (heating RP provided by the ground-based equipment has been made through modeling of the RP [1] temperature preparation processes at the stage of design and operation of the groundbased fueling equipment.The RP temperature preparation in the tanks of the ground-based systems can be provided through the heat-exchangers built-in the internal space and being external with respect to the tank in which antifreeze, air or liquid nitrogen may be used as the heat transfer media. The papers [1-12], which note a promising use of the liquid nitrogen to cool PR, present schematic diagrams and modeling systems for the RP temperature preparation in the fueling equipment of the ground-based systems.We consider the RP temperature preparation using heat exchangers to be placed directly in RP tanks. Feeding the liquid nitrogen into heat exchanger with the antifreeze provides the cooling mode of PR while a heated air fed there does that of heating. The paper gives the systems of equations and results of modeling the processes of RP temperature preparation, and its estimated efficiency.The systems of equations of cooling and heating RP are derived on the assumption that the heat exchange between the fuel and the antifreeze, as well as between the storage tank and the environment is quasi-stationary.The paper presents calculation results of the fuel temperature in the tank, and coolant temperature in the heat exchanger, as

  13. Rocket propulsion elements

    CERN Document Server

    Sutton, George P

    2011-01-01

    The definitive text on rocket propulsion-now revised to reflect advancements in the field For sixty years, Sutton's Rocket Propulsion Elements has been regarded as the single most authoritative sourcebook on rocket propulsion technology. As with the previous edition, coauthored with Oscar Biblarz, the Eighth Edition of Rocket Propulsion Elements offers a thorough introduction to basic principles of rocket propulsion for guided missiles, space flight, or satellite flight. It describes the physical mechanisms and designs for various types of rockets' and provides an unders

  14. International Curriculums.

    Science.gov (United States)

    Neal, Larry L.

    This workshop presentation on international curriculums in the field of parks, recreation, leisure, cultural services, and travel/tourism comments that the literature is replete with articles addressing what the field is about, but not about curriculum issues, models, and structure. It reports an international survey of 12 college educators…

  15. Solar Thermal Rocket Propulsion

    Science.gov (United States)

    Sercel, J. C.

    1986-01-01

    Paper analyzes potential of solar thermal rockets as means of propulsion for planetary spacecraft. Solar thermal rocket uses concentrated Sunlight to heat working fluid expelled through nozzle to produce thrust.

  16. Laser optogalvanic spectroscopy of neon in a discharge plasma and modeling and analysis of rocket plume RF-line emissions

    Science.gov (United States)

    Ogungbemi, Kayode I.

    The Optogalvanic Effect (OGE) of neon in a hollow cathode discharge lamp has been investigated both experimentally and theoretically. A tunable dye laser was tuned to several 1si -- 2pj neon transitions and the associated time--resolved optogalvanic (OG) spectral waveforms recorded corresponding to the DeltaJ = DeltaK = 0, +/-1 selection rules and modeled using a semi-empirical model. Decay rate constants, amplitudes and the instrumentation time constants were recorded following a good least-squares fit (between the experimental and the theoretical OG data) using the Monte Carlo technique and utilizing both the search and random walk methods. Dominant physical processes responsible for the optogalvanic effect have been analyzed, and the corresponding populations of the laser-excited level and collisional excited levels determined. The behavior of the optogalvanic signal waveform as a function of time, together with the decay rate constants as a function of the discharge current and the instrumentation time constant as a function of current have been studied in detail. The decay times of the OG signals and the population redistributions were also determined. Fairly linear relationships between the decay rate constant and the discharge current, as well as between the instrumental time constant and the discharge current, have been observed. The decay times and the electron collisional rate parameters of the 1s levels involved in the OG transitions have been obtained with accuracy. The excitation temperature of the discharge for neon transitions grouped with the same 1s level have been determined and found to be fairly constant for the neon transitions studied. The experimental optogalvanic effort in the visible region of the electromagnetic spectrum has been complemented by a computation-intensive modeling investigation of rocket plumes in the microwave region. Radio frequency lines of each of the plume species identified were archived utilizing the HITRAN and other

  17. The Effects of a Model-Based Physics Curriculum Program with a Physics First Approach: A Causal-Comparative Study

    Science.gov (United States)

    Liang, Ling L.; Fulmer, Gavin W.; Majerich, David M.; Clevenstine, Richard; Howanski, Raymond

    2012-01-01

    The purpose of this study is to examine the effects of a model-based introductory physics curriculum on conceptual learning in a Physics First (PF) Initiative. This is the first comparative study in physics education that applies the Rasch modeling approach to examine the effects of a model-based curriculum program combined with PF in the United…

  18. A modular ducted rocket missile model for threat and performance assessment

    NARCIS (Netherlands)

    Mayer, A.E.H.J.; Halswijk, W.H.C.; Komduur, H.J.; Lauzon, M.; Stowe, R.A.

    2005-01-01

    A model was developed to predict the thrust of throttled ramjet propelled missiles. The model is called DRCORE and fulfils the growing need to predict the performance of air breathing missiles. Each subsystem of the propulsion unit of this model is coded by using engineering formulae and enables the

  19. Developing a Model for an Innovative Culinary Competency Curriculum and Examining Its Effects on Students' Performance

    Science.gov (United States)

    Hu, Meng-Lei I-Chen Monica; Horng, Jeou-Shyan; Teng, Chih-Ching

    2016-01-01

    The present study designs and develops an innovative culinary competency curriculum (ICCC) model comprising seven sections: innovative culture, aesthetics, techniques, service, product, management, and creativity. The model is formulated based on culinary concept, creativity, innovation, and competency theory. The four elements of curriculum…

  20. An Evaluation of High School Curricula Employing Using the Element-Based Curriculum Development Model

    Science.gov (United States)

    Aslan, Dolgun; Günay, Rafet

    2016-01-01

    This study was conducted with the aim of evaluating the curricula that constitute the basis of education provision at high schools in Turkey from the perspective of the teachers involved. A descriptive survey model, a quantitative research method was employed in this study. An item-based curriculum evaluation model was employed as part of the…

  1. Preparedness for clinical: evaluation of the core elements of the Clinical Immersion curriculum model.

    Science.gov (United States)

    Diefenbeck, Cynthia; Herrman, Judith; Wade, Gail; Hayes, Evelyn; Voelmeck, Wayne; Cowperthwait, Amy; Norris, Susan

    2015-01-01

    The Clinical Immersion Model is an innovative baccalaureate nursing curriculum that has demonstrated successful outcomes over the past 10 years. For those intending to adopt the model, individual components in isolation may prove ineffective. This article describes three core components of the curriculum that form the foundation of preparation for the senior-year clinical immersion. Detailed student-centered outcomes evaluation of these critical components is shared. Results of a mixed-methods evaluation, including surveys and focus groups, are presented. Implications of this curricular evaluation and future directions are explored.

  2. A process: development of a model multiculturalism curriculum designed for mobility across geographic borders.

    Science.gov (United States)

    Frels, L; Scott, J; Schramm, M A

    1997-08-01

    The Council on Accreditation Project, Nurse Anesthesia Educational Requirements and Mobility Between North American Free Trade Agreement (NAFTA) Countries, has as one of its outcomes the development of a model curriculum that would minimize educational barriers for mobility of nurse anesthetists across NAFTA geographical borders with a focus on the blending of professional and technical expertise with issues of human diversity and/or cultural differences. The overall long-term outcome of the project is to test a process. The manuscript discusses the process used in year III of the project to integrate cultural concepts into a nurse anesthesia model curriculum.

  3. Development of a model animal welfare act curriculum.

    Science.gov (United States)

    VandeWoude, Sue

    2007-01-01

    Animal-welfare issues are often controversial and frequently have an emotional component. Veterinarians have extensive knowledge, experience, and scientific perspective and are arguably the professionals best suited to advise and develop recommendations on animal welfare. The development of an Animal Welfare Act (AWA) teaching module is a first step toward educating veterinary students about animal welfare. This article presents the current development status of this curriculum project, which is intended to be a valuable addition to the evolving veterinary education on animal welfare.

  4. Rockets two classic papers

    CERN Document Server

    Goddard, Robert

    2002-01-01

    Rockets, in the primitive form of fireworks, have existed since the Chinese invented them around the thirteenth century. But it was the work of American Robert Hutchings Goddard (1882-1945) and his development of liquid-fueled rockets that first produced a controlled rocket flight. Fascinated by rocketry since boyhood, Goddard designed, built, and launched the world's first liquid-fueled rocket in 1926. Ridiculed by the press for suggesting that rockets could be flown to the moon, he continued his experiments, supported partly by the Smithsonian Institution and defended by Charles Lindbergh. T

  5. Condensation of water vapor and carbon dioxide in the jet exhausts of rocket engines: 1. Model calculation of the physical conditions in a jet exhaust

    Science.gov (United States)

    Platov, Yu. V.; Alpatov, V. V.; Klyushnikov, V. Yu.

    2014-01-01

    Model calculations have been performed for the temperature and pressure of combustion products in the jet exhaust of rocket engines of last stages of Proton, Molniya, and Start launchers operating in the upper atmosphere at altitudes above 120 km. It has been shown that the condensation of water vapor and carbon dioxide can begin at distances of 100-150 and 450-650 m away from the engine nozzle, respectively.

  6. Thermal-Flow Code for Modeling Gas Dynamics and Heat Transfer in Space Shuttle Solid Rocket Motor Joints

    Science.gov (United States)

    Wang, Qunzhen; Mathias, Edward C.; Heman, Joe R.; Smith, Cory W.

    2000-01-01

    A new, thermal-flow simulation code, called SFLOW. has been developed to model the gas dynamics, heat transfer, as well as O-ring and flow path erosion inside the space shuttle solid rocket motor joints by combining SINDA/Glo, a commercial thermal analyzer. and SHARPO, a general-purpose CFD code developed at Thiokol Propulsion. SHARP was modified so that friction, heat transfer, mass addition, as well as minor losses in one-dimensional flow can be taken into account. The pressure, temperature and velocity of the combustion gas in the leak paths are calculated in SHARP by solving the time-dependent Navier-Stokes equations while the heat conduction in the solid is modeled by SINDA/G. The two codes are coupled by the heat flux at the solid-gas interface. A few test cases are presented and the results from SFLOW agree very well with the exact solutions or experimental data. These cases include Fanno flow where friction is important, Rayleigh flow where heat transfer between gas and solid is important, flow with mass addition due to the erosion of the solid wall, a transient volume venting process, as well as some transient one-dimensional flows with analytical solutions. In addition, SFLOW is applied to model the RSRM nozzle joint 4 subscale hot-flow tests and the predicted pressures, temperatures (both gas and solid), and O-ring erosions agree well with the experimental data. It was also found that the heat transfer between gas and solid has a major effect on the pressures and temperatures of the fill bottles in the RSRM nozzle joint 4 configuration No. 8 test.

  7. Numerical investigation of high-pressure combustion in rocket engines using Flamelet/Progress-variable models

    CERN Document Server

    Coclite, A; De Palma, P; Pascazio, G

    2015-01-01

    The present paper deals with the numerical study of high pressure LOx/H2 or LOx/hydrocarbon combustion for propulsion systems. The present research effort is driven by the continued interest in achieving low cost, reliable access to space and more recently, by the renewed interest in hypersonic transportation systems capable of reducing time-to-destination. Moreover, combustion at high pressure has been assumed as a key issue to achieve better propulsive performance and lower environmental impact, as long as the replacement of hydrogen with a hydrocarbon, to reduce the costs related to ground operations and increase flexibility. The current work provides a model for the numerical simulation of high- pressure turbulent combustion employing detailed chemistry description, embedded in a RANS equations solver with a Low Reynolds number k-omega turbulence model. The model used to study such a combustion phenomenon is an extension of the standard flamelet-progress-variable (FPV) turbulent combustion model combined ...

  8. Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations

    Directory of Open Access Journals (Sweden)

    David R. Greatrix

    2008-01-01

    Full Text Available A general numerical model based on the Zeldovich-Novozhilov solid-phase energy conservation result for unsteady solid-propellant burning is presented in this paper. Unlike past models, the integrated temperature distribution in the solid phase is utilized directly for estimating instantaneous burning rate (rather than the thermal gradient at the burning surface. The burning model is general in the sense that the model may be incorporated for various propellant burning-rate mechanisms. Given the availability of pressure-related experimental data in the open literature, varying static pressure is the principal mechanism of interest in this study. The example predicted results presented in this paper are to a substantial extent consistent with the corresponding experimental firing response data.

  9. Combining the Old and the New: Designing a Curriculum Based on the Taba Model and the Global Scale of English

    Science.gov (United States)

    Aydin, Belgin; Unver, Meral Melek; Alan, Bülent; Saglam, Sercan

    2017-01-01

    This paper explains the process of designing a curriculum based on the Taba Model and the Global Scale of English (GSE) in an intensive language education program. The Taba Model emphasizing the involvement of the teachers and the learners in the curriculum development process was combined with the GSE, a psychometric tool measuring language…

  10. Low-thrust rocket trajectories

    Energy Technology Data Exchange (ETDEWEB)

    Keaton, P.W.

    1986-01-01

    The development of low-thrust propulsion systems to complement chemical propulsion systems will greatly enhance the evolution of future space programs. Two advantages of low-thrust rockets are stressed: first, in a strong gravitational field, such as occurs near the Earth, freighter missions with low-thrust engines require one-tenth as much propellant as do chemical engines. Second, in a weak gravitational field, such as occurs in the region between Venus and Mars, low-thrust rockets are faster than chemical rockets with comparable propellant mass. The purpose here is to address the physics of low-thrust trajectories and to interpret the results with two simple models. Analytic analyses are used where possible - otherwise, the results of numerical calculations are presented in graphs. The author has attempted to make this a self-contained report. 57 refs., 10 figs.

  11. Low-thrust rocket trajectories

    Energy Technology Data Exchange (ETDEWEB)

    Keaton, P.W.

    1987-03-01

    The development of low-thrust propulsion systems to complement chemical propulsion systems will greatly enhance the evolution of future space programs. Two advantages of low-thrust rockets are stressed: first, in a strong gravitational field, such as occurs near the Earth, freighter missions with low-thrust engines require one-tenth as much propellant as do chemical engines. Second, in a weak gravitational field, such as occurs in the region between Venus and Mars, low-thrust rockets are faster than chemical rockets with comparable propellant mass. The purpose here is to address the physics of low-thrust trajectories and to interpret the results with two simple models. Analytic analyses are used where possible - otherwise, the results of numerical calculations are presented in graphs. The author has attempted to make this a self-contained report.

  12. A Flight Dynamics Model for a Multi-Actuated Flexible Rocket Vehicle

    Science.gov (United States)

    Orr, Jeb S.

    2011-01-01

    A comprehensive set of motion equations for a multi-actuated flight vehicle is presented. The dynamics are derived from a vector approach that generalizes the classical linear perturbation equations for flexible launch vehicles into a coupled three-dimensional model. The effects of nozzle and aerosurface inertial coupling, sloshing propellant, and elasticity are incorporated without restrictions on the position, orientation, or number of model elements. The present formulation is well suited to matrix implementation for large-scale linear stability and sensitivity analysis and is also shown to be extensible to nonlinear time-domain simulation through the application of a special form of Lagrange s equations in quasi-coordinates. The model is validated through frequency-domain response comparison with a high-fidelity planar implementation.

  13. Aerodynamics and flow characterisation of multistage rockets

    Science.gov (United States)

    Srinivas, G.; Prakash, M. V. S.

    2017-05-01

    The main objective of this paper is to conduct a systematic flow analysis on single, double and multistage rockets using ANSYS software. Today non-air breathing propulsion is increasing dramatically for the enhancement of space exploration. The rocket propulsion is playing vital role in carrying the payload to the destination. Day to day rocket aerodynamic performance and flow characterization analysis has becoming challenging task to the researchers. Taking this task as motivation a systematic literature is conducted to achieve better aerodynamic and flow characterization on various rocket models. The analyses on rocket models are very little especially in numerical side and experimental area. Each rocket stage analysis conducted for different Mach numbers and having different flow varying angle of attacks for finding the critical efficiency performance parameters like pressure, density and velocity. After successful completion of the analysis the research reveals that flow around the rocket body for Mach number 4 and 5 best suitable for designed payload. Another major objective of this paper is to bring best aerodynamics flow characterizations in both aero and mechanical features. This paper also brings feature prospectus of rocket stage technology in the field of aerodynamic design.

  14. Modeling of Heat Transfer and Ablation of Refractory Material Due to Rocket Plume Impingement

    Science.gov (United States)

    Harris, Michael F.; Vu, Bruce T.

    2012-01-01

    CR Tech's Thermal Desktop-SINDA/FLUINT software was used in the thermal analysis of a flame deflector design for Launch Complex 39B at Kennedy Space Center, Florida. The analysis of the flame deflector takes into account heat transfer due to plume impingement from expected vehicles to be launched at KSC. The heat flux from the plume was computed using computational fluid dynamics provided by Ames Research Center in Moffet Field, California. The results from the CFD solutions were mapped onto a 3-D Thermal Desktop model of the flame deflector using the boundary condition mapping capabilities in Thermal Desktop. The ablation subroutine in SINDA/FLUINT was then used to model the ablation of the refractory material.

  15. A Model Longitudinal Observation Medicine Curriculum for an Emergency Medicine Residency.

    Science.gov (United States)

    Wheatley, Matthew; Baugh, Christopher; Osborne, Anwar; Clark, Carol; Shayne, Philip; Ross, Michael

    2016-04-01

    The role of observation services for emergency department patients has increased in recent years. Driven by changing health care practices and evolving payer policies, many hospitals in the United States currently have or are developing an observation unit (OU) and emergency physicians are most often expected to manage patients in this setting. Yet, few residency programs dedicate a portion of their clinical curriculum to observation medicine. This knowledge set should be integrated into the core training curriculum of emergency physicians. Presented here is a model observation medicine longitudinal training curriculum, which can be integrated into an emergency medicine (EM) residency. It was developed by a consensus of content experts representing the observation medicine interest group and observation medicine section, respectively, from EM's two major specialty societies: the Society for Academic Emergency Medicine (SAEM) and the American College of Emergency Physicians (ACEP). The curriculum consists of didactic, clinical, and self-directed elements. It is longitudinal, with learning objectives for each year of training, focusing initially on the basic principles of observation medicine and appropriate observation patient selection; moving to the management of various observation appropriate conditions; and then incorporating further concepts of OU management, billing, and administration. This curriculum is flexible and designed to be used in both academic and community EM training programs within the United States. Additionally, scholarly opportunities, such as elective rotations and fellowship training, are explored.

  16. Curriculum innovation in an accelerated BSN program: the ACE Model.

    Science.gov (United States)

    Suplee, Patricia D; Glasgow, Mary Ellen

    2008-01-01

    As the demand for registered nurses continues to rise, so too has the creation of accelerated baccalaureate nursing programs for second-degree students. This article describes an 11-month Accelerated Career Entry (ACE) Nursing Program's innovative curriculum design, which has a heavy emphasis on technology, professional socialization, and the use of a standardized patient experience as a form of summative evaluation. In addition, challenges of this program are presented. Since 2002, the ACE Program has graduated over 500 students with an average first-time NCLEX pass rate of 95-100%. Although the number of graduates from accelerated programs does not solve the severe nursing shortage, the contributions of these intelligent, assertive, pioneering graduates are important for health care.

  17. Reynolds-averaged Navier-Stokes analysis of the flow through a model rocket-based combined-cycle engine with an independently-fueled ramjet stream

    Science.gov (United States)

    Bond, Ryan Bomar

    A new concept for the low speed propulsion mode in rocket based combined cycle (RBCC) engines has been developed as part of the NASA GTX program. This concept, called the independent ramjet stream (IRS) cycle, is a variation of the traditional ejector ramjet (ER) design and involves the injection of hydrogen fuel directly into the air stream, where it is ignited by the rocket plume. Experiments and computational fluid dynamics (CFD) are currently being used to evaluate the feasibility of the new design. In this work, a Navier-Stokes code valid for general reactive flows is applied to the model engine under cold flow, ejector ramjet, and IRS cycle operation. Pressure distributions corresponding to cold-flow and ejector ramjet operation are compared with experimental data. The engine response under independent ramjet stream cycle operation is examined for different reaction models and grid sizes. The engine response to variations in fuel injection is also examined. Mode transition simulations are also analyzed both with and without a nitrogen purge of the rocket. The solutions exhibit a high sensitivity to both grid resolution and reaction mechanism, but they do indicate that thermal throat ramjet operation is possible through the injection and burning of additional fuel into the air stream. The solutions also indicate that variations in fuel injection location can affect the position of the thermal throat. The numerical simulations predicted successful mode transition both with and without a nitrogen purge of the rocket; however, the reliability of the mode transition results cannot be established without experimental data to validate the reaction mechanism.

  18. The Effects of Selected Death Education Curriculum Models on Death Anxiety and Death Acceptance.

    Science.gov (United States)

    Combs, Don C.

    1981-01-01

    A comparison of the effects of didactic and experiential death education curriculums show no decrease in death anxiety from mid- to posttesting for any treatment group. Anxiety was increased from pre- to mid-testing for some students. Results may be due to model deficiencies. Further research is suggested. (JAC)

  19. Open Learning and Formal Credentialing in Higher Education: Curriculum Models and Institutional Policies

    Science.gov (United States)

    Reushle, Shirley, Ed.; Antonio, Amy, Ed.; Keppell, Mike, Ed.

    2016-01-01

    The discipline of education is a multi-faceted system that must constantly integrate new strategies and procedures to ensure successful learning experiences. Enhancements in education provide learners with greater opportunities for growth and advancement. "Open Learning and Formal Credentialing in Higher Education: Curriculum Models and…

  20. Training Counselors to Use Computer-Assisted Career Guidance Systems More Effectively: A Model Curriculum

    Science.gov (United States)

    Bobek, Becky L.; Robbins, Steven B.; Gore, Paul A., Jr.; Harris-Bowlsbey, JoAnn; Lapan, Richard T.; Dahir, Carol A.; Jepsen, David A.

    2005-01-01

    A model graduate training curriculum that emphasizes the counselor's role in assisting clients in the effective use of computer-assisted career guidance (CACG) systems is described in this article. This 4-module graduate training program emphasizes client readiness and exploration using CACG systems, skill building and simulation exercises, and…

  1. Curriculum-Integrated Information Literacy (CIIL) in a Community College Nursing Program: A Practical Model

    Science.gov (United States)

    Argüelles, Carlos

    2016-01-01

    This article describes a strategy to integrate information literacy into the curriculum of a nursing program in a community college. The model is articulated in four explained phases: preparatory, planning, implementation, and evaluation. It describes a collaborative process encouraging librarians to work with nursing faculty, driving students to…

  2. Curriculum-Integrated Information Literacy (CIIL) in a Community College Nursing Program: A Practical Model

    Science.gov (United States)

    Argüelles, Carlos

    2016-01-01

    This article describes a strategy to integrate information literacy into the curriculum of a nursing program in a community college. The model is articulated in four explained phases: preparatory, planning, implementation, and evaluation. It describes a collaborative process encouraging librarians to work with nursing faculty, driving students to…

  3. A Sustainable Model for Integrating Current Topics in Machine Learning Research into the Undergraduate Curriculum

    Science.gov (United States)

    Georgiopoulos, M.; DeMara, R. F.; Gonzalez, A. J.; Wu, A. S.; Mollaghasemi, M.; Gelenbe, E.; Kysilka, M.; Secretan, J.; Sharma, C. A.; Alnsour, A. J.

    2009-01-01

    This paper presents an integrated research and teaching model that has resulted from an NSF-funded effort to introduce results of current Machine Learning research into the engineering and computer science curriculum at the University of Central Florida (UCF). While in-depth exposure to current topics in Machine Learning has traditionally occurred…

  4. A Sustainable Model for Integrating Current Topics in Machine Learning Research into the Undergraduate Curriculum

    Science.gov (United States)

    Georgiopoulos, M.; DeMara, R. F.; Gonzalez, A. J.; Wu, A. S.; Mollaghasemi, M.; Gelenbe, E.; Kysilka, M.; Secretan, J.; Sharma, C. A.; Alnsour, A. J.

    2009-01-01

    This paper presents an integrated research and teaching model that has resulted from an NSF-funded effort to introduce results of current Machine Learning research into the engineering and computer science curriculum at the University of Central Florida (UCF). While in-depth exposure to current topics in Machine Learning has traditionally occurred…

  5. Emergency Medical Science (T-139). Curriculum Models, Guidelines, and Outcome-Competencies.

    Science.gov (United States)

    Lovin, Barbara Keelor

    Developed for use by curriculum planners in Emergency Medical Science (EMS) programs throughout the North Carolina Community College System (NCCCS), and by evaluators in their reviews of existing programs, this manual provides a model set of guidelines for the education and training of the Emergency Medical Technician-Paramedic (EMT-P) in…

  6. Investigation of different modeling approaches for computational fluid dynamics simulation of high-pressure rocket combustors

    Science.gov (United States)

    Ivancic, B.; Riedmann, H.; Frey, M.; Knab, O.; Karl, S.; Hannemann, K.

    2016-07-01

    The paper summarizes technical results and first highlights of the cooperation between DLR and Airbus Defence and Space (DS) within the work package "CFD Modeling of Combustion Chamber Processes" conducted in the frame of the Propulsion 2020 Project. Within the addressed work package, DLR Göttingen and Airbus DS Ottobrunn have identified several test cases where adequate test data are available and which can be used for proper validation of the computational fluid dynamics (CFD) tools. In this paper, the first test case, the Penn State chamber (RCM1), is discussed. Presenting the simulation results from three different tools, it is shown that the test case can be computed properly with steady-state Reynolds-averaged Navier-Stokes (RANS) approaches. The achieved simulation results reproduce the measured wall heat flux as an important validation parameter very well but also reveal some inconsistencies in the test data which are addressed in this paper.

  7. Writings as modelling examples: Scaffolds for academic writing in a post-graduate curriculum

    OpenAIRE

    Firssova, Olga

    2014-01-01

    The presented study investigated the effectiveness of learning from models in the context of post-graduate academic writing. Two questions were pursued: whether studying model writings supports mature students in writing in a new genre and whether integrating additional scaffolds in such models has added value. A quasi-experimental control group design study was realised in an on-going distance learning curriculum. Performance on a sequel of writing tasks in a new genre was compared both with...

  8. Introduction to rocket science and engineering

    CERN Document Server

    Taylor, Travis S

    2009-01-01

    What Are Rockets? The History of RocketsRockets of the Modern EraRocket Anatomy and NomenclatureWhy Are Rockets Needed? Missions and PayloadsTrajectoriesOrbitsOrbit Changes and ManeuversBallistic Missile TrajectoriesHow Do Rockets Work? ThrustSpecific ImpulseWeight Flow RateTsiolkovsky's Rocket EquationStagingRocket Dynamics, Guidance, and ControlHow Do Rocket Engines Work? The Basic Rocket EngineThermodynamic Expansion and the Rocket NozzleExit VelocityRocket Engine Area Ratio and LengthsRocket Engine Design ExampleAre All Rockets the Same? Solid Rocket EnginesLiquid Propellant Rocket Engines

  9. Integrated approach for hybrid rocket technology development

    Science.gov (United States)

    Barato, Francesco; Bellomo, Nicolas; Pavarin, Daniele

    2016-11-01

    Hybrid rocket motors tend generally to be simple from a mechanical point of view but difficult to optimize because of their complex and still not well understood cross-coupled physics. This paper addresses the previous issue presenting the integrated approach established at University of Padua to develop hybrid rocket based systems. The methodology tightly combines together system analysis and design, numerical modeling from elementary to sophisticated CFD, and experimental testing done with incremental philosophy. As an example of the approach, the paper presents the experience done in the successful development of a hybrid rocket booster designed for rocket assisted take off operations. It is thought that following the proposed approach and selecting carefully the most promising applications it is possible to finally exploit the major advantages of hybrid rocket motors as safety, simplicity, low cost and reliability.

  10. Evaluation of an integrative model for professional development and research in a dental curriculum.

    Science.gov (United States)

    Ditmyer, Marcia M; Mobley, Connie C; Davenport, William D

    2014-03-01

    The purpose of this project was to evaluate a Research, Professional Development, and Critical Thinking Integrative Model developed for use in a dental curriculum. This article outlines strategies used in developing a competency-based pedagogical model designed to provide a tailored student learning environment with objective, measurable, and calibrated assessment outcomes. The theoretical model integrated elements of critical thinking, professionalism, and evidence-based dentistry across dental school disciplines; implementation was based on consensus of dental faculty and student representatives about course content, faculty allocation, and curriculum alignment. Changes introduced included the following: 1) conversion and integration of previously siloed course content taught in Years 1 and 2 to sequential two-year combined courses; 2) reduction of course and content redundancies; 3) delivery of courses by teams of faculty members in biomedical, behavioral, and clinical sciences; and 4) reduction of total curriculum credit/contact hours from 13.5 (201 contact hours) to 5.0 (60 contact hours), allowing the Curriculum Committee to accommodate additional courses. These changes resulted in improvement in student satisfaction.

  11. Numerical Modeling of Fluid Transient in Cryogenic Fluid Network of Rocket Propulsion System

    Science.gov (United States)

    Majumdar, Alok; Flachbart, Robin

    2003-01-01

    Fluid transients, also known as water hammer, can have a significant impact on the design and operation of both spacecraft and launch vehicles propulsion systems. These transients often occur at system activation and shut down. For ground safety reasons, many spacecrafts are launched with the propellant lines dry. These lines are often evacuated by the time the spacecraft reaches orbit. When the propellant isolation valve opens during propulsion system activation, propellant rushes into lines creating a pressure surge. During propellant system shutdown, a pressure surge is created due to sudden closure of a valve. During both activation and shutdown, pressure surges must be predicted accurately to ensure structural integrity of the propulsion system fluid network. The method of characteristics is the most widely used method of calculating fluid transients in pipeline [ 1,2]. The method of characteristics, however, has limited applications in calculating flow distribution in complex flow circuits with phase change, heat transfer and rotational effects. A robust cryogenic propulsion system analyzer must have the capability to handle phase change, heat transfer, chemical reaction, rotational effects and fluid transients in conjunction with subsystem flow model for pumps, valves and various pipe fittings. In recent years, such a task has been undertaken at Marshall Space Flight Center with the development of the Generalized Fluid System Simulation Program (GFSSP), which is based on finite volume method in fluid network [3]. GFSSP has been extensively verified and validated by comparing its predictions with test data and other numerical methods for various applications such as internal flow of turbo-pump [4], propellant tank pressurization [5,6], chilldown of cryogenic transfer line [7] and squeeze film damper rotordynamics [8]. The purpose of the present paper is to investigate the applicability of the finite volume method to predict fluid transient in cryogenic flow

  12. The flight of uncontrolled rockets

    CERN Document Server

    Gantmakher, F R; Dryden, H L

    1964-01-01

    International Series of Monographs on Aeronautics and Astronautics, Division VII, Volume 5: The Flight of Uncontrolled Rockets focuses on external ballistics of uncontrolled rockets. The book first discusses the equations of motion of rockets. The rocket as a system of changing composition; application of solidification principle to rockets; rotational motion of rockets; and equations of motion of the center of mass of rockets are described. The text looks at the calculation of trajectory of rockets and the fundamentals of rocket dispersion. The selection further focuses on the dispersion of f

  13. Hybrid Rocket Technology

    National Research Council Canada - National Science Library

    Sankaran Venugopal; K K Rajesh; V Ramanujachari

    2011-01-01

    With their unique operational characteristics, hybrid rockets can potentially provide safer, lower-cost avenues for spacecraft and missiles than the current solid propellant and liquid propellant systems...

  14. A model for teaching raptor medicine in the veterinary curriculum.

    Science.gov (United States)

    Degernes, Laurel A; Osborne, Julie A Nettifee

    2006-01-01

    Injured or sick wild avian species, especially raptors (birds of prey, including hawks, owls, falcons, and eagles), can present different challenges to veterinary students and veterinarians who are trained in companion avian medicine (e.g., parrot medicine). Proper capture and restraint, feeding, housing, and certain diagnostic and treatment techniques involving raptors require different skills, knowledge, and resources than working with parrots. We developed an innovative raptor medicine program that enables students to acquire proficiency in safe capture, restraint, and examination techniques and in common diagnostic and treatment procedures. A self-assessment survey was developed to determine students' confidence and proficiency in 10 procedures taught in the lab. Groups were compared by class status (Year 1 vs. Year 2 and 3) and level of prior raptor experience (non-experienced or experienced). In surveys conducted before and after teaching two sets of raptor training labs, students rated themselves significantly more proficient in all 10 diagnostic and treatment procedures after completing the two raptor laboratories. The greatest improvements were observed in technical skill procedures such as fluid administration, intramuscular injections, cloacal swabs, venipuncture, and bandaging. Our approach to incorporating elective wildlife learning experiences into the veterinary curriculum may be replicable in other veterinary schools, with or without a wildlife rehabilitation program.

  15. A behavioural modelling approach to curriculum development and evaluation of health promotion for nurses.

    Science.gov (United States)

    Kelly, M P; Maloney, W A

    1992-05-01

    This paper outlines the way in which two behavioural science models may be used in the processes of curriculum development and course evaluation. The models are the stress-coping paradigm associated with the work of Lazarus and the theory of self and identity developed from the work of Mead. It is suggested that a clear articulation of the underlying behavioural processes is fundamental in course design and appraisal.

  16. Changes of high school English teaching model under the directions of new English Curriculum Standard

    Institute of Scientific and Technical Information of China (English)

    杨丽萍

    2014-01-01

    Communications around the world becomes common with the quickening of China’s reform and open door policies and widening of international communications, thus it is very pressing to modify the model of high school English class for students’concept of English use as a tool. This paper focuses on the change of English class teaching model in high schools under the direction of New English Curriculum Standard and its purposes and effects.

  17. Developing professional skills at tertiary level: A model to integrate competencies across the curriculum

    OpenAIRE

    Sánchez Carracedo, Fermín; Soler Cervera, Antonia; López Álvarez, David; Martín Escofet, Carme; Ageno Pulido, Alicia; Belanche Muñoz, Luis Antonio; Cabré Garcia, José M.; Cobo Valeri, Erik; Farré Cirera, Rafael; García Almiñana, Jordi; Marès Martí, Pere

    2014-01-01

    In the context of the European Higher Education Area, curriculum design needs to be based on the defined competencies of each degree programs, including both domain specific and professional competencies. In this educational context, developing students’ professional skills poses a new challenge we need to face. The present work proposes a model to globally develop professional skills in an Engineering degree program. Based on competency maps, this model allows careful analysis, revision and ...

  18. The Ion Rocket

    Science.gov (United States)

    1961-05-29

    discharge velocity w and the speci- fic impulse lap respectively cannot be increased. At this limit condition the thermal rocket oecouos "choked up...structural quality is 900 t, 3) In the case of an atomic-driven thermal rocket ’,;lth specific Ipipulse ISjy«8C0 sec and thrust to weight ratio « 1, the

  19. Flow Formulation-based Model for the Curriculum-based Course Timetabling Problem

    DEFF Research Database (Denmark)

    Bagger, Niels-Christian Fink; Kristiansen, Simon; Sørensen, Matias;

    2015-01-01

    In this work we will present a new mixed integer programming formulation for the curriculum-based course timetabling problem. We show that the model contains an underlying network model by dividing the problem into two models and then connecting the two models back into one model using a maximum ow...... problem. This decreases the number of integer variables signicantly and improves the performance compared to the basic formulation. It also shows competitiveness with other approaches based on mixed integer programming from the literature and improves the currently best known lower bound on one data...

  20. Replacement of chemical rocket launchers by beamed energy propulsion.

    Science.gov (United States)

    Fukunari, Masafumi; Arnault, Anthony; Yamaguchi, Toshikazu; Komurasaki, Kimiya

    2014-11-01

    Microwave Rocket is a beamed energy propulsion system that is expected to reach space at drastically lower cost. This cost reduction is estimated by replacing the first-stage engine and solid rocket boosters of the Japanese H-IIB rocket with Microwave Rocket, using a recently developed thrust model in which thrust is generated through repetitively pulsed microwave detonation with a reed-valve air-breathing system. Results show that Microwave Rocket trajectory, in terms of velocity versus altitude, can be designed similarly to the current H-IIB first stage trajectory. Moreover, the payload ratio can be increased by 450%, resulting in launch-cost reduction of 74%.

  1. Improving education in primary care: development of an online curriculum using the blended learning model

    Directory of Open Access Journals (Sweden)

    Lewin Linda

    2009-06-01

    Full Text Available Abstract Background Standardizing the experiences of medical students in a community preceptorship where clinical sites vary by geography and discipline can be challenging. Computer-assisted learning is prevalent in medical education and can help standardize experiences, but often is not used to its fullest advantage. A blended learning curriculum combining web-based modules with face-to-face learning can ensure students obtain core curricular principles. Methods This course was developed and used at The Case Western Reserve University School of Medicine and its associated preceptorship sites in the greater Cleveland area. Leaders of a two-year elective continuity experience at the Case Western Reserve School of Medicine used adult learning principles to develop four interactive online modules presenting basics of office practice, difficult patient interviews, common primary care diagnoses, and disease prevention. They can be viewed at http://casemed.case.edu/cpcp/curriculum. Students completed surveys rating the content and technical performance of each module and completed a Generalist OSCE exam at the end of the course. Results Participating students rated all aspects of the course highly; particularly those related to charting and direct patient care. Additionally, they scored very well on the Generalist OSCE exam. Conclusion Students found the web-based modules to be valuable and to enhance their clinical learning. The blended learning model is a useful tool in designing web-based curriculum for enhancing the clinical curriculum of medical students.

  2. Improving education in primary care: development of an online curriculum using the blended learning model.

    Science.gov (United States)

    Lewin, Linda Orkin; Singh, Mamta; Bateman, Betzi L; Glover, Pamela Bligh

    2009-06-10

    Standardizing the experiences of medical students in a community preceptorship where clinical sites vary by geography and discipline can be challenging. Computer-assisted learning is prevalent in medical education and can help standardize experiences, but often is not used to its fullest advantage. A blended learning curriculum combining web-based modules with face-to-face learning can ensure students obtain core curricular principles. This course was developed and used at The Case Western Reserve University School of Medicine and its associated preceptorship sites in the greater Cleveland area. Leaders of a two-year elective continuity experience at the Case Western Reserve School of Medicine used adult learning principles to develop four interactive online modules presenting basics of office practice, difficult patient interviews, common primary care diagnoses, and disease prevention. They can be viewed at (http://casemed.case.edu/cpcp/curriculum). Students completed surveys rating the content and technical performance of each module and completed a Generalist OSCE exam at the end of the course. Participating students rated all aspects of the course highly; particularly those related to charting and direct patient care. Additionally, they scored very well on the Generalist OSCE exam. Students found the web-based modules to be valuable and to enhance their clinical learning. The blended learning model is a useful tool in designing web-based curriculum for enhancing the clinical curriculum of medical students.

  3. A Critical Information Literacy Model: Library Leadership within the Curriculum

    Science.gov (United States)

    Swanson, Troy

    2011-01-01

    It is a time for a new model for teaching students to find, evaluate, and use information by drawing on critical pedagogy theory in the education literature. This critical information literacy model views the information world as a dynamic place where authors create knowledge for many reasons; it seeks to understand students as information users,…

  4. Cyber Enabled Collaborative Environment for Data and Modeling Driven Curriculum Modules for Hydrology and Geoscience Education

    Science.gov (United States)

    Merwade, V.; Ruddell, B. L.; Manduca, C. A.; Fox, S.; Kirk, K. B.

    2012-12-01

    With the access to emerging datasets and computational tools, there is a need to bring these capabilities into hydrology and geoscience classrooms. However, developing curriculum modules using data and models to augment classroom teaching is hindered by steep technology learning curve, rapid technology turnover, and lack of an organized community cyberinfrastructure (CI) for the dissemination, publication, and sharing of the latest tools and curriculum material for hydrology and geoscience education. The objective of this project is to overcome some of these limitations by developing a cyber enabled collaborative environment for publishing, sharing and adoption of data and modeling driven curriculum modules in hydrology and geoscience classroom. The CI is based on Carleton College's Science Education Resource Center (SERC) Content Management System. Building on its existing community authoring capabilities the system is being extended to allow assembly of new teaching activities by drawing on a collection of interchangeable building blocks; each of which represents a step in the modeling process. This poster presentation will describe the structure of the CI, the type and description of the modules that are under development, and the approach that will be used in assessing students' learning from using modules.

  5. The Yellow Brick Road: a values based curriculum model.

    Science.gov (United States)

    McLean, Christopher

    2012-05-01

    Within the United Kingdom, the Nursing and Midwifery Council (NMC) requires that nurses and midwives are of 'good character' at the point of registration. This paper sets out how good character has been conceptualised within one U.K. higher education institution and presents a model of "values based enquiry" which aims to develop the 'character' of students. The paper presents three qualities ("the heart", "the nerve" and "the brain") which represent 'good character' and which are believed to underpin values based Nursing or Midwifery practice. The development of these qualities is argued to be reliant upon helping students to develop intrinsic professional values of care and compassion. The role of these character qualities in nursing practice and education is outlined, as are the ways in which they have led to the development of a model for values based enquiry. This model represents a vision of the nature of professional education which may be shared by staff and students, whilst offering a model for learning and teaching based upon recognised educational principles. An argument is advanced that the adoption of a values based enquiry model may develop and nurture the habits of mind which are necessary for the development of 'good character'. Copyright © 2011 Elsevier Ltd. All rights reserved.

  6. Development of a death education curriculum model for the general public using DACUM method.

    Science.gov (United States)

    Kim, Yong-Ha; Ahn, Sang-Yoon; Lee, Chong-Hyung; Lee, Moo-Sik; Kim, Moon-Joon; Arma, Park; Hwang, Hye-Jeong; Song, Hyeon-Dong; Shim, Moon-Sook; Kim, Kwang-Hwan

    2016-05-18

    In order to analyze tasks of the death education curriculum for the public, DACUM method was used. A committee for DACUM was gathered and a survey was conducted on professors of health care, humanities and social sciences for an interdisciplinary study. In the survey used to verify the model for death education for the public, a compilation based on difficulty and importance factor shows that the 27 tasks including the psychological changes in terminally ill or suicidal patients, healing of stress, acceptance and understanding of death and suicide prevention were identified as needing to be included in the curriculum. The data thus concluded will have to be reviewed when they are applied to actual education to revise the education program to make it more appropriate.

  7. Another Look at Rocket Thrust

    Science.gov (United States)

    Hester, Brooke; Burris, Jennifer

    2012-01-01

    Rocket propulsion is often introduced as an example of Newton's third law. The rocket exerts a force on the exhaust gas being ejected; the gas exerts an equal and opposite force--the thrust--on the rocket. Equivalently, in the absence of a net external force, the total momentum of the system, rocket plus ejected gas, remains constant. The law of…

  8. Another Look at Rocket Thrust

    Science.gov (United States)

    Hester, Brooke; Burris, Jennifer

    2012-01-01

    Rocket propulsion is often introduced as an example of Newton's third law. The rocket exerts a force on the exhaust gas being ejected; the gas exerts an equal and opposite force--the thrust--on the rocket. Equivalently, in the absence of a net external force, the total momentum of the system, rocket plus ejected gas, remains constant. The law of…

  9. A Model Aerospace Curriculum: August Martin High School.

    Science.gov (United States)

    Strickler, Mervin K., Jr.

    This document presents an operational model of a thematic aerospace education school--the August Martin High School (New York). Part 1 briefly describes the nature of aviation/aerospace education and the background of the school. This background information includes how the school was formed, rationale for an aerospace thematic school, research…

  10. Towards a Model of Integrated English Language Curriculum for Secondary Schools in Kenya

    Science.gov (United States)

    Okwara, M. O.; Shiundu, J. O.; Indoshi, F. C.

    2009-01-01

    Design of the Integrated English Language Curriculum has been blamed for falling standards of students' competence in the subject. Teacher input in the curriculum design has rarely been considered in the centralized curriculum development approach used in Kenya. However, it is now recognized that teacher input is critical if curriculum is to be…

  11. Characterization of rocket propellant combustion products. Chemical characterization and computer modeling of the exhaust products from four propellant formulations: Final report, September 23, 1987--April 1, 1990

    Energy Technology Data Exchange (ETDEWEB)

    Jenkins, R.A.; Nestor, C.W.; Thompson, C.V.; Gayle, T.M.; Ma, C.Y.; Tomkins, B.A.; Moody, R.L.

    1991-12-09

    The overall objective of the work described in this report is four-fold: to (a) develop a standardized and experimentally validated approach to the sampling and chemical and physical characterization of the exhaust products of scaled-down rocket launch motors fired under experimentally controlled conditions at the Army`s Signature Characterization Facility (ASCF) at Redstone Arsenal in Huntsville, Alabama; (b) determine the composition of the exhaust produces; (c) assess the accuracy of a selected existing computer model for predicting the composition of major and minor chemical species; (d) recommended alternations to both the sampling and analysis strategy and the computer model in order to achieve greater congruence between chemical measurements and computer prediction. 34 refs., 2 figs., 35 tabs.

  12. A3 Subscale Rocket Hot Fire Testing

    Science.gov (United States)

    Saunders, G. P.; Yen, J.

    2009-01-01

    This paper gives a description of the methodology and results of J2-X Subscale Simulator (JSS) hot fire testing supporting the A3 Subscale Diffuser Test (SDT) project at the E3 test facility at Stennis Space Center, MS (SSC). The A3 subscale diffuser is a geometrically accurate scale model of the A3 altitude simulating rocket test facility. This paper focuses on the methods used to operate the facility and obtain the data to support the aerodynamic verification of the A3 rocket diffuser design and experimental data quantifying the heat flux throughout the facility. The JSS was operated at both 80% and 100% power levels and at gimbal angle from 0 to 7 degrees to verify the simulated altitude produced by the rocket-rocket diffuser combination. This was done with various secondary GN purge loads to quantify the pumping performance of the rocket diffuser. Also, special tests were conducted to obtain detailed heat flux measurements in the rocket diffuser at various gimbal angles and in the facility elbow where the flow turns from vertical to horizontal upstream of the 2nd stage steam ejector.

  13. Presentation on the Modeling and Educational Demonstrations Laboratory Curriculum Materials Center (MEDL-CMC): A Working Model and Progress Report

    Science.gov (United States)

    Glesener, G. B.; Vican, L.

    2015-12-01

    Physical analog models and demonstrations can be effective educational tools for helping instructors teach abstract concepts in the Earth, planetary, and space sciences. Reducing the learning challenges for students using physical analog models and demonstrations, however, can often increase instructors' workload and budget because the cost and time needed to produce and maintain such curriculum materials is substantial. First, this presentation describes a working model for the Modeling and Educational Demonstrations Laboratory Curriculum Materials Center (MEDL-CMC) to support instructors' use of physical analog models and demonstrations in the science classroom. The working model is based on a combination of instructional resource models developed by the Association of College & Research Libraries and by the Physics Instructional Resource Association. The MEDL-CMC aims to make the curriculum materials available for all science courses and outreach programs within the institution where the MEDL-CMC resides. The sustainability and value of the MEDL-CMC comes from its ability to provide and maintain a variety of physical analog models and demonstrations in a wide range of science disciplines. Second, the presentation then reports on the development, progress, and future of the MEDL-CMC at the University of California Los Angeles (UCLA). Development of the UCLA MEDL-CMC was funded by a grant from UCLA's Office of Instructional Development and is supported by the Department of Earth, Planetary, and Space Sciences. Other UCLA science departments have recently shown interest in the UCLA MEDL-CMC services, and therefore, preparations are currently underway to increase our capacity for providing interdepartmental service. The presentation concludes with recommendations and suggestions for other institutions that wish to start their own MEDL-CMC in order to increase educational effectiveness and decrease instructor workload. We welcome an interuniversity collaboration to

  14. Rocket noise - A review

    Science.gov (United States)

    McInerny, S. A.

    1990-10-01

    This paper reviews what is known about far-field rocket noise from the controlled studies of the late 1950s and 1960s and from launch data. The peak dimensionless frequency, the dependence of overall sound power on exhaust parameters, and the directivity of the overall sound power of rockets are compared to those of subsonic jets and turbo-jets. The location of the dominant sound source in the rocket exhaust plume and the mean flow velocity in this region are discussed and shown to provide a qualitative explanation for the low peak Strouhal number, fD(e)/V(e), and large angle of maximum directivity. Lastly, two empirical prediction methods are compared with data from launches of a Titan family vehicle (two, solid rocket motors of 5.7 x 10 to the 6th N thrust each) and the Saturn V (five, liquid oxygen/rocket propellant engines of 6.7 x 10 to the 6th N thrust, each). The agreement is favorable. In contrast, these methods appear to overpredict the far-field sound pressure levels generated by the Space Shuttle.

  15. A Comparative Study of Tyler Model and Doll’s Perspective on Curriculum%泰勒模式与多尔课程观的比较研究

    Institute of Scientific and Technical Information of China (English)

    沈是琳

    2015-01-01

    Tyler Model is one of the most influential curriculum paradigms in modern curriculum studies. But it has been challenged by post-modernism represented by Doll’s curriculum paradigm since the 1970s. In spite of the criticisms towards Tyler Model, it should not be replaced completely by a post-modern one. Tyler Model and Doll’s perspective on curriculum are not contradictory but complementary. In the study of curriculum development, we should combine these two paradigms together.

  16. The Robust Learning Model with a Spiral Curriculum: Implications for the Educational Effectiveness of Online Master Degree Programs

    Science.gov (United States)

    Neumann, Yoram; Neumann, Edith; Lewis, Shelia

    2017-01-01

    This study integrated the Spiral Curriculum approach into the Robust Learning Model as part of a continuous improvement process that was designed to improve educational effectiveness and then assessed the differences between the initial and integrated models as well as the predictability of the first course in the integrated learning model on a…

  17. Regenerative Cooling for Liquid Rocket Engines

    Institute of Scientific and Technical Information of China (English)

    QiFeng

    1995-01-01

    Heat transfer in the thrust chamber is of great importance in the design of liquid propellant rocket engines.Regenerative cooling is and advanced method which can ensure not only the proper running but also higher performance of a rocket engine.The theoretical model is complicated,it relates to fluid bynamics,heat transfer,combustion.etc…,In this paper,a regenerative cooling model is presented.Effects such as radiation,heat transfer to environment,variable thermal properties and coking are included in the model.This model can be applied to all kinds of liquid propellant rocket engines as well as similar constructions.The modularized computer code is completed in the work.

  18. Model-based analysis and reasoning in science: The MARS curriculum

    Science.gov (United States)

    Raghavan, Kalyani; Glaser, Robert

    Scientists and researchers in many disciplines frequently resort to modeling and model-based reasoning to concretize abstract ideas, to simplify and clarify complex phenomena, to predict trends, and to explain mechanisms and processes. National projects working to reform science education explicitly recommend the development of an appreciation for the centrality of models in the teaching and learning of science. This article describes a model-centered, computer-supported, semester-long science curriculum for middle-school students designed to encourage conceptual understanding and to foster the development of model-based reasoning skills. In the Model-based Analysis and Reasoning in Science (MARS) project, an attempt is made to create an environment conducive to fostering conceptual understanding and reasoning about scientific phenomena that involve balance of forces. Visual models that are dynamic and interactive are presented not only to concretize abstract ideas but also as reasoning tools that give students the leverage to solve problems in a variety of contexts. This model-centered curriculum focuses on a network of concepts important for understanding hydrostatics; that is, floating and sinking, as an exemplar for the general principle of balance of forces. How students understand these concepts and use models as a disciplinary resource to engage in chains of reasoning that integrate concepts into networks of relations is of special interest for study. How students use that understanding in new situations within the same explanatory system is also being studied. A major pedagogical question is how middle-school students can be taught to engage in model-based reasoning, a form of reasoning that scientists routinely use.

  19. A Flight Investigation of the Damping in Roll and Rolling Effectiveness Including Aeroelastic Effects of Rocket Propelled Missile Models Having Cruciform, Triangular, Interdigitated Wings and Tails

    Science.gov (United States)

    Hopko, R. N.

    1951-01-01

    The damping in roll and rolling effectiveness of two models of a missile having cruciform, triangular, interdigitated wings and tails have been determined through a Mach number range of 0.8 to 1.8 by utilizing rocket-propelled test vehicles. Results indicate that the damping in roll was relatively constant over the Mach umber range investigated. The rolling effectiveness was essentially constant at low supersonic speeds and increased with increasing mach numbers in excess of 1.4 over the Mach number range investigated. Aeroelastic effects increase the rolling-effectiveness parameters pb/2V divided by delta and decrease both the rolling-moment coefficient due to wing deflection and the damping-in-roll coefficient.

  20. A community initiative for developing data and modeling driven curriculum modules for hydrology education

    Science.gov (United States)

    Ruddell, B. L.; Merwade, V.

    2010-12-01

    Hydrology and geoscience education at the undergraduate and graduate levels may benefit greatly from a structured approach to pedagogy that utilizes modeling, authentic data, and simulation exercises to engage students in practice-like activities. Extensive evidence in the educational literature suggests that students retain more of their instruction, and attain higher levels of mastery over content, when interactive and practice-like activities are used to contextualize traditional lecture-based and theory-based instruction. However, it is also important that these activities carefully link the use of data and modeling to abstract theory, to promote transfer of knowledge to other contexts. While this type of data-based activity has been practiced in the hydrology classroom for decades, the hydrology community still lacks a set of standards and a mechanism for community-based development, publication, and review of this type of curriculum material. A community-based initiative is underway to develop a set curriculum materials to teach hydrology in the engineering and geoscience university classroom using outcomes-based, pedagogically rigorous modules that use authentic data and modeling experiences to complement traditional lecture-based instruction. A preliminary design for a community cyberinfrastructure for shared module development and publication, and for module topics and outcomes and ametadata and module interoperability standards, will be presented, along with the results of a series of community surveys and workshops informing this design.

  1. Flutter Analysis of RX-420 Balistic Rocket Fin Involving Rigid Body Modes of Rocket Structures

    OpenAIRE

    Novi Andria

    2013-01-01

    Flutter is a phenomenon that has brought a catastrophic failure to the flight vehicle structure. In this experiment, flutter was analyzed for its symmetric and antisymmetric configuration to understand the effect of rocket rigid modes to the fin flutter characteristic. This research was also expected to find out the safety level of RX-420 structure design. The analysis was performed using half rocket model. Fin structure used in this research was a fin which has semispan 600 mm, thickness 12 ...

  2. Rockets in World War I

    Science.gov (United States)

    2004-01-01

    World War I enlisted rockets once again for military purposes. French pilots rigged rockets to the wing struts of their airplanes and aimed them at enemy observation balloons filled with highly inflammable hydrogen.

  3. An Evaluation Of Rocket Parameters

    Directory of Open Access Journals (Sweden)

    J. N. Beri

    1959-07-01

    Full Text Available The dependence of conventional parameters of internal ballistics of Solid Propellant Rockets using external burning cruciform charge, on the geometry of charge aad rocket motor is discussed and results applied in a special case.

  4. The Development of a National Curriculum Guide for Persian: Themes, Genres, Standards-based Goals, and Models

    Directory of Open Access Journals (Sweden)

    Nicole Mills

    2014-08-01

    Full Text Available Wang (2009 has challenged foreign language scholars to “engage in rigorous discussions to develop language-specific examples and performance indicators to guide program development and decision-making for less commonly taught language (LCTL instructors” (p. 284. The 2011-2012 STARTALK programs in Persian aimed to encourage such rigorous discussion through the development of a National Curriculum Guide in Persian. Persian professionals explored current theories in second language acquisition, examined curricular resources and models, and shared successful teaching materials. This article describes the rationale, procedures, and outcomes of a series of faculty development events that aimed to create a model for curriculum development for the LCTLs and, perhaps, also for other language programs in the context of higher education. The final curriculum guide produced by the program participants includes overarching themes and genres, Standards-based goals, strategies for authentic assessment, and model unit plans.

  5. A person-task-context model for designing curriculum and in-training assessment in postgraduate education

    DEFF Research Database (Denmark)

    Skaarup, Anne Marie; Ringsted, Charlotte Vibeke; Henriksen, Ann-Helen

    2006-01-01

    The aim of this study was to trial a person-task-context model in designing a curriculum and in-training assessment programme that embraces trainee level of professional development and the work-based context of postgraduate medical education. The model was applied to the design of a programme...

  6. Simulation of Airplane and Rocket Trajectories

    Science.gov (United States)

    Wahbah, Magdy M.; Berning, Michael J.; Choy, Tony S.

    1987-01-01

    Simulation and Optimization of Rocket Trajectories program (SORT) contains comprehensive mathematical models for simulating aircraft dynamics, freely falling objects, and many types of ballistic trajectories. Provides high-fidelity, three-degrees-of-freedom simulation for atmospheric and exoatmospheric flight. It numerically models vehicle subsystems and vehicle environment. Used for wide range of simulations. Written in machine-independent FORTRAN 77.

  7. Baking Soda and Vinegar Rockets

    Science.gov (United States)

    Claycomb, James R.; Zachary, Christopher; Tran, Quoc

    2009-01-01

    Rocket experiments demonstrating conservation of momentum will never fail to generate enthusiasm in undergraduate physics laboratories. In this paper, we describe tests on rockets from two vendors that combine baking soda and vinegar for propulsion. The experiment compared two analytical approximations for the maximum rocket height to the…

  8. Baking Soda and Vinegar Rockets

    Science.gov (United States)

    Claycomb, James R.; Zachary, Christopher; Tran, Quoc

    2009-01-01

    Rocket experiments demonstrating conservation of momentum will never fail to generate enthusiasm in undergraduate physics laboratories. In this paper, we describe tests on rockets from two vendors that combine baking soda and vinegar for propulsion. The experiment compared two analytical approximations for the maximum rocket height to the…

  9. Introduction to Rocket Propulsion

    Science.gov (United States)

    1991-12-01

    Von Braun; 1966. 4. Introduction to Ordnance Technology; IHSP 76-129; 1976. 5. Physics; D. Halliday and R. Resnick ; 1963. 6. Physics Tells Why: 0...to Luke Sky- walker in Star Wars when he said "Don’t get cocky." We never plan for EVERYTHING, though we like to think we do. As we’ve said, rocket

  10. Low toxicity rocket propellants

    NARCIS (Netherlands)

    Wink, J.

    2014-01-01

    Hydrazine (N2H4) and its hypergolic mate nitrogen tetroxide (N2O4) are used on virtually all spacecraft and on a large number of launch vehicles. In recent years however, there has been an effort in identifying and developing alternatives to replace hydrazine as a rocket propellant.

  11. The Relativistic Rocket

    Science.gov (United States)

    Antippa, Adel F.

    2009-01-01

    We solve the problem of the relativistic rocket by making use of the relation between Lorentzian and Galilean velocities, as well as the laws of superposition of successive collinear Lorentz boosts in the limit of infinitesimal boosts. The solution is conceptually simple, and technically straightforward, and provides an example of a powerful…

  12. Rocketing to the Skies

    Institute of Scientific and Technical Information of China (English)

    1999-01-01

    ONE sunny morning,we startedfor Yanqi Lake,Huairou District,Beijing,to try“rocket bungy”,so farthe only facility for this sport inChina.On the way there,wequestioned our courage and heartendurance. Entering the gate we saw,towering over a banner saying,

  13. Low toxicity rocket propellants

    NARCIS (Netherlands)

    Wink, J.

    2014-01-01

    Hydrazine (N2H4) and its hypergolic mate nitrogen tetroxide (N2O4) are used on virtually all spacecraft and on a large number of launch vehicles. In recent years however, there has been an effort in identifying and developing alternatives to replace hydrazine as a rocket propellant.

  14. Providing competency-based family medicine residency training in substance abuse in the new millennium: a model curriculum

    Directory of Open Access Journals (Sweden)

    Shellenberger Sylvia

    2010-05-01

    Full Text Available Abstract Background This article, developed for the Betty Ford Institute Consensus Conference on Graduate Medical Education (December, 2008, presents a model curriculum for Family Medicine residency training in substance abuse. Methods The authors reviewed reports of past Family Medicine curriculum development efforts, previously-identified barriers to education in high risk substance use, approaches to overcoming these barriers, and current training guidelines of the Accreditation Council for Graduate Medical Education (ACGME and their Family Medicine Residency Review Committee. A proposed eight-module curriculum was developed, based on substance abuse competencies defined by Project MAINSTREAM and linked to core competencies defined by the ACGME. The curriculum provides basic training in high risk substance use to all residents, while also addressing current training challenges presented by U.S. work hour regulations, increasing international diversity of Family Medicine resident trainees, and emerging new primary care practice models. Results This paper offers a core curriculum, focused on screening, brief intervention and referral to treatment, which can be adapted by residency programs to meet their individual needs. The curriculum encourages direct observation of residents to ensure that core skills are learned and trains residents with several "new skills" that will expand the basket of substance abuse services they will be equipped to provide as they enter practice. Conclusions Broad-based implementation of a comprehensive Family Medicine residency curriculum should increase the ability of family physicians to provide basic substance abuse services in a primary care context. Such efforts should be coupled with faculty development initiatives which ensure that sufficient trained faculty are available to teach these concepts and with efforts by major Family Medicine organizations to implement and enforce residency requirements for

  15. Technical and educational improvements of the Student Rocket Program at NAROM and Andøya Rocket Range

    Science.gov (United States)

    Nylund, Amund; Rønningen, Jan-Erik

    2007-06-01

    Norwegian Centre for Space-Related Education (NAROM) is co-located with Andøya Rocket Range (ARR) and was established in 2000 as a field station for space-related education. The Student Rocket Program (SRP) was introduced to give the students hands-on experience and a comprehensive introduction to an ordinary scientific rocket launch. NAROM and ARR have since 1998 developed and launched more than 30 student rockets. Since summer 2005 the SRP has been significantly improved with a more powerful rocket motor and a new telemetry system. With these technical improvements, NAROM can introduce new challenges for the students concerning rocket technique, instrumentation, telemetry and data processing. It has also opened possibilities for new pedagogical improvements in terms of a larger curriculum, more use of the ARR infrastructure and making the SRP more adapted to the different participants' qualifications and background. But even though the SRP has been significantly improved during the last years, the program still is in continuously development, making the SRP at NAROM and ARR a unique educational activity for students at different levels of education.

  16. Potential Climate and Ozone Impacts From Hybrid Rocket Engine Emissions

    Science.gov (United States)

    Ross, M.

    2009-12-01

    Hybrid rocket engines that use N2O as an oxidizer and a solid hydrocarbon (such as rubber) as a fuel are relatively new. Little is known about the composition of such hybrid engine emissions. General principles and visual inspection of hybrid plumes suggest significant soot and possibly NO emissions. Understanding hybrid rocket emissions is important because of the possibility that a fleet of hybrid powered suborbital rockets will be flying on the order of 1000 flights per year by 2020. The annual stratospheric emission for these rockets would be about 10 kilotons, equal to present day solid rocket motor (SRM) emissions. We present a preliminary analysis of the magnitude of (1) the radiative forcing from soot emissions and (2) the ozone depletion from soot and NO emissions associated with such a fleet of suborbital hybrid rockets. Because the details of the composition of hybrid emissions are unknown, it is not clear if the ozone depletion caused by these hybrid rockets would be more or less than the ozone depletion from SRMs. We also consider the climate implications associated with the N2O production and use requirements for hybrid rockets. Finally, we identify the most important data collection and modeling needs that are required to reliably assess the complete range of environmental impacts of a fleet of hybrid rockets.

  17. Adapting a community of practice model to design an innovative ethics curriculum in healthcare.

    Science.gov (United States)

    Naidoo, Sudeshni; Vernillo, Anthony T

    2014-01-01

    The focus of healthcare ethics within the framework of ethical principles and philosophical foundations has always, in recent times, been the community, namely, the healthcare provider, the patient or, in research, the study participant. An initiative is thus described whereby a community of practice (CoP) model was developed around health ethics in health research, education and clinical care. The ethics curriculum was redesigned to include several components that are integrated and all embracing, namely, health research ethics, healthcare ethics, health personnel education in ethics and global and public health ethics. A CoP is a group who share a common interest and a desire to learn from and contribute to the community with their variety of experiences. The CoP is dynamic and organic, generating knowledge that can be translated into effective healthcare delivery and ethical research. It requires the collaboration and social presence of active participants such as community members, healthcare professionals and educators, ethicists and policy makers to benefit the community by developing approaches that adapt to and resonate with the community and its healthcare needs. Philosophical principles constitute the foundation or underpinning of this innovative curriculum. Recommendations are presented that will continue to guide the consolidation and sustainability of the CoP.

  18. A stepwise model for simulation-based curriculum development for clinical skills, a modification of the six-step approach.

    Science.gov (United States)

    Khamis, Nehal N; Satava, Richard M; Alnassar, Sami A; Kern, David E

    2016-01-01

    Despite the rapid growth in the use of simulation in health professions education, courses vary considerably in quality. Many do not integrate efficiently into an overall school/program curriculum or conform to academic accreditation requirements. Moreover, some of the guidelines for simulation design are specialty specific. We designed a model that integrates best practices for effective simulation-based training and a modification of Kern et al.'s 6-step approach for curriculum development. We invited international simulation and health professions education experts to complete a questionnaire evaluating the model. We reviewed comments and suggested modifications from respondents and reached consensus on a revised version of the model. We recruited 17 simulation and education experts. They expressed a consensus on the seven proposed curricular steps: problem identification and general needs assessment, targeted needs assessment, goals and objectives, educational strategies, individual assessment/feedback, program evaluation, and implementation. We received several suggestions for descriptors that applied the steps to simulation, leading to some revisions in the model. We have developed a model that integrates principles of curriculum development and simulation design that is applicable across specialties. Its use could lead to high-quality simulation courses that integrate efficiently into an overall curriculum.

  19. FEM Modelling and Oscillation Analysis of Solid Propellant Rocket Motor%固体火箭发动机柔性喷管有限元建模及摆动分析

    Institute of Scientific and Technical Information of China (English)

    王成林; 刘勇; 文立华

    2012-01-01

    The methods of FEM Modelling and Oscillation Analysis of Solid Propellant Rocket Motor were explores. The FEM model of flexible nozzle using the equivalent model of flexible joint based on the three-direction custom spring elements is build; modify the FEM model of the flexible joint according to the experiment data; and carry out the oscillation analysis of solid propellant rocket motor.%研究了固态火箭发动机柔性喷管有限元建模及摆动分析方法.利用基于自定义三向弹簧单元的柔性接头线性等效模型,建立了发动机柔性喷管有限元模型.根据试验数据对柔性接头模型进行修正,并对发动机柔性喷管进行了摆动分析.

  20. Hybrid Rocket Technology

    Directory of Open Access Journals (Sweden)

    Sankaran Venugopal

    2011-04-01

    Full Text Available With their unique operational characteristics, hybrid rockets can potentially provide safer, lower-cost avenues for spacecraft and missiles than the current solid propellant and liquid propellant systems. Classical hybrids can be throttled for thrust tailoring, perform in-flight motor shutdown and restart. In classical hybrids, the fuel is stored in the form of a solid grain, requiring only half the feed system hardware of liquid bipropellant engines. The commonly used fuels are benign, nontoxic, and not hazardous to store and transport. Solid fuel grains are not highly susceptible to cracks, imperfections, and environmental temperature and are therefore safer to manufacture, store, transport, and use for launch. The status of development based on the experience of the last few decades indicating the maturity of the hybrid rocket technology is given in brief.Defence Science Journal, 2011, 61(3, pp.193-200, DOI:http://dx.doi.org/10.14429/dsj.61.518

  1. Liquid rocket engine injectors

    Science.gov (United States)

    Gill, G. S.; Nurick, W. H.

    1976-01-01

    The injector in a liquid rocket engine atomizes and mixes the fuel with the oxidizer to produce efficient and stable combustion that will provide the required thrust without endangering hardware durability. Injectors usually take the form of a perforated disk at the head of the rocket engine combustion chamber, and have varied from a few inches to more than a yard in diameter. This monograph treats specifically bipropellant injectors, emphasis being placed on the liquid/liquid and liquid/gas injectors that have been developed for and used in flight-proven engines. The information provided has limited application to monopropellant injectors and gas/gas propellant systems. Critical problems that may arise during injector development and the approaches that lead to successful design are discussed.

  2. Liquid Rocket Engine Testing

    Science.gov (United States)

    2016-10-21

    booster rocket engines • 6000-10000 psia capabilities – Can use gaseous nitrogen, helium, or hydrogen to pressurize propellant tanks 9Distribution A...Approved for Public Release; Distribution Unlimited. PA Clearance 16493 Simplified Test Stand Layout Oxidizer  TankFuel  Tank High  Pressure   Gas (GN2...requires large, complex facilities to deliver propellant at the proper pressure , temperature, and flow rates • The enormous energies involved

  3. Solid propellant rocket motor

    Science.gov (United States)

    Dowler, W. L.; Shafer, J. I.; Behm, J. W.; Strand, L. D. (Inventor)

    1973-01-01

    The characteristics of a solid propellant rocket engine with a controlled rate of thrust buildup to a desired thrust level are discussed. The engine uses a regressive burning controlled flow solid propellant igniter and a progressive burning main solid propellant charge. The igniter is capable of operating in a vacuum and sustains the burning of the propellant below its normal combustion limit until the burning propellant surface and combustion chamber pressure have increased sufficiently to provide a stable chamber pressure.

  4. Health Policy in Physician Assistant Education: Teaching Considerations and a Model Curriculum.

    Science.gov (United States)

    Kidd, Vasco Deon; Cawley, James F; Kayingo, Gerald

    2016-03-01

    Recognition is growing within the medical academic community that future clinicians will need the tools to understand and influence health policy decisions. With the passage of the Patient Protection and Affordable Care Act of 2010, future clinicians will need not only clinical competence for successful practice but also an understanding of how health systems function. Although the fourth edition of the Accreditation Standards for Physician Assistant Education contains provisions and stipulations for the teaching of health topics in general and health policy specifically, physician assistant (PA) educators retain little consensus regarding either learning objectives or specific rubrics for teaching these important concepts. In this article, we discuss approaches for teaching health policy, delineate useful educational resources for PA faculty, and propose a model curriculum.

  5. Model training curriculum for Low-Level Radioactive Waste Disposal Facility Operations

    Energy Technology Data Exchange (ETDEWEB)

    Tyner, C.J.; Birk, S.M.

    1995-09-01

    This document is to assist in the development of the training programs required to be in place for the operating license for a low-level radioactive waste disposal facility. It consists of an introductory document and four additional appendixes of individual training program curricula. This information will provide the starting point for the more detailed facility-specific training programs that will be developed as the facility hires and trains new personnel and begins operation. This document is comprehensive and is intended as a guide for the development of a company- or facility-specific program. The individual licensee does not need to use this model training curriculum as written. Instead, this document can be used as a menu for the development, modification, or verification of customized training programs.

  6. The rocket problem in general relativity

    CERN Document Server

    Henriques, Pedro G

    2011-01-01

    We derive the covariant optimality conditions for rocket trajectories in general relativity, with and without a bound on the magnitude of the proper acceleration. The resulting theory is then applied to solve two specific problems: the minimum fuel consumption transfer between two galaxies in a FLRW model, and between two stable circular orbits in the Schwarzschild spacetime.

  7. Damage assessment of long-range rocket system by electromagnetic pulse weapon

    Science.gov (United States)

    Cao, Lingyu; Liu, Guoqing; Li, Jinming

    2017-08-01

    This paper analyzes the damage mechanism and characteristics of electromagnetic pulse weapon, establishes the index system of survivability of long-range rocket launcher system, and uses AHP method to establish the combat effectiveness model of long-range rocket missile system. According to the damage mechanism and characteristics of electromagnetic pulse weapon, the damage effect of the remote rocket system is established by using the exponential method to realize the damage efficiency of the remote rocket system.

  8. The ECOMA 2007 campaign: rocket observations and numerical modelling of aerosol particle charging and plasma depletion in a PMSE/NLC layer

    Directory of Open Access Journals (Sweden)

    A. Brattli

    2009-02-01

    Full Text Available The ECOMA series of rocket payloads use a set of aerosol particle, plasma, and optical instruments to study the properties of aerosol particles and their interaction with the ambient plasma environment in the polar mesopause region. In August 2007 the ECOMA-3 payload was launched into a region with Polar Mesosphere Summer Echoes (PMSE and noctilucent clouds (NLC. An electron depletion was detected in a broad region between 83 and 88 km, coincident with enhanced density of negatively charged aerosol particles. We also find evidence for positive ion depletion in the same region. Charge neutrality requires that a population of positively charged particles smaller than 2 nm and with a density of at least 2×108 m−3 must also have been present in the layer, undetected by the instruments. A numerical model for the charging of aerosol particles and their interaction with the ambient plasma is used to analyse the results, showing that high aerosol particle densities are required in order to explain the observed ion density depletion. The model also shows that a very high photoionisation rate is required for the particles smaller than 2 nm to become positively charged, indicating that these may have a lower work function than pure water ice.

  9. Models and Materials: Bridging Art and Science in the Secondary Curriculum

    Science.gov (United States)

    Pak, D.; Cavazos, L.

    2006-12-01

    Creating and sustaining student engagement in science is one challenge facing secondary teachers. The visual arts provide an alternative means of communicating scientific concepts to students who may not respond to traditional formats or identify themselves as interested in science. We have initiated a three-year teacher professional development program at U C Santa Barbara focused on bridging art and science in secondary curricula, to engage students underrepresented in science majors, including girls, English language learners and non-traditional learners. The three-year format provides the teams of teachers with the time and resources necessary to create innovative learning experiences for students that will enhance their understanding of both art and science content. Models and Materials brings together ten secondary art and science teachers from six Santa Barbara County schools. Of the five participating science teachers, three teach Earth Science and two teach Life Science. Art and science teachers from each school are teamed and challenged with the task of creating integrated curriculum projects that bring visual art concepts to the science classroom and science concepts to the art classroom. Models and Materials were selected as unifying themes; understanding the concept of models, their development and limitations, is a prominent goal in the California State Science and Art Standards. Similarly, the relationship between composition, structure and properties of materials is important to both art and science learning. The program began with a 2-week institute designed to highlight the natural links between art and science through presentations and activities by both artists and scientists, to inspire teachers to develop new ways to present models in their classrooms, and for the teacher teams to brainstorm ideas for curriculum projects. During the current school year, teachers will begin to integrate science and art and the themes of modeling and materials

  10. Curriculum Animation

    Science.gov (United States)

    Gose, Michael D.

    2004-01-01

    Twenty-five teachers with reputations for artistry in curriculum planning were interviewed about their "curriculum animation" plans or how they ensured their curriculum was brought to life. Their statements indicated that much of their planning is informal and intuitive, and that the criteria they use for their curriculum includes: (1) it is…

  11. Unsteady Three-Dimensional Simulation of a Shear Coaxial GO2/GH2 Rocket Injector with RANS and Hybrid-RAN-LES/DES Using Flamelet Models

    Science.gov (United States)

    Westra, Doug G.; West, Jeffrey S.; Richardson, Brian R.

    2015-01-01

    Historically, the analysis and design of liquid rocket engines (LREs) has relied on full-scale testing and one-dimensional empirical tools. The testing is extremely expensive and the one-dimensional tools are not designed to capture the highly complex, and multi-dimensional features that are inherent to LREs. Recent advances in computational fluid dynamics (CFD) tools have made it possible to predict liquid rocket engine performance, stability, to assess the effect of complex flow features, and to evaluate injector-driven thermal environments, to mitigate the cost of testing. Extensive efforts to verify and validate these CFD tools have been conducted, to provide confidence for using them during the design cycle. Previous validation efforts have documented comparisons of predicted heat flux thermal environments with test data for a single element gaseous oxygen (GO2) and gaseous hydrogen (GH2) injector. The most notable validation effort was a comprehensive validation effort conducted by Tucker et al. [1], in which a number of different groups modeled a GO2/GH2 single element configuration by Pal et al [2]. The tools used for this validation comparison employed a range of algorithms, from both steady and unsteady Reynolds Averaged Navier-Stokes (U/RANS) calculations, large-eddy simulations (LES), detached eddy simulations (DES), and various combinations. A more recent effort by Thakur et al. [3] focused on using a state-of-the-art CFD simulation tool, Loci/STREAM, on a two-dimensional grid. Loci/STREAM was chosen because it has a unique, very efficient flamelet parameterization of combustion reactions that are too computationally expensive to simulate with conventional finite-rate chemistry calculations. The current effort focuses on further advancement of validation efforts, again using the Loci/STREAM tool with the flamelet parameterization, but this time with a three-dimensional grid. Comparisons to the Pal et al. heat flux data will be made for both RANS and

  12. Simulation and experimental research on line throwing rocket with flight

    Institute of Scientific and Technical Information of China (English)

    Wen-bin GU; Ming LU; Jian-qing LIU; Qin-xing DONG; Zhen-xiong WANG; Jiang-hai CHEN

    2014-01-01

    The finite segment method is used to model the line throwing rocket system. A dynamic model of line throwing rocket with flight motion based on Kane’s method is presented by the kinematics description of the system and the consideration of the forces acting on the system. The experiment designed according to the parameters of the dynamic model is made. The simulation and experiment results, such as range, velocity and flight time, are compared and analyzed. The simulation results are basically agreed with the test data, which shows that the flight motion of the line throwing rocket can be predicted by the dynamic model. A theoretical model and guide for the further research on the disturbance of rope and the guidance, flight control of line throwing rocket are provided by the dynamic modeling.

  13. Modeling Potential Carbon Monoxide Exposure Due to Operation of a Major Rocket Engine Altitude Test Facility Using Computational Fluid Dynamics

    Science.gov (United States)

    Blotzer, Michael J.; Woods, Jody L.

    2009-01-01

    This viewgraph presentation reviews computational fluid dynamics as a tool for modelling the dispersion of carbon monoxide at the Stennis Space Center's A3 Test Stand. The contents include: 1) Constellation Program; 2) Constellation Launch Vehicles; 3) J2X Engine; 4) A-3 Test Stand; 5) Chemical Steam Generators; 6) Emission Estimates; 7) Located in Existing Test Complex; 8) Computational Fluid Dynamics; 9) Computational Tools; 10) CO Modeling; 11) CO Model results; and 12) Next steps.

  14. Nuclear Thermal Rocket Propulsion Systems

    Science.gov (United States)

    2007-11-02

    NUCLEAR THERMAL ROCKET PROPULSION SYSTEMS, IAA WHITE PAPER PARIS, FRANCE, MARCH 2005 Lt Col Timothy J. Lawrence U.S. Air Force Academy...YYYY) 18-03-2005 2. REPORT TYPE White Paper 3. DATES COVERED (From - To) 18 Mar 2005 4. TITLE AND SUBTITLE NUCLEAR THERMAL ROCKET PROPULSION...reduce radiation exposure, is to have a high energy system like a nuclear thermal rocket that can get the payload to the destination in the fastest

  15. Rocket Assembly and Checkout Facility

    Data.gov (United States)

    Federal Laboratory Consortium — FUNCTION: Integrates, tests, and calibrates scientific instruments flown on sounding rocket payloads. The scientific instruments are assembled on an optical bench;...

  16. Computational simulation of liquid rocket injector anomalies

    Science.gov (United States)

    Przekwas, A. J.; Singhal, A. K.; Tam, L. T.; Davidian, K.

    1986-01-01

    A computer model has been developed to analyze the three-dimensional two-phase reactive flows in liquid fueled rocket combustors. The model is designed to study the influence of liquid propellant injection nonuniformities on the flow pattern, combustion and heat transfer within the combustor. The Eulerian-Lagrangian approach for simulating polidisperse spray flow, evaporation and combustion has been used. Full coupling between the phases is accounted for. A nonorthogonal, body fitted coordinate system along with a conservative control volume formulation is employed. The physical models built into the model include a kappa-epsilon turbulence model, a two-step chemical reaction, and the six-flux radiation model. Semiempirical models are used to describe all interphase coupling terms as well as chemical reaction rates. The purpose of this study was to demonstrate an analytical capability to predict the effects of reactant injection nonuniformities (injection anomalies) on combustion and heat transfer within the rocket combustion chamber. The results show promising application of the model to comprehensive modeling of liquid propellant rocket engines.

  17. Integrating Spanish language training across a Doctor of Physical Therapy curriculum: a case report of one program's evolving model.

    Science.gov (United States)

    Pechak, Celia; Diaz, Deborah; Dillon, Loretta

    2014-12-01

    As the Hispanic population continues to expand in the United States, health professionals increasingly may encounter people who speak Spanish and have limited English proficiency. Responding to these changes, various health profession educators have incorporated Spanish language training into their curricula. Of 12 doctor of physical therapy (DPT) programs identified as including elective or required Spanish courses, the program at The University of Texas at El Paso is the only one integrating required Spanish language training across the curriculum. The purpose of this case report is to describe the development, implementation, and preliminary outcomes of the evolving educational model at The University of Texas at El Paso. The University of Texas at El Paso is situated immediately across the border from Mexico. Responding to the large population with limited English proficiency in the community, faculty began to integrate required Spanish language training during a transition from a master-level to a DPT curriculum. The Spanish language curriculum pillar includes a Spanish medical terminology course, language learning opportunities threaded throughout the clinical courses, clinical education courses, and service-learning. Forty-five DPT students have completed the curriculum. Assessment methods were limited for early cohorts. Clinically relevant Spanish verbal proficiency was assessed with a practical examination in the Spanish course, a clinical instructor-rated instrument, and student feedback. Preliminary data suggested that the model is improving Spanish language proficiency. The model still is evolving. Spanish language learning opportunities in the curriculum are being expanded. Also, problems with the clinical outcome measure have been recognized. Better definition of intended outcomes and validation of a revised tool are needed. This report should promote opportunities for collaboration with others who are interested in linguistic competence. © 2014

  18. Rocket + Science = Dialogue

    Science.gov (United States)

    Morris,Bruce; Sullivan, Greg; Burkey, Martin

    2010-01-01

    It's a cliche that rocket engineers and space scientists don t see eye-to-eye. That goes double for rocket engineers working on human spaceflight and scientists working on space telescopes and planetary probes. They work fundamentally different problems but often feel that they are competing for the same pot of money. Put the two groups together for a weekend, and the results could be unscientific or perhaps combustible. Fortunately, that wasn't the case when NASA put heavy lift launch vehicle designers together with astronomers and planetary scientists for two weekend workshops in 2008. The goal was to bring the top people from both groups together to see how the mass and volume capabilities of NASA's Ares V heavy lift launch vehicle could benefit the science community. Ares V is part of NASA's Constellation Program for resuming human exploration beyond low Earth orbit, starting with missions to the Moon. In the current mission scenario, Ares V launches a lunar lander into Earth orbit. A smaller Ares I rocket launches the Orion crew vehicle with up to four astronauts. Orion docks with the lander, attached to the Ares V Earth departure stage. The stage fires its engine to send the mated spacecraft to the Moon. Standing 360 feet high and weighing 7.4 million pounds, NASA's new heavy lifter will be bigger than the 1960s-era Saturn V. It can launch almost 60 percent more payload to translunar insertion together with the Ares I and 35 percent more mass to low Earth orbit than the Saturn V. This super-sized capability is, in short, designed to send more people to more places to do more things than the six Apollo missions.

  19. The Construction and Application of Curriculum Performance Appraisal Model in Colleges%高校课程绩效评估模型的构建与运用

    Institute of Scientific and Technical Information of China (English)

    况志华

    2012-01-01

    构建高校课程绩效评估机制对于高校课程建设具有重要实践指导意义。该文在剖析高校课程绩效影响因子的基础上,提出了高校课程绩效评估的一般模型,并对该模型的运用以及课程绩效管理实践提出了若干对策建议。%It has important guiding significance to construct curriculum performance appraisal mechanism in colleges for curriculum constructions.This thesis first analyses the influence factors of curriculum performance appraisal in colleges.It then introduces a general model of curriculum performance appraisal;third,several countermeasures and suggestions are put forward concerning applications to the curriculum performance appraisal model.

  20. A proposed monitoring and evaluation curriculum based on a model that institutionalises monitoring and evaluation

    Directory of Open Access Journals (Sweden)

    Kambidima Wotela

    2017-04-01

    Full Text Available Background: African politicians, bureaucrats and technocrats have thrown their weight in support of monitoring and evaluation (M&E. This weight has compelled training institutions to add M&E to their offerings. Most often at the end of these training programmes, attendees know what they have learnt but seem not to internalise it and, worse, they hardly ever put their newly acquired knowledge into practice. This allegation has led to what we term ‘monitoring and evaluation training hopping’ where participants move from one training to another hoping that they will eventually fully comprehend the skill and apply it to their work. This rarely happens and as such participants often blame themselves and yet the problem is with the training institutions that are teaching the middle-third tier (how to monitor and evaluate as well as the bottom-third tier (data and information management. However, the top-third tier that links M&E to ‘the what’ and ‘the how’ as well as ‘the why’ in the development intervention and public policy landscape is missing.Objectives: To propose a M&E curriculum that institutionalises M&E within implementation and management of development interventions.Method: We use systems thinking to derive the key themes of our discussion and then apply summative thematic content analysis to interrogate M&E and related literature. Firstly, we present and describe a model that situates M&E within development and public policy. This model ‘idealises or realises’ an institutionalised M&E by systematically linking the contextual as well as key terms prominent in established descriptions of M&E. Secondly, we briefly describe M&E from a systems thinking approach by pointing out its components, processes, established facts, as well as issues and debates. Lastly, we use this model and the systems thinking description of M&E to propose an institutionalised M&E curriculum.Results: Our results show that for an explicit

  1. Rocket Experiment For Neutral Upwelling

    Science.gov (United States)

    Kenward, D. R.; Lessard, M.

    2015-12-01

    Observations from the CHAMP satellite from 2004 show relatively small scale heating in the thermosphere. Several different mechanisms have been proposed to explain this phenomenon. The RENU 2 rocket mission includes a suite of 14 instruments which will acquire data to help understand processes involved in neutral upwelling in the cusp. Neutral, ion, and electron measurements will be made to provide an assessment of the upwelling process. SUPERDarn measurements of large- scale Joule heating in the cusp during overflight will also be acquired. Small-scale data which could possibly be associated with Alfvén waves, will be acquired using onboard electric field measurements. In-situ measurement of precipitating electrons and all other measurements will be used in thermodynamic and electrodynamic models for comparison to the observed upwelling.

  2. A mental model for successful inter-disciplinary collaboration in curriculum innovation for information literacy

    Directory of Open Access Journals (Sweden)

    M. Detken Scheepers

    2011-01-01

    Full Text Available The University of Pretoria introduced a compulsory Information Literacy module to address the need for delivering motivated knowledgeable employees that embrace information and have the skills to find, select and use relevant information accurately, efficiently and effectively in an explosive information age. Low class attendance, an indication of unmotivated students, as well as the limited scholarly application of information literacy skills in consecutive academic years of study have been identified as possible barriers to the application of the desired skills. A collaborative action research project based on Whole Brain principles was introduced to motivate learners through innovative learning material in the module. A deeper understanding of the role of thinking preferences and thinking avoidances is essential in selecting a team that is responsible for the planning, design, development and delivery of learning opportunities and material. This article discusses the Whole Brain Model® as a mental model that underpins the successful collaboration of multidisciplinary teams and enhances innovative curriculum design that addresses alternative approaches to the teaching of Information Literacy.

  3. Mars Rocket Propulsion System

    Science.gov (United States)

    Zubrin, Robert; Harber, Dan; Nabors, Sammy

    2008-01-01

    A report discusses the methane and carbon monoxide/LOX (McLOx) rocket for ascent from Mars as well as other critical space propulsion tasks. The system offers a specific impulse over 370 s roughly 50 s higher than existing space-storable bio-propellants. Current Mars in-situ propellant production (ISPP) technologies produce impure methane and carbon monoxide in various combinations. While separation and purification of methane fuel is possible, it adds complexity to the propellant production process and discards an otherwise useful fuel product. The McLOx makes such complex and wasteful processes unnecessary by burning the methane/CO mixtures produced by the Mars ISPP systems without the need for further refinement. Despite the decrease in rocket-specific impulse caused by the CO admixture, the improvement offered by concomitant increased propellant density can provide a net improvement in stage performance. One advantage is the increase of the total amount of propellant produced, but with a decrease in mass and complexity of the required ISPP plant. Methane/CO fuel mixtures also may be produced by reprocessing the organic wastes of a Moon base or a space station, making McLOx engines key for a human Lunar initiative or the International Space Station (ISS) program. Because McLOx propellant components store at a common temperature, very lightweight and compact common bulkhead tanks can be employed, improving overall stage performance further.

  4. Assessing the Effects of the "Rocket Math" Program with a Primary Elementary School Student at Risk for School Failure: A Case Study

    Science.gov (United States)

    Smith, Christina R.; Marchand-Martella, Nancy E.; Martella, Ronald C.

    2011-01-01

    This study assessed the effects of the "Rocket Math" program on the math fluency skills of a first grade student at risk for school failure. The student received instruction in the "Rocket Math" program over 6 months. He was assessed using a pre- and posttest curriculum-based measurement (CBM) and individualized fluency checkouts within the…

  5. Scaled Rocket Testing in Hypersonic Flow

    Science.gov (United States)

    Dufrene, Aaron; MacLean, Matthew; Carr, Zakary; Parker, Ron; Holden, Michael; Mehta, Manish

    2015-01-01

    NASA's Space Launch System (SLS) uses four clustered liquid rocket engines along with two solid rocket boosters. The interaction between all six rocket exhaust plumes will produce a complex and severe thermal environment in the base of the vehicle. This work focuses on a recent 2% scale, hot-fire SLS base heating test. These base heating tests are short-duration tests executed with chamber pressures near the full-scale values with gaseous hydrogen/oxygen engines and RSRMV analogous solid propellant motors. The LENS II shock tunnel/Ludwieg tube tunnel was used at or near flight duplicated conditions up to Mach 5. Model development was strongly based on the Space Shuttle base heating tests with several improvements including doubling of the maximum chamber pressures and duplication of freestream conditions. Detailed base heating results are outside of the scope of the current work, rather test methodology and techniques are presented along with broader applicability toward scaled rocket testing in supersonic and hypersonic flow.

  6. Investigations of Rocket Engine Combustion Emissions During ACCENT

    Science.gov (United States)

    Ross, M. N.; Friedl, R. R.

    2001-12-01

    The composition of rocket combustion emissions and the atmospheric processes that determine their stratospheric impacts are poorly understood. While present day rocket emissions do not significantly affect stratospheric chemistry, the potential for vigorous growth of the space transportation industry in coming decades suggests that rocket emissions and their stratospheric impacts should be better understood. A variety of in-situ measurements and modeling results were obtained during the Atmospheric Chemistry of Combustion Emissions Near the Tropopause (ACCENT) effort that will be used to evaluate the role of rocket exhaust in perturbing ozone chemistry in plume wakes and in the global stratosphere. We present a review of the ACCENT rocket emissions science objectives, summarize data obtained during the WB-57F plume wake sorties, and briefly discuss how the data will help resolve several outstanding questions regarding the impact of rocket emissions on the stratosphere. These include measurement of the emission indices for several important rocket engine combustion products and validation of plume wake chemistry models.

  7. What fuel for a rocket?

    CERN Document Server

    Miranda, E N

    2012-01-01

    Elementary concepts from general physics and thermodynamics have been used to analyze rocket propulsion. Making some reasonable assumptions, an expression for the exit velocity of the gases is found. From that expression one can conclude what are the desired properties for a rocket fuel.

  8. DANCE CURRICULUM MODEL FOR HIGH SCHOOLS IN PALACES STUDENTS IN ROMANIA

    National Research Council Canada - National Science Library

    Popa Daniela; Neamtu Mircea

    2015-01-01

      The research undertaken was intended to achieve a high school dance curriculum educational Palaces pupils for contribute to the knowledge, skills and abilities to the all practitioners participating in these programs...

  9. A Model to Predict Student Failure in the First Year of the Undergraduate Medical Curriculum

    Directory of Open Access Journals (Sweden)

    Gerard J.A. Baars

    2017-06-01

    Discussion: The earliest moment with the highest specificity to predict student failure in the first-year curriculum seems to be at 6 months. However, additional factors are needed to improve this prediction or to bring forward the predictive moment.

  10. A Model for Adapting. Bloom's Taxonomy to a Preschool Curriculum for the Gifted

    Science.gov (United States)

    Bailey, Donald B.; Leonard, Judith

    1977-01-01

    Presented is a rationale for the use of B. Bloom's taxonomy of educational objectives in the development of preschool curriculum units for the gifted and talented which translates taxonomical objectives into activities. (BB)

  11. International Federation for Emergency Medicine model curriculum for emergency medicine specialists

    Directory of Open Access Journals (Sweden)

    Cherri Hobgood

    2011-06-01

    Full Text Available To meet a critical and growing need for emergency physicians and emergency medicine resources worldwide, physicians must be trained to deliver time-sensitive interventions and lifesaving emergency care. Currently, there is no globally recognized, standard curriculum that defines the basic minimum standards for specialist trainees in emergency medicine. To address this deficit, the International Federation for Emergency Medicine (IFEM convened a committee of international physicians, health professionals, and other experts in emergency medicine and international emergency medicine development to outline a curriculum for training of specialists in emergency medicine. This curriculum document represents the consensus of recommendations by this committee. The curriculum is designed to provide a framework for educational programs in emergency medicine. The focus is on the basic minimum emergency medicine educational content that any emergency medicine physician specialist should be prepared to deliver on completion of a training program. It is designed not to be prescriptive but to assist educators and emergency medicine leadership to advance physician education in basic emergency medicine no matter the training venue. The content of this curriculum is relevant not just for communities with mature emergency medicine systems but in particular for developing nations or for nations seeking to expand emergency medicine within the current educational structure. We anticipate that there will be wide variability in how this curriculum is implemented and taught. This variability will reflect the existing educational milieu, the resources available, and the goals of the institutions’ educational leadership with regard to the training of emergency medicine specialists.

  12. A Tiered Mentoring Model of Exposing and Engaging Students with Research Throughout the Undergraduate Curriculum

    Science.gov (United States)

    Guerard, J.; Hayes, S. M.

    2015-12-01

    Incorporating research into undergraduate curricula has been linked to improved critical thinking, intellectual independence, and student retention, resulting in a graduating population more ready for the workforce or graduate school. We have designed a three-tier model of undergraduate chemistry courses that enable first-year students with no previous research experience to gain the skills needed to develop, fund and execute independent research projects by the close of their undergraduate studies. First-year students are provided with context through a broadly focused introductory class that exposes them to current faculty research activities, and also gives them direct experience with the research process through peer mentored research teams as they participate in faculty-directed projects. Mid-career undergraduate students receive exposure and support in two formats: illustrative examples from current faculty research are incorporated into lessons in core classes, and courses specially designed to foster research independence. This is done by providing content and process mentoring as students develop independent projects, write proposals, and build relationships with faculty and graduate students in research groups. Advanced undergraduates further develop their research independence performing student-designed projects with faculty collaboration that frequently result in tangible research products. Further, graduate students gain experience in mentoring though formal training, as well as through actively mentoring mid-career undergraduates. This novel, integrated approach enables faculty to directly incorporate their research into all levels of the undergraduate curriculum while fostering undergraduates in developing and executing independent projects and empowering mentoring relationships.

  13. Culture Matters in Successful Curriculum Change: An International Study of the Influence of National and Organizational Culture Tested With Multilevel Structural Equation Modeling.

    Science.gov (United States)

    Jippes, Mariëlle; Driessen, Erik W; Broers, Nick J; Majoor, Gerard D; Gijselaers, Wim H; van der Vleuten, Cees P M

    2015-07-01

    National culture has been shown to play a role in curriculum change in medical schools, and business literature has described a similar influence of organizational culture on change processes in organizations. This study investigated the impact of both national and organizational culture on successful curriculum change in medical schools internationally. The authors tested a literature-based conceptual model using multilevel structural equation modeling. For the operationalization of national and organizational culture, the authors used Hofstede's dimensions of culture and Quinn and Spreitzer's competing values framework, respectively. To operationalize successful curriculum change, the authors used two derivates: medical schools' organizational readiness for curriculum change developed by Jippes and colleagues, and change-related behavior developed by Herscovitch and Meyer. The authors administered a questionnaire in 2012 measuring the described operationalizations to medical schools in the process of changing their curriculum. Nine hundred ninety-one of 1,073 invited staff members from 131 of 345 medical schools in 56 of 80 countries completed the questionnaire. An initial poor fit of the model improved to a reasonable fit by two suggested modifications which seemed theoretically plausible. In sum, characteristics of national culture and organizational culture, such as a certain level of risk taking, flexible policies and procedures, and strong leadership, affected successful curriculum change. National and organizational culture influence readiness for change in medical schools. Therefore, medical schools considering curriculum reform should anticipate the potential impact of national and organizational culture.

  14. A Cyber Enabled Collaborative Environment for Creating, Sharing and Using Data and Modeling Driven Curriculum Modules for Hydrology Education

    Science.gov (United States)

    Merwade, V.; Ruddell, B. L.; Fox, S.; Iverson, E. A. R.

    2014-12-01

    With the access to emerging datasets and computational tools, there is a need to bring these capabilities into hydrology classrooms. However, developing curriculum modules using data and models to augment classroom teaching is hindered by a steep technology learning curve, rapid technology turnover, and lack of an organized community cyberinfrastructure (CI) for the dissemination, publication, and sharing of the latest tools and curriculum material for hydrology and geoscience education. The objective of this project is to overcome some of these limitations by developing a cyber enabled collaborative environment for publishing, sharing and adoption of data and modeling driven curriculum modules in hydrology and geosciences classroom. The CI is based on Carleton College's Science Education Resource Center (SERC) Content Management System. Building on its existing community authoring capabilities the system is being extended to allow assembly of new teaching activities by drawing on a collection of interchangeable building blocks; each of which represents a step in the modeling process. Currently the system hosts more than 30 modules or steps, which can be combined to create multiple learning units. Two specific units: Unit Hydrograph and Rational Method, have been used in undergraduate hydrology class-rooms at Purdue University and Arizona State University. The structure of the CI and the lessons learned from its implementation, including preliminary results from student assessments of learning will be presented.

  15. Nuclear Rocket Engine Reactor

    CERN Document Server

    Lanin, Anatoly

    2013-01-01

    The development of a nuclear rocket engine reactor (NRER ) is presented in this book. The working capacity of an active zone NRER under mechanical and thermal load, intensive neutron fluxes, high energy generation (up to 30 MBT/l) in a working medium (hydrogen) at temperatures up to 3100 K is displayed. Design principles and bearing capacity of reactors area discussed on the basis of simulation experiments and test data of a prototype reactor. Property data of dense constructional, porous thermal insulating and fuel materials like carbide and uranium carbide compounds in the temperatures interval 300 - 3000 K are presented. Technological aspects of strength and thermal strength resistance of materials are considered. The design procedure of possible emergency processes in the NRER is developed and risks for their origination are evaluated. Prospects of the NRER development for pilotless space devices and piloted interplanetary ships are viewed.

  16. Computational Analysis for Rocket-Based Combined-Cycle Systems During Rocket-Only Operation

    Science.gov (United States)

    Steffen, C. J., Jr.; Smith, T. D.; Yungster, S.; Keller, D. J.

    2000-01-01

    A series of Reynolds-averaged Navier-Stokes calculations were employed to study the performance of rocket-based combined-cycle systems operating in an all-rocket mode. This parametric series of calculations were executed within a statistical framework, commonly known as design of experiments. The parametric design space included four geometric and two flowfield variables set at three levels each, for a total of 729 possible combinations. A D-optimal design strategy was selected. It required that only 36 separate computational fluid dynamics (CFD) solutions be performed to develop a full response surface model, which quantified the linear, bilinear, and curvilinear effects of the six experimental variables. The axisymmetric, Reynolds-averaged Navier-Stokes simulations were executed with the NPARC v3.0 code. The response used in the statistical analysis was created from Isp efficiency data integrated from the 36 CFD simulations. The influence of turbulence modeling was analyzed by using both one- and two-equation models. Careful attention was also given to quantify the influence of mesh dependence, iterative convergence, and artificial viscosity upon the resulting statistical model. Thirteen statistically significant effects were observed to have an influence on rocket-based combined-cycle nozzle performance. It was apparent that the free-expansion process, directly downstream of the rocket nozzle, can influence the Isp efficiency. Numerical schlieren images and particle traces have been used to further understand the physical phenomena behind several of the statistically significant results.

  17. Rocket propulsion elements - An introduction to the engineering of rockets (6th revised and enlarged edition)

    Science.gov (United States)

    Sutton, George P.

    The subject of rocket propulsion is treated with emphasis on the basic technology, performance, and design rationale. Attention is given to definitions and fundamentals, nozzle theory and thermodynamic relations, heat transfer, flight performance, chemical rocket propellant performance analysis, and liquid propellant rocket engine fundamentals. The discussion also covers solid propellant rocket fundamentals, hybrid propellant rockets, thrust vector control, selection of rocket propulsion systems, electric propulsion, and rocket testing.

  18. Ignition transient analysis of solid rocket motor

    Science.gov (United States)

    Han, Samuel S.

    1991-01-01

    Measurement data on the performance of Space Shuttle Solid Rocket Motor show wide variations in the head-end pressure changes and the total thrust build-up during the ignition transient periods. To analyze the flow and thermal behavior in the tested solid rocket motors, a 1-dimensional, ideal gas flow model via the SIMPLE algorithm was developed. Numerical results showed that burning patterns in the star-shaped head-end segment of the propellant and the erosive burning rate are two important factors controlling the ignition transients. The objective of this study is to extend the model to include the effects of aluminum particle commonly used in solid propellants. To treat the effects of aluminum-oxide particles in the combustion gas, conservation of mass, momentum, and energy equations for the particles are added in the numerical formulation and integrated by an inter-phase-slip algorithm.

  19. Rocket plume tomography of combustion species

    OpenAIRE

    2001-01-01

    Interest in accurate detection and targeting of aggressor missiles has received considerable interest with the national priority of developing a missile defense system. Understanding the thermal signatures of the exhaust plumes of such missiles is key to accomplishing that mission. Before signature models can be precisely developed for specific rockets, the radiation of the molecular or combustion species within those plumes must be accurately predicted. A combination translation / rotation s...

  20. The Bohr Model and the Fifth Grade: A New Standards-Based Hands-On Physics Curriculum

    Science.gov (United States)

    Brock, Jeff; Springer, Russell; Goldberg, Bennett

    2004-03-01

    A semester-long, standards-based, hands-on physics curriculum appropriate for the fifth grade was developed. Previously available curricula were successful in using hands-on activities to teach basic fifth-grade physics skills and concepts, but did not attempt to foster understanding of the fundamental underlying physics. We expanded the role of inquiry-based instruction to expose students to the fundamental physics behind electricity, forces, energy, light and sound. Central to the course, the Bohr model of the atom was used as a key tool both to motivate exploration of these topics as well as to develop basic conceptual understanding of fundamental ideas in quantum and electromagnetic physics. The curriculum was designed to be compatible with both district and state-mandated standards in a high-stakes test environment. This work was supported by NSF grant DGE-0231909.

  1. British used Congreve Rockets to Attack Napoleon

    Science.gov (United States)

    2004-01-01

    Sir William Congreve developed a rocket with a range of about 9,000 feet. The incendiary rocket used black powder, an iron case, and a 16-foot guide stick. In 1806, British used Congreve rockets to attack Napoleon's headquarters in France. In 1807, Congreve directed a rocket attack against Copenhagen.

  2. Emerging identities: A proposed model for an interactive science curriculum for First Nations students

    Science.gov (United States)

    Sable, Trudy

    including language itself This identity is based on personal, cultural, historical and social factors that come to bear on each student's definition of who they are and what knowledge is pertinent to survival and well being. Five fundamental themes emerged from the interviews and field trips---fragile ontologies, multiple layers of identity (personal, cultural, pan-tribal, and societal), border crossings, the continuing and emerging aspects of culture, and beyond borders to a spiritual narrative---and became the foundation for a culturally interactive science education model of learning. The model assists educators through a visualization of layers of identity, porous borders and seeming paradoxes, and "narrative unity" beyond boundaries---all of which affect the learning of science. The content of a culturally interactive curriculum is drawn from the cultural heritage of the students, giving them an historical context with which to identify. Working with Mi'kmaw language and notational representation is shown to assist educators in cultural border crossing and creating cultural continuity for the students. Taken into the classroom, this interactive paradigm could be adapted to pedagogical methods as "speaking together" times, in which students explore the processes of doing science while appreciating their own cultural traditions. In so doing, educators can come to know the larger narrative that gives shape to student's identities and ways of relating to the world. Then it becomes possible for educators to recognize the boundaries that obstruct or open a path to meaningful learning experiences.

  3. Alternate Propellant Thermal Rocket Project

    Data.gov (United States)

    National Aeronautics and Space Administration — The Alternate Propellant Thermal Rocket (APTR) is a novel concept for propulsion of space exploration or orbit transfer vehicles. APTR propulsion is provided by...

  4. Safety Analysis of Liquid Rocket Engine Using Bayesian Networks

    Institute of Scientific and Technical Information of China (English)

    WANG Hua-wei; YAN Zhi-qiang

    2007-01-01

    Safety analysis for liquid rocket engine has a great meaning for shortening development cycle, saving development expenditure and reducing development risk. The relationship between the structure and component of liquid rocket engine is much more complex, furthermore test data are absent in development phase. Thereby, the uncertainties exist in safety analysis for liquid rocket engine. A safety analysis model integrated with FMEA(failure mode and effect analysis)based on Bayesian networks (BN) is brought forward for liquid rocket engine, which can combine qualitative analysis with quantitative decision. The method has the advantages of fusing multi-information, saving sample amount and having high veracity. An example shows that the method is efficient.

  5. Integrating critical thinking and evidence-based dentistry across a four-year dental curriculum: a model for independent learning.

    Science.gov (United States)

    Marshall, Teresa A; Straub-Morarend, Cheryl L; Handoo, Nidhi; Solow, Catherine M; Cunningham-Ford, Marsha A; Finkelstein, Michael W

    2014-03-01

    Introducing critical thinking and evidence-based dentistry (EBD) content into an established dental curriculum can be a difficult and challenging process. Over the past three years, the University of Iowa College of Dentistry has developed and implemented a progressive four-year integrated critical thinking and EBD curriculum. The objective of this article is to describe the development and implementation process to make it available as a model for other dental schools contemplating introduction of critical thinking and EBD into their curricula. The newly designed curriculum built upon an existing problem-based learning foundation, which introduces critical thinking and the scientific literature in the D1 year, in order to expose students to the rationale and resources for practicing EBD in the D2 and D3 years and provide opportunities to practice critical thinking and apply the EBD five-step process in the D2, D3, and D4 years. All curricular content is online, and D3 and D4 EBD activities are integrated within existing clinical responsibilities. The curricular content, student resources, and student activities are described.

  6. Improved hybrid rocket fuel

    Science.gov (United States)

    Dean, David L.

    1995-01-01

    McDonnell Douglas Aerospace, as part of its Independent R&D, has initiated development of a clean burning, high performance hybrid fuel for consideration as an alternative to the solid rocket thrust augmentation currently utilized by American space launch systems including Atlas, Delta, Pegasus, Space Shuttle, and Titan. It could also be used in single stage to orbit or as the only propulsion system in a new launch vehicle. Compared to solid propellants based on aluminum and ammonium perchlorate, this fuel is more environmentally benign in that it totally eliminates hydrogen chloride and aluminum oxide by products, producing only water, hydrogen, nitrogen, carbon oxides, and trace amounts of nitrogen oxides. Compared to other hybrid fuel formulations under development, this fuel is cheaper, denser, and faster burning. The specific impulse of this fuel is comparable to other hybrid fuels and is between that of solids and liquids. The fuel also requires less oxygen than similar hybrid fuels to produce maximum specific impulse, thus reducing oxygen delivery system requirements.

  7. Not just rocket science

    Energy Technology Data Exchange (ETDEWEB)

    MacAdam, S.; Anderson, R. [Celan Energy Systems, Rancho Cordova, CA (United States)

    2007-10-15

    The paper explains a different take on oxyfuel combustion. Clean Energy Systems (CES) has integrated aerospace technology into conventional power systems, creating a zero-emission power generation technology that has some advantages over other similar approaches. When using coal as a feedstock, the CES process burns syngas rather than raw coal. The process uses recycled water and steam to moderate the temperature, instead of recycled CO{sub 2}. With no air ingress, the CES process produces very pure CO{sub 2}. This makes it possible to capture over 99% of the CO{sub 2} resulting from combustion. CES uses the combustion products to drive the turbines, rather than indirectly raising steam for steam turbines, as in the oxyfuel process used by companies such as Vattenfall. The core of the process is a high-pressure oxy-combustor adapted from rocket engine technology. This combustor burns gaseous or liquid fuels with gaseous oxygen in the presence of water. Fuels include natural gas, coal or coke-derived synthesis gas, landfill and biodigester gases, glycerine solutions and oil/water emulsion. 2 figs.

  8. Development of a subspecialty cardiology curriculum for paediatric registrars in Malawi: Implementation of a long-distance hybrid model.

    Science.gov (United States)

    Newberry, Laura; Kennedy, Neil; Greene, Elizabeth A

    2016-06-01

    Malawi has a high burden of paediatric cardiac disease but a limited number of health providers familiar with these chronic diseases. Given the rising number of Malawian postgraduate paediatric trainees at the University of Malawi College of Medicine, we sought to remedy this lack of basic cardiology training with a long-distance, module-based curriculum that could be utilised independently, as needed, with on-site teaching. We also wished to evaluate the initial modules for utility and improvement in knowledge and confidence in each topic. After an initial site visit to determine curriculum needs, online modules with interactive evaluations and quizzes were developed by a paediatric cardiologist in the United States, in collaboration with paediatric registrar training directors in Malawi. This online interactive curriculum was followed by several site visits to Malawi, by the United States-based paediatric cardiologist, to provide bedside teaching, case-based discussions and hands-on skill training in cardiac ultrasound and electrocardiogram interpretation. Evaluation of the curriculum model included post-module quizzes on cardiac topics as well as registrar self-assessments regarding confidence in content areas. The average post-module quiz score was 93.6%. Repeat testing with the same questions four months later yielded an average score of 78%, with a range from 60 to 100%. Pre- and post-module registrar self-assessment regarding confidence in content areas showed a substantial gain in knowledge and confidence mean. In their qualitative feedback, registrars noted that the modules were helpful in studying for their certifying examinations, and all four of the registrars sitting Part I of their Malawian and South African paediatric certifying examinations passed. Our innovative hybrid approach, combining online educational modules with in-person teaching visits, is a useful approach in expanding paediatric cardiology subspecialty education in Malawi.

  9. A New Pedagogical Model for Adventure in the Curriculum: Part One-Advocating for the Model

    Science.gov (United States)

    Williams, Andy; Wainwright, Nalda

    2016-01-01

    Background: In recent years increasing attention has been given to models-based approaches to physical education as a way of promoting standards and particular types of learning through better alignment of teacher planning and delivery with pupil learning and achievement. However, little attention has been given to the specific contribution a…

  10. Testing a causal model for learning in a problem-based curriculum

    NARCIS (Netherlands)

    Hurk, M.M. van den; Dolmans, D.H.J.M.; Wolfhagen, H.A.P.; Vleuten, C.P.M. van der

    2001-01-01

    The aim of this study was to identify the relationship between elements that are important for the tutorial group process and the individual learning process in a problem-based curriculum. The variables under investigation were student-generated learning issues, individual learning process, reportin

  11. "Paideia Kyriou": Biblical and Patristic Models for an Integrated Christian Curriculum

    Science.gov (United States)

    Turley, Stephen Richard

    2009-01-01

    In recent years, a number of studies corroborate the importance of an integrated or interdisciplinary curriculum for an effective education. However, contemporary proposals for the function of theology as the integrative center have been limited mainly to sectarian communities and remain a work in progress. Noting the fruitfulness of historical…

  12. Developing a Process Model for Student Reformation of Curriculum and Instruction.

    Science.gov (United States)

    Grimaldi, Ettore P.; Garrett, Philip R.

    This paper presents a working framework for a controlled change of instructional practices within a community college. A methodology for the training of students and faculty in the evaluation of curriculum and instruction is presented: (1) establish a positive rationale for evaluation within a context of meaningful philosophy; (2) determine a…

  13. Applying the Kirkpatrick Model: Evaluating an "Interaction for Learning Framework" Curriculum Intervention

    Science.gov (United States)

    Paull, Megan; Whitsed, Craig; Girardi, Antonia

    2016-01-01

    Global perspectives and interpersonal and intercultural communication competencies are viewed as a priority within higher education. For management educators, globalisation, student mobility and widening pathways present numerous challenges, but afford opportunities for curriculum innovation. The "Interaction for Learning Framework"…

  14. From World War to Woods Hole: The Use of Wartime Research Models for Curriculum Reform.

    Science.gov (United States)

    Rudolph, John L.

    2002-01-01

    Considers the curriculum reform movement of the 1950s as an experiment in applying innovative research and development techniques perfected by scientists during World War II, tracing the development of newer methods of scientific analysis and examining how they were imported from military research to the field of education by a select group of…

  15. A Curriculum Model for Teaching Telecommunications to Middle and Secondary School Students.

    Science.gov (United States)

    Daughenbaugh, Richard L.

    This curriculum guide is intended for use in teaching a unit on telecommunications to students with a basic understanding of computing. Introductory materials spell out the purpose of the unit--to provide an introduction to the sending and receiving of electronic information using a personal computer system and the telephone communications…

  16. A Model for Curriculum Intervention in the Desegregation-Integration Process.

    Science.gov (United States)

    Strickler, John W.

    The desegregation process has pinpointed areas of curriculum reform that are needed to help establish quality integrated educational experiences. A racial and ethnic mix is only a beginning. Institutional procedures have become established in schools which may prohibit the realization of the goal of integrated education. School systems should…

  17. A model curriculum for a course on the built environment and public health: training for an interdisciplinary workforce.

    Science.gov (United States)

    Botchwey, Nisha D; Hobson, Susan E; Dannenberg, Andrew L; Mumford, Karen G; Contant, Cheryl K; McMillan, Tracy E; Jackson, Richard J; Lopez, Russell; Winkle, Curtis

    2009-02-01

    Despite growing evidence of the direct and indirect effects of the built environment on public health, planners, who shape the built environment, and public health professionals, who protect the public's health, rarely interact. Most public health professionals have little experience with urban planners, zoning boards, city councils, and others who make decisions about the built environment. Likewise, few planners understand the health implications of design, land use, or transportation decisions. One strategy for bridging this divide is the development of interdisciplinary courses in planning and public health that address the health implications of the built environment. Professional networking and Internet-based searches in 2007 led to the identification of six primarily graduate-level courses in the U.S. that address the links between the built environment and public health. Common content areas in most of the identified courses included planning and public health histories, health disparities, interdisciplinary approaches, air and water quality, physical activity, social capital, and mental health. Instructors of these courses collaborated on course content, assignments, and evaluations to develop a model curriculum that follows an active learning-centered approach to course design. The proposed model curriculum is adaptable by both planning and public health departments to promote interdisciplinary learning. Results show that students gain planning and public health perspectives through this instruction, benefiting from active-learning opportunities. Faculty implementation of the proposed interdisciplinary model curriculum will help bridge the divide between the built environment and public health and enable both planners and public health professionals to value, create, and promote healthy environments.

  18. Framework Construction of MOOC Curriculum Model oriented by Computational Thinking%计算思维导向的MOOC课程模式框架构建

    Institute of Scientific and Technical Information of China (English)

    孔德宇; 徐久成; 孙全党; 孙林

    2015-01-01

    The MOOC is a new form of online education, and explore of its curriculum models is a hotspot in present education research. There exist some problems in current MOOC curriculum models, such as insufifciency theory back-up support, undeifned curriculum objectives, and poor model generalization. In view of these problems above, computational thinking was acted as orientation, the three elements, which are the model theme, function and structure setting as well as support system and applicable condition, were acted as cutting point. The current curriculum models were improved and innovated from five aspects including curriculum objectives, teacher roles, learning manners of student, organization and management modes.%针对目前MOOC课程模式中存在的理论支持不足、课程目标不明确、模式推广性较差等问题,以计算思维为指导,以课程模式的主题、功能、环境三个要素为切入点,依次从课程目标、教师角色、学生学习方式、组织机构、管理方式五个方面,对当前的MOOC课程模式进行改进和创新,构建基于计算思维的MOOC课程模式框架.

  19. International Federation for Emergency Medicine Model curriculum for medical student education in emergency medicine

    Directory of Open Access Journals (Sweden)

    Cherri Hobgood

    2011-09-01

    The curriculum is designed with a focus on the basic minimum emergency medicine educational content that any medical school should be delivering to its students during their undergraduate years of training. It is designed, not to be prescriptive, but to assist educators and emergency medicine leadership in advancing physician education in basic emergency medicine content. The content would be relevant, not just for communities with mature emergency medicine systems, but also for developing nations or for nations seeking to expand emergency medicine within current educational structures. We anticipate that there will be wide variability in how this curriculum is implemented and taught, reflecting the existing educational milieu, the resources available, and the goals of the institutions’ educational leadership.

  20. Improving education in primary care: development of an online curriculum using the blended learning model

    OpenAIRE

    Lewin Linda; Singh Mamta; Bateman Betzi L; Glover Pamela

    2009-01-01

    Abstract Background Standardizing the experiences of medical students in a community preceptorship where clinical sites vary by geography and discipline can be challenging. Computer-assisted learning is prevalent in medical education and can help standardize experiences, but often is not used to its fullest advantage. A blended learning curriculum combining web-based modules with face-to-face learning can ensure students obtain core curricular principles. Methods This course was developed and...

  1. Rocket Science 101 Interactive Educational Program

    Science.gov (United States)

    Armstrong, Dennis; Funkhouse, Deborah; DiMarzio, Donald

    2007-01-01

    To better educate the public on the basic design of NASA s current mission rockets, Rocket Science 101 software has been developed as an interactive program designed to retain a user s attention and to teach about basic rocket parts. This program also has helped to expand NASA's presence on the Web regarding educating the public about the Agency s goals and accomplishments. The software was designed using Macromedia s Flash 8. It allows the user to select which type of rocket they want to learn about, interact with the basic parts, assemble the parts to create the whole rocket, and then review the basic flight profile of the rocket they have built.

  2. Nuclear Thermal Rocket Simulation in NPSS

    Science.gov (United States)

    Belair, Michael L.; Sarmiento, Charles J.; Lavelle, Thomas M.

    2013-01-01

    Four nuclear thermal rocket (NTR) models have been created in the Numerical Propulsion System Simulation (NPSS) framework. The models are divided into two categories. One set is based upon the ZrC-graphite composite fuel element and tie tube-style reactor developed during the Nuclear Engine for Rocket Vehicle Application (NERVA) project in the late 1960s and early 1970s. The other reactor set is based upon a W-UO2 ceramic-metallic (CERMET) fuel element. Within each category, a small and a large thrust engine are modeled. The small engine models utilize RL-10 turbomachinery performance maps and have a thrust of approximately 33.4 kN (7,500 lbf ). The large engine models utilize scaled RL-60 turbomachinery performance maps and have a thrust of approximately 111.2 kN (25,000 lbf ). Power deposition profiles for each reactor were obtained from a detailed Monte Carlo N-Particle (MCNP5) model of the reactor cores. Performance factors such as thermodynamic state points, thrust, specific impulse, reactor power level, and maximum fuel temperature are analyzed for each engine design.

  3. Rocket Science at the Nanoscale.

    Science.gov (United States)

    Li, Jinxing; Rozen, Isaac; Wang, Joseph

    2016-06-28

    Autonomous propulsion at the nanoscale represents one of the most challenging and demanding goals in nanotechnology. Over the past decade, numerous important advances in nanotechnology and material science have contributed to the creation of powerful self-propelled micro/nanomotors. In particular, micro- and nanoscale rockets (MNRs) offer impressive capabilities, including remarkable speeds, large cargo-towing forces, precise motion controls, and dynamic self-assembly, which have paved the way for designing multifunctional and intelligent nanoscale machines. These multipurpose nanoscale shuttles can propel and function in complex real-life media, actively transporting and releasing therapeutic payloads and remediation agents for diverse biomedical and environmental applications. This review discusses the challenges of designing efficient MNRs and presents an overview of their propulsion behavior, fabrication methods, potential rocket fuels, navigation strategies, practical applications, and the future prospects of rocket science and technology at the nanoscale.

  4. Teacher learning in collaborative curriculum design

    NARCIS (Netherlands)

    Vries, Bregje de; Voogt, J.; Westbroek, H.; Handelzalts, A.; Walraven, A.; McKenney, S.; Pieters, J.

    2011-01-01

    The Interconnected Model of Professional Growth (Clarke & Hollingsworth, 2002) was used to identify processes of teacher learning during the collaborative design of curriculum materials in the context of curriculum innovation. Nine published studies from six different countries about teachers’ colla

  5. The “unknown” Greek Paleoenvironment: Curriculum Proposals through an Infusion Model for Elementary School, Using Ammonite Fossils

    Directory of Open Access Journals (Sweden)

    Stiliani FRAGOULI

    2017-06-01

    Full Text Available In this study we introduce an infusion model to “inject” ammonites and ammonite fossils in current subjects of Greek primary curriculum. Paleontology and mainly fossils attract more and more elementary students and teachers, yet in Greece this trend is solely about dinosaurs, despite the fact that the most common Greek fossils are not dinosaurs, but ammonites. Ammonites can be found in large population and diversity inside Greek rocks, as these rocks were part of Tethys΄ seafloor at their geological time. Apart from the informal sources of education, these science topics are excluded from elementary national curriculum, and leave the regional paleoenvironment and geological history practically “unknown” to students. Data collected through a pre-test study, in 558 students of 4th, 5th, and 6th grade confirmed the above belief. A post-test at the original sample, using an open ended questionnaire and students’ drawings, evaluated positively the infusion teaching model, whose core were the ammonite fossils.

  6. Evaluation of how a curriculum change in nurse education was managed through the application of a business change management model: A qualitative case study.

    Science.gov (United States)

    Chowthi-Williams, Annette; Curzio, Joan; Lerman, Stephen

    2016-01-01

    Curriculum changes are a regular feature of nurse education, yet little is known about how such changes are managed. Research in this arena is yet to emerge. Evaluation of how a curriculum change in nurse education was managed through the application of a business change management model. A qualitative case study: the single case was the new curriculum, the Primary Care Pathway. One executive, three senior managers, two academics and nineteen students participated in this study in one faculty of health and social care in a higher education institution. The findings suggest that leadership was pivotal to the inception of the programme and guiding teams managed the change and did not take on a leadership role. The vision for the change and efforts to communicate it did not reach the frontline. Whilst empowerment was high amongst stakeholders and students, academics felt dis-empowered. Short-term wins were not significant in keeping up the momentum of change. The credibility of the change was under challenge and the concept of the new programme was not yet embedded in academia. Differences between the strategic and operational part of the organisation surfaced with many challenges occurring at the implementation stage. The business change model used was valuable, but was found to not be applicable during curriculum changes in nurse education. A new change model emerged, and a tool was developed alongside to aid future curriculum changes. Copyright © 2015 Elsevier Ltd. All rights reserved.

  7. Some typical solid propellant rocket motors

    NARCIS (Netherlands)

    Zandbergen, B.T.C.

    2013-01-01

    Typical Solid Propellant Rocket Motors (shortly referred to as Solid Rocket Motors; SRM's) are described with the purpose to form a database, which allows for comparative analysis and applications in practical SRM engineering.

  8. Integrated Composite Rocket Nozzle Extension Project

    Data.gov (United States)

    National Aeronautics and Space Administration — ORBITEC proposes to develop and demonstrate an Integrated Composite Rocket Nozzle Extension (ICRNE) for use in rocket thrust chambers. The ICRNE will utilize an...

  9. Some typical solid propellant rocket motors

    NARCIS (Netherlands)

    Zandbergen, B.T.C.

    2013-01-01

    Typical Solid Propellant Rocket Motors (shortly referred to as Solid Rocket Motors; SRM's) are described with the purpose to form a database, which allows for comparative analysis and applications in practical SRM engineering.

  10. 'RCHX-1-STORM' first Slovenian meteorological rocket program

    Science.gov (United States)

    Kerstein, Aleksander; Matko, Drago; Trauner, Amalija; Britovšek, Zvone

    2004-08-01

    Astronautic and Rocket Society Celje (ARSC) formed a special working team for research and development of a small meteorological hail suppression rocket in the 70th. The hail suppression system was established in former Yugoslavia in the late 60th as an attempt to protect important agricultural regions from one of the summer's most vicious storm. In this time Slovenia was a part of Yugoslavia as one of the federal republic with relative high developed agricultural region production. The Rocket program 'RCHX-STORM' was a second attempt, for Slovenia indigenously developed in the production of meteorological hail suppression rocket. ARSC has designed a family of small sounding rocket that were based on highly promising hybrid propellant propulsion. Hybrid propulsion was selected for this family because it was offering low cost, save production and operation and simple logistics. Conventional sounding rockets use solid propellant motor for their propulsion. The introduction of hybrid motors has enabled a considerable decrease in overall cost. The transportation handling and storage procedures were greatly simplified due to the fact that a hybrid motor was not considered as explosive matter. A hybrid motor may also be designed to stand a severe environment without resorting to conditioning arrangements. The program started in the late 70th when the team ARSC was integrated in the Research and Development Institute in Celje (RDIC). The development program aimed to produce three types of meteorological rockets with diameters 76, 120 and 160 mm. Development of the RCHX-76 engine and rocket vehicle including flight certification has been undertaken by a joint team comprising of the ARCS, RDIC and the company Cestno podjetje Celje (CPC), Road building company Celje. Many new techniques and methods were used in this program such as computer simulation of external and internal ballistics, composite materials for rocket construction, intensive static testing of models and

  11. The entomologist as a science partner and curriculum advisor: The Earth School model for grades 6--8

    Science.gov (United States)

    Marshall, Bethany Johnston

    The Earth School model for creation of partnerships between university scientists and public schools began with a traditional research project involving the study of macroinvertebrate recolonization of agriculturally based restored wetlands. From fieldwork designed to address hypotheses of community composition over time, protocols and equipment evolved for application in middle-school classrooms. In addition to classroom teachers guiding their students in replicating active scientific research, the inclusion of a science partner was key to the success of this model. To ensure that the classroom teachers were themselves comfortable as researchers, monthly staff development workshops were conducted as a component of the Earth School model. The use of entomology as a unifying theme for educational scientific investigation lets the student explore virtually every other system in the biosphere. Because of the unparalleled survivability and adaptability of insects, we can find examples from all biomes, all time references and all disciplines. Over the course of long-term continuous exploration, learners become familiar with relationships and patterns evident in natural situations. These same patterns of birth, growth and decay are much more vividly demonstrated in the field than in textbooks. Similarly, concrete examples of feeding relationships between organisms are plentiful in nearly any outdoor situation. The following model incorporates current research from multiple scientific disciplines but focuses on the many and varied research activities offered by the entomological community. Teachers and students in a primarily urban setting made extensive use of the materials developed through the course of this model's development. Their feedback as the materials were integrated into an established curriculum allowed for the fine-tuning of activity development. A conversion template has evolved that gives teachers, curriculum directors, parents and other educators a

  12. The Influence of Curriculum, Instruction, Technology, and Social Interactions on Two Fifth-Grade Students' Epistemologies in Modeling throughout a Model-Based Curriculum Unit

    Science.gov (United States)

    Baek, Hamin; Schwarz, Christina V.

    2015-01-01

    In the past decade, reform efforts in science education have increasingly attended to engaging students in scientific practices such as scientific modeling. Engaging students in scientific modeling can help them develop their epistemologies by allowing them to attend to the roles of mechanism and empirical evidence when constructing and revising…

  13. Summarization on variable liquid thrust rocket engines

    Institute of Scientific and Technical Information of China (English)

    2009-01-01

    The technology actuality and development trend of variable thrust rocket engines at home and abroad are summarized. Key technologies of developing variable thrust rocket engines are analyzed. Development advices on developing variable thrust rocket engines that are adapted to the situation of our country are brought forward.

  14. Nuclear-Thermal Rocket Orbits Mars

    Science.gov (United States)

    1960-01-01

    Originally investigated in the 1960's by Marshall Space Flight Center plarners as part of the Nuclear Energy for Rocket Vehicle Applications (NERVA) program, nuclear-thermal rocket propulsion has been more recently considered in spacecraft designs for interplanetary human exploration. This artist's concept illustrates a nuclear-thermal rocket with an aerobrake disk as it orbits Mars.

  15. Longitudinales, bologna-kompatibles Modell-Curriculum "Kommunikative und Soziale Kompetenzen": Ergebnisse eines interdisziplinären Workshops deutschsprachiger medizinischer Fakultäten [A longitudinal, Bologna-compatible model curriculum "communication and social competencies": Results of an interdisciplinary workshop of German-speaking medical schools

    Directory of Open Access Journals (Sweden)

    Hölzer, Henrike

    2009-11-01

    Full Text Available [english] Aim: The aim of the project is to present and discuss a longitudinal model curriculum “Communication and social competencies” for undergraduate medical education. Procedure and results: In a two-day workshop, a multidisciplinary, cross-faculty group of medical educators developed a curriculum model based on the “Basel Consensus Statement”. It can now be used by German-speaking medical schools as a blueprint for curriculum planning and implementation processes. The modular structure enables it to be implemented either in whole or in part. The model can also be used to facilitate the conversion of medical education into Bachelor and Master degree programmes. The longitudinal model curriculum features 131 educational objectives and makes suggestions for didactic concepts and assessment tools. For various disciplines, it also recommends at what point in time specific topics should be taught. Conclusion: The longitudinal model curriculum “Communication and social competencies”, based on the educational objectives of the “Basel Consensus Statement”, is a new curricular instrument that can be used by German, Austrian and Swiss medical schools. It can help to simplify the realisation of the Bologna process, also across different faculties. [german] Zielsetzung: Ziel des Projekts ist es, ein longitudinales Modell-Curriculum „Kommunikative und soziale Kompetenzen“ für die medizinische Ausbildung zur Diskussion zu stellen. Vorgehen und Ergebnisse: Auf einem 2-tägigen Workshop wurde interfakultär und interdisziplinär auf der Grundlage des „Basler Consensus Statements: Kommunikative und soziale Kompetenzen im Medizinstudium“ ein Curriculum entwickelt, das deutschsprachigen Fakultäten bei der Planung und Implementierung als Vorlage dienen kann. Das Modell lässt sich als Gesamt-Curriculum oder in Teilmodulen implementieren. Es kann auch bei der Umstellung auf Bachelor- und Masterstudiengänge genutzt werden. Das

  16. Model curriculum outline for Alternatively Fueled Vehicle (AFV) automotive technician training in light and medium duty CNG and LPG

    Energy Technology Data Exchange (ETDEWEB)

    NONE

    1997-04-01

    This model curriculum outline was developed using a turbo-DACUM (Developing a Curriculum) process which utilizes practicing experts to undertake a comprehensive job and task analysis. The job and task analysis serves to establish current baseline data accurately and to improve both the process and the product of the job through constant and continuous improvement of training. The DACUM process is based on the following assumptions: (1) Expert workers are the best source for task analysis. (2) Any occupation can be described effectively in terms of tasks. (3) All tasks imply knowledge, skills, and attitudes/values. A DACUM panel, comprised of six experienced and knowledgeable technicians who are presently working in the field, was given an orientation to the DACUM process. The panel then identified, verified, and sequenced all the necessary job duty areas and tasks. The broad duty categories were rated according to relative importance and assigned percentage ratings in priority order. The panel then rated every task for each of the duties on a scale of 1 to 3. A rating of 3 indicates an {open_quotes}essential{close_quotes} task, a rating of 2 indicates an {open_quotes}important{close_quotes} task, and a rating of 1 indicates a {open_quotes}desirable{close_quotes} task.

  17. Program evaluation of an Integrated Basic Science Medical Curriculum in Shiraz Medical School, Using CIPP Evaluation Model.

    Science.gov (United States)

    Rooholamini, Azadeh; Amini, Mitra; Bazrafkan, Leila; Dehghani, Mohammad Reza; Esmaeilzadeh, Zohreh; Nabeiei, Parisa; Rezaee, Rita; Kojuri, Javad

    2017-07-01

    In recent years curriculum reform and integration was done in many medical schools. The integrated curriculum is a popular concept all over the world. In Shiraz medical school, the reform was initiated by stablishing the horizontal basic science integration model and Early Clinical Exposure (ECE) for undergraduate medical education. The purpose of this study was to provide the required data for the program evaluation of this curriculum for undergraduate medical students, using CIPP program evaluation model. This study is an analytic descriptive and triangulation mixed method study which was carried out in Shiraz Medical School in 2012, based on the views of professors of basic sciences courses and first and second year medical students. The study evaluated the quality of the relationship between basic sciences and clinical courses and the method of presenting such courses based on the Context, Input, Process and Product (CIPP) model. The tools for collecting data, both quantitatively and qualitatively, were some questionnaires, content analysis of portfolios, semi- structured interview and brain storming sessions. For quantitative data analysis, SPSS software, version 14, was used. In the context evaluation by modified DREEM questionnaire, 77.75%of the students believed that this educational system encourages them to actively participate in classes. Course schedule and atmosphere of class were reported suitable by 87.81% and 83.86% of students. In input domain that was measured by a researcher made questionnaire, the facilities for education were acceptable except for shortage of cadavers. In process evaluation, the quality of integrated modules presentation and Early Clinical Exposure (ECE) was good from the students' viewpoint. In product evaluation, students' brain storming, students' portfolio and semi-structured interview with faculties were done, showing some positive aspects of integration and some areas that need improvement. The main advantage of assessing

  18. Performance of an Axisymmetric Rocket Based Combined Cycle Engine During Rocket Only Operation Using Linear Regression Analysis

    Science.gov (United States)

    Smith, Timothy D.; Steffen, Christopher J., Jr.; Yungster, Shaye; Keller, Dennis J.

    1998-01-01

    The all rocket mode of operation is shown to be a critical factor in the overall performance of a rocket based combined cycle (RBCC) vehicle. An axisymmetric RBCC engine was used to determine specific impulse efficiency values based upon both full flow and gas generator configurations. Design of experiments methodology was used to construct a test matrix and multiple linear regression analysis was used to build parametric models. The main parameters investigated in this study were: rocket chamber pressure, rocket exit area ratio, injected secondary flow, mixer-ejector inlet area, mixer-ejector area ratio, and mixer-ejector length-to-inlet diameter ratio. A perfect gas computational fluid dynamics analysis, using both the Spalart-Allmaras and k-omega turbulence models, was performed with the NPARC code to obtain values of vacuum specific impulse. Results from the multiple linear regression analysis showed that for both the full flow and gas generator configurations increasing mixer-ejector area ratio and rocket area ratio increase performance, while increasing mixer-ejector inlet area ratio and mixer-ejector length-to-diameter ratio decrease performance. Increasing injected secondary flow increased performance for the gas generator analysis, but was not statistically significant for the full flow analysis. Chamber pressure was found to be not statistically significant.

  19. Teacher Learning in Collaborative Curriculum Design

    Science.gov (United States)

    Voogt, J.; Westbroek, H.; Handelzalts, A.; Walraven, A.; McKenney, S.; Pieters, J.; de Vries, B.

    2011-01-01

    The Interconnected Model of Professional Growth (Clarke & Hollingsworth, 2002) was used to identify processes of teacher learning during the collaborative design of curriculum materials in the context of curriculum innovation. Nine published studies from six different countries about teachers' collaborative curriculum design were analyzed to…

  20. The North Dakota Mental Health and Aging Education Project: Curriculum Design and Training Outcomes for a Train-the-Trainer Model

    Science.gov (United States)

    Fitzgerald, Margaret A.; Chromy, Barbara; Philbrick, Candace A.; Sanders, Gregory F.; Muske, Kara L.; Bratteli, Marlys

    2009-01-01

    A training curriculum on mental health and aging was developed and disseminated to 32 natural caregivers throughout a frontier state using a train-the-trainer model. Those certified as trainers included social workers, religious professionals, volunteers, long-term care employees, nurses, home health workers, and professional and informal…

  1. Using a Systematic Conceptual Model for a Process Evaluation of a Middle School Obesity Risk-Reduction Nutrition Curriculum Intervention: Choice, Control & Change

    Science.gov (United States)

    Lee, Heewon; Contento, Isobel R.; Koch, Pamela

    2012-01-01

    Objective To use and review a conceptual model of process evaluation and to examine the implementation of a nutrition education curriculum, Choice, Control & Change, designed to promote dietary and physical activity behaviors that reduce obesity risk. Design A process evaluation study based on a systematic conceptual model. Setting Five middle schools in New York City. Participants 562 students in 20 classes and their science teachers (n=8). Main Outcome Measures Based on the model, teacher professional development, teacher implementation, and student reception were evaluated. Also measured were teacher characteristics, teachers’ curriculum evaluation, and satisfaction with teaching the curriculum. Analysis Descriptive statistics and Spearman’s Rho Correlation for quantitative analysis and content analysis for qualitative data were used. Results Mean score of the teacher professional development evaluation was 4.75 on a 5-point scale. Average teacher implementation rate was 73%, and student reception rate was 69%. Ongoing teacher support was highly valued by teachers. Teachers’ satisfaction with teaching the curriculum was highly correlated with students’ satisfaction (p <.05). Teachers’ perception of amount of student work was negatively correlated with implementation and with student satisfaction (p<.05). Conclusions and implications Use of a systematic conceptual model and comprehensive process measures improves understanding of the implementation process and helps educators to better implement interventions as designed. PMID:23321021

  2. "¡Cocinar Para Su Salud!" Development of a Culturally Based Nutrition Education Curriculum for Hispanic Breast Cancer Survivors Using a Theory-Driven Procedural Model

    Science.gov (United States)

    Aycinena, Ana Corina; Jennings, Kerri-Ann; Gaffney, Ann Ogden; Koch, Pamela A.; Contento, Isobel R.; Gonzalez, Monica; Guidon, Ela; Karmally, Wahida; Hershman, Dawn; Greenlee, Heather

    2017-01-01

    We developed a theory-based dietary change curriculum for Hispanic breast cancer survivors with the goal of testing the effects of the intervention on change in dietary intake of fruits/vegetables and fat in a randomized, clinical trial. Social cognitive theory and the transtheoretical model were used as theoretical frameworks to structure…

  3. The North Dakota Mental Health and Aging Education Project: Curriculum Design and Training Outcomes for a Train-the-Trainer Model

    Science.gov (United States)

    Fitzgerald, Margaret A.; Chromy, Barbara; Philbrick, Candace A.; Sanders, Gregory F.; Muske, Kara L.; Bratteli, Marlys

    2009-01-01

    A training curriculum on mental health and aging was developed and disseminated to 32 natural caregivers throughout a frontier state using a train-the-trainer model. Those certified as trainers included social workers, religious professionals, volunteers, long-term care employees, nurses, home health workers, and professional and informal…

  4. Maximising Students' Progress and Engagement in Science through the Use of the Biological Sciences Curriculum Study (BSCS) 5E Instructional Model

    Science.gov (United States)

    Hoskins, Peter

    2013-01-01

    The Biological Sciences Curriculum Studies (BSCS) 5E Instructional Model (often referred to as the 5Es) consists of five phases. Each phase has a specific function and contributes both to teachers' coherent instruction and to students' formulation of a better understanding of scientific knowledge, attitudes and skills. Evidence indicates that the…

  5. Maximising Students' Progress and Engagement in Science through the Use of the Biological Sciences Curriculum Study (BSCS) 5E Instructional Model

    Science.gov (United States)

    Hoskins, Peter

    2013-01-01

    The Biological Sciences Curriculum Studies (BSCS) 5E Instructional Model (often referred to as the 5Es) consists of five phases. Each phase has a specific function and contributes both to teachers' coherent instruction and to students' formulation of a better understanding of scientific knowledge, attitudes and skills. Evidence indicates…

  6. "¡Cocinar Para Su Salud!" Development of a Culturally Based Nutrition Education Curriculum for Hispanic Breast Cancer Survivors Using a Theory-Driven Procedural Model

    Science.gov (United States)

    Aycinena, Ana Corina; Jennings, Kerri-Ann; Gaffney, Ann Ogden; Koch, Pamela A.; Contento, Isobel R.; Gonzalez, Monica; Guidon, Ela; Karmally, Wahida; Hershman, Dawn; Greenlee, Heather

    2017-01-01

    We developed a theory-based dietary change curriculum for Hispanic breast cancer survivors with the goal of testing the effects of the intervention on change in dietary intake of fruits/vegetables and fat in a randomized, clinical trial. Social cognitive theory and the transtheoretical model were used as theoretical frameworks to structure…

  7. Rocket Plume Scaling for Orion Wind Tunnel Testing

    Science.gov (United States)

    Brauckmann, Gregory J.; Greathouse, James S.; White, Molly E.

    2011-01-01

    A wind tunnel test program was undertaken to assess the jet interaction effects caused by the various solid rocket motors used on the Orion Launch Abort Vehicle (LAV). These interactions of the external flowfield and the various rocket plumes can cause localized aerodynamic disturbances yielding significant and highly non-linear control amplifications and attenuations. This paper discusses the scaling methodologies used to model the flight plumes in the wind tunnel using cold air as the simulant gas. Comparisons of predicted flight, predicted wind tunnel, and measured wind tunnel forces-and-moments and plume flowfields are made to assess the effectiveness of the selected scaling methodologies.

  8. SYMBIOSIS: development, implementation, and assessment of a model curriculum across biology and mathematics at the introductory level.

    Science.gov (United States)

    Depelteau, Audrey M; Joplin, Karl H; Govett, Aimee; Miller, Hugh A; Seier, Edith

    2010-01-01

    "It takes a lot of courage to release the familiar and seemingly secure, to embrace the new. But there is no real security in what is no longer meaningful. There is more security in the adventurous and exciting, for in movement there is life, and in change there is power." Alan Cohen (Used by permission. All rights reserved. For more information on Alan Cohen's books and programs, see (www.alancohen.com.) With the support of the East Tennessee State University (ETSU) administration and a grant from Howard Hughes Medical Institute, the departments of Biological Sciences, Mathematics and Statistics, and Curriculum and Instruction have developed a biology-math integrated curriculum. An interdisciplinary faculty team, charged with teaching the 18 curriculum modules, designed this three-semester curriculum, known as SYMBIOSIS. This curriculum was piloted to two student cohorts during the developmental stage. The positive feedback and assessment results of this project have given us the foundation to implement the SYMBIOSIS curriculum as a replacement for the standard biology majors curriculum at the introductory level. This article addresses the history and development of the curriculum, previous assessment results and current assessment protocol, and the future of ETSU's approach to implementing the SYMBIOSIS curriculum.

  9. SYMBIOSIS: Development, Implementation, and Assessment of a Model Curriculum across Biology and Mathematics at the Introductory Level

    Science.gov (United States)

    Joplin, Karl H.; Govett, Aimee; Miller, Hugh A.; Seier, Edith

    2010-01-01

    “It takes a lot of courage to release the familiar and seemingly secure, to embrace the new. But there is no real security in what is no longer meaningful. There is more security in the adventurous and exciting, for in movement there is life, and in change there is power.”Alan Cohen (Used by permission. All rights reserved. For more information on Alan Cohen's books and programs, see (www.alancohen.com.) With the support of the East Tennessee State University (ETSU) administration and a grant from Howard Hughes Medical Institute, the departments of Biological Sciences, Mathematics and Statistics, and Curriculum and Instruction have developed a biology–math integrated curriculum. An interdisciplinary faculty team, charged with teaching the 18 curriculum modules, designed this three-semester curriculum, known as SYMBIOSIS. This curriculum was piloted to two student cohorts during the developmental stage. The positive feedback and assessment results of this project have given us the foundation to implement the SYMBIOSIS curriculum as a replacement for the standard biology majors curriculum at the introductory level. This article addresses the history and development of the curriculum, previous assessment results and current assessment protocol, and the future of ETSU's approach to implementing the SYMBIOSIS curriculum. PMID:20810967

  10. Unique nuclear thermal rocket engine

    Energy Technology Data Exchange (ETDEWEB)

    Culver, D.W. (Aerojet Propulsion Division, P.O. Box 13222, Sacramento, California 95813-6000 (United States)); Rochow, R. (Babcock Wilcox Space Nuclear Systems, P.O. Box 11165, Lynchburg, Virginia 24506-1165 (United States))

    1993-01-15

    Earlier this year Aerojet Propulsion Division (APD) introduced a new, advanced nuclear thermal rocket engine (NTRE) concept intended for manned missions to the moon and to Mars. This NTRE promises to be both shorter and lighter in weight than conventionally designed engines, because its forward flowing reactor is located within an expansion-deflection (E-D) rocket nozzle. The concept has matured during the year, and this paper discusses a nearer term version that resolves four open issues identified in the initial concept: (1)Reactor design and cooling scheme simplification while retaining a high pressure power balance option; (2)Eliminate need for a new, uncooled nozzle throat material suitable for long life application; (3)Practical provision for reactor power control; and (4)Use near term, long life turbopumps.

  11. Nanoparticles for solid rocket propulsion

    Energy Technology Data Exchange (ETDEWEB)

    Galfetti, L [Politecnico di Milano, SPLab, Milan (Italy); De Luca, L T [Politecnico di Milano, SPLab, Milan (Italy); Severini, F [Politecnico di Milano, SPLab, Milan (Italy); Meda, L [Polimeri Europa, Istituto G Donegani, Novara (Italy); Marra, G [Polimeri Europa, Istituto G Donegani, Novara (Italy); Marchetti, M [Universita di Roma ' La Sapienza' , Dipartimento di Ingegneria Aerospaziale ed Astronautica, Rome (Italy); Regi, M [Universita di Roma ' La Sapienza' , Dipartimento di Ingegneria Aerospaziale ed Astronautica, Rome (Italy); Bellucci, S [INFN, Laboratori Nazionali di Frascati, Frascati (Italy)

    2006-08-23

    The characterization of several differently sized aluminium powders, by BET (specific surface), EM (electron microscopy), XRD (x-ray diffraction), and XPS (x-ray photoelectron spectroscopy), was performed in order to evaluate their application in solid rocket propellant compositions. These aluminium powders were used in manufacturing several laboratory composite solid rocket propellants, based on ammonium perchlorate (AP) as oxidizer and hydroxil-terminated polybutadiene (HTPB) as binder. The reference formulation was an AP/HTPB/Al composition with 68/17/15% mass fractions respectively. The ballistic characterization of the propellants, in terms of steady burning rates, shows better performance for propellant compositions employing nano-aluminium when compared to micro-aluminium. Results obtained in the pressure range 1-70 bar show that by increasing the nano-Al mass fraction or decreasing the nano-Al size, larger steady burning rates are measured with essentially the same pressure sensitivity.

  12. Unique nuclear thermal rocket engine

    Science.gov (United States)

    Culver, Donald W.; Rochow, Richard

    1993-06-01

    In January, 1992, a new, advanced nuclear thermal rocket engine (NTRE) concept intended for manned missions to the moon and to Mars was introduced (Culver, 1992). This NTRE promises to be both shorter and lighter in weight than conventionally designed engines, because its forward flowing reactor is located within an expansion-deflection rocket nozzle. The concept has matured during the year, and this paper discusses a nearer term version that resolves four open issues identified in the initial concept: (1) the reactor design and cooling scheme simplification while retaining a high pressure power balance option; (2) elimination need for a new, uncooled nozzle throat material suitable for long life application; (3) a practical provision for reactor power control; and (4) use of near-term, long-life turbopumps.

  13. Nanoparticles for solid rocket propulsion

    Science.gov (United States)

    Galfetti, L.; DeLuca, L. T.; Severini, F.; Meda, L.; Marra, G.; Marchetti, M.; Regi, M.; Bellucci, S.

    2006-08-01

    The characterization of several differently sized aluminium powders, by BET (specific surface), EM (electron microscopy), XRD (x-ray diffraction), and XPS (x-ray photoelectron spectroscopy), was performed in order to evaluate their application in solid rocket propellant compositions. These aluminium powders were used in manufacturing several laboratory composite solid rocket propellants, based on ammonium perchlorate (AP) as oxidizer and hydroxil-terminated polybutadiene (HTPB) as binder. The reference formulation was an AP/HTPB/Al composition with 68/17/15% mass fractions respectively. The ballistic characterization of the propellants, in terms of steady burning rates, shows better performance for propellant compositions employing nano-aluminium when compared to micro-aluminium. Results obtained in the pressure range 1-70 bar show that by increasing the nano-Al mass fraction or decreasing the nano-Al size, larger steady burning rates are measured with essentially the same pressure sensitivity.

  14. Extended temperature range rocket injector

    Science.gov (United States)

    Schneider, Steven J. (Inventor)

    1991-01-01

    A rocket injector is provided with multiple sets of manifolds for supplying propellants to injector elements. Sensors transmit the temperatures of the propellants to a suitable controller which is operably connnected to valves between these manifolds and propellant storage tanks. When cryogenic propellant temperatures are sensed, only a portion of the valves are opened to furnish propellants to some of the manifolds. When lower temperatures are sensed, additional valves are opened to furnish propellants to more of the manifolds.

  15. Mini-Rocket User Guide

    Science.gov (United States)

    2007-08-01

    Missile Research , Development, and Engineering Center and Ray Sells DESE Research , Inc. 315 Wynn Drive Huntsville, AL 35805 August 2007...with the minirock command, you are prompted for a filename: Mini-Rocket v1.01 by Ray Sells, DESE Research , Inc. Input file: - Output is printed...nancv.bucher@us.army.mil Commander, U.S. Army ARDEC Picatinny Arsenal, NJ 07806-5000 ATTN: AMSRD-AR-AIS -SA DESE Research , Inc. 3 15 Wynn Drive

  16. Optimization Problem of Multistage Rocket

    Directory of Open Access Journals (Sweden)

    V. B. Tawakley

    1972-04-01

    Full Text Available The necessary conditions for the existence of minimum of a function of initial and final values of mass, position and velocity components and time of a multistage rocket have been reviewed when the thrust levels in each stage are considered to bounded and variation in gravity with height has been taken into account. The nature of the extremal subarcs comprising the complete extremal are has been studied. A few simple examples have been given as illustrations.

  17. The Effect of Resistance on Rocket Injector Acoustics

    Science.gov (United States)

    Morgan, C. J.

    2015-01-01

    Combustion instability, where unsteady heat release couples with acoustic modes, has long been an area of concern in liquid rocket engines. Accurate modeling of the acoustic normal modes of the combustion chamber is important to understanding and preventing combustion instability. The injector resistance can have a significant influence on the chamber normal mode shape, and hence on the system stability.

  18. Psychopharmacology Curriculum Field Test

    Science.gov (United States)

    Zisook, Sidney; Balon, Richard; Benjamin, Sheldon; Beresin, Eugene; Goldberg, David A.; Jibson, Michael D.; Thrall, Grace

    2009-01-01

    Objective: As part of an effort to improve psychopharmacology training in psychiatric residency programs, a committee of residency training directors and associate directors adapted an introductory schizophrenia presentation from the American Society of Clinical Psychopharmacology's Model Psychopharmacology Curriculum to develop a multimodal,…

  19. 澳大利亚TAFE课程模式在《旅行社经营与管理》课程设计中的应用%Application of Australian TAFE Curriculum Model in the Curriculum Design of Business of Tour Operation

    Institute of Scientific and Technical Information of China (English)

    王建军

    2011-01-01

    本文借鉴TAFE课程模式,围绕工学结合的职业教育理念,以学生能力为本位,在《旅行社经营与管理》课程设计进行应用,尝试探索一条行之有效的特色课程模式。%Centering on vocational education concept of the integration of production education,and orienting students' competency,the paper tries to explore an effective curriculum model by applying TAFE curriculum model in the curriculum design of Business of Tour Operation.

  20. Software for Collaborative Engineering of Launch Rockets

    Science.gov (United States)

    Stanley, Thomas Troy

    2003-01-01

    The Rocket Evaluation and Cost Integration for Propulsion and Engineering software enables collaborative computing with automated exchange of information in the design and analysis of launch rockets and other complex systems. RECIPE can interact with and incorporate a variety of programs, including legacy codes, that model aspects of a system from the perspectives of different technological disciplines (e.g., aerodynamics, structures, propulsion, trajectory, aeroheating, controls, and operations) and that are used by different engineers on different computers running different operating systems. RECIPE consists mainly of (1) ISCRM a file-transfer subprogram that makes it possible for legacy codes executed in their original operating systems on their original computers to exchange data and (2) CONES an easy-to-use filewrapper subprogram that enables the integration of legacy codes. RECIPE provides a tightly integrated conceptual framework that emphasizes connectivity among the programs used by the collaborators, linking these programs in a manner that provides some configuration control while facilitating collaborative engineering tradeoff studies, including design to cost studies. In comparison with prior collaborative-engineering schemes, one based on the use of RECIPE enables fewer engineers to do more in less time.

  1. Computational simulation of liquid fuel rocket injectors

    Science.gov (United States)

    Landrum, D. Brian

    1994-01-01

    A major component of any liquid propellant rocket is the propellant injection system. Issues of interest include the degree of liquid vaporization and its impact on the combustion process, the pressure and temperature fields in the combustion chamber, and the cooling of the injector face and chamber walls. The Finite Difference Navier-Stokes (FDNS) code is a primary computational tool used in the MSFC Computational Fluid Dynamics Branch. The branch has dedicated a significant amount of resources to development of this code for prediction of both liquid and solid fuel rocket performance. The FDNS code is currently being upgraded to include the capability to model liquid/gas multi-phase flows for fuel injection simulation. An important aspect of this effort is benchmarking the code capabilities to predict existing experimental injection data. The objective of this MSFC/ASEE Summer Faculty Fellowship term was to evaluate the capabilities of the modified FDNS code to predict flow fields with liquid injection. Comparisons were made between code predictions and existing experimental data. A significant portion of the effort included a search for appropriate validation data. Also, code simulation deficiencies were identified.

  2. Solid Rocket Launch Vehicle Explosion Environments

    Science.gov (United States)

    Richardson, E. H.; Blackwood, J. M.; Hays, M. J.; Skinner, T.

    2014-01-01

    Empirical explosion data from full scale solid rocket launch vehicle accidents and tests were collected from all available literature from the 1950s to the present. In general data included peak blast overpressure, blast impulse, fragment size, fragment speed, and fragment dispersion. Most propellants were 1.1 explosives but a few were 1.3. Oftentimes the data from a single accident was disjointed and/or missing key aspects. Despite this fact, once the data as a whole was digitized, categorized, and plotted clear trends appeared. Particular emphasis was placed on tests or accidents that would be applicable to scenarios from which a crew might need to escape. Therefore, such tests where a large quantity of high explosive was used to initiate the solid rocket explosion were differentiated. Also, high speed ground impacts or tests used to simulate such were also culled. It was found that the explosions from all accidents and applicable tests could be described using only the pressurized gas energy stored in the chamber at the time of failure. Additionally, fragmentation trends were produced. Only one accident mentioned the elusive "small" propellant fragments, but upon further analysis it was found that these were most likely produced as secondary fragments when larger primary fragments impacted the ground. Finally, a brief discussion of how this data is used in a new launch vehicle explosion model for improving crew/payload survival is presented.

  3. Understanding China's Curriculum Reform for the 21st Century

    Science.gov (United States)

    Law, Wing-Wah

    2014-01-01

    This article uses curriculum-making frameworks to analyse and reconstruct the Chinese curriculum-making model and unpack the dynamics, complexity and constraints of China's curriculum reform since the early 1990s. It argues that curriculum reform is China's main human capital development strategy for coping with the challenges of the 21st century,…

  4. Understanding China's Curriculum Reform for the 21st Century

    Science.gov (United States)

    Law, Wing-Wah

    2014-01-01

    This article uses curriculum-making frameworks to analyse and reconstruct the Chinese curriculum-making model and unpack the dynamics, complexity and constraints of China's curriculum reform since the early 1990s. It argues that curriculum reform is China's main human capital development strategy for coping with the challenges of the 21st century,…

  5. A Model for Technovocational School-Based Curriculum Planning and Evaluation under the Framework of Total Quality Management.

    Science.gov (United States)

    Wang, Yen-Zen

    In the current climate of rapid technological advance and social value change, many have suggested that schools should use a school-based approach to curriculum planning. How to design such a curriculum in order to train graduates suited for employment has become an important issue. Many domestic and international enterprises have successfully…

  6. A Critical Review of Qualitative Research Methods in Evaluating Nursing Curriculum Models: Implication for Nursing Education in the Arab World

    Science.gov (United States)

    Devadas, Briliya

    2016-01-01

    Aim: The purpose of this critical literature review was to examine qualitative studies done on innovative nursing curriculums in order to determine which qualitative methods have been most effective in investigating the effectiveness of the curriculum and which would be most appropriate in an Arab Islamic country. Data Sources: At least 25 studies…

  7. Potential Teaching Model for Applying Novel Approaches of Renewed Estonian National Curriculum into Visual Art Classes in Primary School

    Science.gov (United States)

    Vahter, Edna

    2015-01-01

    In 2010, the renewed national curriculum was legislated in Estonia. Major changes include a new list of cross-curricular topics, increased importance of integration and specification of the components of the art learning process. In this situation, the question arises--how to fully implement the challenges of the renewed curriculum in primary…

  8. CFD Simulation of Liquid Rocket Engine Injectors

    Science.gov (United States)

    Farmer, Richard; Cheng, Gary; Chen, Yen-Sen; Garcia, Roberto (Technical Monitor)

    2001-01-01

    Detailed design issues associated with liquid rocket engine injectors and combustion chamber operation require CFD methodology which simulates highly three-dimensional, turbulent, vaporizing, and combusting flows. The primary utility of such simulations involves predicting multi-dimensional effects caused by specific injector configurations. SECA, Inc. and Engineering Sciences, Inc. have been developing appropriate computational methodology for NASA/MSFC for the past decade. CFD tools and computers have improved dramatically during this time period; however, the physical submodels used in these analyses must still remain relatively simple in order to produce useful results. Simulations of clustered coaxial and impinger injector elements for hydrogen and hydrocarbon fuels, which account for real fluid properties, is the immediate goal of this research. The spray combustion codes are based on the FDNS CFD code' and are structured to represent homogeneous and heterogeneous spray combustion. The homogeneous spray model treats the flow as a continuum of multi-phase, multicomponent fluids which move without thermal or velocity lags between the phases. Two heterogeneous models were developed: (1) a volume-of-fluid (VOF) model which represents the liquid core of coaxial or impinger jets and their atomization and vaporization, and (2) a Blob model which represents the injected streams as a cloud of droplets the size of the injector orifice which subsequently exhibit particle interaction, vaporization, and combustion. All of these spray models are computationally intensive, but this is unavoidable to accurately account for the complex physics and combustion which is to be predicted, Work is currently in progress to parallelize these codes to improve their computational efficiency. These spray combustion codes were used to simulate the three test cases which are the subject of the 2nd International Workshop on-Rocket Combustion Modeling. Such test cases are considered by

  9. Characterization of rocket propellant combustion products

    Energy Technology Data Exchange (ETDEWEB)

    Jenkins, R.A.; Nestor, C.W.; Thompson, C.V.; Gayle, T.M.; Ma, C.Y.; Tomkins, B.A.; Moody, R.L.

    1991-12-09

    The overall objective of the work described in this report is four-fold: to (a) develop a standardized and experimentally validated approach to the sampling and chemical and physical characterization of the exhaust products of scaled-down rocket launch motors fired under experimentally controlled conditions at the Army's Signature Characterization Facility (ASCF) at Redstone Arsenal in Huntsville, Alabama; (b) determine the composition of the exhaust produces; (c) assess the accuracy of a selected existing computer model for predicting the composition of major and minor chemical species; (d) recommended alternations to both the sampling and analysis strategy and the computer model in order to achieve greater congruence between chemical measurements and computer prediction. 34 refs., 2 figs., 35 tabs.

  10. Heat transfer in rocket combustion chambers

    Science.gov (United States)

    Anderson, P.; Cheng, G.; Farmer, R.

    1993-01-01

    Complexities of liquid rocket engine heat transfer which involve the injector faceplate and film cooled walls are being investigated by computational analysis. A conjugate heat transfer analysis was used to describe localized heating phenomena associated with particular injector configurations and film coolant flows. These components were analyzed, and the analyses verified when appropriate test data were available. The component analyses are being synthesized into an overall flowfield/heat transfer model. A Navier-Stokes flow solver, the FDNS code, was used to make the analyses. Particular attention was given to the representation of the thermodynamic properties of the fluid streams. Unit flow models of specific coaxial injector elements have been developed and are being used to describe the flame structure near the injector faceplate.

  11. Reusable rocket engine optical condition monitoring

    Science.gov (United States)

    Wyett, L.; Maram, J.; Barkhoudarian, S.; Reinert, J.

    1987-01-01

    Plume emission spectrometry and optical leak detection are described as two new applications of optical techniques to reusable rocket engine condition monitoring. Plume spectrometry has been used with laboratory flames and reusable rocket engines to characterize both the nominal combustion spectra and anomalous spectra of contaminants burning in these plumes. Holographic interferometry has been used to identify leaks and quantify leak rates from reusable rocket engine joints and welds.

  12. Welding Curriculum.

    Science.gov (United States)

    Alaska State Dept. of Education, Juneau. Div. of Adult and Vocational Education.

    This competency-based curriculum guide is a handbook for the development of welding trade programs. Based on a survey of Alaskan welding employers, it includes all competencies a student should acquire in such a welding program. The handbook stresses the importance of understanding the principles associated with the various elements of welding.…

  13. Curriculum Analysis

    Institute of Scientific and Technical Information of China (English)

    Xu Xiaoying

    2011-01-01

    The English as a Second Language (ESL) Curriculum for grades K - 12 is a scope that builds and develops linguistic proficiency for students between the ages of six and 21 years. The ESL professionals defines ESL students as those students who are non - native English speakers and who may or may not have English proficiency.

  14. Ionospheric effects of whistler waves from rocket-triggered lightning

    Science.gov (United States)

    Cotts, B. R. T.; Gołkowski, M.; Moore, R. C.

    2011-12-01

    Lightning-induced electron precipitation (LEP) is one of the primary mechanisms for energetic electron loss from Earth's radiation belts. While previous works have emphasized lightning location and the return stroke peak current in quantifying lightning's role in radiation belt electron loss, the spectrum of the lightning return stroke has received far less attention. Rocket-triggered lightning experiments performed at the International Center for Lightning Research and Testing (ICLRT) at Camp Blanding, Florida, provide a means to directly measure the spectral content of individual lightning return strokes. Using an integrated set of numerical models and directly observed rocket-triggered lightning channel-base currents we calculate the latitudinal dependence of the precipitation signature. Model results indicate that rocket-triggered lightning may produce detectable LEP events and that return strokes with higher ELF (3 Hz-3 kHz) content cause proportionally more ionospheric ionization and precipitate more electrons at higher latitudes than return strokes with proportionally higher VLF (3 kHz-30 kHz) content. The predicted spatio-temporal signature of the induced electron precipitation is highly dependent upon the return stroke spectral content. As a result, we postulate that rocket-triggered lightning experiments enable us to the estimate the spectral profile of energetic electrons precipitated from the Earth's radiation belts.

  15. The four INTA-300 rocket prototypes

    Science.gov (United States)

    Calero, J. S.

    1985-03-01

    A development history and performance capability assessment is presented for the INTA-300 'Flamenco' sounding rocket prototype specimens. The Flamenco is a two-stage solid fuel rocket, based on British sounding rocket technology, that can lift 50 km payloads to altitudes of about 300 km. The flight of the first two prototypes, in 1974 and 1975, pointed to vibration problems which reduced the achievable apogee, and the third prototype's flight was marred by a premature detonation that destroyed the rocket. The fourth Flamenco flight, however, yielded much reliable data.

  16. Gagne's and Laurillard's Models of Instruction Applied to Distance Education: A theoretically driven evaluation of an online curriculum in public health

    Directory of Open Access Journals (Sweden)

    Peggy Hannon

    2002-10-01

    Full Text Available This article presents an overview of the instructional models of Gagne, Briggs, and Wager (1992 and Laurillard (1993; 2002, followed by student evaluations from the first year of an online public health core curriculum. Both online courses and their evaluations were developed in accordance with the two models of instruction. The evaluations by students indicated that they perceived they had achieved the course objectives and were generally satisfied with the experience of taking the courses online. However, some students were dissatisfied with the feedback and learning guidance they received; these students’ comments supported Laurillard’s model of instruction. Discussion captured in this paper focuses on successes of the first year of the online curriculum, suggestions for solving problem areas, and the importance of the perceived relationship between teacher and student in the distance education environment.

  17. Demilitarization of Lance rocket motors

    Science.gov (United States)

    Sargent, Peter

    1995-02-01

    In 1992 Royal Ordnance was awarded contract by NAMSA for the demilitarization of NATO's European stock of Lance missile rocket motors. Lance is a liquid fueled surface to surface guided missile designed to give general battlefield support with either a nuclear or conventional capability at ranges of up to 130 km. The NAMSA contract required Royal Ordnance to undertake the following: (1) transportation of missiles from NATO depots in Europe to Royal Ordnance's factory at Bishopton in Scotland; (2) establishment of a dedicated demilitarization facility at Bishopton; and (3) demilitarization of live M5 and M6 training missiles by the end of 1994.

  18. The Advanced Solid Rocket Motor

    Science.gov (United States)

    Mitchell, Royce E.

    1992-08-01

    The Advanced Solid Rocket Motor will utilize improved design features and automated manufacturing methods to produce an inherently safer propulsive system for the Space Shuttle and future launch systems. This second-generation motor will also provide an additional 12,000 pounds of payload to orbit, enhancing the utility and efficiency of the Shuttle system. The new plant will feature strip-wound, asbestos-free insulation; propellant continuous mixing and casting; and extensive robotic systems. Following a series of static tests at the Stennis Space Center, MS flights are targeted to begin in early 1997.

  19. The Advanced Solid Rocket Motor

    Science.gov (United States)

    Mitchell, Royce E.

    1992-01-01

    The Advanced Solid Rocket Motor will utilize improved design features and automated manufacturing methods to produce an inherently safer propulsive system for the Space Shuttle and future launch systems. This second-generation motor will also provide an additional 12,000 pounds of payload to orbit, enhancing the utility and efficiency of the Shuttle system. The new plant will feature strip-wound, asbestos-free insulation; propellant continuous mixing and casting; and extensive robotic systems. Following a series of static tests at the Stennis Space Center, MS flights are targeted to begin in early 1997.

  20. From Classrooms to Geosciences Careers: Developing and Testing a Curriculum Module and Web Application for Modeling Water in Urban Environments

    Science.gov (United States)

    Cervenec, J. M.; Durand, M. T.

    2014-12-01

    A curriculum module created to teach basic principles of hydrology and promote geoscience careers at the high school level will be shared. The module, consisting of five exercises of increasing complexity, focuses on investigating local problems in hydrology using tangible models, readily available online tools, and a custom-built web application. The module culminates in students examining changing land use patterns over time and looking at subsequent impacts on runoff. Materials were field tested during two summer workshops for educators and support was provided during the subsequent school years. Participants reported that the materials filled existing voids in their instructional materials, that they preferred to select individual exercises for use in their classrooms rather than the module as a whole, and that they found online tools in geosciences and connections to local field sites and geoscience professionals to be particularly valuable. Furthermore, while the five exercises where developed for use together in high school classrooms, individual exercises were found to be applicable in classrooms from the elementary through graduate levels. The module addresses NGSS Disciplinary Core Idea - The Role of Water in Earth's Surface Processes in addition to Cross Cutting Concepts - Systems and System Models and Influence of Engineering, Technology, and Science on Society and the Natural World and multiple NGSS Practices.

  1. Writings as modelling examples: Scaffolds for academic writing in a post-graduate curriculum

    NARCIS (Netherlands)

    Firssova, Olga

    2014-01-01

    The presented study investigated the effectiveness of learning from models in the context of post-graduate academic writing. Two questions were pursued: whether studying model writings supports mature students in writing in a new genre and whether integrating additional scaffolds in such models has

  2. Model texts in an advanced academic writing curriculum: Unravelling an instructional strategy

    NARCIS (Netherlands)

    Firssova, Olga

    2014-01-01

    The study investigated the effectiveness of learning from models in the context of post-graduate academic writing. Two questions were pursued: whether studying model writings supports mature students in writing in a new genre and whether integrating additional scaffolds in such models has added valu

  3. Helping Teachers Grow: Toward Theory and Practice of an "Emergent Curriculum" Model of Staff Development

    Science.gov (United States)

    Riley, David A.; Roach, Mary A.

    2006-01-01

    A model of developmentally appropriate practice in helping teachers grow is described. The model derives from a consideration of the psychological processes by which adults learn, and our desire to teach adults by the same methods we hope they will use in teaching children. The model includes a sequence of six kinds of interactions that the…

  4. Systems Models in Educational Research: A Review and Realignment in the Context of Curriculum

    Science.gov (United States)

    Lee, Nicolette

    2015-01-01

    System models are commonly used in tertiary education as a mechanism for describing the interacting components of educational phenomena, but have hitherto been uncritically accepted. This paper provides a critical review of existing systems models, including the 3P model defined Biggs, and outlines their conceptual challenges. A revised model…

  5. Writings as modelling examples: Scaffolds for academic writing in a post-graduate curriculum

    NARCIS (Netherlands)

    Firssova, Olga

    2014-01-01

    The presented study investigated the effectiveness of learning from models in the context of post-graduate academic writing. Two questions were pursued: whether studying model writings supports mature students in writing in a new genre and whether integrating additional scaffolds in such models has

  6. Model texts in an advanced academic writing curriculum: Unravelling an instructional strategy

    NARCIS (Netherlands)

    Firssova, Olga

    2014-01-01

    The study investigated the effectiveness of learning from models in the context of post-graduate academic writing. Two questions were pursued: whether studying model writings supports mature students in writing in a new genre and whether integrating additional scaffolds in such models has added valu

  7. Model texts in an advanced academic writing curriculum: Unravelling an instructional strategy

    OpenAIRE

    Firssova, Olga

    2014-01-01

    The study investigated the effectiveness of learning from models in the context of post-graduate academic writing. Two questions were pursued: whether studying model writings supports mature students in writing in a new genre and whether integrating additional scaffolds in such models has added value

  8. Additive Manufacturing a Liquid Hydrogen Rocket Engine

    Science.gov (United States)

    Jones, Carl P.; Robertson, Elizabeth H.; Koelbl, Mary Beth; Singer, Chris

    2016-01-01

    Space Propulsion is a 5 day event being held from 2nd May to the 6th May 2016 at the Rome Marriott Park Hotel in Rome, Italy. This event showcases products like Propulsion sub-systems and components, Production and manufacturing issues, Liquid, Solid, Hybrid and Air-breathing Propulsion Systems for Launcher and Upper Stages, Overview of current programmes, AIV issues and tools, Flight testing and experience, Technology building blocks for Future Space Transportation Propulsion Systems : Launchers, Exploration platforms & Space Tourism, Green Propulsion for Space Transportation, New propellants, Rocket propulsion & global environment, Cost related aspects of Space Transportation propulsion, Modelling, Pressure-Thrust oscillations issues, Impact of new requirements and regulations on design etc. in the Automotive, Manufacturing, Fabrication, Repair & Maintenance industries.

  9. Solid Rocket Booster-Illustration

    Science.gov (United States)

    1977-01-01

    This illustration is a cutaway of the solid rocket booster (SRB) sections with callouts. The Shuttle's two SRB's are the largest solids ever built and the first designed for refurbishment and reuse. Standing nearly 150-feet high, the twin boosters provide the majority of thrust for the first two minutes of flight, about 5.8 million pounds, augmenting the Shuttle's main propulsion system during liftoff. The major design drivers for the solid rocket motors (SRM's) were high thrust and reuse. The desired thrust was achieved by using state-of-the-art solid propellant and by using a long cylindrical motor with a specific core design that allows the propellant to burn in a carefully controlled marner. At burnout, the boosters separate from the external tank and drop by parachute to the ocean for recovery and subsequent refurbishment. The boosters are designed to survive water impact at almost 60 miles per hour, maintain flotation with minimal damage, and preclude corrosion of the hardware exposed to the harsh seawater environment. Under the project management of the Marshall Space Flight Center, the SRB's are assembled and refurbished by the United Space Boosters. The SRM's are provided by the Morton Thiokol Corporation.

  10. Reducing Thrusts In Solid-Fuel Rockets

    Science.gov (United States)

    Bement, Laurence J.

    1989-01-01

    Thrust-terminating system conceived to reduce thrust of solid-propellant rocket motor in controlled manner such that thrust loads not increased or decreased beyond predictable levels. Concept involves explosively cutting opposing venting pairs in case of rocket motor above nozzles to initiate venting of chamber and reduction of thrust. Vents sized and numbered to control amount and rate of reduction in thrust.

  11. Correlation Educational Model in Primary Education Curriculum of Mathematics and Computer Science

    Science.gov (United States)

    Macinko Kovac, Maja; Eret, Lidija

    2012-01-01

    This article gives insight into methodical correlation model of teaching mathematics and computer science. The model shows the way in which the related areas of computer science and mathematics can be supplemented, if it transforms the way of teaching and creates a "joint" lessons. Various didactic materials are designed, in which all…

  12. Using the QUAIT Model to Effectively Teach Research Methods Curriculum to Master's-Level Students

    Science.gov (United States)

    Hamilton, Nancy J.; Gitchel, Dent

    2017-01-01

    Purpose: To apply Slavin's model of effective instruction to teaching research methods to master's-level students. Methods: Barriers to the scientist-practitioner model (student research experience, confidence, and utility value pertaining to research methods as well as faculty research and pedagogical incompetencies) are discussed. Results: The…

  13. Development of “Functional Groups in Molecules” Models For Fundamental Science Curriculum

    Directory of Open Access Journals (Sweden)

    Kowit KITTIWUTTHISAKDI

    2007-06-01

    Full Text Available In order to teach quantum concepts to primary school students, new molecular models have been developed to better visualize a few typical molecules. Both computer and physical molecular models particularly those displaying functional groups were created from Atoms in Molecules (AIM theory. The surface of each model was calculated from 0.01 atomic unit (au electron density surface of the molecule. MORPHY was used to calculate an inter-atomic surface (IAS, and several software programs such as Gaussian, VMD, Points2Polys, and Vizx3D were utilized to create three dimensional models. Different functional groups were colored, and connections between the functional groups were shown by IAS. The final physical molecular models were prepared by a rapid prototype machine at Thailand National Metal and Materials Technology Center (MTEC.

  14. Hybrid Rocket Experiment Station for Capstone Design

    Science.gov (United States)

    Conley, Edgar; Hull, Bethanne J.

    2012-01-01

    Portable hybrid rocket motors and test stands can be seen in many papers but none have been reported on the design or instrumentation at such a small magnitude. The design of this hybrid rocket and test stand is to be small and portable (suitcase size). This basic apparatus will be used for demonstrations in rocket propulsion. The design had to include all of the needed hardware to operate the hybrid rocket unit (with the exception of the external Oxygen tank). The design of this project includes making the correlation between the rocket's thrust and its size, the appropriate transducers (physical size, resolution, range, and cost), compatability with a laptop analog card, the ease of setup, and its portability.

  15. Gastroenterology Fellowship Training: Approaches to Curriculum Assessment and Evaluation

    Directory of Open Access Journals (Sweden)

    Maitreyi Raman

    2008-01-01

    Full Text Available BACKGROUND: Medical education requires ongoing curriculum development and evaluation to incorporate new knowledge and competencies. The Kern model of curricular development is a generic model to guide curriculum design, whereas the Royal College of Physicians and Surgeons of Canada (RCPSC has a specific model for curriculum development through its accreditation structure.

  16. Electrets used in measuring rocket exhaust effluents from the space shuttle's solid rocket booster during static test firing, DM-3

    Science.gov (United States)

    Susko, M.

    1979-01-01

    The purpose of this experimental research was to compare Marshall Space Flight Center's electrets with Thiokol's fixed flow air samplers during the Space Shuttle Solid Rocket Booster Demonstration Model-3 static test firing on October 19, 1978. The measurement of rocket exhaust effluents by Thiokol's samplers and MSFC's electrets indicated that the firing of the Solid Rocket Booster had no significant effect on the quality of the air sampled. The highest measurement by Thiokol's samplers was obtained at Plant 3 (site 11) approximately 8 km at a 113 degree heading from the static test stand. At sites 11, 12, and 5, Thiokol's fixed flow air samplers measured 0.0048, 0.00016, and 0.00012 mg/m3 of CI. Alongside the fixed flow measurements, the electret counts from X-ray spectroscopy were 685, 894, and 719 counts. After background corrections, the counts were 334, 543, and 368, or an average of 415 counts. An additional electred, E20, which was the only measurement device at a site approximately 20 km northeast from the test site where no power was available, obtained 901 counts. After background correction, the count was 550. Again this data indicate there was no measurement of significant rocket exhaust effluents at the test site.

  17. Problems in network model curriculum and corresponding solutions%网络示范课程建设中存在的问题及对策

    Institute of Scientific and Technical Information of China (English)

    郑磊琦; 肖文雅

    2013-01-01

    对新乡医学院建设有自身特色的网络示范课程进行调研,通过问卷调查与分析,认为网络示范课程以学生学习为中心,进行“三层次教学设计”,满足学生自学和辅助课堂教学,对于学分制、弹性学制的实施和学生的个性化培养有重要意义.对存在的问题提出具体的建议,为今后加强网络示范课程的建设和应用提供参考.%This article surveys the characteristic of network model curriculum of Xinxiang Medical College. By qustionnaires we discovery that the network model curriculum of students' learning centre has three-level teaching design, it meets the students' self-learning and assistant classroom teaching and has important sense for implementation of credit system and flexible schooling and personalized training for students. It puts forword concrete proposals for the existing problems to provide a reference for the future to strengthen the construction and application of the network model curriculum.

  18. Energy Management Curriculum Starter Kit

    Energy Technology Data Exchange (ETDEWEB)

    Turner, W.C.

    1987-02-01

    The Energy Management Curriculum Starter Kit was designed to help engineering educators develop and teach energy management courses. Montana State University and Oklahoma State University courses are embodied in the model curriculum given. The curricula offered at many other universities throughout the United States are also presented. The kit was designed specifically to train engineering students to be good energy managers. Courses at both the undergraduate and postgraduate level are presented.

  19. Ignition and Flame Stabilization of a Strut-Jet RBCC Combustor with Small Rocket Exhaust

    OpenAIRE

    Jichao Hu; Juntao Chang; Wen Bao

    2014-01-01

    A Rocket Based Combined Cycle combustor model is tested at a ground direct connected rig to investigate the flame holding characteristics with a small rocket exhaust using liquid kerosene. The total temperature and the Mach number of the vitiated air flow, at exit of the nozzle are 1505 K and 2.6, respectively. The rocket base is embedded in a fuel injecting strut and mounted in the center of the combustor. The wall of the combustor is flush, without any reward step or cavity, so the strut-je...

  20. Envisioning Curriculum as Six Simultaneities

    Science.gov (United States)

    Hussain, Hanin; Conner, Lindsey; Mayo, Elaine

    2014-01-01

    This paper uses the discourse of complexity thinking to envision curriculum as six partial and coupled facets that exist simultaneously: curriculum as structure, curriculum as process, curriculum as content, curriculum as teaching, curriculum as learning and curriculum as activity. Such a curriculum is emergent and self-organising. It is emergent…

  1. Characterization of abandoned rocket body families for active removal

    Science.gov (United States)

    Pardini, Carmen; Anselmo, Luciano

    2016-09-01

    A new ranking index was developed and applied to a wide set of rocket body families, characterized by stage dry masses greater than 500 kg and by the presence of at least 5 stages abandoned in LEO. The upper stages selected accounted for more than 80% of the unclassified rocket bodies in LEO and nearly 95% of the associated dry mass. The detailed results obtained for 657 objects clearly identified the most critical altitude-inclination bands and stage models, to be targeted first if and when a debris remediation strategy including the active removal of intact abandoned objects were deemed necessary. Apart from the evaluation of the criticality regarding the long-term evolution of the debris environment, resulting in a priority listing for optimal active removal, the application of the new ranking index is not limited to debris remediation. In fact, if applied before launch to spacecraft and rocket bodies to be disposed in orbit, at the end of mission, it would provide an additional debris mitigation analysis tool for evaluating competing disposal options. Concerning the rocket bodies abandoned in LEO, 274 resulted to have a criticality equal or larger than the average intact object abandoned in an 800 km sun-synchronous orbit. Among them, 243 belonged to the Russian Federation and Ukraine, 25 to China, 5 to Europe and 1 to Japan. In addition to being concentrated in relatively few and narrow altitude-inclinations bands, the most numerous rocket body families often present a quite uniform distribution in right ascension of the ascending node, which is especially convenient for multiple target removal missions.

  2. Heterogeneous fuel for hybrid rocket

    Science.gov (United States)

    Stickler, David B. (Inventor)

    1996-01-01

    Heterogeneous fuel compositions suitable for use in hybrid rocket engines and solid-fuel ramjet engines, The compositions include mixtures of a continuous phase, which forms a solid matrix, and a dispersed phase permanently distributed therein. The dispersed phase or the matrix vaporizes (or melts) and disperses into the gas flow much more rapidly than the other, creating depressions, voids and bumps within and on the surface of the remaining bulk material that continuously roughen its surface, This effect substantially enhances heat transfer from the combusting gas flow to the fuel surface, producing a correspondingly high burning rate, The dispersed phase may include solid particles, entrained liquid droplets, or gas-phase voids having dimensions roughly similar to the displacement scale height of the gas-flow boundary layer generated during combustion.

  3. Combustion oscillation study in a kerosene fueled rocket-based combined-cycle engine combustor

    Science.gov (United States)

    Huang, Zhi-Wei; He, Guo-Qiang; Qin, Fei; Xue, Rui; Wei, Xiang-Geng; Shi, Lei

    2016-12-01

    This study reports the combustion oscillation features in a three-dimensional (3D) rocket-based combined-cycle (RBCC) engine combustor under flight Mach number (Mflight) 3.0 conditions both experimentally and numerically. Experiment is performed on a direct-connect ground test facility, which measures the wall pressure along the flow-path. High-speed imaging of the flame luminosity and schlieren is carried out at exit of the primary rocket. Compressible reactive large eddy simulation (LES) with reduced chemical kinetics of a surrogate model for kerosene is performed to further understand the combustion oscillation mechanisms in the combustor. LES results are validated with experimental data by the time-averaged and root mean square (RMS) pressure values, and show acceptable agreement. Effects of the primary rocket jet on pressure oscillation in the combustor are analyzed. Relation of the high speed rocket jet oscillation, which is thought to among the most probable sources of combustion oscillation, with the RBCC combustor is recognized. Results reveal that the unsteady over-expanded rocket jet has significant impacts on the combustion oscillation feature of the RBCC combustor, which is different from a thermo-acoustics type oscillation. The rocket jet/air inflow physical interactions under different rocket jet expansion degrees are experimentally studied.

  4. Ignition and Flame Stabilization of a Strut-Jet RBCC Combustor with Small Rocket Exhaust

    Directory of Open Access Journals (Sweden)

    Jichao Hu

    2014-01-01

    Full Text Available A Rocket Based Combined Cycle combustor model is tested at a ground direct connected rig to investigate the flame holding characteristics with a small rocket exhaust using liquid kerosene. The total temperature and the Mach number of the vitiated air flow, at exit of the nozzle are 1505 K and 2.6, respectively. The rocket base is embedded in a fuel injecting strut and mounted in the center of the combustor. The wall of the combustor is flush, without any reward step or cavity, so the strut-jet is used to make sure of the flame stabilization of the second combustion. Mass flow rate of the kerosene and oxygen injected into the rocket is set to be a small value, below 10% of the total fuel when the equivalence ratio of the second combustion is 1. The experiment has generated two different kinds of rocket exhaust: fuel rich and pure oxygen. Experiment result has shown that, with a relative small total mass flow rate of the rocket, the fuel rich rocket plume is not suitable for ignition and flame stabilization, while an oxygen plume condition is suitable. Then the paper conducts a series of experiments to investigate the combustion characteristics under this oxygen pilot method and found that the flame stabilization characteristics are different at different combustion modes.

  5. Ignition and flame stabilization of a strut-jet RBCC combustor with small rocket exhaust.

    Science.gov (United States)

    Hu, Jichao; Chang, Juntao; Bao, Wen

    2014-01-01

    A Rocket Based Combined Cycle combustor model is tested at a ground direct connected rig to investigate the flame holding characteristics with a small rocket exhaust using liquid kerosene. The total temperature and the Mach number of the vitiated air flow, at exit of the nozzle are 1505 K and 2.6, respectively. The rocket base is embedded in a fuel injecting strut and mounted in the center of the combustor. The wall of the combustor is flush, without any reward step or cavity, so the strut-jet is used to make sure of the flame stabilization of the second combustion. Mass flow rate of the kerosene and oxygen injected into the rocket is set to be a small value, below 10% of the total fuel when the equivalence ratio of the second combustion is 1. The experiment has generated two different kinds of rocket exhaust: fuel rich and pure oxygen. Experiment result has shown that, with a relative small total mass flow rate of the rocket, the fuel rich rocket plume is not suitable for ignition and flame stabilization, while an oxygen plume condition is suitable. Then the paper conducts a series of experiments to investigate the combustion characteristics under this oxygen pilot method and found that the flame stabilization characteristics are different at different combustion modes.

  6. Competentiegericht curriculum en cursusontwerp

    NARCIS (Netherlands)

    Firssova, Olga; Giesbertz, Wil

    2012-01-01

    Firssova, O., & Giesbertz, W. (2011, 30 mei). Competentiegericht curriculum en cursusontwerp. Presentatie gegeven tijdens de workshop van de BKO cursus Competentiegericht curriculum en cursusontwerp, Eindhoven, Nederland: Open Universiteit.

  7. ¡Cocinar Para Su Salud! Development of a Culturally Based Nutrition Education Curriculum for Hispanic Breast Cancer Survivors Using a Theory-Driven Procedural Model.

    Science.gov (United States)

    Aycinena, Ana Corina; Jennings, Kerri-Ann; Gaffney, Ann Ogden; Koch, Pamela A; Contento, Isobel R; Gonzalez, Monica; Guidon, Ela; Karmally, Wahida; Hershman, Dawn; Greenlee, Heather

    2017-02-01

    We developed a theory-based dietary change curriculum for Hispanic breast cancer survivors with the goal of testing the effects of the intervention on change in dietary intake of fruits/vegetables and fat in a randomized, clinical trial. Social cognitive theory and the transtheoretical model were used as theoretical frameworks to structure curriculum components using the Nutrition Education DESIGN Procedure. Formative assessments were conducted to identify facilitators and barriers common to Hispanic women and test the degree of difficulty and appropriateness of program materials. Focus groups provided valuable insight and informed preimplementation modifications to the dietary program. The result was a systematically planned, evidence-based, culturally tailored dietary intervention for Hispanic breast cancer survivors, ¡Cocinar Para Su Salud! (Cook for Your Health!). The methodology described here may serve as a framework for the development of future dietary interventions among diverse and minority populations. Short- and long-term study results will be reported elsewhere.

  8. A Modular Approach to Teaching Mathematical Modeling in Biotechnology in the Undergraduate Curriculum

    Science.gov (United States)

    Larripa, Kamila R.; Mazzag, Borbala

    2016-01-01

    Our paper describes a solution we found to a still existing need to develop mathematical modeling courses for undergraduate biology majors. Some challenges of such courses are: (i) relatively limited exposure of biology students to higher-level mathematical and computational concepts; (ii) availability of texts that can give a flavor of how…

  9. Faculty Learning Communities: A Model for Supporting Curriculum Changes in Higher Education

    Science.gov (United States)

    Engin, Marion; Atkinson, Fairlie

    2015-01-01

    This article reports on a faculty learning community (FLC) as a professional development model for faculty in an English-medium university in the United Arab Emirates. The authors describe how the introduction of a new learning and teaching technology, in the form of iPads, resulted in many of the faculty feeling unsure about their pedagogy. A…

  10. Coordinated control for regulation/protection mode-switching of ducted rockets

    Science.gov (United States)

    Qi, Yiwen; Bao, Wen; Zhao, Jun; Chang, Juntao

    2014-05-01

    This study is concerned with the coordinated control problem for regulation/protection mode-switching of a ducted rocket, in order to obtain the maximum system performance while ensuring safety. The proposed strategy has an inner/outer loop control structure which decomposes the contradiction between performance and safety into two modes of regulation and protection. Specifically, first, the mathematical model including the actuator (gas regulating system) and the plant (ducted rocket engine) is introduced. Second, taking the inlet buzz for instance, the ducted rocket coordinated control problem for thrust regulation and inlet buzz limit protection is formulated and discussed. Third, to solve the problem, based on the main inner loop, a limit protection controller (outer loop) design method is developed utilizing a linear quadratic optimal control technique, and a coordinated control logic is then presented. At last, the whole coordinated control strategy is applied to the ducted rocket control model, and simulation results demonstrate its effectiveness.

  11. Flutter Analysis of RX-420 Balistic Rocket Fin Involving Rigid Body Modes of Rocket Structures

    Directory of Open Access Journals (Sweden)

    Novi Andria

    2013-03-01

    Full Text Available Flutter is a phenomenon that has brought a catastrophic failure to the flight vehicle structure. In this experiment, flutter was analyzed for its symmetric and antisymmetric configuration to understand the effect of rocket rigid modes to the fin flutter characteristic. This research was also expected to find out the safety level of RX-420 structure design. The analysis was performed using half rocket model. Fin structure used in this research was a fin which has semispan 600 mm, thickness 12 mm, chord root 700 mm, chord tip 400 mm, made by Al 6061-T651, double spar configuration with skin thickness of 2 mm. Structural dynamics and flutter stability were analyzed using finite element software implemented on MSC. Nastran. The analysis shows that the antisymmetric flutter mode is more critical than symmetric flutter mode. At sea level altitude, antisymmetric flutter occurs at 6.4 Mach, and symmetric flutter occurs at 10.15 Mach. Compared to maximum speed of RX-420 which is 4.5 Mach at altitude 11 km or equivalent to 2.1 Mach at sea level, it can be concluded that the RX-420 structure design is safe, and flutter will not occur during flight.

  12. Scaling theory for liquid propellant rocket thrust chambers

    Directory of Open Access Journals (Sweden)

    C. M. Sethna

    1960-04-01

    Full Text Available With the advent of the very large liquid propellant rocket, it has become necessary, if possible, to derive a rational scaling theory for combustion chamber design so as to enable relatively simple and economical initial tests to be carried out on small scaled models using scaled parameters of propellant mass flows, pressure etc., and from these to predict operating and design data for the full scale rocket. Owing to the complex and interdependent nature of the aerothermo-chemical processes in the chamber involving evaporation, diffusion and chemical reaction, the similarity criteria must necessarily extend over several, non-dimensional parameters, but it is still possible to evolve relatively simple rules for correlating the design and performance of the model and large scale motors-as shown by Penner-Tsien and Crocco. The paper concludes with a discussion of the accuracy and practical feasibility of such scaling rules.

  13. Centaur Rocket Installation in PSL #1

    Science.gov (United States)

    1962-01-01

    Centaur Rocket Installation in PSL - Propulsion Systems Laboratory #1. The RL-10 Rocket was developed by Pratt and Whitney in the late 1950's and tested at the Lewis Research Center (now known as the John H. Glenn Research Lewis Field). This power plant was the propulsion system for NASA's upper stage Centaur rocket and was significant for being the first to use liquid hydrogen and oxygen as fuel. The Centaur suffered a number of early failures, but later proved to be a very successful upper stage for numerous commercial, NASA and military payloads.

  14. A model for forensic dental education in the predoctoral dental school curriculum.

    Science.gov (United States)

    Hermsen, Kenneth P; Johnson, J Dane

    2012-05-01

    Forensic odontologists play an important role locally and nationally in assisting in the identification of the victims of mass fatality incidents, whether natural or human-made. With the recent passage of legislation by Congress identifying dentists as a first-responder resource, knowledge of their expanding role in disaster response is particularly important. The purpose of this article is to describe the forensic dental course being taught at Creighton University School of Dentistry in Omaha, Nebraska, as a model for providing a fundamental education in forensic dentistry and disaster preparedness at the predoctoral dental level. This model is designed to 1) provide students with a broad view of forensic odontology; 2) give them a functional knowledge of the tools and techniques of the modern forensic dentist; 3) provide basic knowledge of their potential role in disaster preparedness and response; and 4) encourage students to pursue further forensic education, become active in national forensic organizations, and get involved in disaster preparedness/response in their home communities following graduation. This article includes lecture topics, demonstrations, and hands-on exercises being used at Creighton to teach students the fundamentals of forensic odontology and disaster preparedness.

  15. 国外学前课程模式对我国学前课程设置的启示--以瑞吉欧课程模式和 high scope 课程模式为例%The inspiration of Overseas Preschool Curriculum Model to Chinese Preschool Curriculum Arrangement

    Institute of Scientific and Technical Information of China (English)

    赵菲菲

    2014-01-01

    In recent decades , there are many achievements in the preschool education curriculum models in terms of its theory and practice , some good models are adopted all over the world .Reggio model from Italy and the High Scope model from USA have become a big concern of preschool education curriculum theorists and practitioners .Being the most popular curriculum models , Reg-gio and high scope curriculum models have both similarities and differences in the theoretical background , children perspective , en-vironmental settings, curriculum and teaching, teacher’s role.This essay is to seek the appropriate curriculum models for us by an-alyzing the similarities and differences of the above two models .%近几十年来,国外许多学前教育课程模式在理论和实践上都取得了一定的成就,一些优秀的课程模式在世界范围内得到推广,其中意大利的瑞吉欧课程模式和美国的 high scope课程模式引起了学前教育课程理论与实践者的高度关注。作为两种最受欢迎的课程模式,瑞吉欧课程模式和high scope课程模式在理论背景、儿童观、环境设置、课程与教学、教师角色等方面有许多异同之处,可以从两种课程模式的异同中寻求适合于我国学前课程的课程模式。

  16. Thrust Vector Control for Nuclear Thermal Rockets

    Science.gov (United States)

    Ensworth, Clinton B. F.

    2013-01-01

    Future space missions may use Nuclear Thermal Rocket (NTR) stages for human and cargo missions to Mars and other destinations. The vehicles are likely to require engine thrust vector control (TVC) to maintain desired flight trajectories. This paper explores requirements and concepts for TVC systems for representative NTR missions. Requirements for TVC systems were derived using 6 degree-of-freedom models of NTR vehicles. Various flight scenarios were evaluated to determine vehicle attitude control needs and to determine the applicability of TVC. Outputs from the models yielded key characteristics including engine gimbal angles, gimbal rates and gimbal actuator power. Additional factors such as engine thrust variability and engine thrust alignment errors were examined for impacts to gimbal requirements. Various technologies are surveyed for TVC systems for the NTR applications. A key factor in technology selection is the unique radiation environment present in NTR stages. Other considerations including mission duration and thermal environments influence the selection of optimal TVC technologies. Candidate technologies are compared to see which technologies, or combinations of technologies best fit the requirements for selected NTR missions. Representative TVC systems are proposed and key properties such as mass and power requirements are defined. The outputs from this effort can be used to refine NTR system sizing models, providing higher fidelity definition for TVC systems for future studies.

  17. Early Spin-Stabilised Rockets - the Rockets of Bergrat Heinrich Gottlob Kuhn

    Science.gov (United States)

    Fricke, H.-D.

    19th century's war rockets were at first stabilised by sticks, but these sticks produced a very uncertain flight path and it often happened that rockets changed their direction and even flew back to their firing position. So very many early inventors in Europe, America, and British-India tried to stabilise the rocket's flight in a better way. They tried fins and even rotation but they did not succeed. It is said in history that William Hale was the first who succeeded in constructing a spin stabilised (i.e. rotating) rocket which worked. But before him, in the thirties of that century, a German amateur rocket inventor succeeded as well and secretly proved his stickless rotating rockets in trials for Prussian officers and some years later officially for Saxon artillery officers. His invention was then bought by the kingdom of Saxony, but these were never use in the field because of lack of money.

  18. Medical imaging education in biomedical engineering curriculum: courseware development and application through a hybrid teaching model.

    Science.gov (United States)

    Zhao, Weizhao; Li, Xiping; Chen, Hairong; Manns, Fabrice

    2012-01-01

    Medical Imaging is a key training component in Biomedical Engineering programs. Medical imaging education is interdisciplinary training, involving physics, mathematics, chemistry, electrical engineering, computer engineering, and applications in biology and medicine. Seeking an efficient teaching method for instructors and an effective learning environment for students has long been a goal for medical imaging education. By the support of NSF grants, we developed the medical imaging teaching software (MITS) and associated dynamic assessment tracking system (DATS). The MITS/DATS system has been applied to junior and senior medical imaging classes through a hybrid teaching model. The results show that student's learning gain improved, particularly in concept understanding and simulation project completion. The results also indicate disparities in subjective perception between junior and senior classes. Three institutions are collaborating to expand the courseware system and plan to apply it to different class settings.

  19. A Study of Classics-Reading Curriculum, Classics-Reading Promotion, and Classics-Reading Effect Modeling Exploration in Elementary Schools

    Directory of Open Access Journals (Sweden)

    Chuen-An Tang

    2014-01-01

    Full Text Available The purposes of this study are to test reliabilities and validities of classics-reading curriculum (CRC scale, classics-reading promotion (CRP scale, and classics-reading effect (CRE scale and to examine the relationships between CRC, CRP, and CRE in elementary schools through applying CORPS framework. The pilot sample and formal sample contain 141 and 500 participants from elementary school faculties and classics-reading volunteers in the north, central, south, and east regions of Taiwan. The findings indicate that Cronbach α coefficients of curriculum cognition (CC, curriculum teaching (CT, inside-school promotion (IP, outside-school promotion (EP, learning effect (LE, and class management effect (CME subscales are .88, .85, .93, .91, .91, .94, respectively, through exploratory factor analysis and they have good internal reliabilities and construct validities, respectively, through confirmatory factor analysis. Moreover, CC, CT, IP, and EP have positive influences on LE (standardized coefficients .34, .25, .14, and .22 and on CME (standardized coefficients .41, .14, .14, and .20, respectively. CC, CT, IP, and EP can explain 69% of LE and 61% of CME. The model is supported by the data. Lastly, this study proposes some suggestions regarding the classics-reading education for elementary schools.

  20. Hydrocarbon Rocket Technology Impact Forecasting

    Science.gov (United States)

    Stuber, Eric; Prasadh, Nishant; Edwards, Stephen; Mavris, Dimitri N.

    2012-01-01

    Forecasting method is a normative forecasting technique that allows the designer to quantify the effects of adding new technologies on a given design. This method can be used to assess and identify the necessary technological improvements needed to close the gap that exists between the current design and one that satisfies all constraints imposed on the design. The TIF methodology allows for more design knowledge to be brought to the earlier phases of the design process, making use of tools such as Quality Function Deployments, Morphological Matrices, Response Surface Methodology, and Monte Carlo Simulations.2 This increased knowledge allows for more informed decisions to be made earlier in the design process, resulting in shortened design cycle time. This paper will investigate applying the TIF method, which has been widely used in aircraft applications, to the conceptual design of a hydrocarbon rocket engine. In order to reinstate a manned presence in space, the U.S. must develop an affordable and sustainable launch capability. Hydrocarbon-fueled rockets have drawn interest from numerous major government and commercial entities because they offer a low-cost heavy-lift option that would allow for frequent launches1. However, the development of effective new hydrocarbon rockets would likely require new technologies in order to overcome certain design constraints. The use of advanced design methods, such as the TIF method, enables the designer to identify key areas in need of improvement, allowing one to dial in a proposed technology and assess its impact on the system. Through analyses such as this one, a conceptual design for a hydrocarbon-fueled vehicle that meets all imposed requirements can be achieved.

  1. 21 CFR 866.4830 - Rocket immunoelectro-phoresis equipment.

    Science.gov (United States)

    2010-04-01

    ... 21 Food and Drugs 8 2010-04-01 2010-04-01 false Rocket immunoelectro-phoresis equipment. 866.4830... § 866.4830 Rocket immunoelectro-phoresis equipment. (a) Identification. Rocket immunoelectrophoresis... called rocket immunoelectrophoresis. In this procedure, an electric current causes the protein...

  2. Personal health records in the preclinical medical curriculum: modeling student responses in a simple educational environment utilizing Google Health

    Directory of Open Access Journals (Sweden)

    Karamanlis Dimokratis A

    2012-09-01

    Full Text Available Abstract Background Various problems concerning the introduction of personal health records in everyday healthcare practice are reported to be associated with physicians’ unfamiliarity with systematic means of electronically collecting health information about their patients (e.g. electronic health records - EHRs. Such barriers may further prevent the role physicians have in their patient encounters and the influence they can have in accelerating and diffusing personal health records (PHRs to the patient community. One way to address these problems is through medical education on PHRs in the context of EHR activities within the undergraduate medical curriculum and the medical informatics courses in specific. In this paper, the development of an educational PHR activity based on Google Health is reported. Moreover, student responses on PHR’s use and utility are collected and presented. The collected responses are then modelled to relate the satisfaction level of students in such a setting to the estimation about their attitude towards PHRs in the future. Methods The study was conducted by designing an educational scenario about PHRs, which consisted of student instruction on Google Health as a model PHR and followed the guidelines of a protocol that was constructed for this purpose. This scenario was applied to a sample of 338 first-year undergraduate medical students. A questionnaire was distributed to each one of them in order to obtain Likert-like scale data on the sample’s response with respect to the PHR that was used; the data were then further analysed descriptively and in terms of a regression analysis to model hypothesised correlations. Results Students displayed, in general, satisfaction about the core PHR functions they used and they were optimistic about using them in the future, as they evaluated quite high up the level of their utility. The aspect they valued most in the PHR was its main role as a record-keeping tool, while

  3. Development of Kabila rocket: A radioisotope heated thermionic plasma rocket engine

    OpenAIRE

    2015-01-01

    A new type of plasma rocket engine, the Kabila rocket, using a radioisotope heated thermionic heating chamber instead of a conventional combustion chamber or catalyst bed is introduced and it achieves specific impulses similar to the ones of conventional solid and bipropellant rockets. Curium-244 is chosen as a radioisotope heat source and a thermal reductive layer is also used to obtain precise thermionic emissions. The self-sufficiency principle is applied by simultaneously heating up the e...

  4. High-speed schlieren imaging of rocket exhaust plumes

    Science.gov (United States)

    Coultas-McKenney, Caralyn; Winter, Kyle; Hargather, Michael

    2016-11-01

    Experiments are conducted to examine the exhaust of a variety of rocket engines. The rocket engines are mounted in a schlieren system to allow high-speed imaging of the engine exhaust during startup, steady state, and shutdown. A variety of rocket engines are explored including a research-scale liquid rocket engine, consumer/amateur solid rocket motors, and water bottle rockets. Comparisons of the exhaust characteristics, thrust and cost for this range of rockets is presented. The variety of nozzle designs, target functions, and propellant type provides unique variations in the schlieren imaging.

  5. Effects of turbulent and spray models on combustion process simultion of LOX/GH2 rocket engine%湍流、喷雾模型对氢氧火箭发动机燃烧仿真的影响

    Institute of Scientific and Technical Information of China (English)

    程钰锋; 聂万胜; 丰松江

    2011-01-01

    Based on the improved PISO algorithm, the numerical simulation for the combustion instability of a LOX/GH2 rocket engine was conducted by changing the turbulent and spay models of κ-ε equations. The compared results of the theoretical analysis and numerical simulation show that in the two-dimensional situation, both droplet collision model and TAB droplet breakup model are not suitable for the numerical simulation of LOX/GH2 combustion instability; the pressure oscillation in the combustion chamber can be simulated by combining the TVB droplet breakup model with the turbulent models of κ-ε equations, but the oscillation frequency can not be simulated; if the turbulent models of Realizable κ-ε equations are adopted without consideration of the droplet spray models, both the pressure oscillation in the combustion chamber and the distribution of the oscillation frequency can be simulated.%基于完善的压力隐式算子分裂(PISO)算法,通过改变κ-ε两方程湍流模型和喷雾模型,对氢氧火箭发动机不稳定燃烧进行数值仿真。比较理论分析和数值仿真的结果得出,在二维情况下,液滴碰撞模型和TAB液滴破碎模型不适于模拟氢氧火箭发动机不稳定燃烧;TVB液滴破碎模型与κ-ε两方程湍流模型的组合情况能够捕捉到燃烧室中的压力振荡,但不能体现出振荡频率;而采用Realizableκ-ε湍流模型不考虑液滴雾化模型时不但能够捕捉燃烧室内压力振荡情况,还能够很好地得出振荡频率的分布情况。

  6. Curriculum Mapping. Focus On

    Science.gov (United States)

    Molineaux, Rebecca

    2008-01-01

    This "Focus On" discusses curriculum mapping, a process that allows educators to align the curriculum both within and across grades and to ensure that the curriculum is in line with school, local, and state standards. It outlines the steps of the curriculum mapping process from planning the mapping initiative to creating and editing curriculum…

  7. Hydroxyl Tagging Velocimetry for Rocket Plumes Project

    Data.gov (United States)

    National Aeronautics and Space Administration — A non-intrusive method for measuring velocities in a rocket exhaust is proposed in a joint effort by MetroLaser and Vanderbilt University. Hydroxyl Tagging...

  8. Fundamentals of aircraft and rocket propulsion

    CERN Document Server

    El-Sayed, Ahmed F

    2016-01-01

    This book provides a comprehensive basics-to-advanced course in an aero-thermal science vital to the design of engines for either type of craft. The text classifies engines powering aircraft and single/multi-stage rockets, and derives performance parameters for both from basic aerodynamics and thermodynamics laws. Each type of engine is analyzed for optimum performance goals, and mission-appropriate engines selection is explained. Fundamentals of Aircraft and Rocket Propulsion provides information about and analyses of: thermodynamic cycles of shaft engines (piston, turboprop, turboshaft and propfan); jet engines (pulsejet, pulse detonation engine, ramjet, scramjet, turbojet and turbofan); chemical and non-chemical rocket engines; conceptual design of modular rocket engines (combustor, nozzle and turbopumps); and conceptual design of different modules of aero-engines in their design and off-design state. Aimed at graduate and final-year undergraduate students, this textbook provides a thorough grounding in th...

  9. Magnesium Based Rockets for Martian Exploration Project

    Data.gov (United States)

    National Aeronautics and Space Administration — In the proposed Phase II program, we will continue the development of Mg bipropellant rockets for Martian PAV applications. In Phase I, we proved the feasibility of...

  10. Magnesium Based Rockets for Martian Exploration Project

    Data.gov (United States)

    National Aeronautics and Space Administration — We propose to develop Mg rockets for Martian ascent vehicle applications. The propellant can be acquired in-situ from MgO in the Martian regolith (5.1% Mg by mass)...

  11. Advanced Vortex Hybrid Rocket Engine (AVHRE) Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Orbital Technologies Corporation (ORBITEC) proposes to develop a unique Advanced Vortex Hybrid Rocket Engine (AVHRE) to achieve a highly-reliable, low-cost and...

  12. Advanced Vortex Hybrid Rocket Engine (AVHRE) Project

    Data.gov (United States)

    National Aeronautics and Space Administration — ORBITEC proposes to develop a unique Advanced Vortex Hybrid Rocket Engine (AVHRE) to achieve a safe, highly-reliable, low-cost and uniquely versatile propulsion...

  13. Nuclear Thermal Rocket Element Environmental Simulator (NTREES)

    Science.gov (United States)

    Schoenfeld, Michael

    2009-01-01

    A detailed description of the Nuclear Thermal Rocket Element Environmental Simulator (NTREES) is presented. The contents include: 1) Design Requirements; 2) NTREES Layout; 3) Data Acquisition and Control System Schematics; 4) NTREES System Schematic; and 5) NTREES Setup.

  14. Hydroxyl Tagging Velocimetry for Rocket Plumes Project

    Data.gov (United States)

    National Aeronautics and Space Administration — To address the need for non-intrusive sensors for rocket plume properties, we propose a laser-based velocity diagnostic that does not require seeding, works in high...

  15. Electrodynamic actuators for rocket engine valves

    Science.gov (United States)

    Fiet, O.; Doshi, D.

    1972-01-01

    Actuators, employed in acoustic loudspeakers, operate liquid rocket engine valves by replacing light paper cones with flexible metal diaphragms. Comparative analysis indicates better response time than solenoid actuators, and improved service life and reliability.

  16. Manufacturing Advanced Channel Wall Rocket Liners Project

    Data.gov (United States)

    National Aeronautics and Space Administration — This SBIR will adapt and demonstrate a low cost flexible method of manufacturing channel wall liquid rocket nozzles and combustors, while providing developers a...

  17. Collaborative Sounding Rocket launch in Alaska and Development of Hybrid Rockets

    Science.gov (United States)

    Ono, Tomohisa; Tsutsumi, Akimasa; Ito, Toshiyuki; Kan, Yuji; Tohyama, Fumio; Nakashino, Kyouichi; Hawkins, Joseph

    Tokai University student rocket project (TSRP) was established in 1995 for a purpose of the space science and engineering hands-on education, consisting of two space programs; the one is sounding rocket experiment collaboration with University of Alaska Fairbanks and the other is development and launch of small hybrid rockets. In January of 2000 and March 2002, two collaborative sounding rockets were successfully launched at Poker Flat Research Range in Alaska. In 2001, the first Tokai hybrid rocket was successfully launched at Alaska. After that, 11 hybrid rockets were launched to the level of 180-1,000 m high at Hokkaido and Akita in Japan. Currently, Tokai students design and build all parts of the rockets. In addition, they are running the organization and development of the project under the tight budget control. This program has proven to be very effective in providing students with practical, real-engineering design experience and this program also allows students to participate in all phases of a sounding rocket mission. Also students learn scientific, engineering subjects, public affairs and system management through experiences of cooperative teamwork. In this report, we summarize the TSRP's hybrid rocket program and discuss the effectiveness of the program in terms of educational aspects.

  18. Estimation of Initial Disturbances for Rockets Based on Interactions of Rockets and Directional Tubes

    Institute of Scientific and Technical Information of China (English)

    2006-01-01

    In the range of the rockets/launcher system itself, the dynamic equations for rocket and directional tube during semi-constraint period have been constructed by using Newton-Euler method. Considering the interaction of rockets and directional tubes when clearances exist, the method of estimating initial disturbances for the rocket by using vibration data of the directional tube has been given. The estimated results have been compared with the simulation results computed by the dynamic simulating software ADAMS. Results computed by the two methods are basically consistent and the computing errors do not increase with the variation of the clearance. The validity of the proposed method has been proved.

  19. What to Consider When Preparing a Model Core Curriculum for GIS Ethics: Objectives, Methods, and a Sketch of Content

    Science.gov (United States)

    Davis, Michael

    2014-01-01

    The purpose of this article is to provide a summary of what is known about teaching ethics in engineering, science, and related disciplines. Such a summary should provide a useful starting point for preparation of a detailed curriculum for teaching the ethics of geo-coded information systems broadly understood ("GIS ethics" for short).…

  20. Service Learning and the Core Curriculum: Two Models for Doing Theology as Service Learning in the Core

    Science.gov (United States)

    McMahon, Christopher

    2014-01-01

    In principle, theology ought to play a decisive role in the mission and identity of Catholic colleges and universities, but theology's role often comes under fire from students and other constituencies who consider theology an uncritical intrusion into the curriculum or a holdover from a bygone era. This essay reflects on the role of theology…

  1. Model Wind Turbine Design in a Project-Based Middle School Engineering Curriculum Built on State Frameworks

    Science.gov (United States)

    Cogger, Steven D.; Miley, Daniel H.

    2012-01-01

    This paper proposes that project-based active learning is a key part of engineering education at the middle school level. One project from a comprehensive middle school engineering curriculum developed by the authors is described to show how active learning and state frameworks can coexist. The theoretical basis for learning and assessment in a…

  2. A "Resident-as-Teacher" Curriculum Using a Flipped Classroom Approach: Can a Model Designed for Efficiency Also Be Effective?

    Science.gov (United States)

    Chokshi, Binny D; Schumacher, Heidi K; Reese, Kristen; Bhansali, Priti; Kern, Jeremy R; Simmens, Samuel J; Blatt, Benjamin; Greenberg, Larrie W

    2017-04-01

    The Accreditation Council for Graduate Medical Education requires training that enhances resident teaching skills. Despite this requirement, many residency training programs struggle to implement effective resident-as-teacher (RAT) curricula, particularly within the context of the 80-hour resident workweek. In 2013, the authors developed and evaluated an intensive one-day RAT curriculum using a flipped classroom approach. Twenty-nine second-year residents participated in daylong RAT sessions. The curriculum included four 1-hour workshops focusing on adult learning principles, giving feedback, teaching a skill, and orienting a learner. Each workshop, preceded by independent reading, featured peer co-teaching, application, and feedback. The authors evaluated the curriculum using pre- and postworkshop objective structured teaching examinations (OSTEs) and attitudinal and self-efficacy teaching questionnaires. Residents demonstrated statistically significant improvements in performance between pre- and postworkshop OSTEs on each of three core skills: giving feedback (P = .005), orienting a learner (P classroom approach is an efficient and effective method for training residents to improve teaching skills, especially in an era of work hour restrictions. They have committed to the continuation of this curriculum and are planning to include assessment of its long-term effects on resident behavior change and educational outcomes.

  3. Spatial Visualization Research and Theories: Their Importance in the Development of an Engineering and Technical Design Graphics Curriculum Model.

    Science.gov (United States)

    Miller, Craig L.; Bertoline, Gary R.

    1991-01-01

    An overview that gives an introduction to the theories, terms, concepts, and prior research conducted on visualization is presented. This information is to be used as a basis for developing spatial research studies that lend support to the theory that the engineering and technical design graphics curriculum is important in the development of…

  4. Student Gains in Self-Efficacy in an Advanced MSW Curriculum: A Customized Model for Outcomes Assessment

    Science.gov (United States)

    Rishel, Carrie W.; Majewski, Virginia

    2009-01-01

    The new Educational Policy and Accreditation Standards (EPAS) identify assessment as "an integral component of competency-based education." It is not new, however, that programs must demonstrate plans to assess attainment of competencies or expected program outcomes and show how data collection and analysis inform curriculum decisions. Previous…

  5. Chemistry, Life, the Universe, and Everything: A New Approach to General Chemistry, and a Model for Curriculum Reform

    Science.gov (United States)

    Cooper, Melanie; Klymkowsky, Michael

    2013-01-01

    The history of general chemistry is one of almost constant calls for reform, yet over the past 60 years little of substance has changed. Those reforms that have been implemented are almost entirely concerned with how the course is taught, rather than what is to be learned. Here we briefly discuss the history of the general chemistry curriculum and…

  6. Chemistry, Life, the Universe, and Everything: A New Approach to General Chemistry, and a Model for Curriculum Reform

    Science.gov (United States)

    Cooper, Melanie; Klymkowsky, Michael

    2013-01-01

    The history of general chemistry is one of almost constant calls for reform, yet over the past 60 years little of substance has changed. Those reforms that have been implemented are almost entirely concerned with how the course is taught, rather than what is to be learned. Here we briefly discuss the history of the general chemistry curriculum and…

  7. Influence of determination of reference position of image on rocket take-off drift

    Science.gov (United States)

    Cui, Shuhua; Liu, Jun; Shen, Si; Hu, Shaolin

    2016-01-01

    Mathematical analysis model for influence of reference position deviation on carrier rocket take-off drift has been made to tackle the issue on determination of reference position of reticule for optical tracking and measurement of video image in aerospace test range and the variation in rocket take-off drift due to reference position deviation has been subjected to quantitative analysis based on angular error of tracking and lateral error of measuring point as a result of deviation of reference position of reticule cross. The method serves as technical support to quality analysis of rocket take-off deviation measurement data and improvement in data processing precision for carrier rocket take-off drift.

  8. Rocket injector anomalies study. Volume 2: Results of parametric studies

    Science.gov (United States)

    Przekwas, A. J.; Singhal, A. K.; Tam, L. T.

    1984-01-01

    The employment of a existing computer program to simulate three dimensional two phase gas spray flows in liquid propellant rocket engines. This was accomplished by modification of an existing three dimensional computer program (REFLAN3D) with Euler/Lagrange approach for simulating two phase spray flow, evaporation and combustion. The modified code is referred to as REFLAN3D-SPRAY. Computational studies of the model rocket engine combustion chamber are presented. The parametric studies of the two phase flow and combustion shows qualitatively correct response for variations in geometrical and physical parameters. The injection nonuniformity test with blocked central fuel injector holes shows significant changes in the central flame core and minor influence on the wall heat transfer fluxes.

  9. Characteristics of response factors of coaxial gaseous rocket injectors

    Science.gov (United States)

    Janardan, B. A.; Daniel, B. R.; Zinn, B. T.

    1975-01-01

    The results of an experimental investigation undertaken to determine the frequency dependence of the response factors of various gaseous propellant rocket injectors subject to axial instabilities are presented. The injector response factors were determined, using the modified impedance-tube technique, under cold-flow conditions simulating those observed in unstable rocket motors. The tested injectors included a gaseous-fuel injector element, a gaseous-oxidizer injector element and a coaxial injector with both fuel and oxidizer elements. Emphasis was given to the determination of the dependence of the injector response factor upon the open-area ratio of the injector, the length of the injector orifice, and the pressure drop across the injector orifices. The measured data are shown to be in reasonable agreement with the corresponding injector response factor data predicted by the Feiler and Heidmann model.

  10. Stability of Rocket Flight during Burning

    Directory of Open Access Journals (Sweden)

    T. N. Srivastava

    1967-10-01

    Full Text Available Stability of the rocket motion during burning is discussed taking into consideration gravity, aerodynamic forces and torques. Conditions for stabilizing the rocket motion are investigated. Analysis for initial and final phases of burning is given separately. Stability regions of the projected motions on two dimensional co-ordinate planes are obtained and thereby stability region of the actual motion is derived. Stability diagrams illustrate statically and dynamically stable and unstable regions.

  11. Rocket Rendezvous at Preassigned Destinations with Optimum

    Directory of Open Access Journals (Sweden)

    T. N. Srivastava

    1982-10-01

    Full Text Available The problem of rendezvous of an interceptor rocket vehicle through optimal exit path with a destination rocket vehicle at a preassigned location on the destination orbit has been investigated for non-coaxial coplanar elliptic launch and destination orbits in an inverse square gravitational field. The case, when launch and destination orbits are coplanar circular, is also discussed. In the end numerical results for rendezvous have been obtained taking Earth and Mars orbits as launch and destination orbits respectively.

  12. Improving Education in Medical Statistics: Implementing a Blended Learning Model in the Existing Curriculum.

    Directory of Open Access Journals (Sweden)

    Natasa M Milic

    Full Text Available Although recent studies report on the benefits of blended learning in improving medical student education, there is still no empirical evidence on the relative effectiveness of blended over traditional learning approaches in medical statistics. We implemented blended along with on-site (i.e. face-to-face learning to further assess the potential value of web-based learning in medical statistics.This was a prospective study conducted with third year medical undergraduate students attending the Faculty of Medicine, University of Belgrade, who passed (440 of 545 the final exam of the obligatory introductory statistics course during 2013-14. Student statistics achievements were stratified based on the two methods of education delivery: blended learning and on-site learning. Blended learning included a combination of face-to-face and distance learning methodologies integrated into a single course.Mean exam scores for the blended learning student group were higher than for the on-site student group for both final statistics score (89.36±6.60 vs. 86.06±8.48; p = 0.001 and knowledge test score (7.88±1.30 vs. 7.51±1.36; p = 0.023 with a medium effect size. There were no differences in sex or study duration between the groups. Current grade point average (GPA was higher in the blended group. In a multivariable regression model, current GPA and knowledge test scores were associated with the final statistics score after adjusting for study duration and learning modality (p<0.001.This study provides empirical evidence to support educator decisions to implement different learning environments for teaching medical statistics to undergraduate medical students. Blended and on-site training formats led to similar knowledge acquisition; however, students with higher GPA preferred the technology assisted learning format. Implementation of blended learning approaches can be considered an attractive, cost-effective, and efficient alternative to traditional

  13. Stochastic rocket dynamics under random nozzle side loads: Ornstein-Uhlenbeck boundary layer separation and its coarse grained connection to side loading and rocket response

    CERN Document Server

    Keanini, R G; Tkacik, Peter T; Weggel, David C; Knight, P Douglas

    2011-01-01

    A long-standing, though ill-understood problem in rocket dynamics, rocket response to random, altitude-dependent nozzle side-loads, is investigated. Side loads arise during low altitude flight due to random, asymmetric, shock-induced separation of in-nozzle boundary layers. In this paper, stochastic evolution of the in-nozzle boundary layer separation line, an essential feature underlying side load generation, is connected to random, altitude-dependent rotational and translational rocket response via a set of simple analytical models. Separation line motion, extant on a fast boundary layer time scale, is modeled as an Ornstein-Uhlenbeck process. Pitch and yaw responses, taking place on a long, rocket dynamics time scale, are shown to likewise evolve as OU processes. Stochastic, altitude-dependent rocket translational motion follows from linear, asymptotic versions of the full nonlinear equations of motion; the model is valid in the practical limit where random pitch, yaw, and roll rates all remain small. Comp...

  14. 3-D thermal analysis using finite difference technique with finite element model for improved design of components of rocket engine turbomachines for Space Shuttle Main Engine SSME

    Science.gov (United States)

    Sohn, Kiho D.; Ip, Shek-Se P.

    1988-01-01

    Three-dimensional finite element models were generated and transferred into three-dimensional finite difference models to perform transient thermal analyses for the SSME high pressure fuel turbopump's first stage nozzles and rotor blades. STANCOOL was chosen to calculate the heat transfer characteristics (HTCs) around the airfoils, and endwall effects were included at the intersections of the airfoils and platforms for the steady-state boundary conditions. Free and forced convection due to rotation effects were also considered in hollow cores. Transient HTCs were calculated by taking ratios of the steady-state values based on the flow rates and fluid properties calculated at each time slice. Results are presented for both transient plots and three-dimensional color contour isotherm plots; they were also converted into universal files to be used for FEM stress analyses.

  15. 3-D thermal analysis using finite difference technique with finite element model for improved design of components of rocket engine turbomachines for Space Shuttle Main Engine SSME

    Science.gov (United States)

    Sohn, Kiho D.; Ip, Shek-Se P.

    1988-01-01

    Three-dimensional finite element models were generated and transferred into three-dimensional finite difference models to perform transient thermal analyses for the SSME high pressure fuel turbopump's first stage nozzles and rotor blades. STANCOOL was chosen to calculate the heat transfer characteristics (HTCs) around the airfoils, and endwall effects were included at the intersections of the airfoils and platforms for the steady-state boundary conditions. Free and forced convection due to rotation effects were also considered in hollow cores. Transient HTCs were calculated by taking ratios of the steady-state values based on the flow rates and fluid properties calculated at each time slice. Results are presented for both transient plots and three-dimensional color contour isotherm plots; they were also converted into universal files to be used for FEM stress analyses.

  16. Wind Tunnel Tests on Aerodynamic Characteristics of Advanced Solid Rocket

    Science.gov (United States)

    Kitamura, Keiichi; Fujimoto, Keiichiro; Nonaka, Satoshi; Irikado, Tomoko; Fukuzoe, Moriyasu; Shima, Eiji

    The Advanced Solid Rocket is being developed by JAXA (Japan Aerospace Exploration Agency). Since its configuration has been changed very recently, its aerodynamic characteristics are of great interest of the JAXA Advanced Solid Rocket Team. In this study, we carried out wind tunnel tests on the aerodynamic characteristics of the present configuration for Mach 1.5. Six test cases were conducted with different body configurations, attack angles, and roll angles. A six component balance, oilflow visualization, Schlieren images were used throughout the experiments. It was found that, at zero angle-of-attack, the flow around the body were perturbed and its drag (axial force) characteristics were significantly influenced by protruding body components such as flanges, cable ducts, and attitude control units of SMSJ (Solid Motor Side Jet), while the nozzle had a minor role. With angle-of-attack of five degree, normal force of CNα = 3.50±0.03 was measured along with complex flow features observed in the full-component model; whereas no crossflow separations were induced around the no-protuberance model with CNα = 2.58±0.10. These values were almost constant with respect to the angle-of-attack in both of the cases. Furthermore, presence of roll angle made the flow more complicated, involving interactions of separation vortices. These data provide us with fundamental and important aerodynamic insights of the Advanced Solid Rocket, and they will be utilized as reference data for the corresponding numerical analysis.

  17. Robust lateral pulse jet control of an atmospheric rocket

    Science.gov (United States)

    Burchett, Bradley Thomas

    Uncontrolled direct fire rockets exhibit high impact point dispersion, even at relatively short range, and as such have been employed as area weapons on the battlefield. In order to reduce the dispersion of a direct fire rocket, feedback control is employed to fire short-duration solid rocket pulses mounted near the nose of the projectile and acting perpendicular to the projectile axis of symmetry. The feedback law is developed by first determining a piece wise linear model of the projectile swerving motion, subsequently using this linear model to predict the projectile impact point both with and without control, and using the results to command pulses at appropriate times to drive the impact point closer to the specified target. Candidate optimal control laws are formed using rules based on decision grids, and a global control strategy search algorithm. The global search control law proves to be prohibitively computationally expensive for on-line implementation. The performance of the baseline control law is found to be comparable to the rule based and global search optimal control laws. The control gains of the baseline control law are optimized in the presence of parametric plant uncertainty using a Monte Carlo simulation. Performance of the system in the presence of parametric plant uncertainty using the optimized gains is deemed comparable to performance of the baseline controller with no plant uncertainty. The level of uncertainty of several plant parameters is varied in order to compare robustness of the controller when optimized with uncertainty viz. without uncertainty.

  18. Solid Rocket Motor Design Using Hybrid Optimization

    Directory of Open Access Journals (Sweden)

    Kevin Albarado

    2012-01-01

    Full Text Available A particle swarm/pattern search hybrid optimizer was used to drive a solid rocket motor modeling code to an optimal solution. The solid motor code models tapered motor geometries using analytical burn back methods by slicing the grain into thin sections along the axial direction. Grains with circular perforated stars, wagon wheels, and dog bones can be considered and multiple tapered sections can be constructed. The hybrid approach to optimization is capable of exploring large areas of the solution space through particle swarming, but is also able to climb “hills” of optimality through gradient based pattern searching. A preliminary method for designing tapered internal geometry as well as tapered outer mold-line geometry is presented. A total of four optimization cases were performed. The first two case studies examines designing motors to match a given regressive-progressive-regressive burn profile. The third case study studies designing a neutrally burning right circular perforated grain (utilizing inner and external geometry tapering. The final case study studies designing a linearly regressive burning profile for right circular perforated (tapered grains.

  19. MHD thrust vectoring of a rocket engine

    Science.gov (United States)

    Labaune, Julien; Packan, Denis; Tholin, Fabien; Chemartin, Laurent; Stillace, Thierry; Masson, Frederic

    2016-09-01

    In this work, the possibility to use MagnetoHydroDynamics (MHD) to vectorize the thrust of a solid propellant rocket engine exhaust is investigated. Using a magnetic field for vectoring offers a mass gain and a reusability advantage compared to standard gimbaled, elastomer-joint systems. Analytical and numerical models were used to evaluate the flow deviation with a 1 Tesla magnetic field inside the nozzle. The fluid flow in the resistive MHD approximation is calculated using the KRONOS code from ONERA, coupling the hypersonic CFD platform CEDRE and the electrical code SATURNE from EDF. A critical parameter of these simulations is the electrical conductivity, which was evaluated using a set of equilibrium calculations with 25 species. Two models were used: local thermodynamic equilibrium and frozen flow. In both cases, chlorine captures a large fraction of free electrons, limiting the electrical conductivity to a value inadequate for thrust vectoring applications. However, when using chlorine-free propergols with 1% in mass of alkali, an MHD thrust vectoring of several degrees was obtained.

  20. Measurements of reactive gaseous rocket injector admittances

    Science.gov (United States)

    Janardan, B. A.; Daniel, B. R.; Bell, W. A.; Zinn, B. T.

    1979-01-01

    The paper describes the results of an experimental study of the quantitative determination of the capabilities of the combustion processes associated with coaxial gaseous propellant rocket injectors to drive combustor pressure oscillations. The data, obtained by employing the modified impedance tube technique with compressed air as the oxidizer and acetylene gas as the fuel, describe the frequency dependence of the admittance of the combined injector-combustion process. The measured data are compared with the predictions of the Feiler and Heidmann analytical model utilizing different values for the characteristic combustion time tau sub b. The values of tau sub b which result in a best fit between the measured and predicted data are indicated for different equivalence ratios. It is shown that for the coaxial injector investigated in this study the tau sub b varies between 0.7 and 1.2 msec for equivalence ratios in the range of 0.57 to 1.31. In addition, the experimental data indicate that the tested injector system could drive combustion instabilities over a frequency range that is in qualitative agreement with the predictions of the Feiler and Heidmann model.

  1. The CODEX sounding rocket payload

    Science.gov (United States)

    Zeiger, B.; Shipley, A.; Cash, W.; Rogers, T.; Schultz, T.; McEntaffer, R.; Kaiser, M.

    2011-05-01

    We present the CODEX sounding rocket payload, a soft x-ray (0.1-1.0 keV) spectrometer designed to observe diffuse high-surface brightness astronomical sources. The payload is composed of two modules, each with a 3.25° x 3.25° field of view defined by a stack of wire grids that block light not coming to a 3.0 m focus and admit only nearly-collimated light onto an array of 67 diffraction gratings in an off-plane mount. After a 2.0 m throw, the spectrum is detected by offset large-format gaseous electron multiplier (GEM) detectors. CODEX will target the Vela supernova remnant later this year to measure the temperature and abundances and to determine the contributions of various soft x-ray emission mechanisms to the remnant's energy budget; resulting spectra will have resolution (E/▵E) ranging from 50 to 100 across the band. CODEX is the third-generation of similar payloads from the University of Colorado, with an increased bandpass, higher throughput, and a more robust mechanical structure than its predecessors.

  2. NASA Space Rocket Logistics Challenges

    Science.gov (United States)

    Neeley, James R.; Jones, James V.; Watson, Michael D.; Bramon, Christopher J.; Inman, Sharon K.; Tuttle, Loraine

    2014-01-01

    The Space Launch System (SLS) is the new NASA heavy lift launch vehicle and is scheduled for its first mission in 2017. The goal of the first mission, which will be uncrewed, is to demonstrate the integrated system performance of the SLS rocket and spacecraft before a crewed flight in 2021. SLS has many of the same logistics challenges as any other large scale program. Common logistics concerns for SLS include integration of discreet programs geographically separated, multiple prime contractors with distinct and different goals, schedule pressures and funding constraints. However, SLS also faces unique challenges. The new program is a confluence of new hardware and heritage, with heritage hardware constituting seventy-five percent of the program. This unique approach to design makes logistics concerns such as commonality especially problematic. Additionally, a very low manifest rate of one flight every four years makes logistics comparatively expensive. That, along with the SLS architecture being developed using a block upgrade evolutionary approach, exacerbates long-range planning for supportability considerations. These common and unique logistics challenges must be clearly identified and tackled to allow SLS to have a successful program. This paper will address the common and unique challenges facing the SLS programs, along with the analysis and decisions the NASA Logistics engineers are making to mitigate the threats posed by each.

  3. Environmentally compatible solid rocket propellants

    Science.gov (United States)

    Jacox, James L.; Bradford, Daniel J.

    1995-01-01

    Hercules' clean propellant development research is exploring three major types of clean propellant: (1) chloride-free formulations (no chlorine containing ingredients), being developed on the Clean Propellant Development and Demonstration (CPDD) contract sponsored by Phillips Laboratory, Edwards Air Force Base, CA; (2) low HCl scavenged formulations (HCl-scavenger added to propellant oxidized with ammonium perchlorate (AP)); and (3) low HCl formulations oxidized with a combination of AN and AP (with or without an HCl scavenger) to provide a significant reduction (relative to current solid rocket boosters) in exhaust HCl. These propellants provide performance approaching that of current systems, with less than 2 percent HCl in the exhaust, a significant reduction (greater than or equal to 70 percent) in exhaust HCl levels. Excellent processing, safety, and mechanical properties were achieved using only readily available, low cost ingredients. Two formulations, a sodium nitrate (NaNO3) scavenged HTPB and a chloride-free hydroxy terminated polyether (HTPE) propellant, were characterized for ballistic, mechanical, and rheological properties. In addition, the hazards properties were demonstrated to provide two families of class 1.3, 'zero-card' propellants. Further characterization is planned which includes demonstration of ballistic tailorability in subscale (one to 70 pound) motors over the range of burn rates required for retrofit into current Hercules space booster designs (Titan 4 SRMU and Delta 2 GEM).

  4. NASA's Advanced solid rocket motor

    Science.gov (United States)

    Mitchell, Royce E.

    The Advanced Solid Rocket Motor (ASRM) will not only bring increased safety, reliability and performance for the Space Shuttle Booster, it will enhance overall Shuttle safety by effectively eliminating 174 failure points in the Space Shuttle Main Engine throttling system and by reducing the exposure time to aborts due to main engine loss or shutdown. In some missions, the vulnerability time to Return-to-Launch Site aborts is halved. The ASRM uses case joints which will close or remain static under the effects of motor ignition and pressurization. The case itself is constructed of the weldable steel alloy HP 9-4-0.30, having very high strength and with superior fracture toughness and stress corrosion resistance. The internal insulation is strip-wound and is free of asbestos. The nozzle employs light weight ablative parts and is some 5,000 pounds lighter than the Shuttle motor used to date. The payload performance of the ASRM-powered Shuttle is 12,000 pounds higher than that provided by the present motor. This is of particular benefit for payloads delivered to higher inclinations and/or altitudes. The ASRM facility uses state-of-the-art manufacturing techniques, including continuous propellant mixing and direct casting.

  5. NASA's Advanced solid rocket motor

    Science.gov (United States)

    Mitchell, Royce E.

    1993-01-01

    The Advanced Solid Rocket Motor (ASRM) will not only bring increased safety, reliability and performance for the Space Shuttle Booster, it will enhance overall Shuttle safety by effectively eliminating 174 failure points in the Space Shuttle Main Engine throttling system and by reducing the exposure time to aborts due to main engine loss or shutdown. In some missions, the vulnerability time to Return-to-Launch Site aborts is halved. The ASRM uses case joints which will close or remain static under the effects of motor ignition and pressurization. The case itself is constructed of the weldable steel alloy HP 9-4-0.30, having very high strength and with superior fracture toughness and stress corrosion resistance. The internal insulation is strip-wound and is free of asbestos. The nozzle employs light weight ablative parts and is some 5,000 pounds lighter than the Shuttle motor used to date. The payload performance of the ASRM-powered Shuttle is 12,000 pounds higher than that provided by the present motor. This is of particular benefit for payloads delivered to higher inclinations and/or altitudes. The ASRM facility uses state-of-the-art manufacturing techniques, including continuous propellant mixing and direct casting.

  6. Nitrous Oxide/Paraffin Hybrid Rocket Engines

    Science.gov (United States)

    Zubrin, Robert; Snyder, Gary

    2010-01-01

    Nitrous oxide/paraffin (N2OP) hybrid rocket engines have been invented as alternatives to other rocket engines especially those that burn granular, rubbery solid fuels consisting largely of hydroxyl- terminated polybutadiene (HTPB). Originally intended for use in launching spacecraft, these engines would also be suitable for terrestrial use in rocket-assisted takeoff of small airplanes. The main novel features of these engines are (1) the use of reinforced paraffin as the fuel and (2) the use of nitrous oxide as the oxidizer. Hybrid (solid-fuel/fluid-oxidizer) rocket engines offer advantages of safety and simplicity over fluid-bipropellant (fluid-fuel/fluid-oxidizer) rocket en - gines, but the thrusts of HTPB-based hybrid rocket engines are limited by the low regression rates of the fuel grains. Paraffin used as a solid fuel has a regression rate about 4 times that of HTPB, but pure paraffin fuel grains soften when heated; hence, paraffin fuel grains can, potentially, slump during firing. In a hybrid engine of the present type, the paraffin is molded into a 3-volume-percent graphite sponge or similar carbon matrix, which supports the paraffin against slumping during firing. In addition, because the carbon matrix material burns along with the paraffin, engine performance is not appreciably degraded by use of the matrix.

  7. Advanced Solid Rocket Launcher and Its Evolution

    Science.gov (United States)

    Morita, Yasuhiro; Imoto, Takayuki; Habu, Hiroto; Ohtsuka, Hirohito; Hori, Keiichi; Koreki, Takemasa; Fukuchi, Apollo; Uekusa, Yasuyuki; Akiba, Ryojiro

    The research on next generation solid propellant rockets is actively underway in various spectra. JAXA is developing the Advanced Solid Rocket (ASR) as a successor to the M-V launch vehicle, which was utilized over past ten years for space science programs including planetary missions. ASR is a result of the development of the next generation technology including a highly intelligent autonomous check-out system, which is connected to not only the solid rocket but also future transportation systems. It is expected to improve the efficiency of the launch system and double the cost performance. Far beyond this effort, the passion of the volunteers among the industry-government-academia cooperation has been united to establish the society of the freewheeling thinking “Next generation Solid Rocket Society (NSRS)”. It aims at a larger revolution than what the ASR provides so that the order of the cost performance is further improved. A study of the Low melting temperature Thermoplastic Propellant (LTP) is now at the experimental stage, which is expected to reform the manufacturing process of the solid rocket propellant and lead to a significant increase in cost performance. This paper indicates the direction of the big flow towards the next generation solid-propellant rockets: the concept of the intelligent ASR under development; and the innovation behind LTP.

  8. Study and Practice of Electromechanical Integrated Curriculum Design Teaching Model%机电综合课程设计教学模式的研究与实践

    Institute of Scientific and Technical Information of China (English)

    袁冬梅

    2012-01-01

    本文论述了机电综合课程设计的重要性,提出了以工程实践能力培养为目标的机电综合课程设计教学模式,制定了机电综合课程设计的选题原则,完善了组织实施方案,提高了机电综合课程设计教学质量。%This paper discusses the importance of the electromechanical integrated curriculum design,engineering practice ability to target the electromechanical integrated curriculum design teaching model,developed the principle of the electromechanical integrated curriculum design topics,and improve the organization and implementation of programs to improve the mechanical and electrical integrated curriculum design teaching quality.

  9. Understanding Curriculum as a Racial Text.

    Science.gov (United States)

    Pinar, William F.

    1991-01-01

    Discusses curriculum as a racial text, focusing on European Americans as a major part of the racial dilemma. The Eurocentric curriculum denies nonwhite students role models and denies white students self-understanding. African Americans' presence informs every element of U.S. life, and the absence of African-American knowledge in curriculum…

  10. A Differentiated Program: Significant Curriculum Adaptations.

    Science.gov (United States)

    Alonso, Juan A.

    1999-01-01

    This article describes a model for curricular adaptations for gifted students. A distinction is made between non-significant curriculum adaptations that can be easily made by the regular teacher and significant curriculum adaptations that involve deep changes in aims, content, and evaluation criteria. (Contains references.) (DB)

  11. Use of the Iowa Model of Research in Practice as a Curriculum Framework for Doctor of Nursing Practice (DNP) Project Completion.

    Science.gov (United States)

    Lloyd, Susan T; D'Errico, Ellen; Bristol, Shirley T

    2016-01-01

    Doctoral education requires academic motivation and persistence on the part of nursing students; commitment to the process is essential and should be linked to programmatic structure. Programmatic issues in doctor of nursing practice (DNP) programs may be barriers to completion of the final project and lead to attrition. A large, private health care university developed an infrastructure for the DNP curriculum and final project utilizing the Iowa Model of Research in Practice. The purpose was to ensure competency fulfillment, retention and timely completion, and implementation of evidence-based practice and translation science utilizing a leadership approach. The program has experienced a high completion rate to date.

  12. Rockets and People. Volume 1

    Science.gov (United States)

    Chertok, Boris E; Siddiqi, Asif A. (Editor)

    2005-01-01

    Much has been written in the West on the history of the Soviet space program but few Westerners have read direct first-hand accounts of the men and women who were behind the many Russian accomplishments in exploring space.The memoirs of Academician Boris Chertok, translated from the original Russian, fills that gap.Chertok began his career as an electrician in 1930 at an aviation factory near Moscow.Twenty-seven years later, he became deputy to the founding figure of the Soviet space program, the mysterious Chief Designer Sergey Korolev. Chertok s sixty-year-long career and the many successes and failures of the Soviet space program constitute the core of his memoirs, Rockets and People. These writings are spread over four volumes. This is volume I. Academician Chertok not only describes and remembers, but also elicits and extracts profound insights from an epic story about a society s quest to explore the cosmos. In Volume 1, Chertok describes his early years as an engineer and ends with the mission to Germany after the end of World War II when the Soviets captured Nazi missile technology and expertise. Volume 2 takes up the story with the development of the world s first intercontinental ballistic missile ICBM) and ends with the launch of Sputnik and the early Moon probes. In Volume 3, Chertok recollects the great successes of the Soviet space program in the 1960s including the launch of the world s first space voyager Yuriy Gagarin as well as many events connected with the Cold War. Finally, in Volume 4, Chertok meditates at length on the massive Soviet lunar project designed to beat the Americans to the Moon in the 1960s, ending with his remembrances of the Energiya-Buran project.

  13. Ultra-fast Escape of a Octopus-inspired Rocket

    Science.gov (United States)

    Weymouth, Gabriel; Triantafyllou, Michael

    2013-11-01

    The octopus, squid, and other cephalopods inflate with water and then release a jet to accelerate in the opposite direction. This escape mechanism is particularly interesting in the octopus because they become initially quite bluff, yet this does not hinder them in achieving impressive bursts of speed. We examine this somewhat paradoxical maneuver using a simple deflating spheroid model in both potential and viscous flow. We demonstrate that the dynamic reduction of the width of the body completely changes the flow and forces acting on the escaping rocket in three ways. First, a body which reduces in size can generate an added mass thrust which counteracts the added mass inertia. Second, the motion of the shrinking wall acts similar to suction on a static wall, reducing separation and drag forces in a viscous fluid, but that this effects depends on the rate of size change. Third, using a combination of these two features it is possible to initially load the fluid with kinetic energy when heavy and bluff and then recover that energy when streamlined and light, enabling ultra-fast accelerations. As a notable example, these mechanisms allow a shrinking spheroid rocket in a heavy inviscid fluid to achieve speeds greater than an identical rocket in the vacuum of space. Southampton Marine and Maritime Institute.

  14. Analysis of Regen Cooling in Rocket Combustors

    Science.gov (United States)

    Harper, Brent (Technical Monitor); Merkle, C. L.; Li, D.; Sankaran, V.

    2004-01-01

    The use of detailed CFD modeling for the description of cooling in rocket chambers is discussed. The overall analysis includes a complete three-dimensional analysis of the flow in the regenerative cooling passages, conjugate heat transfer in the combustor walls, and the effects of film cooling on the inside chamber. The results in the present paper omit the effects of film cooling and include only regen cooling and the companion conjugate heat transfer. The hot combustion gases are replaced by a constant temperature wall boundary condition. Load balancing for parallel cluster computations is ensured by using single-block unstructured grids for both fluids and solids, and by using a 'multiple physical zones' to account for differences in the number of equations. Validation of the method is achieved by comparing simple two-dimensional solutions with analytical results. Representative results for cooling passages are presents showing the effects of heat conduction in the copper walls with tube aspect ratios of 1.5:l.

  15. Optical Signature Analysis of Tumbling Rocket Bodies via Laboratory Measurements

    Science.gov (United States)

    Cowardin, H.; Lederer, S.; Liou, J.-C.

    2012-01-01

    The NASA Orbital Debris Program Office has acquired telescopic lightcurve data on massive intact objects, specifically spent rocket bodies, in order to ascertain tumble rates in support of the Active Debris Removal (ADR) task to help remediate the LEO environment. Rotation rates are needed to plan and develop proximity operations for potential future ADR operations. To better characterize and model optical data acquired from ground-based telescopes, the Optical Measurements Center (OMC) at NASA/JSC emulates illumination conditions in space using equipment and techniques that parallel telescopic observations and source-target-sensor orientations. The OMC employs a 75-watt Xenon arc lamp as a solar simulator, an SBIG CCD camera with standard Johnson/Bessel filters, and a robotic arm to simulate an object's position and rotation. The light source is mounted on a rotary arm, allowing access any phase angle between 0 -- 360 degrees. The OMC does not attempt to replicate the rotation rates, but focuses on how an object is rotating as seen from multiple phase angles. The two targets studied are scaled (1:48), SL-8 Cosmos 3M second stages. The first target is painted in the standard government "gray" scheme and the second target is primary white, as used for commercial missions. This paper summarizes results of the two scaled rocket bodies, each rotated about two primary axes: (a) a spin-stabilized rotation and (b) an end-over-end rotation. The two rotation states are being investigated as a basis for possible spin states of rocket bodies, beginning with simple spin states about the two primary axes. The data will be used to create a database of potential spin states for future works to convolve with more complex spin states. The optical signatures will be presented for specific phase angles for each rocket body and shown in conjunction with acquired optical data from multiple telescope sources.

  16. Curriculum Development Research Based on the Model of College Physical Education Teaching Club with Wushu Curriculum as an Example%基于高校俱乐部教学模式下的课程开发研究——以武术课程开发为例

    Institute of Scientific and Technical Information of China (English)

    邱服冰

    2012-01-01

    This research analyzed the definition,organizational form,guiding ideology and developing management of the model of college physical education teaching club(MCPC),using approach of Wushu teaching theory system and curriculum development system(CDS).And it discussed the development of college Martial Art curriculum based on the MCPC through bring in Wushu rank system,analyzed the feasibility of Wushu curriculum and setting of curriculum content,curriculum definition,curriculum implementation and evaluation in MCPC,aimed at providing theory framework for curriculum development and reformation based on MCPC%应用武术教学理论方法和课程开发理论的科学方法,分析了高校体育教学俱乐部模式定义、组织形式、指导思想和开发需求,并探讨在基于此模式之下,通过引入武术段位制的内容进行高校武术课程的课程开发,分析武术课程在高校体育俱乐部的模式下开发的可行性以及课程内容设置、课程目标的界定、课程实施和课程评价等内容,旨在为普通高校在俱乐部教学模式下进行课程改革和开发提供一定的理论架构依据。

  17. Is It Finally Time To Implement "Curriculum S"?

    Science.gov (United States)

    Hake, Richard R.

    This document describes the need for improved physics education of K-12 teachers and suggests "Curriculum S" as a possible partial solution. "Curriculum S" for synthesis intends to serve students who want to study physics as background for something other than physics research. The document presents some models of "Curriculum S" programs proposed…

  18. Curriculum and Assessment: Two Sides of the Same Coin.

    Science.gov (United States)

    Shoemaker, Berry Jean Eklund; Lewin, Larry

    1993-01-01

    Eugene (Oregon) Public Schools want to replace the traditional content-driven curriculum with a general concepts-based curriculum stressing the relationships among ideas. To help district educators understand the new model, a coin metaphor describing the two interlocking areas of curriculum (learning core conceptual knowledge and strategic…

  19. Particle Size Distributions Measured in the Stratospheric Plumes of Three Rockets During the ACCENT Missions

    Science.gov (United States)

    Wiedinmyer, C.; Brock, C. A.; Reeves, J. M.; Ross, M. N.; Schmid, O.; Toohey, D.; Wilson, J. C.

    2001-12-01

    The global impact of particles emitted by rocket engines on stratospheric ozone is not well understood, mainly due to the lack of comprehensive in situ measurements of the size distributions of these emitted particles. During the Atmospheric Chemistry of Combustion Emissions Near the Tropopause (ACCENT) missions in 1999, the NASA WB-57F aircraft carried the University of Denver N-MASS and FCAS instruments into the stratospheric plumes from three rockets. Size distributions of particles with diameters from 4 to approximately 2000 nm were calculated from the instrument measurements using numerical inversion techniques. The data have been averaged over 30-second intervals. The particle size distributions observed in all of the rocket plumes included a dominant mode near 60 nm diameter, probably composed of alumina particles. A smaller mode at approximately 25 nm, possibly composed of soot particles, was seen in only the plumes of rockets that used liquid oxygen and kerosene as a propellant. Aircraft exhaust emitted by the WB-57F was also sampled; the size distributions within these plumes are consistent with prior measurements in aircraft plumes. The size distributions for all rocket intercepts have been fitted to bimodal, lognormal distributions to provide input for global models of the stratosphere. Our data suggest that previous estimates of the solid rocket motor alumina size distributions may underestimate the alumina surface area emission index, and so underestimate the particle surface area available for heterogeneous chlorine activation reactions in the global stratosphere.

  20. Analysis of rocket beacon transmissions for computerized reconstruction of ionospheric densities

    Science.gov (United States)

    Bernhardt, P. A.; Huba, J. D.; Chaturvedi, P. K.; Fulford, J. A.; Forsyth, P. A.; Anderson, D. N.; Zalesak, S. T.

    1993-08-01

    Three methods are described to obtain ionospheric electron densities from transionospheric, rocket-beacon TEC data. First, when the line-of-sight from a ground receiver to the rocket beacon is tangent to the flight trajectory, the electron concentration can be obtained by differentiating the TEC with respect to the distance to the rocket. A similar method may be used to obtain the electron-density profile if the layer is horizontally stratified. Second, TEC data obtained during chemical release experiments may be interpreted with the aid of physical models of the disturbed ionosphere to yield spatial maps of the modified regions. Third, computerized tomography (CT) can be used to analyze TEC data obtained along a chain of ground-based receivers aligned along the plane of the rocket trajectory. CT analysis of TEC data is used to reconstruct a 2D image of a simulated equatorial plume. TEC data is computed for a linear chain of nine receivers with adjacent spacings of either 100 or 200 km. The simulation data are analyzed to provide an F region reconstruction on a grid with 15 x 15 km pixels. Ionospheric rocket tomography may also be applied to rocket-assisted measurements of amplitude and phase scintillations and airglow intensities.

  1. 77 FR 4363 - Solicitation for a Cooperative Agreement-Curriculum Development: Thinking for a Change 3.1...

    Science.gov (United States)

    2012-01-27

    ... National Institute of Corrections Solicitation for a Cooperative Agreement--Curriculum Development... expertise in the following: Curriculum design and development; the ITIP model; distance learning development... collaborating with the awardee throughout the development of the curriculum, and specifically for the...

  2. Modeling Collaboration and Partnership in a Program Integrating NMR across the Chemistry Curriculum at a University and a Community and Technical College

    Science.gov (United States)

    Webb, Cathleen; Dahl, Darwin; Pesterfield, Lester; Lovell, Donielle; Zhang, Rui; Ballard, Sue; Kellie, Shawn

    2013-01-01

    In this NSF-supported project, two Anasazi FT-NMRs are being integrated simultaneously across the chemistry curriculum at Western Kentucky University (WKU) and Elizabethtown Community and Technical College (ECTC). The collaborative project adds to a new curriculum initiative by integrating NMR throughout the chemistry curriculum to enhance both…

  3. Modeling Collaboration and Partnership in a Program Integrating NMR across the Chemistry Curriculum at a University and a Community and Technical College

    Science.gov (United States)

    Webb, Cathleen; Dahl, Darwin; Pesterfield, Lester; Lovell, Donielle; Zhang, Rui; Ballard, Sue; Kellie, Shawn

    2013-01-01

    In this NSF-supported project, two Anasazi FT-NMRs are being integrated simultaneously across the chemistry curriculum at Western Kentucky University (WKU) and Elizabethtown Community and Technical College (ECTC). The collaborative project adds to a new curriculum initiative by integrating NMR throughout the chemistry curriculum to enhance both…

  4. Collaboration leads to enhanced curriculum.

    Science.gov (United States)

    Valerius, J; Mohan, V; Doctor, D; Hersh, W

    2015-01-01

    In 2007, we initiated a health information management (HIM) track of our biomedical informatics graduate program, and subsequent ongoing program assessment revealed a confluence of topics and courses within HIM and clinical informatics (CI) tracks. We completed a thorough comparative analysis of competencies derived from AMIA, AHIMA, and CAHIIM. Coupled with the need to streamline course offerings, the process, described in this paper allowed new opportunities for faculty collaboration, resulted in the creation of a model assessment for best practice in courses, and led to new avenues of growth within the program. The objective of the case study is to provide others in the informatics educational community with a model for analysis of curriculum in order to improve quality of student learning. We describe a case study where an academic informatics program realigned its course offerings to better reflect the HIM of today, and prepare for challenges of the future. Visionary leadership, intra-departmental self-analysis and alignment of the curriculum through defined mapping process reduced overlap within the CI and HIM tracks. Teaching within courses was optimized through the work of core faculty collaboration. The analysis of curriculum resulted in reduction of overlap within course curriculum. This allowed for additional and new course content to be added to existing courses. Leadership fostered an environment where top-down as well as bottom-up collaborative assessment activities resulted in a model to consolidate learning and reduce unnecessary duplication within courses. A focus on curriculum integration, emphasis on course alignment and strategic consolidation of course content raised the quality of informatics education provided to students. Faculty synergy was an essential component of this redesign process. Continuous quality improvement strategy included an ongoing alignment of curriculum and competencies through a comparative analysis approach. Through

  5. The Guggenheim Aeronautics Laboratory at Caltech and the creation of the modern rocket motor (1936-1946): How the dynamics of rocket theory became reality

    Science.gov (United States)

    Zibit, Benjamin Seth

    creation of the jet Propulsion Laboratory, the founding of the Aerojet Corporation, and emphasizes the issue of JPL's close relation to military development of the rocket becomes a core subject of this thesis. Cooperation between engineers in an academic setting and the military was not merely inevitable in the 1940s---it was actively fostered and proved quite profitable to all concerned. The deep relationship between the Guggenheim Aeronautics Laboratory and the Army Air Force was one model of the evolution of a permanent institutional edifice, weaving academic research and military end-use together. The dissertation concludes that what began as a modest effort to understand rocket theory in greater depth led within ten years to both research and development tracks which have profoundly altered the technological and military definition of modern history.

  6. EXTRUSION FORMING OF A DOUBLE BASE SOLID ROCKET PROPELLANT BY FINITE ELEMENT METHOD

    Directory of Open Access Journals (Sweden)

    Barış KALAYCIOĞLU

    2007-01-01

    Full Text Available In this study, three dimensional modelling of extrusion forming of a double base solid rocket propellant is performed on Ansys® finite element simulation package. For the purpose of initial model construction and later comparisons with elastoviscoplastik model, the solid propellant is assumed to obey the elastic-plastic material response during the direct extrusion process. Taking into account the contact surface behavior with Coulomb friction and geometric and material nonlinearities, an incremental large large strain solution methodology has been adapted in the simulation. The hydrostatic pressure, stress, strain, and displacement values during extrusion of the solid rocket propellant are obtained from the simulation.

  7. Metallic Hydrogen: A Game Changing Rocket Propellant

    Science.gov (United States)

    Silvera, Isaac F.

    2016-01-01

    The objective of this research is to produce metallic hydrogen in the laboratory using an innovative approach, and to study its metastability properties. Current theoretical and experimental considerations expect that extremely high pressures of order 4-6 megabar are required to transform molecular hydrogen to the metallic phase. When metallic hydrogen is produced in the laboratory it will be extremely important to determine if it is metastable at modest temperatures, i.e. remains metallic when the pressure is released. Then it could be used as the most powerful chemical rocket fuel that exists and revolutionize rocketry, allowing single-stage rockets to enter orbit and chemically fueled rockets to explore our solar system.

  8. Laser-fusion rocket for interplanetary propulsion

    Energy Technology Data Exchange (ETDEWEB)

    Hyde, R.A.

    1983-09-27

    A rocket powered by fusion microexplosions is well suited for quick interplanetary travel. Fusion pellets are sequentially injected into a magnetic thrust chamber. There, focused energy from a fusion Driver is used to implode and ignite them. Upon exploding, the plasma debris expands into the surrounding magnetic field and is redirected by it, producing thrust. This paper discusses the desired features and operation of the fusion pellet, its Driver, and magnetic thrust chamber. A rocket design is presented which uses slightly tritium-enriched deuterium as the fusion fuel, a high temperature KrF laser as the Driver, and a thrust chamber consisting of a single superconducting current loop protected from the pellet by a radiation shield. This rocket can be operated with a power-to-mass ratio of 110 W gm/sup -1/, which permits missions ranging from occasional 9 day VIP service to Mars, to routine 1 year, 1500 ton, Plutonian cargo runs.

  9. The Norwegian Sounding Rocket and Balloon Program

    Science.gov (United States)

    Skatteboe, Rolf

    2001-08-01

    The status and recent developments of the Norwegian Sounding Rocket and Balloon Program are presented with focus on national activities and recent achievements. The main part of the Norwegian program is sounding rocket launches conducted by Andøya Rocket Range from the launch facilities on Andøya and at Svalbard. For the majority of the programs, the scientific goal is investigation of processes in the middle and upper atmosphere. The in situ measurements are supplemented by a large number of ground-based support instruments located at the ALOMAR Observatory. The ongoing and planned projects are described and the highlights of the latest completed projects are given. The scientific program for the period 2001-2003 will be reviewed. Several new programs have been started to improve the services available to the international science comunity. The Hotel Payload project and MiniDusty are important examples that will be introduced in the paper. Available space related infrastructure is summarized.

  10. Atmospheric scavenging of solid rocket exhaust effluents

    Science.gov (United States)

    Fenton, D. L.; Purcell, R. Y.

    1978-01-01

    Solid propellant rocket exhaust was directly utilized to ascertain raindrop scavenging rates for hydrogen chloride. Two chambers were used to conduct the experiments; a large, rigid walled, spherical chamber stored the exhaust constituents, while the smaller chamber housing all the experiments was charged as required with rocket exhaust HCl. Surface uptake experiments demonstrated an HCl concentration dependence for distilled water. Sea water and brackish water HCl uptake was below the detection limit of the chlorine-ion analysis technique used. Plant life HCl uptake experiments were limited to corn and soybeans. Plant age effectively correlated the HCl uptake data. Metallic corrosion was not significant for single 20 minute exposures to the exhaust HCl under varying relative humidity. Characterization of the aluminum oxide particles substantiated the similarity between the constituents of the small scale rocket and the full size vehicles.

  11. Liquid rocket combustion chamber acoustic characterization

    Directory of Open Access Journals (Sweden)

    Cândido Magno de Souza

    2010-09-01

    Full Text Available Over the last 40 years, many solid and liquid rocket motors have experienced combustion instabilities. Among other causes, there is the interaction of acoustic modes with the combustion and/or fluid dynamic processes inside the combustion chamber. Studies have been showing that, even if less than 1% of the available energy is diverted to an acoustic mode, combustion instability can be generated. On one hand, this instability can lead to ballistic pressure changes, couple with other propulsion systems such as guidance or thrust vector control, and in the worst case, cause motor structural failure. In this case, measures, applying acoustic techniques, must be taken to correct/minimize these influences on the combustion. The combustion chamber acoustic behavior in operating conditions can be estimated by considering its behavior in room conditions. In this way, acoustic tests can be easily performed, thus identifying the cavity modes. This paper describes the procedures to characterize the acoustic behavior in the inner cavity of four different configurations of a combustion chamber. Simple analytical models are used to calculate the acoustic resonance frequencies and these results are compared with acoustic natural frequencies measured at room conditions. Some comments about the measurement procedures are done, as well as the next steps for the continuity of this research. The analytical and experimental procedures results showed good agreement. However, limitations on high frequency band as well as in the identification of specific kinds of modes indicate that numerical methods able to model the real cavity geometry and an acoustic experimental modal analysis may be necessary for a more complete analysis. Future works shall also consider the presence of passive acoustic devices such as baffles and resonators capable of introducing damping and avoiding or limiting acoustic instabilities.

  12. Gastroenterology Fellowship Training: Approaches to Curriculum Assessment and Evaluation

    OpenAIRE

    Maitreyi Raman; Eldon Shaffer; Jocelyn Lockyear

    2008-01-01

    BACKGROUND: Medical education requires ongoing curriculum development and evaluation to incorporate new knowledge and competencies. The Kern model of curricular development is a generic model to guide curriculum design, whereas the Royal College of Physicians and Surgeons of Canada (RCPSC) has a specific model for curriculum development through its accreditation structure.OBJECTIVE: To apply the Kern model to an assessment of a residency program in gastroenterology.METHODS: A case study was u...

  13. Additive Manufacturing for Affordable Rocket Engines

    Science.gov (United States)

    West, Brian; Robertson, Elizabeth; Osborne, Robin; Calvert, Marty

    2016-01-01

    Additive manufacturing (also known as 3D printing) technology has the potential to drastically reduce costs and lead times associated with the development of complex liquid rocket engine systems. NASA is using 3D printing to manufacture rocket engine components including augmented spark igniters, injectors, turbopumps, and valves. NASA is advancing the process to certify these components for flight. Success Story: MSFC has been developing rocket 3D-printing technology using the Selective Laser Melting (SLM) process. Over the last several years, NASA has built and tested several injectors and combustion chambers. Recently, MSFC has 3D printed an augmented spark igniter for potential use the RS-25 engines that will be used on the Space Launch System. The new design is expected to reduce the cost of the igniter by a factor of four. MSFC has also 3D printed and tested a liquid hydrogen turbopump for potential use on an Upper Stage Engine. Additive manufacturing of the turbopump resulted in a 45% part count reduction. To understanding how the 3D printed parts perform and to certify them for flight, MSFC built a breadboard liquid rocket engine using additive manufactured components including injectors, turbomachinery, and valves. The liquid rocket engine was tested seven times in 2016 using liquid oxygen and liquid hydrogen. In addition to exposing the hardware to harsh environments, engineers learned to design for the new manufacturing technique, taking advantage of its capabilities and gaining awareness of its limitations. Benefit: The 3D-printing technology promises reduced cost and schedule for rocket engines. Cost is a function of complexity, and the most complicated features provide the largest opportunities for cost reductions. This is especially true where brazes or welds can be eliminated. The drastic reduction in part count achievable with 3D printing creates a waterfall effect that reduces the number of processes and drawings, decreases the amount of touch

  14. Working towards an inclusive curriculum.

    Science.gov (United States)

    Wren, Y; Parkhouse, J

    1998-01-01

    The move towards an inclusive model of education presents teachers with the difficulty of differentiating the curriculum for children with speech, language and communication impairments. This paper focuses on the 'WiSaLT Curriculum Appendix'-a tool which can be used by teachers and speech and language therapists to help such children access the mainstream curriculum and to promote improvement in their language and communication skills. As well as highlighting potential areas of difficulty within each attainment target for key stage one, the appendix guides users to specific strategies and activities. Thus the speech and language therapist and teacher can identify which attainment targets might prove problematic for any one child and also have access to ideas which can help.

  15. CODEX sounding rocket wire grid collimator design

    Science.gov (United States)

    Shipley, Ann; Zeiger, Ben; Rogers, Thomas

    2011-05-01

    CODEX is a sounding rocket payload designed to operate in the soft x-ray (0.1-1.0 kV) regime. The instrument has a 3.25 degree square field of view that uses a one meter long wire grid collimator to create a beam that converges to a line in the focal plane. Wire grid collimator performance is directly correlated to the geometric accuracy of actual grid features and their relative locations. Utilizing a strategic combination of manufacturing and assembly techniques, this design is engineered for precision within the confines of a typical rocket budget. Expected resilience of the collimator under flight conditions is predicted by mechanical analysis.

  16. [Chicano Counselor Training: Curriculum and Beyond Curriculum].

    Science.gov (United States)

    Aleman, Ramon

    The particulars of the evolved curriculum and how the training has evolved around the change-agent concept are stressed in this presentation. The measure of success achieved in attempting to influence the staff and course of studies of the regular guidance department is also emphasized. The curriculum of this counselor training institute has, from…

  17. Curriculum Development: Teacher Involvement in Curriculum Development

    Science.gov (United States)

    Alsubaie, Merfat Ayesh

    2016-01-01

    In order for curriculum development to be effective and schools to be successful, teachers must be involved in the development process. An effective curriculum should reflect the philosophy, goals, objectives, learning experiences, instructional resources, and assessments that comprise a specific educational program ("Guide to curriculum…

  18. The Parallel Curriculum: A Design To Develop High Potential and Challenge High-Ability Learners.

    Science.gov (United States)

    Tomlinson, Carol Ann; Kaplan, Sandra N.; Renzulli, Joseph S.; Purcell, Jeanne; Leppien, Jann; Burns, Deborah

    This book presents a model of curriculum development for gifted students and offers four parallel approaches that focus on ascending intellectual demand as students develop expertise in learning. The parallel curriculum's four approaches include: (1) the core or basic curriculum; (2) the curriculum of connections, which expands on the core…

  19. The XQC microcalorimeter sounding rocket: a stable LTD platform 30 seconds after rocket motor burnout

    Energy Technology Data Exchange (ETDEWEB)

    Porter, F.S. E-mail: frederick.s.porter@gsfc.nasa.gov; Almy, R.; Apodaca, E.; Figueroa-Feliciano, E.; Galeazzi, M.; Kelley, R.; McCammon, D.; Stahle, C.K.; Szymkowiak, A.E.; Sanders, W.T

    2000-04-07

    The XQC microcalorimeter sounding rocket experiment is designed to provide a stable thermal environment for an LTD detector system within 30 s of the burnout of its second stage rocket motor. The detector system used for this instrument is a 36-pixel microcalorimeter array operated at 60 mK with a single-stage adiabatic demagnetization refrigerator (ADR). The ADR is mounted on a space-pumped liquid helium tank with vapor cooled shields which is vibration isolated from the rocket structure. We present here some of the design and performance details of this mature LTD instrument, which has just completed its third suborbital flight.

  20. Competence, Curriculum, and Control.

    Science.gov (United States)

    Jackson, Nancy S.

    1988-01-01

    Draws upon a case study of a community college program review to examine the application of a competency-based approach to the process of curriculum design. Suggests that competency-based curriculum development shifts the basis for decision making from teacher knowledge to an objectified accounting system of employers and curriculum technicians.…

  1. Cusp Alfven and Plasma Electrodynamics Rocket (CAPER) Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Launch a single rocket from Andoya Rocket Range into an active cusp event. Observe electric and magnetic fields, HF waves, electron and ion distributions and...

  2. Hydrocarbon Rocket Engine Plume Imaging with Laser Induced Incandescence Project

    Data.gov (United States)

    National Aeronautics and Space Administration — NASA/ Marshall Space Flight Center (MSFC) needs sensors that can be operated on rocket engine plume environments to improve NASA/SSC rocket engine performance. In...

  3. A study of early korean rockets (1377-1600)

    Science.gov (United States)

    Chae, Yeon Seok

    The first Korean rocket was fired between 1377 and 1389 and began the Korean development of rockets as a tactical weapon. Although, Korea had successfully demonstrated the use of rockets as firearms in the fifteenth century, there had been no effort to present the historical development of the early Korean rockets in a paper which will be useful to both historians and scientists. The book entitled Kuk Cho Ore Sorye (1474) in the Korean language provided extensive rocket system description, however it required considerable research to interpret them. This paper is the first study of early Korean rockets and launchers. The major effort in this study is directed toward the development of design concepts and details of early Korean rockets. Also, to substantiate support of the historical data presented, some versions of the early Korean rockets were made according to their specifications and fired successfully by the author in 1981.

  4. Computational Thermochemistry of Jet Fuels and Rocket Propellants

    Science.gov (United States)

    Crawford, T. Daniel

    2002-01-01

    The design of new high-energy density molecules as candidates for jet and rocket fuels is an important goal of modern chemical thermodynamics. The NASA Glenn Research Center is home to a database of thermodynamic data for over 2000 compounds related to this goal, in the form of least-squares fits of heat capacities, enthalpies, and entropies as functions of temperature over the range of 300 - 6000 K. The chemical equilibrium with applications (CEA) program written and maintained by researchers at NASA Glenn over the last fifty years, makes use of this database for modeling the performance of potential rocket propellants. During its long history, the NASA Glenn database has been developed based on experimental results and data published in the scientific literature such as the standard JANAF tables. The recent development of efficient computational techniques based on quantum chemical methods provides an alternative source of information for expansion of such databases. For example, it is now possible to model dissociation or combustion reactions of small molecules to high accuracy using techniques such as coupled cluster theory or density functional theory. Unfortunately, the current applicability of reliable computational models is limited to relatively small molecules containing only around a dozen (non-hydrogen) atoms. We propose to extend the applicability of coupled cluster theory- often referred to as the 'gold standard' of quantum chemical methods- to molecules containing 30-50 non-hydrogen atoms. The centerpiece of this work is the concept of local correlation, in which the description of the electron interactions- known as electron correlation effects- are reduced to only their most important localized components. Such an advance has the potential to greatly expand the current reach of computational thermochemistry and thus to have a significant impact on the theoretical study of jet and rocket propellants.

  5. The Effects of Integrated Information Literacy in Science Curriculum on First-Grade Students’ Memory and Comprehension Using the Super3 Model

    Directory of Open Access Journals (Sweden)

    Lin Ching Chen

    2011-09-01

    Full Text Available The purpose of this study was to investigate the effects of integrated information literacy in first-grade science curriculum on students’ science learning. In this quasi-experimental study, two first-grade classrooms from a public elementary school were randomly assigned into the experimental group and control group. The former accepted an inquiry-based science curriculum infused information literacy using the Super3 model, while the latter accepted the traditional lecture-oriented instruction. The instructional unit in both experimental and control groups was taught by the same science teacher and lasted around three weeks, seven periods of time per week. Two tests were designed to test student’s memory of factual information and comprehension of scientific concepts. Results from the analyses of covariance showed that the experimental group significantly outperformed their counterparts on two measures of science learning. It is suggested that integrated information literacy instruction could have a positive impact on first-graders’ subject content learning and lay a foundation for young children to be lifelong learners.

  6. 运用联系法进行C语言教学%Practice of Teaching Model of Correlation in C Language Curriculum

    Institute of Scientific and Technical Information of China (English)

    沙爱军

    2012-01-01

      With the features of complex in content and flexible in use, C language curriculum is very hard to beginners. Ac⁃cording to the relation between the contents,the key points of C language curriculum can be integrated as follows: data types, algorithm, function, file and other aspects. And the teaching model of vertical and horizontal correlation of knowledge is ap⁃plied to guide students to form a proper way of thinking and learning, and to help the students to build the knowledge struc⁃ture,which promoted the students ability and improved the C language teaching effect.%  C语言具有内容复杂、使用灵活等特点,给初学者学习带来困难。根据知识点间的联系,C语言课程的主要内容可整合为数据类型、算法、函数、文件及其他等几大部分,教学中运用纵横联系法,可引导学生形成正确的思维方式和学习方法,帮助学生建立课程知识体系。这一方法的运用,提升了学生的综合能力,提高了C语言教学效果。

  7. Application of ‘Iceberg Model ’ in the Curriculum System Constructing of Vocational Colleges%“冰山模型”在高职课程体系构建中的应用

    Institute of Scientific and Technical Information of China (English)

    陶红; 李存园

    2014-01-01

    Curriculum system is the key to protect and enhance the quality of education. The “iceberg model” basic theory is applied to vocational tourism management curriculum system construction, and it can help to change the disciplinary system for the training of student-led curriculum model and recessive quality. Using the basic theory of “iceberg model” to exporting the higher education curriculum system, constructing the curriculum system of the specific ability, general ability, and cross-professional ability, professional core competencies corresponding with platform courses, orientation courses, expanding courses and public courses consisting of a complete curriculum. In the course of teaching staff, curriculum such as the practice of teaching and learning condition, to ensure smooth implementation of the curriculum system. In the course of teaching methods emphasis on the construction process, the order and proportion, teaching staff, curriculum, such as the practice of teaching and learning conditions, to ensure smooth implementation of the curriculum system.%课程体系是保障和提升教育质量的关键。将“冰山模型”基本理论应用于高职旅游管理课程体系的构建,有利于改变学科体系为主导的课程模式和学生隐性素质的培养。以“冰山模型”基本理论为基础构建与职业特定能力、行业通用能力、跨行业职业能力、职业核心能力相对应的平台课程、方向课程、拓展课程和公共课程组成的完整课程体系,在课程建设过程中重视教学方式、课程的顺序和比例、师资队伍建设、实践教学条件等,能够确保课程体系的顺利实施。

  8. Preparing nurses to intervene in the tobacco epidemic: Developing a model for faculty development and curriculum redesign.

    Science.gov (United States)

    Petersen, Anne Berit; Meyer, Bonnie; Sachs, Bonnie L; Bialous, Stella A; Cataldo, Janine K

    2017-07-01

    As the largest group of health professionals, nurses have a tremendous potential to help curb the tobacco epidemic. However, studies conducted across a range of global settings continue to indicate that both practicing nurses and nursing student have limited knowledge, skills and confidence needed to implement evidence-based tobacco cessation interventions. A contributing factor is the limited inclusion of tobacco control content in nursing curricula. Additionally, there is limited understanding of nurse educators' knowledge and perceptions about teaching tobacco dependence content. This paper presents the Loma Linda University School of Nursing's concurrent experience with both faculty development and curriculum redesign in the area of tobacco dependence prevention and treatment. An internal survey was administered at baseline and at 2-year follow-up to assess faculty's knowledge, perceptions and practices related to teaching tobacco dependence content and skills (n = 42). Faculty and curriculum development strategies and resources utilized, evaluation findings and subsequent lessons learned are described. The findings have implications for nursing programs seeking to enhance their curricula and commitment to ensuring that their graduates are prepared to provide evidence-based tobacco cessation interventions with each patient they encounter. Copyright © 2017 Elsevier Ltd. All rights reserved.

  9. Regression Rate Study in HTPB/GOX Hybrid Rocket Motors.

    OpenAIRE

    Philmon George; Krishnan, S; Lalitha Ramachandran; P. M. Varkey; Raveendran, M.

    1996-01-01

    The theoretical and experimenIal studies on hybrid rocket motor combustion research are briefly reviewed and the need for a clear understanding of hybrid rocket fuel regression rate mechanism is brought out. A test facility established at the Indian Institute of Technology, Madras, for hybrid rocket motor research study is described.The results of an experimental study on hydroxyl terminated polybutadiene and gaseous oxygen hybrid rocket motor are presented. Fuel grains with ammonium perchlor...

  10. On the hydrodynamics of rocket propellant engine inducers and turbopumps

    Science.gov (United States)

    d'Agostino, L.

    2013-12-01

    The lecture presents an overview of some recent results of the work carried out at Alta on the hydrodynamic design and rotordynamic fluid forces of cavitating turbopumps for liquid propellant feed systems of modern rocket engines. The reduced order models recently developed for preliminary geometric definition and noncavitating performance prediction of tapered-hub axial inducers and centrifugal turbopumps are illustrated. The experimental characterization of the rotordynamic forces acting on a whirling four-bladed, tapered-hub, variable-pitch high-head inducer, under different load and cavitation conditions is presented. Future perspectives of the work to be carried out at Alta in this area of research are briefly illustrated.

  11. Vertical Wind Tunnel for Prediction of Rocket Flight Dynamics

    Directory of Open Access Journals (Sweden)

    Hoani Bryson

    2016-03-01

    Full Text Available A customized vertical wind tunnel has been built by the University of Canterbury Rocketry group (UC Rocketry. This wind tunnel has been critical for the success of UC Rocketry as it allows the optimization of avionics and control systems before flight. This paper outlines the construction of the wind tunnel and includes an analysis of flow quality including swirl. A minimal modelling methodology for roll dynamics is developed that can extrapolate wind tunnel behavior at low wind speeds to much higher velocities encountered during flight. The models were shown to capture the roll flight dynamics in two rocket launches with mean roll angle errors varying from 0.26° to 1.5° across the flight data. The identified model parameters showed consistent and predictable variations over both wind tunnel tests and flight, including canard–fin interaction behavior. These results demonstrate that the vertical wind tunnel is an important tool for the modelling and control of sounding rockets.

  12. Research on Instantaneous Thrust Measurement for Attitude-control Solid Rocket Motor

    Institute of Scientific and Technical Information of China (English)

    OUYANG Hua-bing; WANG Jian-ping; LIN Feng; XU Wen-gan

    2008-01-01

    In order to measure the instantaneous thrust of a certain attitude-control solid rocket motor, based on the analysis of the measurement principles, the difference between the instantaneous thrust and steady thrust measurements is pointed out. According to the measurement characteristics, a dynamic digital filter compensation method is presented. Combined the identification-modeling, dynamic compensation and simulation, the system's dynamic mathematic model is established. And then, a compensation digital filter is also designed. Thus, the dynamic response of the system is improved and the instantaneous thrust measurement can be implemented. The measurement results for the rocket motor show that the digital filter compensation is effective in the instantaneous thrust measurement.

  13. The Coherent Curriculum

    Institute of Scientific and Technical Information of China (English)

    Michael Thomas

    2005-01-01

    @@ What makes a coherent EFL curriculum? How can curriculum planners avoid a mismatch between policy and pragmatics to produce an effective decision-making process? In The Second Language Curriculum, Johnson describes the coherent curriculum as one in which decision outcomes from the various stages of development are mutually consistent and complementary,and learning outcomes reflect curriculum aims.The achievement of coherence is said to depend crucially in most educational contexts upon the formalisation of decision-making processes and products. This formalisation facilitates consensus among those involved and is a prerequisite for effective evaluation and subsequent renewal (1994: xiii)

  14. Influence of Rocket Engine Characteristics on Shaft Sealing Technology Needs

    Science.gov (United States)

    Keba, John E.

    1999-01-01

    This paper presents viewgraphs of The Influence of Rocket Engine Characteristics on Shaft Sealing Technology Needs. The topics include: 1) Rocket Turbomachinery Shaft Seals (Inter-Propellant-Seal (IPS) Systems, Lift-off Seal Systems, and Technology Development Needs); 2) Rocket Engine Characteristics (Engine cycles, propellants, missions, etc., Influence on shaft sealing requirements); and 3) Conclusions.

  15. 14 CFR 437.67 - Tracking a reusable suborbital rocket.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Tracking a reusable suborbital rocket. 437... a reusable suborbital rocket. A permittee must— (a) During permitted flight, measure in real time the position and velocity of its reusable suborbital rocket; and (b) Provide position and...

  16. Specific Impulses Losses in Solid Propellant Rockets

    Science.gov (United States)

    1974-12-17

    to use the collision function form proposed by Golovin to simplify this production term: 4C><=) <P- .: Accordingly: m hence, by integration: Now, we...November 21, 1940 in Paris, Seine. VFirst Thesis. "Contribution to the Study of Specific i Impulse Loss in Solid Propellant Rockets." Second Thesis

  17. An Analysis of Rocket Propulsion Testing Costs

    Science.gov (United States)

    Ramirez, Carmen; Rahman, Shamim

    2010-01-01

    The primary mission at NASA Stennis Space Center (SSC) is rocket propulsion testing. Such testing is commonly characterized as one of two types: production testing for certification and acceptance of engine hardware, and developmental testing for prototype evaluation or research and development (R&D) purposes. For programmatic reasons there is a continuing need to assess and evaluate the test costs for the various types of test campaigns that involve liquid rocket propellant test articles. Presently, in fact, there is a critical need to provide guidance on what represents a best value for testing and provide some key economic insights for decision-makers within NASA and the test customers outside the Agency. Hence, selected rocket propulsion test databases and references have been evaluated and analyzed with the intent to discover correlations of technical information and test costs that could help produce more reliable and accurate cost projections in the future. The process of searching, collecting, and validating propulsion test cost information presented some unique obstacles which then led to a set of recommendations for improvement in order to facilitate future cost information gathering and analysis. In summary, this historical account and evaluation of rocket propulsion test cost information will enhance understanding of the various kinds of project cost information; identify certain trends of interest to the aerospace testing community.

  18. Rocket and Laboratory Studies in Astronomy

    Science.gov (United States)

    Feldman, Paul D.

    2001-01-01

    This is the final report for NASA Grant NAG5-5122 and covers the period from March 1, 1997 to February 28, 2001. This grant was a continuation of a program in rocket and laboratory studies in ultraviolet astronomy that was supported by NASA grant NAG5-619. As of March 1, 2001, this program is continuing under grant NAG5-5315. During the period of the grant, annual status reports have been submitted detailing the scientific achievements and current objectives of each report period. These will not be repeated here. Among the highlights of the program are four successful rocket launches including participation in the campaign to study comet Hale-Bopp in April 1997. We have continued our emphasis on long-slit spectroscopy of extended sources in the shorter wavelength far-ultraviolet, necessitating the development of evacuated telescope/spectrograph payloads. Finally, we also note the use of our ultraviolet calibration facilities in support of other sounding rocket investigators and for other space missions such as the Far Ultraviolet Spectroscopic Explorer. We include a list of the sounding rocket launches performed under NASA sponsorship during this period, a list of Ph.D. degrees awarded to students who worked in this program, and a summary bibliography of publications between 1997 and 2001.

  19. NASA Sounding Rocket Program educational outreach

    Science.gov (United States)

    Eberspeaker, P. J.

    2005-08-01

    Educational and public outreach is a major focus area for the National Aeronautics and Space Administration (NASA). The NASA Sounding Rocket Program (NSRP) shares in the belief that NASA plays a unique and vital role in inspiring future generations to pursue careers in science, mathematics, and technology. To fulfill this vision, the NASA Sounding Rocket Program engages in a host of student flight projects providing unique and exciting hands-on student space flight experiences. These projects include single stage Orion missions carrying "active" high school experiments and "passive" Explorer School modules, university level Orion and Terrier-Orion flights, and small hybrid rocket flights as part of the Small-scale Educational Rocketry Initiative (SERI) currently under development. Efforts also include educational programs conducted as part of major campaigns. The student flight projects are designed to reach students ranging from Kindergarteners to university undergraduates. The programs are also designed to accommodate student teams with varying levels of technical capabilities - from teams that can fabricate their own payloads to groups that are barely capable of drilling and tapping their own holes. The program also conducts a hands-on student flight project for blind students in collaboration with the National Federation of the Blind. The NASA Sounding Rocket Program is proud of its role in inspiring the "next generation of explorers" and is working to expand its reach to all regions of the United States and the international community as well.

  20. Straw Rockets Are out of This World

    Science.gov (United States)

    Gillman, Joan

    2013-01-01

    To capture students' excitement and engage their interest in rocketships and visiting planets in the solar system, the author designed lessons that give students the opportunity to experience the joys and challenges of developing straw rockets, and then observing which design can travel the longest distance. The lessons are appropriate for…

  1. Government Relations: It's Not Rocket Science

    Science.gov (United States)

    Radway, Mike

    2007-01-01

    Many people in the early childhood education field are afraid of government relations work, intimidated by politicians, and believe the whole process is unseemly. The author asserts that they should not be afraid nor be intimidated because government relations is not rocket science and fundamentally officeholders are no different from the rest of…

  2. Infrared spectroradiometer for rocket exhaust analysis

    Science.gov (United States)

    Herget, W. F.

    1968-01-01

    Infrared spectroradiometer measures high-resolution spectral absorption, emission, temperature, and concentration of chemical species in radically symmetric zones of the exhaust plumes of large rocket engines undergoing static firing tests. Measurements are made along predetermined lines of sight through the plume.

  3. Rocketing into the future the history and technology of rocket planes

    CERN Document Server

    van Pelt, Michel

    2012-01-01

    Rocketing into the Future journeys into the exciting world of rocket planes, examining the exotic concepts and actual flying vehicles that have been devised over the last one hundred years. Lavishly illustrated with over 150 photographs, it recounts the history of rocket planes from the early pioneers who attached simple rockets on to their wooden glider airplanes to the modern world of high-tech research vehicles. The book then looks at the possibilities for the future. The technological and economic challenges of the Space Shuttle proved insurmountable, and thus the program was unable to fulfill its promise of low-cost access to space. However, the burgeoning market of suborbital space tourism may yet give the necessary boost to the development of a truly reusable spaceplane.

  4. Cambridge Rocketry Simulator – A Stochastic Six-Degrees-of-Freedom Rocket Flight Simulator

    Directory of Open Access Journals (Sweden)

    Willem J. Eerland

    2017-02-01

    Full Text Available The Cambridge Rocketry Simulator can be used to simulate the flight of unguided rockets for both design and operational applications. The software consists of three parts: The first part is a GUI that enables the user to design a rocket. The second part is a verified and peer-reviewed physics model that simulates the rocket flight. This includes a Monte Carlo wrapper to model the uncertainty in the rocket’s dynamics and the atmospheric conditions. The third part generates visualizations of the resulting trajectories, including nominal performance and uncertainty analysis, e.g. a splash-down region with confidence bounds. The project is available on SourceForge, and is written in Java (GUI, C++ (simulation core, and Python (visualization. While all parts can be executed from the GUI, the three components share information via XML, accommodating modifications, and re-use of individual components.

  5. US Rocket Propulsion Industrial Base Health Metrics

    Science.gov (United States)

    Doreswamy, Rajiv

    2013-01-01

    The number of active liquid rocket engine and solid rocket motor development programs has severely declined since the "space race" of the 1950s and 1960s center dot This downward trend has been exacerbated by the retirement of the Space Shuttle, transition from the Constellation Program to the Space launch System (SLS) and similar activity in DoD programs center dot In addition with consolidation in the industry, the rocket propulsion industrial base is under stress. To Improve the "health" of the RPIB, we need to understand - The current condition of the RPIB - How this compares to past history - The trend of RPIB health center dot This drives the need for a concise set of "metrics" - Analogous to the basic data a physician uses to determine the state of health of his patients - Easy to measure and collect - The trend is often more useful than the actual data point - Can be used to focus on problem areas and develop preventative measures The nation's capability to conceive, design, develop, manufacture, test, and support missions using liquid rocket engines and solid rocket motors that are critical to its national security, economic health and growth, and future scientific needs. center dot The RPIB encompasses US government, academic, and commercial (including industry primes and their supplier base) research, development, test, evaluation, and manufacturing capabilities and facilities. center dot The RPIB includes the skilled workforce, related intellectual property, engineering and support services, and supply chain operations and management. This definition touches the five main segments of the U.S. RPIB as categorized by the USG: defense, intelligence community, civil government, academia, and commercial sector. The nation's capability to conceive, design, develop, manufacture, test, and support missions using liquid rocket engines and solid rocket motors that are critical to its national security, economic health and growth, and future scientific needs

  6. Closure Letter Report for Corrective Action Unit 496: Buried Rocket Site - Antelope Lake

    Energy Technology Data Exchange (ETDEWEB)

    NSTec Environmental Restoration

    2007-05-01

    interviews. Most pertinently, an interview in 2005 with a former TTR range manager recalled a lost rocket that possibly contained a depleted uranium ballast in an inert warhead. The interviewee confirmed that the last tracking coordinate for the rocket indicated it was lost in an area south of Area 9 near the l T R range coordinates X = 6,614.57 feet (ft) and Y = -20,508.79 ft. These coordinates correspond to a location approximately 2,295 ft northeast of the Mid Target, on Mid Lake. CAS TA-55-008-TAAL was removed from CAU 496 before the SAFER investigation could be completed, and before the new information could be evaluated and the conceptual site model assumptions confirmed.

  7. Peregrine 100-km Sounding Rocket Project

    Science.gov (United States)

    Zilliac, Gregory

    2012-01-01

    The Peregrine Sounding Rocket Program is a joint basic research program of NASA Ames Research Center, NASA Wallops, Stanford University, and the Space Propulsion Group, Inc. (SPG). The goal is to determine the applicability of this technology to a small launch system. The approach is to design, build, and fly a stable, efficient liquefying fuel hybrid rocket vehicle to an altitude of 100 km. The program was kicked off in October of 2006 and has seen considerable progress in the subsequent 18 months. This research group began studying liquifying hybrid rocket fuel technology more than a decade ago. The overall goal of the research was to gain a better understanding of the fundamental physics of the liquid layer entrainment process responsible for the large increase in regression rate observed in these fuels, and to demonstrate the effect of increased regression rate on hybrid rocket motor performance. At the time of this reporting, more than 400 motor tests were conducted with a variety of oxidizers (N2O, GOx, LOx) at ever increasing scales with thrust levels from 5 to over 15,000 pounds (22 N to over 66 kN) in order to move this technology from the laboratory to practical applications. The Peregrine program is the natural next step in this development. A number of small sounding rockets with diameters of 3, 4, and 6 in. (7.6, 10.2, and 15.2 cm) have been flown, but Peregrine at a diameter of 15 in. (38.1 cm) and 14,000-lb (62.3-kN) thrust is by far the largest system ever attempted and will be one of the largest hybrids ever flown. Successful Peregrine flights will set the stage for a wide range of applications of this technology.

  8. Development of Kabila rocket: A radioisotope heated thermionic plasma rocket engine

    Directory of Open Access Journals (Sweden)

    Kalomba Mboyi

    2015-04-01

    Full Text Available A new type of plasma rocket engine, the Kabila rocket, using a radioisotope heated thermionic heating chamber instead of a conventional combustion chamber or catalyst bed is introduced and it achieves specific impulses similar to the ones of conventional solid and bipropellant rockets. Curium-244 is chosen as a radioisotope heat source and a thermal reductive layer is also used to obtain precise thermionic emissions. The self-sufficiency principle is applied by simultaneously heating up the emitting material with the radioisotope decay heat and by powering the different valves of the plasma rocket engine with the same radioisotope decay heat using a radioisotope thermoelectric generator. This rocket engine is then benchmarked against a 1 N hydrazine thruster configuration operated on one of the Pleiades-HR-1 constellation spacecraft. A maximal specific impulse and power saving of respectively 529 s and 32% are achieved with helium as propellant. Its advantages are its power saving capability, high specific impulses and simultaneous ease of storage and restart. It can however be extremely voluminous and potentially hazardous. The Kabila rocket is found to bring great benefits to the existing spacecraft and further research should optimize its geometric characteristics and investigate the physical principals of its operation.

  9. Measurements of temperature profiles at the exit of small rockets.

    Science.gov (United States)

    Griggs, M; Harshbarger, F C

    1966-02-01

    The sodium line reversal technique was used to determine the reversal temperature profile across the exit of small rockets. Measurements were made on one 73-kg thrust rocket, and two 23-kg thrust rockets with different injectors. The large rocket showed little variation of reversal temperature across the plume. However, the 23-kg rockets both showed a large decrease of reversal temperature from the axis to the edge of the plume. In addition, the sodium line reversal technique of temperature measurement was compared with an infrared technique developed in these laboratories.

  10. Mixing and reaction processes in rocket based combined cycle and conventional rocket engines

    Science.gov (United States)

    Lehman, Matthew Kurt

    Raman spectroscopy was used to make species measurements in two rocket engines. An airbreathing rocket, the rocket based combined cycle (RBCC) engine, and a conventional rocket were investigated. A supersonic rocket plume mixing with subsonic coflowing air characterizes the ejector mode of the RBCC engine. The mixing length required for the air and plume to become homogenous is a critical dimension. For the conventional rocket experiments, a gaseous oxygen/gaseous hydrogen single-element shear coaxial injector was used. Three chamber Mach number conditions, 0.1, 0.2 and 0.3, were chosen to assess the effect of Mach number on mixing. The flow within the chamber was entirely subsonic. For the RBCC experiments, vertical Raman line measurements were made at multiple axial locations downstream from the rocket nozzle plane. Species profiles assessed the mixing progress between the supersonic plume and subsonic air. For the conventional rocket, Raman line measurements were made downstream from the injector face. The goal was to evaluate the effect of increased chamber Mach number on injector mixing/reaction. For both engines, quantitative and qualitative information was collected for computational fluid dynamics (CFD development. The RBCC experiments were conducted for three distinct geometries. The primary flow path was a diffuse and afterburner design with a direct-connect air supply. A sea-level static (SLS) version and a thermally choked variant were also tested. The experimental results show that mixing length increases with additional coflow air in the DAB geometry. Operation of variable rocket mixture ratios at identical air flow rates did not significantly affect the mixing length. The thermally choked variant had a longer mixing length compared to the DAB geometry, and the SLS modification had a shorter mixing length due to a reduced air flow. The conventional rocket studies focused on the effect of chamber Mach number on primary injector mixing. Chamber Mach

  11. School Curriculum Committee: Its Role In Curriculum ...

    African Journals Online (AJOL)

    Ethiopian Journal of Education and Sciences ... smooth relationship among staff members, and to participate in decision making process related to curriculum. Except secondary school principals, supervisors, students parents, and community ...

  12. Pressure-Equalizing Cradle for Booster Rocket Mounting

    Science.gov (United States)

    Rutan, Elbert L. (Inventor)

    2015-01-01

    A launch system and method improve the launch efficiency of a booster rocket and payload. A launch aircraft atop which the booster rocket is mounted in a cradle, is flown or towed to an elevation at which the booster rocket is released. The cradle provides for reduced structural requirements for the booster rocket by including a compressible layer, that may be provided by a plurality of gas or liquid-filled flexible chambers. The compressible layer contacts the booster rocket along most of the length of the booster rocket to distribute applied pressure, nearly eliminating bending loads. Distributing the pressure eliminates point loading conditions and bending moments that would otherwise be generated in the booster rocket structure during carrying. The chambers may be balloons distributed in rows and columns within the cradle or cylindrical chambers extending along a length of the cradle. The cradle may include a manifold communicating gas between chambers.

  13. Nuclear-thermal rocket thrust transient effects on minimum-fuel lunar trajectories

    Science.gov (United States)

    Rivas, Matthew L.

    1995-01-01

    A technically viable option for low-cost minimum-fuel Lunar transfers with short trip times is the use of nuclear thermal rockets. However, little work has been done on the effects the associated thrust transients have on these optimal trajectories. The nominal thrust level of an engine is not immediately reached when the rocket is turned ``on.'' Similarly, when the engine is turned ``off'', the thrust and specific impulse levels decrease over a period of time which is directly related to both the flow effecs of the engine and cooling requirements. This paper presents an analysis of these effects on a typical optimal Lunar transfer. Several different models simulating the transient effects are used. They range from simple ``mass dumps'' to account for the extra required propellant to curve-fits of actual engine characteristics obtained from the NERVA nuclear rocket program.

  14. Development of small solid rocket boosters for the ILR-33 sounding rocket

    Science.gov (United States)

    Nowakowski, Pawel; Okninski, Adam; Pakosz, Michal; Cieslinski, Dawid; Bartkowiak, Bartosz; Wolanski, Piotr

    2017-09-01

    This paper gives an overview of the development of a 6000 Newton-class solid rocket motor for suborbital applications. The design configuration and results of interior ballistics calculations are given. The initial use of the motor as the main propulsion system of the H1 experimental in-flight test platform, within the Polish Small Sounding Rocket Program, is presented. Comparisons of theoretical and experimental performance are shown. Both on-ground and in-flight tests are discussed. A novel composite-case manufacturing technology, which enabled to reach high propellant mass fractions, was validated and significant cost-reductions were achieved. This paper focuses on the process of adapting the design for use as the booster stage of the ILR-33 sounding rocket, under development at the Institute of Aviation in Warsaw, Poland. Parallel use of two of the flight-proven rocket motors along with the main stage is planned. The process of adapting the rocket motor for booster application consists of stage integration, aerothermodynamics and reliability analyses. The separation mechanism and environmental impact are also discussed within this paper. Detailed performance analysis with focus on propellant grain geometry is provided. The evolution of the design since the first flights of the H1 rocket is covered and modifications of the manufacturing process are described. Issues of simultaneous ignition of two motors and their non-identical performance are discussed. Further applications and potential for future development are outlined. The presented results are based on the initial work done by the Rocketry Group of the Warsaw University of Technology Students' Space Association. The continuation of the Polish Small Sounding Rocket Program on a larger scale at the Institute of Aviation proves the value of the outcomes of the initial educational project.

  15. Rocket center Peenemünde — Personal memories

    Science.gov (United States)

    Dannenberg, Konrad; Stuhlinger, Ernst

    Von Braun built his first rockets as a young teenager. At 14, he started making plans for rockets for human travel to the Moon and Mars. The German Army began a rocket program in 1929. Two years later, Colonel (later General) Becker contacted von Braun who experimented with rockets in Berlin, gave him a contract in 1932, and, jointly with the Air Force, in 1936 built the rocket center Peenemünde where von Braun and his team developed the A-4 (V-2) rocket under Army auspices, while the Air Force developed the V-1 (buzz bomb), wire-guided bombs, and rocket planes. Albert Speer, impressed by the work of the rocketeers, allowed a modest growth of the Peenemünde project; this brought Dannenberg to the von Braun team in 1940. Hitler did not believe in rockets; he ignored the A-4 project until 1942 when he began to support it, expecting that it could turn the fortunes of war for him. He drastically increased the Peenemünde work force and allowed the transfer of soldiers from the front to Peenemünde; that was when Stuhlinger, in 1943, came to Peenemünde as a Pfc.-Ph.D. Later that year, Himmler wrenched the authority over A-4 production out of the Army's hands, put it under his command, and forced production of the immature rocket at Mittelwerk, and its military deployment against targets in France, Belgium, and England. Throughout the development of the A-4 rocket, von Braun was the undisputed leader of the project. Although still immature by the end of the war, the A-4 had proceeded to a status which made it the first successful long-range precision rocket, the prototype for a large number of military rockets built by numerous nations after the war, and for space rockets that launched satellites and traveled to the Moon and the planets.

  16. Regression rate behaviors of HTPB-based propellant combinations for hybrid rocket motor

    Science.gov (United States)

    Sun, Xingliang; Tian, Hui; Li, Yuelong; Yu, Nanjia; Cai, Guobiao

    2016-02-01

    The purpose of this paper is to characterize the regression rate behavior of hybrid rocket motor propellant combinations, using hydrogen peroxide (HP), gaseous oxygen (GOX), nitrous oxide (N2O) as the oxidizer and hydroxyl-terminated poly-butadiene (HTPB) as the based fuel. In order to complete this research by experiment and simulation, a hybrid rocket motor test system and a numerical simulation model are established. Series of hybrid rocket motor firing tests are conducted burning different propellant combinations, and several of those are used as references for numerical simulations. The numerical simulation model is developed by combining the Navies-Stokes equations with the turbulence model, one-step global reaction model, and solid-gas coupling model. The distribution of regression rate along the axis is determined by applying simulation mode to predict the combustion process and heat transfer inside the hybrid rocket motor. The time-space averaged regression rate has a good agreement between the numerical value and experimental data. The results indicate that the N2O/HTPB and GOX/HTPB propellant combinations have a higher regression rate, since the enhancement effect of latter is significant due to its higher flame temperature. Furthermore, the containing of aluminum (Al) and/or ammonium perchlorate(AP) in the grain does enhance the regression rate, mainly due to the more energy released inside the chamber and heat feedback to the grain surface by the aluminum combustion.

  17. Pre-Eminent Curriculum in Islamic Basic School Integrated Comparative Studies in Islamic Basic School Integrated Al-Izzah Serang and Al-Hanif Cilegon, Banten, Indonesia

    Science.gov (United States)

    Fauz, Anis; Hasbullah

    2016-01-01

    Compare to General SD (Primary school), the superiority of SD Islam Terpadu (Integrated Islamic Primary School) lies on the development of the curriculum and learning that is more emphasize on integrated curriculum and integrated learning. Curriculum model applied in Sekolah Dasar Islam Terpadu (SDIT) is integrated curriculum. This curriculum is…

  18. Modeling and Simulation of Cooperative Defense Against Wire-guided Torpedo with Rocket Assisted Noise-jammer and Hovering Depth Charge%火箭助飞式声干扰器和悬浮式深弹协同对抗线导鱼雷建模与仿真

    Institute of Scientific and Technical Information of China (English)

    贾跃; 姚奉亮; 丁贝

    2011-01-01

    提出了使用火箭助飞式声干扰器和悬浮式深弹组合协同防御潜射线导鱼雷战术,根据线导鱼雷射击原理,仿真估算了导引艇的舷角,建立了火箭助飞式声干扰器和悬浮式深弹这一软硬反鱼雷武器组合协同防御潜射线导鱼雷的数学模型,利用运筹学中的优化方法确定了两型武器的布放策略及舰艇的规避航向,并对使用软硬武器协同对抗与单一软对抗的对抗成功概率进行了仿真比较,结果表明,使用软硬武器协同对抗效果显著,较单一使用软对抗线导鱼雷的成功概率提高了20%~36%.%We propose a torpedo defense tactic for a vessel cooperative defense against wire-guided torpedo with a rocket assisted noise-jammer and a hovering depth charge, named hard-kill and soft-kill anti-torpedo weapons. We simulate the board angle of guided submarine based on the firing principle of a wire-guided torpedo, establish a model of cooperative defense against a submarine-launched wire-guided torpedo using a rocket-assisted noise-jammer and a hovering depth charge, determine the deploying strategy of hard-kill and soft-kill anti-torpedo weapons and evading course of surface ship through the optimization method in operational research, and compare the success probabilities of the cooperative defense with hard-kill and soft-kill anti-torpedo weapons and the defense with single rocket-assisted noise-jammer via simulations. The results show that the proposed tactic can increase success probability by 20%~36% compared with only using a rocket assisted noise-jammer.

  19. Nuclear rocket using indigenous Martian fuel NIMF

    Science.gov (United States)

    Zubrin, Robert

    1991-01-01

    In the 1960's, Nuclear Thermal Rocket (NTR) engines were developed and ground tested capable of yielding isp of up to 900 s at thrusts up to 250 klb. Numerous trade studies have shown that such traditional hydrogen fueled NTR engines can reduce the inertial mass low earth orbit (IMLEO) of lunar missions by 35 percent and Mars missions by 50 to 65 percent. The same personnel and facilities used to revive the hydrogen NTR can also be used to develop NTR engines capable of using indigenous Martian volatiles as propellant. By putting this capacity of the NTR to work in a Mars descent/acent vehicle, the Nuclear rocket using Indigenous Martian Fuel (NIMF) can greatly reduce the IMLEO of a manned Mars mission, while giving the mission unlimited planetwide mobility.

  20. Performance Charts for Multistage Rocket Boosters

    Science.gov (United States)

    MacKay, John S.; Weber, Richard J.

    1961-01-01

    Charts relating the stage propellant fractions are given for two-and three-stage rockets launching payloads into nominal low-altitude circular orbits about the earth. A simple method is described for extending these data to higher orbit or escape missions. Various combinations of stages using RP - liquid-oxygen and hydrogen - liquid-oxygen propellants are considered. However, the results can be generalized with little error to any other propellant combination.Charts relating the stage propellant fractions are given for two-and three-stage rockets launching payloads into nominal low-altitude circular orbits about the earth. A simple method is described for extending these data to higher orbit or escape missions. Various combinations of stages using RP - liquid-oxygen and hydrogen - liquid-oxygen propellants are considered. However, the results can be generalized with little error to any other propellant combination.

  1. Design Study: Rocket Based MHD Generator

    Science.gov (United States)

    1997-01-01

    This report addresses the technical feasibility and design of a rocket based MHD generator using a sub-scale LOx/RP rocket motor. The design study was constrained by assuming the generator must function within the performance and structural limits of an existing magnet and by assuming realistic limits on (1) the axial electric field, (2) the Hall parameter, (3) current density, and (4) heat flux (given the criteria of heat sink operation). The major results of the work are summarized as follows: (1) A Faraday type of generator with rectangular cross section is designed to operate with a combustor pressure of 300 psi. Based on a magnetic field strength of 1.5 Tesla, the electrical power output from this generator is estimated to be 54.2 KW with potassium seed (weight fraction 3.74%) and 92 KW with cesium seed (weight fraction 9.66%). The former corresponds to a enthalpy extraction ratio of 2.36% while that for the latter is 4.16%; (2) A conceptual design of the Faraday MHD channel is proposed, based on a maximum operating time of 10 to 15 seconds. This concept utilizes a phenolic back wall for inserting the electrodes and inter-electrode insulators. Copper electrode and aluminum oxide insulator are suggested for this channel; and (3) A testing configuration for the sub-scale rocket based MHD system is proposed. An estimate of performance of an ideal rocket based MHD accelerator is performed. With a current density constraint of 5 Amps/cm(exp 2) and a conductivity of 30 Siemens/m, the push power density can be 250, 431, and 750 MW/m(sup 3) when the induced voltage uB have values of 5, 10, and 15 KV/m, respectively.

  2. 高职院校武术课程组织模式的改革%Reform on the Curriculum Organization Model of Wushu in Higher Vocational Colleges

    Institute of Scientific and Technical Information of China (English)

    李鸯

    2014-01-01

    以云南国防工业职业技术学院为例,分析了目前高职院校的武术课程组织模式的不足,主要体现在武术课程的内容设置、课程的组织形式等方面。在此基础上,结合学校特点,提出了调整和丰富武术课的教学内容、改进教学方法、完善教学环境、提高学生对武术的认识水平及提高教师业务素质等改革举措,转变教学观念,针对学生兴趣爱好和学习动机设置课程的内容和组织教法安排,在武术课的教学中大力实施创新教育。%Exemplified by Yunnan Vocational& Technical Col-lege of National Defense Industry, this paper analyzed the short-comings of the curriculum organization model of Wushu in higher vocational colleges,mainly reflecting in content setting and orga-nization form. Based on this,combined with college characteris-tics,this paper proposed corresponding reform measures, such as adjusting and enriching the teaching content of Wushu, improving teaching methods, perfecting teaching environment, improving students' recognition of Wushu and improving teachers' profes-sional qualities, and besides, the teacher should transform teach-ing ideas, set curriculum content and organize teaching methods in accordance with students' interest and learning motivation, and vigorously implement innovative education in Wushu teaching.

  3. Integration of Basic-Clinical Sciences, PBL, CBL, and IPE in U.S. Dental Schools' Curricula and a Proposed Integrated Curriculum Model for the Future.

    Science.gov (United States)

    Elangovan, Satheesh; Venugopalan, Shankar Rengasamy; Srinivasan, Sreedevi; Karimbux, Nadeem Y; Weistroffer, Paula; Allareddy, Veerasathpurush

    2016-03-01

    The integration of basic and clinical sciences in dental curricula enhances the application of basic science principles to clinical decision making and improves students' critical thinking. The aim of this study was to define the characteristics of U.S. dental schools' curricula with regard to level of course integration and degree of incorporation of problem-based and case-based learning. A second aim was to propose a dental curriculum that supports effective integration of courses and addresses some of the concerns facing academic dentistry. A survey was sent to 58 academic deans in U.S. dental schools. The survey included questions about integrating courses in the schools' curricula and major changes in curricular structure or teaching pedagogy that respondents anticipated in the immediate future. A total of 31 schools responded to the survey, for a 53.4% response rate. The results showed that three-quarters of the responding schools still teach basic and clinical sciences separately, although 61.3% reported having an integrated curriculum. Among the responding schools, 16 had a PBL component integrated into their curricula (two had integrated PBL in all courses and 14 used a hybrid PBL approach). Two schools had CBL integrated in all courses, and ten had CBL integrated in >75% of courses. Only slightly more than half agreed that their curricula foster students' thinking "outside the box." Faculty shortages and lack of protected time and resources were the most frequent reasons given for a lack of integrated courses. The integrated model proposed in this article has the potential to provide a low stress environment for students and to address important issues like faculty shortages.

  4. Thermal Design for the Micro-X Rocket Payload

    Science.gov (United States)

    Goldfinger, D. C.; Figueroa-Feliciano, E.; Danowski, M.; Heine, S. N. T.

    2016-08-01

    Micro-X is a NASA funded, rocket borne X-ray imaging spectrometer that uses transition edge sensors (TESs) to do high-resolution microcalorimetry. The TESs are cooled by an adiabatic demagnetization refrigerator, whose salt pill functions as a heat sink for the detectors. We have made a thermal model of the cryostat with SPICE for the purposes of understanding its behavior at low temperatures. Implementing modifications based on this model has further allowed us to cool the system down to a lower temperature than had previously been accessible and to improve its low-temperature hold time. These modifications include a variety of schemes for power through heat sinks and tweaking the conductance between the cold baths and the refrigerated hardware. We present an overview of the model and its constituent parameters, information about thermal modifications, and a summary of results from thermal tests of the entire system.

  5. Software for Estimating Costs of Testing Rocket Engines

    Science.gov (United States)

    Hines, Merlon M.

    2004-01-01

    A high-level parametric mathematical model for estimating the costs of testing rocket engines and components at Stennis Space Center has been implemented as a Microsoft Excel program that generates multiple spreadsheets. The model and the program are both denoted, simply, the Cost Estimating Model (CEM). The inputs to the CEM are the parameters that describe particular tests, including test types (component or engine test), numbers and duration of tests, thrust levels, and other parameters. The CEM estimates anticipated total project costs for a specific test. Estimates are broken down into testing categories based on a work-breakdown structure and a cost-element structure. A notable historical assumption incorporated into the CEM is that total labor times depend mainly on thrust levels. As a result of a recent modification of the CEM to increase the accuracy of predicted labor times, the dependence of labor time on thrust level is now embodied in third- and fourth-order polynomials.

  6. CAC - NUCLEAR THERMAL ROCKET CORE ANALYSIS CODE

    Science.gov (United States)

    Clark, J. S.

    1994-01-01

    One of the most important factors in the development of nuclear rocket engine designs is to be able to accurately predict temperatures and pressures throughout a fission nuclear reactor core with axial hydrogen flow through circular coolant passages. CAC is an analytical prediction program to study the heat transfer and fluid flow characteristics of a circular coolant passage. CAC predicts as a function of time axial and radial fluid conditions, passage wall temperatures, flow rates in each coolant passage, and approximate maximum material temperatures. CAC incorporates the hydrogen properties model STATE to provide fluid-state relations, thermodynamic properties, and transport properties of molecular hydrogen in any fixed ortho-para combination. The program requires the general core geometry, the core material properties as a function of temperature, the core power profile, and the core inlet conditions as function of time. Although CAC was originally developed in FORTRAN IV for use on an IBM 7094, this version is written in ANSI standard FORTRAN 77 and is designed to be machine independent. It has been successfully compiled on IBM PC series and compatible computers running MS-DOS with Lahey F77L, a Sun4 series computer running SunOS 4.1.1, and a VAX series computer running VMS 5.4-3. CAC requires 300K of RAM under MS-DOS, 422K of RAM under SunOS, and 220K of RAM under VMS. No sample executable is provided on the distribution medium. Sample input and output data are included. The standard distribution medium for this program is a 5.25 inch 360K MS-DOS format diskette. CAC was developed in 1966, and this machine independent version was released in 1992. IBM-PC and IBM are registered trademarks of International Business Machines. Lahey F77L is a registered trademark of Lahey Computer Systems, Inc. SunOS is a trademark of Sun Microsystems, Inc. VMS is a trademark of Digital Equipment Corporation. MS-DOS is a registered trademark of Microsoft Corporation.

  7. Development of high temperature materials for solid propellant rocket nozzle applications

    Science.gov (United States)

    Manning, C. R., Jr.; Lineback, L. D.

    1974-01-01

    Aspects of the development and characteristics of thermal shock resistant hafnia ceramic material for use in solid propellant rocket nozzles are presented. The investigation of thermal shock resistance factors for hafnia based composites, and the preparation and analysis of a model of elastic materials containing more than one crack are reported.

  8. Nuclear Thermal Rocket Element Environmental Simulator (NTREES)

    Science.gov (United States)

    Emrich, William J.

    2008-01-01

    To support a potential future development of a nuclear thermal rocket engine, a state-of-the-art non nuclear experimental test setup has been constructed to evaluate the performance characteristics of candidate fuel element materials and geometries in representative environments. The test device simulates the environmental conditions (minus the radiation) to which nuclear rocket fuel components could be subjected during reactor operation. Test articles mounted in the simulator are inductively heated in such a manner as to accurately reproduce the temperatures and heat fluxes normally expected to occur as a result of nuclear fission while at the same time being exposed to flowing hydrogen. This project is referred to as the Nuclear Thermal Rocket Element Environment Simulator or NTREES. The NTREES device is located at the Marshall Space flight Center in a laboratory which has been modified to accommodate the high powers required to heat the test articles to the required temperatures and to handle the gaseous hydrogen flow required for the tests. Other modifications to the laboratory include the installation of a nitrogen gas supply system and a cooling water supply system. During the design and construction of the facility, every effort was made to comply with all pertinent regulations to provide assurance that the facility could be operated in a safe and efficient manner. The NTREES system can currently supply up to 50 kW of inductive heating to the fuel test articles, although the facility has been sized to eventually allow test article heating levels of up to several megawatts.

  9. Nuclear Thermal Rocket Element Environmental Simulator (NTREES)

    Science.gov (United States)

    Emrich, William J., Jr.

    2008-01-01

    To support the eventual development of a nuclear thermal rocket engine, a state-of-the-art experimental test setup has been constructed to evaluate the performance characteristics of candidate fuel element materials and geometries in representative environments. The test device simulates the environmental conditions (minus the radiation) to which nuclear rocket fuel components will be subjected during reactor operation. Test articles mounted in the simulator are inductively heated in such a manner as to accurately reproduce the temperatures and heat fluxes normally expected to occur as a result of nuclear fission while at the same time being exposed to flowing hydrogen. This project is referred to as the Nuclear Thermal Rocket Element Environment Simulator or NTREES. The NTREES device is located at the Marshall Space flight Center in a laboratory which has been modified to accommodate the high powers required to heat the test articles to the required temperatures and to handle the gaseous hydrogen flow required for the tests. Other modifications to the laboratory include the installation of a nitrogen gas supply system and a cooling water supply system. During the design and construction of the facility, every effort was made to comply with all pertinent regulations to provide assurance that the facility could be operated in a safe and efficient manner. The NTREES system can currently supply up to 50 kW of inductive heating to the fuel test articles, although the facility has been sized to eventually allow test article heating levels of up to several megawatts.

  10. Rocket dust storms and detached layers in the Martian atmosphere

    CERN Document Server

    Spiga, Aymeric; Madeleine, Jean-Baptiste; Määttänen, Anni; Forget, François

    2012-01-01

    Airborne dust is the main climatic agent in the Martian environment. Local dust storms play a key role in the dust cycle; yet their life cycle is poorly known. Here we use mesoscale modeling with radiatively-active transported dust to predict the evolution of a local dust storm monitored by OMEGA on board Mars Express. We show that the evolution of this dust storm is governed by deep convective motions. The supply of convective energy is provided by the absorption of incoming sunlight by dust particles, in lieu of latent heating in moist convection on Earth. We propose to use the terminology "rocket dust storm", or conio-cumulonimbus, to describe those storms in which rapid and efficient vertical transport takes place, injecting dust particles at high altitudes in the Martian troposphere (30 to 50 km). Combined to horizontal transport by large-scale winds, rocket dust storms form detached layers of dust reminiscent of those observed with instruments on board Mars Global Surveyor and Mars Reconnaissance Orbite...

  11. Propellant removal from rocket motors containing double-base compositions

    Energy Technology Data Exchange (ETDEWEB)

    Whinnery, L.; Griffiths, S.; Hruby, J.; Larson, R.; Lipkin, J.; Long, B.; Schoenfelder, C.

    1992-01-01

    The uncertain environmental consequences and regulations associated with using open burning/open detonation for the disposal of energetic materials are forcing both manufacturers and users to examine alternative disposal technologies. In general, these alternatives involve a material removal operation followed by processing steps that lead to reuse of valuable constituents and/or disposal of waste. While a number of post-removal processing options appear to be viable, the initial step of removing an energetic material, such as a solid rocket motor propellant, from its container remains a significant technological challenge. Large rocket motors containing highly energetic propellant, hazard class 1.1, are of particular concern because of their inherent handling hazards. We will describe the results of a study using thermal cycling to increase the surface area of inert propellant formulations. The propellant removal method studied employs thermal cycling to cryogenic temperatures (cryocycling). Using inert propellants and liquid nitrogen we have demonstrated that this process produces multiple cracks throughout the bulk of the grain. The properties of the actual and inert propellants are being measured, and a model is being developed to relate experiments on inert material to actual propellant. Possible methods to increase thermal gradients, crack propagation and initiation are also presented.

  12. The 2003 Goddard Rocket Replica Project: A Reconstruction of the World's First Functional Liquid Rocket System

    Science.gov (United States)

    Farr, R. A.; Elam, S. K.; Hicks, G. D.; Sanders, T. M.; London, J. R.; Mayne, A. W.; Christensen, D. L.

    2003-01-01

    As a part of NASA s 2003 Centennial of Flight celebration, engineers and technicians at Marshall Space Flight Center (MSFC), Huntsville, Alabama, in cooperation with the Alabama-Mississippi AIAA Section, have reconstructed historically accurate, functional replicas of Dr. Robert H. Goddard s 1926 first liquid- fuel rocket. The purposes of this project were to clearly understand, recreate, and document the mechanisms and workings of the 1926 rocket for exhibit and educational use, creating a vital resource for researchers studying the evolution of liquid rocketry for years to come. The MSFC team s reverse engineering activity has created detailed engineering-quality drawings and specifications describing the original rocket and how it was built, tested, and operated. Static hot-fire tests, as well as flight demonstrations, have further defined and quantified the actual performance and engineering actual performance and engineering challenges of this major segment in early aerospace history.

  13. Security Operations Curriculum Package: BS in Global Security and Intelligence Studies, Security Operations Management Track, Embry-Riddle Aeronautical University, Prescott, AZ. BS in Security Operations Management, Model Curriculum

    Science.gov (United States)

    2011-10-24

    that would bring you under the university‘s procedures for academic dishonesty . Papers that go beyond reportage or description and include an...Operations 2010: Curriculum and Academic Certification Guidelines for Undergraduate Degree Programs in Security Operations, Version 2.0.‖ These...Operations and Management Track to ERAU, Prescott. This academic year the GSIS Program is already teaching two of the new courses, and we are confident the

  14. Optimal Reference Strain Structure for Studying Dynamic Responses of Flexible Rockets

    Science.gov (United States)

    Tsushima, Natsuki; Su, Weihua; Wolf, Michael G.; Griffin, Edwin D.; Dumoulin, Marie P.

    2017-01-01

    In the proposed paper, the optimal design of reference strain structures (RSS) will be performed targeting for the accurate observation of the dynamic bending and torsion deformation of a flexible rocket. It will provide the detailed description of the finite-element (FE) model of a notional flexible rocket created in MSC.Patran. The RSS will be attached longitudinally along the side of the rocket and to track the deformation of the thin-walled structure under external loads. An integrated surrogate-based multi-objective optimization approach will be developed to find the optimal design of the RSS using the FE model. The Kriging method will be used to construct the surrogate model. For the data sampling and the performance evaluation, static/transient analyses will be performed with MSC.Natran/Patran. The multi-objective optimization will be solved with NSGA-II to minimize the difference between the strains of the launch vehicle and RSS. Finally, the performance of the optimal RSS will be evaluated by checking its strain-tracking capability in different numerical simulations of the flexible rocket.

  15. Scale Effects on Solid Rocket Combustion Instability Behaviour

    Directory of Open Access Journals (Sweden)

    David R. Greatrix

    2011-01-01

    Full Text Available The ability to understand and predict the expected internal behaviour of a given solid-propellant rocket motor under transient conditions is important. Research towards predicting and quantifying undesirable transient axial combustion instability symptoms necessitates a comprehensive numerical model for internal ballistic simulation under dynamic flow and combustion conditions. A numerical model incorporating pertinent elements, such as a representative transient, frequency-dependent combustion response to pressure wave activity above the burning propellant surface, is applied to the investigation of scale effects (motor size, i.e., grain length and internal port diameter on influencing instability-related behaviour in a cylindrical-grain motor. The results of this investigation reveal that the motor’s size has a significant influence on transient pressure wave magnitude and structure, and on the appearance and magnitude of an associated base pressure rise.

  16. Thermal rocketing and the Laser Geodynamic Satellite (LAGEOS-1)

    Energy Technology Data Exchange (ETDEWEB)

    Miller, W.A.

    1997-08-01

    This is the final report of a one-year, Laboratory Directed Research and Development (LDRD) project at the Los Alamos National Laboratory. LAGEOS is the most accurately tracked satellite in orbit. It is a totally passive, dense spherical satellite covered with 426 cube corner reflectors. Besides its great utility in measuring the Earth`s length of day and polar wobble, this satellite can be used to measure, for the first time, the general relativistic frame-dragging effect. Of the five dominant error sources in such an experiment, the largest one involves surface interaction of thermal forces (thermal rocketing) and its influence on the orbital nodal precession. The project objective was to enhance an already available theoretical model (computer code) developed at Los Alamos based on new optical-spin data obtained at the University of Maryland. The project objective was met and the enhanced code will serve as the new spin-dynamics model for future LAGEOS satellite missions.

  17. Artificial Intelligence and the High School Computer Curriculum.

    Science.gov (United States)

    Dillon, Richard W.

    1993-01-01

    Describes a four-part curriculum that can serve as a model for incorporating artificial intelligence (AI) into the high school computer curriculum. The model includes examining questions fundamental to AI, creating and designing an expert system, language processing, and creating programs that integrate machine vision with robotics and…

  18. Finding Order: Curriculum Theory and the Qualities of Museum Education

    Science.gov (United States)

    Vallance, Elizabeth

    2006-01-01

    Museum education is a field of practice that is guided effectively by traditions of practice addressing museums' purposes and expected audiences, and rarely explicitly refers to the numerous models of curriculum theory that are available to guide educational practice in the school setting. But curriculum models can be useful both for describing…

  19. Marketing Education Curriculum Guide.

    Science.gov (United States)

    Michigan State Univ., East Lansing. Coll. of Agriculture and Natural Resources Education Inst.

    This curriculum guide is intended to provide a common core of competencies from which to design an effective secondary marketing education program. Introductory materials include a definition of marketing education, objectives, outline of instructional content, and questions and answers regarding the curriculum guide. These practical materials are…

  20. Cosmetology. Secondary Curriculum Guide.

    Science.gov (United States)

    Moye, Michael D.; And Others

    This curriculum guide is designed to offer guidelines along with supporting resources and teaching ideas from which the local secondary instructor can extract a cosmetology curriculum that meets local needs. Following an outline of the philosophy and goals underlying state and local vocational education programs in Georgia, the purpose and…