Sample records for raytheon missile systems

  1. Ballistic Missile Defense System (BMDS)


    Estimate RDT&E - Research , Development, Test, and Evaluation SAR - Selected Acquisition Report SCP - Service Cost Position TBD - To Be Determined TY - Then...all ranges and in all phases of flight. Following guidance from the President, the Secretary of Defense approved the Ballistic Missile Defense (BMD...based Midcourse Defense (GMD) system to enhance our capability against Intercontinental Ballistic Missiles. We are currently sustaining 30

  2. Bayesian Missile System Reliability from Point Estimates


    OCT 2014 2. REPORT TYPE N/A 3. DATES COVERED - 4. TITLE AND SUBTITLE Bayesian Missile System Reliability from Point Estimates 5a. CONTRACT...Principle (MEP) to convert point estimates to probability distributions to be used as priors for Bayesian reliability analysis of missile data, and...illustrate this approach by applying the priors to a Bayesian reliability model of a missile system. 15. SUBJECT TERMS priors, Bayesian , missile

  3. Embedded Systems - Missile Detection/Interception

    Luis Cintron


    Full Text Available Missile defense systems are often related to major military resources aimed at shielding a specific region from incoming attacks. They are intended to detect, track, intercept, and destruct incoming enemy missiles. These systems vary in cost, efficiency, dependability, and technology. In present times, the possession of these types of systems is associated with large capacity military countries. Demonstrated here are the mathematical techniques behind missile systems which calculate trajectories of incoming missiles and potential intercept positions after initial missile detection. This procedure involved the use of vector-valued functions, systems of equations, and knowledge of projectile motion concepts.

  4. Quality and Reliability of Missile System

    Mr. Prahlada


    Full Text Available Missile system is a single-shot weapon system which requires very high quality and reliability. Therefore, quality and reliability have to be built into the system from designing to testing and evaluation. In this paper, the technological challenges encountered during development of operational missile system and the factors considered to build quality and reliability through the design, manufacture, assembly, testing and by sharing the knowledge with other aerospace agencies, industries and institutions, etc. have been presented.

  5. Acquisition of the Army Tactical Missile System Anti-Personnel/Anti-Materiel Block IA Program


    The Army Tactical Missile System Anti-PersonnellAnti-Materiel Block IA missile (Block IA) is a ground-launched missile system consisting of a surface-to-surface guided missile with an anti-personnel/anti-materiel warhead...

  6. Innovative pollution prevention program at Air Force owned Raytheon operated facility incorporating Russian technology

    Stallings, J.H.; Cepeda-Calderon, S.


    Air Force Plant 44 in Tucson, Arizona is owned by the Air Force and operated by Raytheon Missile Systems Company. A joint Air Force/Raytheon Pollution Prevention Team operates at AFP 44 with the ultimate goal to minimize or eliminate the use of hazardous substances. The team works together to uncover new technologies and methods that will replace chemicals used in the plant's missile manufacturing facilities. The program maximizes pollution prevention by first eliminating hazardous material use, then chemical recycling, next hazardous waste reduction and finally wastewater treatment and recycling. From fiscal years 1994 through 1997, nine pollution prevention projects have been implemented, totaling $2.6 million, with a payback averaging less than two years. A unique wastewater treatment method has been demonstrated as part of this program. This is electroflotation, a Russian technology which removes dispersed particles from liquid with gas bubbles obtained during water electrolysis. A unit was built in the US which successfully removed organic emulsions from wastewater. Operational units are planned for the removal of waste from waterfall paint booths. The pollution prevention joint team continues to be very active with two projects underway in FY 98 and two more funded for FY 99.

  7. Intelligent Design and Implementation of Missile Fire Control System

    XIE Chun-si; WANG Min-qing; LI Wei-hai; LIU Xi-zuo; JIN Liang-an


    Missile fire control system is the core of ship-based missile weapon system, whose safeguard levelhas direct relation with the attack ability of naval vessels. After a long period of deep investigation and research, it was found that, in one missile fire control system, there are such problems as single safeguard system, low ratio of cost to efficiency, etc. By adopting intelligent control techniques and many measures to multiple securities, the new type of assistant system is designed, some difficult problems are solved, such as fixed project channel and unitary means of missiles, which can make the equipment carry out combat mission reliably and continuously.

  8. Recent Advances in Antitank Guided Missile Systems

    N. R. Iyer


    Full Text Available The recent advances in tactical antitank guided missile (ATGM systems are discussed. The main driving factors for the technological advances towards realisation of third generation ATGM systems have been the more demanding operational needs of the user services and limitations of earlier generation ATGM systems. The tasks of system design, hardware realisation, integration, testing and qualification have become extremely challenging to meet these stringent operational requirements. The technologies required to be mobilised for meeting these operational requirements and performance envelope and satisfying the operational and logistics constraints are again very demanding. The high technology content and the high level of performance required out of the subsystems have led to the present generation missile systems. The evolution from the earlier generations to current systems has been briefly discussed. Imaging infrared (IIR and Millimetre wave (MMW guidance systems employed for achieving the fire and forget capability of the third generation ATGM are described with specific reference to progress achieved so far. Translating the mission requirements to preliminary system specifications is another area wherein an innovative approach only can lead to meet the multiple performance criteria. Performance growth profile and emerging trends in ATGM systems are also analysed.

  9. Dynamic Simulation for Missile Erection System


    In order to study the dynamic characteristics of the missile erection system, it can be considered as a rigid-flexible coupling multi-body system. Firstly, the actual system is abstracted as an equal and simplified one and then the forces applied to it are analyzed. Secondly, the rigid-flexible coupling dynamic simulation for erection system is accomplished by use of the system simulation software, for example Pro/E, ADAMS, ANSYS, MATLAB/Simulink, etc. Finally, having the aid of simulation results, the kinetic and dynamic characteristics of the flexible bodies in erection system are analyzed.The simulation considering the erection system as a rigid-flexible coupling system can provide valuable results to the research of its kinetic, dynamic and vibrational characteristics.

  10. Missile antenna pattern coordinate system and data formats


    Antenna performance data pertains to missile, space, and aerodynamic vehicles' transmitting or receiving antennas used with range data collection, missile trajectory measurements, impact predictions, communications, or flight termination systems. As used in this document, the terms missile space vehicle, airborne, and aerodynamic vehicle are synonymous. This standard is intended to cover antennas for telemetry, pulsed radar beacons, continuous wave (CW) transponders, communication transmitters and receivers, command control/flight termination, receivers/decoders, pseudo random noise (PRN) ranging systems, and the Global Positioning System.

  11. Information Management Principles Applied to the Ballistic Missile Defense System


    of a BMDS. From this, the Army produced the Nike- Zeus system comprised of four radars, the Zeus missile, and a computer fire control system (General...made the Nike- Zeus our first National Missile Defense (NMD) system named Sentinel. The architecture was to cover 14 locations, 10 of which were...fostered the database system and representation of data in a hierarchy (Galliers & Leidner, 2003). Soon the limits of hierarchies were identified and

  12. Space and Missile Systems Center Standard: Space Flight Pressurized Systems


    pressure and vehicle structural loads. The main propellant tank of a launch vehicle is a typical example. Pressurized System: A system that...SPACE AND MISSILE SYSTEMS CENTER STANDARD SPACE FLIGHT PRESSURIZED SYSTEMS APPROVED FOR PUBLIC RELEASE...Space Flight Pressurized Systems 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e. TASK NUMBER

  13. Analysis of Nonlinear Missile Guidance Systems Through Linear Adjoint Method

    Khaled Gamal Eltohamy


    Full Text Available In this paper, a linear simulation algorithm, the adjoint method, is modified and employed as an efficient tool for analyzing the contributions of system parameters to the miss - distance of a nonlinear time-varying missile guidance system model. As an example for the application of the linear adjoint method, the effect of missile flight time on the miss - distance is studied. Since the missile model is highly nonlinear and a time-varying linearized model is required to apply the adjoint method, a new technique that utilizes the time-reversed linearized coefficients of the missile as a replacement for the time-varying describing functions is applied and proven to be successful. It is found that, when compared with Monte Carlo generated results, simulation results of this linear adjoint technique provide acceptable accuracy and can be produced with much less effort.

  14. 2014 Assessment of the Ballistic Missile Defense System (BMDS)


    and necessary training aids and devices are not currently available and are not scheduled to become available for several years. Analyses of data...and Evaluation ( IOT &E) flight tests for the Aegis BMD 4.0 system and SM-3 Block IB missile. Outcome. INTERCEPT. The ship detected, tracked...missiles in a raid scenario. FTX-18 was the last of the three IOT &E test missions. Outcome. THREE SIMULATED INTERCEPTS. The ship detected, tracked

  15. Strapdown inertial systems applications for tactical missiles (stand-off missiles)



    Strapdown Inertial Systems (SDIS) are particularly well suited for tactical standoff missile applications. This certainty was made clear by several years of theoretical design work and trials. Initial theoretical work made wide use of parameters giving detailed definition of missile trajectories and motions as obtained from measurements made on weapon systems then in development or production. Sensors (principally gyroscopes) were laboratory tested. These preliminary design efforts led to selection of various technologies such as the laser gyro and the mechanical gyro, each being adapted to the weapon system in question. Share-out of functions between various equipment items was defined. Comparison of the advantages and disadvantages of these technologies shows that today the laser gyro is principally retained for high and medium range levels of precision, with the mechanical (spin-stabilized) gyro serving in the medium and low precision range. Since requirements are ever increasing in the fields of dynamic performance and robustness, it is here that most progress is expected.

  16. Electric Loading Simulation System for Missile Wings and Rudders

    QI Rong; LIN Hui; CHEN Ming


    The design and the realization of missile wings and rudders loading simulation system based on digital signal processor (DSP) TMS320LF2407 and direct torque control (DTC) servo driver ACS600 are discussed. The structure and opration principle for the system are presented. Speediness and elimination of superabundant torque are two key difficulties for electric loading simulation system. The method which can eliminate the superabundant torque is researched. Test results show the airflow resistance when missile wings and rudders are spreading can be rapidly simulated with high accuracy.


    DaiLongcheng; XuanYimin


    Anew method in system design of ejecting devices of missiles is first presented.Some important points are dis-cussed,which guid the research and development of new ejecting devices of missileg,amd provid the foundation flr thw design of mew ejecting device is provided.The system design includes the distribution of techmology specifica-tion,3-D solid modeling of ejecting devices of missiles im-ported from abroad,the design of pmeumatic device sys-tem,the design of ejecting mechanism system,the predic-tion of reliability and the experimental analysis,etc.

  18. Raytheon advanced pulse-tube cryocoolers

    Conrad, Ted; Yates, Ryan; Kuo, Daniel; Schaefer, Brian; Arnoult, Matt


    Since the 1970s, Raytheon has developed, built, tested and integrated high performance cryocoolers. Our versatile designs for single and multi-stage cryocoolers provide reliable operation for temperatures from 10 to 200 Kelvin with power levels ranging from 50 W to nearly 600 W. These cryocoolers incorporate clearance seals, flexure suspensions, hermetic housings and dynamic balancing to provide long service life and reliable operation in all relevant environments. Recently, Raytheon has developed an advanced regenerator technology capable of operating efficiently at high frequencies and outperforming traditional screen regenerators. The Raytheon Advanced Miniature (RAM-100) cryocooler, a flight packaged, high frequency, single stage pulse tube cooler with an integrated surge volume and inertance tube, has been designed for use with this regenerator. Design details and experimentally measured performance of two iterations of the RAM cryocooler are presented in this paper.

  19. Shipborne Laser Beam Weapon System for Defence against Cruise Missiles

    J.P. Dudeja


    Full Text Available Sea-skim~ing cruise missiles pose the greatest threat to a surface ship in the present-day war scenario. The convenitional close-in-weapon-systems (CIWSs are becoming less reliable against these new challenges requiring extremely fast reaction time. Naval Forces see a high energy laser as a feasible andjeffective directed energy weapon against sea-skimming antiship cruise missiles becauseof its .ability to deliver destructive energy at the speed of light on to a distant target. The paper comparesthe technology and capability of deuterium fluoride (DF and chemical-oxygen-iodine laser (COIL in effectively performing the role of a shipborne CIWS altainst sea-skimming missiles. Out of these twolasers, it is argued that DF laser wo.uld be more effective a,s a shipborne weapon for defence against sea-skimmin,g cruise missiles. Besides the high energy laser as the primary (killing laser, othersub-systems required in the complete weapon system would be: A beacon laser to sense phase distor'ions in the primary laser, adaptive optics to compensate the atmospheric distortions, beam-directing optics, illuminating lasers, IRST sensors, surveillance and tracking radars, interfacing system, etc.

  20. Hardware in Loop Simulation for Missile Guidance and Control Systems

    S. K. Chaudhuri


    Full Text Available The purpose of the guidance law is to determine appropriate missile flight path dynamics to achieve mission objective in an efficient manner based on navigation information. Today, guided missiles which are aerodynamically unstable or non-linear in all or part of the flight envelopes need control systems for stability as well as for steering. Many classical guidance and control laws have been used for tactical missiles with varying degrees of performance, complexity and seeker/sensor requirements. Increased accuracy requirements and more dynamic tactics of modern warfare demand improvement of performance which is a trade-off between sophisticated hardware and more sophisticated software. To avoid increase in cost by hardware sophistication, today's trend is to exploit new theoretical methods and low cost high speed microprocessor techniques. Missile test flights are very expensive. The missile system with its sophisticated software and hardware is not reusable after a test launch. Hardware-in-loop Simulation (HILS facilities and methodology form a well integrated system aimed at transforming a preliminary guidance and control system design to flight software and hardware with trajectory right from lift-off till its impact. Various guidance and control law studies pertaining to gathering basket and stability margins, pre-flight, post-flight analyses and validation of support systems have been carried out using this methodology. Nearly full spectrum of dynamically accurate six-degrees-of-freedom (6-DOF model of missile systems has been realised in the HILS scenario. The HILS facility allows interconnection of missile hardware in flight configuration. Pre-flight HILS results have matched fairly well with actual flight trial results. It was possible to detect many hidden defects in the onboard guidance and control software as well as in hardware during HILS. Deficiencies in model, like tail-wag-dog (TWD, flexibility, seeker dynamics and defects in

  1. Design and Implementation of One Missile Visual Simulation System Based on OpenGL

    GAO Ying; ZHANG Pu-zhao; PENG Yu-xin; HUANG Jian-guo


    The implementation of a missile's visual simulation system is explained that is developed with OpenGL(open graphic library) and the flight path and flight carriage in different stages of the missile are displayed. The establishment problems of the 3D scene are circumstantiated including the construction and redeployment of the model, creation of the virtual scene, setting of the multi-viewports and multi-windows etc. The missile's data driver, system flow, the modules and their mutual relations of the missile visual simulation system are discussed. The missile flight simulation results and effect of the scenes are given.

  2. Design and development of Propulsion System for Antitank Guided Missile

    T. Mohan Reddy


    Full Text Available A Propulsion system is designed and developed for the third generation antitank guided missile (ATGM. It consists of a separate booster and sustainer. Booster is ahead of sustainer, having four nozzles canted to the missile axis. Sustainer discharges through a supersonic blast tube. Low smoke, high energy nitramine propellant for this propulsion system developed by the High Energy Materials Research Laboratory (HEMRL, Pune, has been successfully flight-tested. The booster grain is tube-in-tube configuration with end inhibition and the sustainer grain is of end burning configuration. High strength aluminium alloy, HE-15, is used for rocket motor components. Glass-phenolic composite ablative material is used for thermal protection of motors and high density graphite is used for nozzle throats. The design considerations and approach, including grain configuration, nozzle, and ignitersare briefly discussed. The propulsion system has been extensively tested in static tests and in flights, establishing the satisfactory performance of the system.

  3. 44th Annual Gun and Missile Systems Conference and Exhibition


    Cup and Detonator Rocket Motor • End-Burning with Centerport Inhibitor • SAA -139 Propellant • Titanium Beta-C Rocket Motor Case TFA (Tail Fin Assembly...FY09 Weapons Funding Allocations FMS 8% Support 6% Development 13% Other to include Army, USCG, DFS 19% Procurement 54% Page 9 UNCLASSIFIED Raytheon ERP ...WR/2 ‘Yesterday’s’ Problem Today - Changing Operational Environment Raytheon ERP /WR/2 Self Defenses lf f Area Defenses r f Outer Defenses Combat Air

  4. Launch Stabilisation System for Vertical Launch of a Missile

    K. Sreekumar


    Full Text Available The launch platform stabilisation control system is a roll-pitch stabilised platform for the vertical launch of a missile from a naval ship. Stabilisation of the launch platform is achievedwith the help of embedded controllers and electro-hydraulic servo control system. The launch platform is stabilised wrt true horizontal with a 2-axis (roll and pitch stabilisation systemconsisting of a gimbal and a set of three high-pressure servo hydraulic actuators. The control system uses rate gyro and tilt sensor feedbacks for stabilising the platform. This paper outlines the details of the launch platform stabilisation control system, results of digital simulation, and the performance during sea trials.

  5. Study on combat effectiveness of air defense missile weapon system based on queuing theory

    Zhao, Z. Q.; Hao, J. X.; Li, L. J.


    Queuing Theory is a method to analyze the combat effectiveness of air defense missile weapon system. The model of service probability based on the queuing theory was constructed, and applied to analyzing the combat effectiveness of "Sidewinder" and "Tor-M1" air defense missile weapon system. Finally aimed at different targets densities, the combat effectiveness of different combat units of two types' defense missile weapon system is calculated. This method can be used to analyze the usefulness of air defense missile weapon system.

  6. Study on Missile Intelligent Fault Diagnosis System Based on Fuzzy NN Expert System


    In order to study intelligent fault diagnosis methods based on fuzzy neural network (NN) expert systemand build up intelligent fault diagnosis for a type of mis-sile weapon system, the concrete implementation of a fuzzyNN fault diagnosis expert system is given in this paper. Based on thorough research of knowledge presentation, theintelligent fault diagnosis system is implemented with artificial intelligence for a large-scale missile weapon equipment.The method is an effective way to perform fuzzy fault diagnosis. Moreover, it provides a new way of the fault diagnosisfor large-scale missile weapon equipment.

  7. Active infrared systems: possible roles in ballistic missile defense?

    Paleologue, A.


    Active Infra-Red (IR) systems developed in the past ten years are now available for missile defense applications. The main purpose of this paper is to describe the advantages an active IR system could offer to a ballistic missile defense (BMD). The active IR system considered in this paper is a LIDAR (LIght Detection And Ranging) system. Historically, the Lincoln Laboratory in the USA began using lasers in the early 1960's. The initial applications included the development of a LIDAR system enabling the measurement of the distance between the earth and the moon in 1962. Satellite tracking using LIDAR began early in 1973. Today, technological developments, with the miniaturization of systems and increased performance levels, have enabled new ambitious projects such as the Discrimination Interceptor Technology Program (DITP) program started in 1998 and the use of LIDAR to help in the discrimination of future exo-atmospheric interceptors within the framework of BMD. The first part of this paper presents the possible contribution of LIDAR to BMD: the main roles, objectives, and strategic advantages. The second part gives a brief overview of the technological features of a generic LIDAR instrument, rapidly addressing laser sources, detectors, optics and electronics. Finally, a modeling of an IR LIDAR system, limited solely to direct detection, and an estimation of performance levels will be presented. A list of possible IR active discriminators will be then presented on the basis of the previous analysis and proposed as new constraints in the design of discrete objects.

  8. The Effectiveness of the U.S. Missile Defense Capabilities as a Deterrent to the North Korean Missile Threat


    THE U.S. MISSILE DEFENSE CAPABILITIES AS A DETERRENT TO THE NORTH KOREAN MISSILE THREAT by Issac G. Gipson December 2007 Thesis Advisor...SUBJECT TERMS Missile Deterrence, Missile Defense , North Korean Missile Threat, North Korean Missile Systems, U.S. Missile Defense Capabilities, 16...19 III. CURRENT MISSILE DEFENSE ANALYSIS AGAINST NORTH KOREAN MISSILE THREAT

  9. Parametric control systems design with applications in missile control

    DUAN GuangRen; YU HaiHua; TAN Feng


    This paper considers parametric control of high-order descriptor linear systems via proportional plus derivative feedback.By employing general parametric solutions to a type of so-called high-order Sylvester matrix equations,complete parametric control approaches for high-order linear systems are presented.The proposed approaches give simple complete parametric expressions for the feedback gains and the closed-loop eigenvector matrices,and produce all the design degrees of freedom.Furthermore,Important special cases are particularly treated.Based on the proposed parametric design approaches,a parametric method for the gain-scheduling controller design of a linear time-varying system is proposed and the design of a BTT missile autopilot is carried out.The simulation results show that the method is superior to the traditional one in sense of either global stability or system performance.

  10. Ballistic Missile Defense System Transition and Transfer Process from Missile Defense Agency to the Army - Innovative or Dysfunctional?


    initiating development of the nuclear-capable Nike Zeus ABM interceptor, intended to destroy an incoming enemy warhead with an airborne nuclear explosion. The...intercept an incoming warhead using the nuclear-tipped Nike Zeus missile. Although DoD cancelled the Nike Zeus system due to technical and operational...budgeting, and initiate issue resolution through the Army/MDA Board of Directors to ensure adequate representation of the Service’s interests

  11. Raytheon RSP2 Cryocooler Low Temperature Testing and Design Enhancements

    Hon, R. C.; Kirkconnell, C. S.; Shrago, J. A.


    The High Capacity Raytheon Stirling/Pulse Tube Hybrid 2-Stage cryocooler (HC-RSP2) was originally developed to provide simultaneous cooling at temperatures of 85 K and 35 K. During testing performed in 2008 it was demonstrated that this stock-configuration cryocooler is capable of providing significant amounts of heat lift at 2nd stage temperatures as low as 12 K, and modeling indicated that minor changes to the 2nd stage inertance tube/surge volume setup could yield improved performance. These changes were implemented and the cooler was successfully retested, producing >350 mW of heat lift at 12 K. A comprehensive redesign of the system has been performed, the result of which is a robust 2-stage cryocooler system that is intended to efficiently produce relatively large amounts of cooling at 2nd stage temperatures system redesign. Expected performance, mass and packaging volume are addressed.

  12. Making sense of ballistic missile defense: an assessment of concepts and systems for U.S. boost-phase missile defense in comparison to other alternatives

    Division on Engineering and Physical Sciences; National Research Council; Naval Studies Board


    "The Committee on an Assessment of Concepts and Systems for U.S. Boost-Phase Missile Defense in Comparison to Other Alternatives set forth to provide an assessment of the feasibility, practicality, and affordability of U.S...

  13. Steady Fault Characteristic Analysis of a Missile Power System Based on a Differential Evolution Algorithm

    XU Zhi-gao; GUAN Zheng-xi; MA Jing


    The differential evolution (DE) algorithm is applied to solving the models' equations of a whole missile power system, and the steady fault characteristics of the whole system are analyzed. The DE algorithm is robust, requires few control variables, is easy to use and lends itself very well to parallel computation. Calculation results indicate that the DE algorithm simulates faults of a missile power system very well.

  14. Solar-blind ultraviolet optical system design for missile warning

    Chen, Yu; Huo, Furong; Zheng, Liqin


    Solar-blind region of Ultraviolet (UV) spectrum has very important application in military field. The spectrum range is from 240nm to 280nm, which can be applied to detect the tail flame from approaching missile. A solar-blind UV optical system is designed to detect the UV radiation, which is an energy system. iKon-L 936 from ANDOR company is selected as the UV detector, which has pixel size 13.5μm x 13.5 μm and active image area 27.6mm x 27.6 mm. CaF2 and F_silica are the chosen materials. The original structure is composed of 6 elements. To reduce the system structure and improve image quality, two aspheric surfaces and one diffractive optical element are adopted in this paper. After optimization and normalization, the designed system is composed of five elements with the maximum spot size 11.988μ m, which is less than the pixel size of the selected CCD detector. Application of aspheric surface and diffractive optical element makes each FOV have similar spot size, which shows the system almost meets the requirements of isoplanatic condition. If the focal length can be decreased, the FOV of the system can be enlarged further.

  15. 15 CFR 744.3 - Restrictions on Certain Rocket Systems (including ballistic missile systems and space launch...


    ... Vehicles (including cruise missile systems, target drones and reconnaissance drones) End-Uses. 744.3... missile systems, target drones and reconnaissance drones) End-Uses. (a) General prohibition. In addition... transfer (in-country) you know that the item: (1) Will be used in the design, development, production...

  16. An affinity-directed protein missile system for targeted proteolysis

    Fulcher, Luke J.; Macartney, Thomas; Bozatzi, Polyxeni; Hornberger, Annika; Rojas-Fernandez, Alejandro


    The von Hippel–Lindau (VHL) protein serves to recruit the hypoxia-inducible factor alpha (HIF1α) protein under normoxia to the CUL2 E3 ubiquitin ligase for its ubiquitylation and degradation through the proteasome. In this report, we modify VHL to engineer an affinity-directed protein missile (AdPROM) system to direct specific endogenous target proteins for proteolysis in mammalian cells. The proteolytic AdPROM construct harbours a cameloid anti-green fluorescence protein (aGFP) nanobody that is fused to VHL for either constitutive or tetracycline-inducible expression. For target proteins, we exploit CRISPR/Cas9 to rapidly generate human kidney HEK293 and U2OS osteosarcoma homozygous knock-in cells harbouring GFP tags at the VPS34 (vacuolar protein sorting 34) and protein associated with SMAD1 (PAWS1, aka FAM83G) loci, respectively. Using these cells, we demonstrate that the expression of the VHL-aGFP AdPROM system results in near-complete degradation of the endogenous GFP-VPS34 and PAWS1-GFP proteins through the proteasome. Additionally, we show that Tet-inducible destruction of GFP-VPS34 results in the degradation of its associated partner, UVRAG, and reduction in levels of cellular phosphatidylinositol 3-phosphate. PMID:27784791

  17. Missile Captive Carry Monitoring and Helicopter Identification Using a Capacitive Microelectromechanical Systems Accelerometer

    Hatchell, Brian K.; Mauss, Fredrick J.; Amaya, Ivan A.; Skorpik, James R.; Silvers, Kurt L.; Marotta, Steve


    Military missiles are exposed to many sources of mechanical vibration that can affect system reliability, safety, and mission effectiveness. The U. S. Army Aviation and Missile Research Development and Engineering Center (AMRDEC) has been developing missile health monitoring systems to assess and improve reliability, reduce life cycle costs, and increase system readiness. One of the most significant exposures to vibration occurs when the missile is being carried by a helicopter or other aviation platform, which is a condition known as captive carry. Recording the duration of captive carry exposure during the missile’s service life can enable the implementation of predictive maintenance and resource management programs. Since the vibration imparted by each class of helicopter varies in frequency and amplitude, tracking the vibration exposure from each helicopter separately can help quantify the severity and harmonic content of the exposure. Under the direction of AMRDEC staff, engineers at the Pacific Northwest National Laboratory have developed a Captive Carry Health Monitor (CCHM) for the Hellfire II missile. The CCHM is an embedded usage monitoring device installed on the outer skin of the Hellfire II missile to record the cumulative hours the host missile has been in captive carry mode. To classify the vibration by class of helicopter, the CCHM analyzes the amplitude and frequency content of the vibration with the Goertzel algorithm to detect the presence of distinctive rotor harmonics. Cumulative usage data are accessible in theater from an external display; monthly usage histograms are accessible through an internal download connector. This paper provides an overview of the CCHM electrical and package design, describes field testing and data analysis techniques used to monitor captive carry identify and the class of helicopter, and discusses the potential application of missile health and usage data for real-time reliability analysis and fleet management.

  18. Advances in LADAR Components and Subsystems at Raytheon

    Jack, Michael; Chapman, George; Edwards, John; McKeag, William; Veeder, Tricia; Wehner, Justin; Roberts, Tom; Robinson, Tom; Neisz, James; Andressen, Cliff; hide


    Raytheon is developing NIR sensor chip assemblies (SCAs) for scanning and staring 3D LADAR systems. High sensitivity is obtained by integrating high performance detectors with gain, i.e., APDs with very low noise Readout Integrated Circuits (ROICs). Unique aspects of these designs include: independent acquisition (non-gated) of pulse returns, multiple pulse returns with both time and intensity reported to enable full 3D reconstruction of the image. Recent breakthrough in device design has resulted in HgCdTe APDs operating at 300K with essentially no excess noise to gains in excess of 100, low NEP <1nW and GHz bandwidths and have demonstrated linear mode photon counting. SCAs utilizing these high performance APDs have been integrated and demonstrated excellent spatial and range resolution enabling detailed 3D imagery both at short range and long ranges. In the following we will review progress in real-time 3D LADAR imaging receiver products in three areas: (1) scanning 256 x 4 configuration for the Multi-Mode Sensor Seeker (MMSS) program and (2) staring 256 x 256 configuration for the Autonomous Landing and Hazard Avoidance Technology (ALHAT) lunar landing mission and (3) Photon-Counting SCAs which have demonstrated a dramatic reduction in dark count rate due to improved design, operation and processing.

  19. System Architecture for Anti-Ship Ballistic Missile Defense (ASBMD)

    Hobgood, Jean; Madison, Kimberly; Pawlowski, Geoffrey; Nedd, Steven.; Roberts, Michael; Rumberg, Paige


    Approved for public release; distribution is unlimited. Recent studies suggest that China is developing a new class of ballistic missiles that can be used against moving targets, such as ships. One such technology is anticipated to cover a range of 2,000 kilometers and operate at a speed of Mach 10. The threat is also capable of maneuvering both during the midcourse and terminal flight phases for the purposes of guidance, target acquisition, and countermeasures. This threat could greatl...

  20. Digital Array Radar for Ballistic Missile Defense and Counter-Stealth Systems Analysis and Parameter Tradeoff Study


    Missile BMD Ballistic Missile Defense CAS Computer Algebra System CDD Capability Development Document CONOPS Concept of Operations CONUS Continental...this section. Analysis and calculations described in this section were conducted using Waterloo Maple® 7 Computer Algebra System (CAS). Initially...When two or more electromagnetic waves combine, their electric fields are integrated vectorially at each point in space for any

  1. Successful hardware-in-the-loop support of the Longbow/HELLFIRE modular missile system

    Ray, Jerry A.; Larson, Gerald A.; Terry, John E.


    The Air-to-Ground Missiles Systems (AGMS) Project Management Office (PMO) chose to invest in hardware-in-the-loop (HWIL) simulation as an integral part of their Longbow/HELLFIRE (Helicopter Launched, Fire-and-Forget) Modular Missile System program throughout the development and production phases. This investment has resulted in two HWIL simulations, developed by the U.S. Army Aviation and Missile Command (AMCOM) Missile Research Development and Engineering Center, that have had unprecedented success in program support from the early development through production phases. The Millimeter Simulation System 1 (MSS-1) facility is capable of edge-of- the-envelope performance analysis and verification using high- fidelity target, background, and countermeasures signature modeling. The System Test/Acceptance Facility (STAF), developed in partnership with Redstone Technical Test Center, tests full-up missiles for production lot acceptance. Between these two facilities, HWIL simulation is responsible for pre- flight confidence testing of missile hardware and software, software independent verification and validation (IV&V) testing, comprehensive performance evaluation, component verification, production lot acceptance, and data gathering for the shelf life extension program. One payoff of the MSS-1 HWIL investment has been an extremely effective flight test program with MSS-1 receiving credit for saving three flight tests and documenting over 40 failure modes. With the advent of the Performance Based Specification, the MSS-1 has become involved in continuous verification of high level specifications since contractor controlled, low-level specifications are subject to change. The STAF has saved 8 million annually through providing a non-destructive lot acceptance-testing paradigm, and further benefited the production phase by discovering three production problems. This paper will highlight the innovative uses of HWIL simulation as utilized in the Longbow/HELLFIRE program and

  2. Ballistic Missile Defense System (BMDS) Programmatic Environmental Impact Statement


    for decommissioning the BMDS to prot(lct the Uruted ~tatoo lU.~.J . ns depbyed forces . friends. and aUlas hom b~Uistic missile throats. The...intcr~contincmal balh:. tic 7) The President would, m reaffirm the entire L’l’- de\\’cl<I•Pmcn:, human rigl:ts ~;caic. leader the ratitlcatlon...aspi."Ct’< oft he Balli~ tic Miss1k DetCnsc (BMD) pwgrarn. Acid rain; The MDA ihcl:·noti..’S i:1 the ?EIS the pn:.sibility cfa..:id rain cuuseC

  3. 基于HLA的导弹仿真系统%Missile simulation system based on HLA

    王利; 赵振南; 张亮


    计算机仿真是解决导弹装备研发过程中遇到难题的有效方法.设计了基于高层体系结构(HLA)分布式协议的仿真框架,给出了搭建系统的实施方案,具体介绍了系统联邦成员的构成及功能,分析设计了主要联邦成员的对象类和交互类,最后给出了整个系统的仿真流程及主要代码实现.该系统是一个模块化、通用化、易扩展、形象直观的导弹仿真系统,可以进行多种想定条件下导弹飞行仿真和性能评估,为导弹装备的论证、定型、验证提供了支撑平台.%The computer simulation is an effective way to solve the missile R&D process problems encountered.The article designs the simulation framework based on High Level Architecture (HLA),gives out the build system solutions,introduces the structure and function of the system of the federal member,analyzes and designs the main federal members of the object class and interaction class,finally present the simulation process and code implementation of the entire system.The system is a modular,extensible,general-purpose,image intuitive missile simulation system,can do many kinds of scenario conditions missile flight simulation and performance evaluation for missile equipment,provides support platform for missile equipment demonstration,qualitative and verify.

  4. Advanced regenerator testing in the Raytheon dual-use cryocoolerr

    Schaefer, B. R.; Bellis, L.; Ellis, M. J.; Conrad, T. J. [Raytheon Space and Airborne Systems 2000 E. El Segundo Blvd., El Segundo, CA 90245 (United States)


    Significant progress has been made on the Raytheon low cost space cryocooler called the Dual-Use Cryocooler (DUC). Most notably, the DUC has been integrated and tested with an advanced regenerator. The advanced regenerator is a drop-in replacement for stainless steel screens and has shown significant thermodynamic performance improvements. This paper will compare the performance of two different regenerators and explain the benefits of the advanced regenerator.

  5. Optical flow based guidance system design for semi-strapdown image homing guided missiles

    Huang Lan


    Full Text Available This paper focuses mainly on semi-strapdown image homing guided (SSIHG system design based on optical flow for a six-degree-of-freedom (6-DOF axial-symmetric skid-to-turn missile. Three optical flow algorithms suitable for large displacements are introduced and compared. The influence of different displacements on computational accuracy of the three algorithms is analyzed statistically. The total optical flow of the SSIHG missile is obtained using the Scale Invariant Feature Transform (SIFT algorithm, which is the best among the three for large displacements. After removing the rotational optical flow caused by rotation of the gimbal and missile body from the total optical flow, the remaining translational optical flow is smoothed via Kalman filtering. The circular navigation guidance (CNG law with impact angle constraint is then obtained utilizing the smoothed translational optical flow and position of the target image. Simulations are carried out under both disturbed and undisturbed conditions, and results indicate the proposed guidance strategy for SSIHG missiles can result in a precise target hit with a desired impact angle without the need for the time-to-go parameter.

  6. Modular Open System Architecture for Reducing Contamination Risk in the Space and Missile Defense Supply Chain

    Seasly, Elaine


    To combat contamination of physical assets and provide reliable data to decision makers in the space and missile defense community, a modular open system architecture for creation of contamination models and standards is proposed. Predictive tools for quantifying the effects of contamination can be calibrated from NASA data of long-term orbiting assets. This data can then be extrapolated to missile defense predictive models. By utilizing a modular open system architecture, sensitive data can be de-coupled and protected while benefitting from open source data of calibrated models. This system architecture will include modules that will allow the designer to trade the effects of baseline performance against the lifecycle degradation due to contamination while modeling the lifecycle costs of alternative designs. In this way, each member of the supply chain becomes an informed and active participant in managing contamination risk early in the system lifecycle.

  7. Raytheon's next generation compact inline cryocooler architecture

    Schaefer, B. R.; Bellis, L.; Ellis, M. J.; Conrad, T. [Raytheon Space and Airborne Systems, 2000 E. El Segundo Blvd., El Segundo, CA 90245 (United States)


    Since the 1970s, Raytheon has developed, built, tested and integrated high performance cryocoolers. Our versatile designs for single and multi-stage cryocoolers provide reliable operation for temperatures from 10 to 200 Kelvin with power levels ranging from 50 W to nearly 600 W. These advanced cryocoolers incorporate clearance seals, flexure suspensions, hermetic housings and dynamic balancing to provide long service life and reliable operation in all relevant environments. Today, sensors face a multitude of cryocooler integration challenges such as exported disturbance, efficiency, scalability, maturity, and cost. As a result, cryocooler selection is application dependent, oftentimes requiring extensive trade studies to determine the most suitable architecture. To optimally meet the needs of next generation passive IR sensors, the Compact Inline Raytheon Stirling 1-Stage (CI-RS1), Compact Inline Raytheon Single Stage Pulse Tube (CI-RP1) and Compact Inline Raytheon Hybrid Stirling/Pulse Tube 2-Stage (CI-RSP2) cryocoolers are being developed to satisfy this suite of requirements. This lightweight, compact, efficient, low vibration cryocooler combines proven 1-stage (RS1 or RP1) and 2-stage (RSP2) cold-head architectures with an inventive set of warm-end mechanisms into a single cooler module, allowing the moving mechanisms for the compressor and the Stirling displacer to be consolidated onto a common axis and in a common working volume. The CI cryocooler is a significant departure from the current Stirling cryocoolers in which the compressor mechanisms are remote from the Stirling displacer mechanism. Placing all of the mechanisms in a single volume and on a single axis provides benefits in terms of package size (30% reduction), mass (30% reduction), thermodynamic efficiency (>20% improvement) and exported vibration performance (≤25 mN peak in all three orthogonal axes at frequencies from 1 to 500 Hz). The main benefit of axial symmetry is that proven balancing

  8. Average-passage simulation of counter-rotating propfan propulsion systems as applied to cruise missiles

    Mulac, Richard A.; Schneider, Jon C.; Adamczyk, John J.


    Counter-rotating propfan (CRP) propulsion technologies are currently being evaluated as cruise missile propulsion systems. The aerodynamic integration concerns associated with this application are being addressed through the computational modeling of the missile body-propfan flowfield interactions. The work described in this paper consists of a detailed analysis of the aerodynamic interactions between the control surfaces and the propfan blades through the solution of the average-passage equation system. Two baseline configurations were studied, the control fins mounted forward of the counter-rotating propeller and the control fins mounted aft of the counter-rotating propeller. In both cases, control fin-propfan separation distance and control fin deflection angle were varied.

  9. 40th Annual Armament Systems: Guns-Ammunition-Rockets-Missiles Conference and Exhibition


    PM] Abraham Overview, Mr. Robert Daunfeldt, Bofors Defence Summary Overview of an Advanced 2.75 Hypervelocity Weapon, Mr. Larry Bradford, CAT Flight...Engineer Tank Ammunition Directorate - IMI Ammunition Group A105/120/125 mm PELE Firing Results, Dr. Lutz Börngen, Rheinmetall Wafe Munition Line Of Sight...Missiles & Rockets Critical Asset Defense - ABRAHAM Rocket Assisted Projectile Mr. Robert Daunfeldt, Bofors Defence Hypervelocity Propulsion System

  10. Space and Missile Systems Center Tailoring: Tailoring Instructions for MIL-STD-882E



  11. Remote control canard missile with a free-rolling tail brake torque system

    Blair, A. B., Jr.


    An experimental wind-tunnel investigation has been conducted at supersonic Mach numbers to determine the static aerodynamic characteristics of a cruciform canard-controlled missile with fixed and free-rolling tail-fin afterbodies. Mechanical coupling effects of the free-rolling tail afterbody were investigated using an electronic/electromagnetic brake system that provides arbitrary tail-fin brake torques with continuous measurements of tail-to-mainframe torque and tail-roll rate. Results are summarized to show the effects of fixed and free-rolling tail-fin afterbodies that include simulated measured bearing friction torques on the longitudinal and lateral-directional aerodynamic characteristics.

  12. Space and Missile Systems Center Compliance Specifications and Standards


    identifying the necessary technical activities, products , and attributes, rather than specific process models or methods. The SMC compliance standards...update to SMC 2013 list. U SAE AS9100 Rev. C Quality Systems – Aerospace – Model for Quality Assurance in Design, Development, Production ...practices and addresses counterfeit parts. N 36 SMC Standard SMC-S-009 Parts, Materials, & Processes Control Program for Space and Launch Vehicles 2009

  13. 2015 Assessment of the Ballistic Missile Defense System (BMDS)


    performance and test adequacy of the BMDS, its four autonomous BMDS systems, and its sensor/command and control architecture . The four autonomous BMDS...Patriot. The Command and Control, Battle Management, and Communications (C2BMC) element anchors the sensor/command and control architecture . This...distributed ground testing in USPACOM in support of the second AN/TPY-2 (FBM) radar fielding to Japan in 2014. Flight testing with C2BMC control

  14. The Regional Dimension of Romania's Participation to the Anti-Missile Defense System

    Florin Iftode


    Full Text Available The current security environment is characterized by a high degree of instability and unpredictability, through the manifestation of new risks and threats, especially those with asymmetrical nature, by redefining the relations between the great powers, and increasing freedom of action of the regional actors (state and non-state. At the international level, the end of the Cold War has led to a fragmentation of efforts in the security field, with direct implications on the need for further efforts of the international community coordination. In this era of profound change and transformation it is not possible the adoption of an isolationist policy of security, but only in a broader context of interdependencies and relationships between general trends, threats or challenges specific to a particular area or geographic areas. Swift operationalization of the anti-missile system will strengthen the national security both directly, through the protection it provides for the entire national territory, and indirectly, as the system will have a deterrent important role, able to mitigate risks of possible attacks by ballistic missiles. The role of deterrence will remove the risk of attack against any Allied territory on which, by virtue of membership in NATO and obligations involved according to article 5 of the Washington Treaty, Romania has also responsibilities.

  15. Global stabilizing controller design for linear time-varying systems and its application on BTT missiles


    A parametric method for the gain-scheduled controller design of a linear time-varying system is given. According to the proposed scheduling method, the performance between adjacent characteristic points is preserved by the invariant eigenvalues and the gradually varying eigenvectors. A sufficient stability criterion is given by constructing a series of Lyapunov functions based on the selected discrete characteristic points. An important contribution is that it provides a simple and feasible approach for the design of gain-scheduled controllers for linear time-varying systems, which can guarantee both the global stability and the desired closed-loop performance of the resulted system. The method is applied to the design of a BTT missile autopilot and the simulation results show that the method is superior to the traditional one in sense of either global stability or system performance.

  16. Simulation of Missile Autopilot with Two-Rate Hybrid Neural Network System

    ASTROV, I.


    Full Text Available This paper proposes a two-rate hybrid neural network system, which consists of two artificial neural network subsystems. These neural network subsystems are used as the dynamic subsystems controllers.1 This is because such neuromorphic controllers are especially suitable to control complex systems. An illustrative example - two-rate neural network hybrid control of decomposed stochastic model of a rigid guided missile over different operating conditions - was carried out using the proposed two-rate state-space decomposition technique. This example demonstrates that this research technique results in simplified low-order autonomous control subsystems with various speeds of actuation, and shows the quality of the proposed technique. The obtained results show that the control tasks for the autonomous subsystems can be solved more qualitatively than for the original system. The simulation and animation results with use of software package Simulink demonstrate that this research technique would work for real-time stochastic systems.

  17. 15 CFR 742.5 - Missile technology.


    ... to the design, development, production, or use of missiles. These items are identified in ECCNs on... air vehicle systems (including cruise missile systems, target drones, and reconnaissance drones... the design, development, production, or use of missiles; (iii) The capabilities and objectives of...

  18. Dynamic planning of navigation determinations of airspace and missile objects in an automated flight test control system

    Lovtsov, D. A.; Karpov, D. S.


    This study considers an approach to planning navigation determinations of airspace and missile objects in the course of preparing for and carrying out an active flight test in an automated flight test control system. The approach is based on special information and mathematical software. The performance indices of the navigation determination subsystem are studied. Results of simulated modeling are provided.

  19. Software system requirements for the Army Tactical Missile System (ATACMS) End-To-End System using the Computer Aided Prototyping System (CAPS) multi-file approach

    Angrisani, David Stuart; Whitbeck, George Steven.


    The Department of Defense (DOD) is seeking software system requirements for the Army Tactical Missile System (ATACMS) End to End System, which comprises both ATACMS and all sensors, links, and command centers which enable integration across system and service boundaries. The complexity, multiple interfaces, and joint nature of planned ATACMS operations demands accurate specification of software system requirements. DOD also desires automated tools capable of developing rapid prototypes to ass...

  20. Modeling and Simulation of Control Actuation System with Fuzzy-PID Logic Controlled Brushless Motor Drives for Missiles Glider Applications.

    Muniraj, Murali; Arulmozhiyal, Ramaswamy


    A control actuation system has been used extensively in automotive, aerospace, and defense applications. The major challenges in modeling control actuation system are rise time, maximum peak to peak overshoot, and response to nonlinear system with percentage error. This paper addresses the challenges in modeling and real time implementation of control actuation system for missiles glider applications. As an alternative fuzzy-PID controller is proposed in BLDC motor drive followed by linkage mechanism to actuate fins in missiles and gliders. The proposed system will realize better rise time and less overshoot while operating in extreme nonlinear dynamic system conditions. A mathematical model of BLDC motor is derived in state space form. The complete control actuation system is modeled in MATLAB/Simulink environment and verified by performing simulation studies. A real time prototype of the control actuation is developed with dSPACE-1104 hardware controller and a detailed analysis is carried out to confirm the viability of the proposed system.

  1. An analysis of Common Missile and TOW 2B using the Janus combat simulation


    Approved for public release; distribution is unlimited. The US Army is currently developing a new close combat missile system, Common Missile, to replace the aging Tubelaunched, Optically-tracked, Wire-guided (TOW 2B) and HELLFIRE missile systems. The Common Missile will have a greater range and improved target acquisition capability over the current missile systems. The purpose of this thesis is to compare the performance of the Common Missile and the TOW 2B missile in a simulated ground ...

  2. Three-time rapid transfer alignment method of SINS/GPS navigation system of high-speed marine missile

    WANG Si; DENG Zheng-long; SU Ling-feng


    The transfer alignment of SINS/GPS navigation system of a high-speed marine missile was investiga-ted. With the help of the big acceleration of a high-speed missile, the transfer alignment was changed into a three-time alignment. The azimuth alignment was coarsely finished in 10s in the first time alignment, the hori-zontal alignment was accurately and rapidly finished in the second time alignment, and the azimuth alignment was accurately finished in the third time alignment. Because the second time alignment and the third time align-ment were finished by GPS after the missile was launched, the horizontal alignment and the second azimuth a-lignment got rid of the influence of the warship body flexibility deforming. The precision and rapidity of the hori-zontal alignment were prominently increased due to the vertical launch of the marine missile with the big accel-eration. Simulation verifies the effectiveness of the proposed alignment method.

  3. Real-time target motion animation for missile warning system testing

    Perkins, Timothy; Sundberg, Robert; Cordell, John; Tun, Zaw; Owen, Mark


    The QUick Image Display (QUID) model accurately computes and displays radiance images of aircraft and other objects, generically called targets, at animation rates while the target undergoes unrestricted flight. Animation rates are obtained without sacrificing radiometric accuracy by using two important innovations. First, QUID has been implemented using the Open Scene Graph (OSG) library, an open-source, cross-platform 3-D graphics toolkit for the development of high performance graphics applications in the fields of visual simulation, virtual reality, scientific visualization and modeling. Written entirely in standard C++ and fully encapsulating OpenGL and its extensions, OSG exploits modern graphics hardware to perform the computationally intensive calculations such as hidden surface removal, 3-D transformations, and shadow casting. Second, a novel formulation for reflective/emissive terms enables rapid and accurate calculation of per-vertex radiance. The bi-directional reflectance distribution function (BRDF) is a decomposed into separable spectral and angular functions. The spectral terms can be pre-calculated for a user specified band pass and for a set of target-observer ranges. The only BRDF calculations which must be performed during target motion involves the observer-target-source angular functions. QUID supports a variety of target geometry files and is capable of rendering scenes containing high level-of-detail targets with thousands of facets. QUID generates accurate visible to LWIR radiance maps, in-band and spectral signatures. The newest features of QUID are illustrated with radiance and apparent temperature images of threat missiles as viewed by an aircraft missile warning system.

  4. Anukalpana 2.0: A Performance Evaluation Software Package for Akash Surface to Air Missile System

    G.S. Raju


    Full Text Available Abstract : "An air defence system is a complex dynamic system comprising sensors, control centres, launchers and missiles. Practical evaluation of such a complex system is almost impossible and very expensive. Further, during development of the system, there is a necessity to evaluate certain design characteristics before it is implemented. Consequently, need arises for a comprehensive simulation package which will simulate various subsystems of the air defence weapon system, so that performance of the system can be evaluated. With the above objectives in mind, a software package, called Anukalpana 2.0, has been developed. The first version of the package was developed at the Indian Institute of Science, Bangalore. This program has been subsequently updated. The main objectives of this package are: (i evaluation of the performance of Akash air defence system and other similar air defence systems against any specified aerial threat, (ii investigation of effectiveness of the deployment tactics and operational logic employed at the firing batteries and refining them, (iii provision of aid for refining standard operating procedures (SOPs for the multitarget defence, and (iv exploring the possibility of using it as a user training tool at the level of Air Defence Commanders. The design specification and the simulation/modelling philosophy adopted for the development of this package are discussed at length. Since Akash air defence system has many probabilistic events, Monte Carlo method of simulation is used for both threat and defence. Implementation details of the package are discussed in brief. These include: data flow diagrams and interface details. Analysis of results for certain input cases is also covered."

  5. Missile Aerodynamics (Aerodynamique des Missiles)


    guerre froide la production des missiles a baisse’, avec pour consequence une diminution des budgets de d6veloppement. Les nouveaux types de conflits ...Roma) Directeur - Gestion de l’information LUXEMBOURG (Recherche et developpement) - DRDGI 3 Voir Belgique Ministbre de la Difense nationale NORVEGE

  6. Software Acquisition: Evolution, Total Quality Management, and Applications to the Army Tactical Missile System.

    presents the concept of software Total Quality Management (TQM) which focuses on the entire process of software acquisition, as a partial solution TQM can be applied to software acquisition. Software Development, Software Acquisition, Total Quality management (TQM), Army Tactical Missile

  7. Modeling and Simulation of Control Actuation System with Fuzzy-PID Logic Controlled Brushless Motor Drives for Missiles Glider Applications

    Muniraj, Murali; Arulmozhiyal, Ramaswamy


    A control actuation system has been used extensively in automotive, aerospace, and defense applications. The major challenges in modeling control actuation system are rise time, maximum peak to peak overshoot, and response to nonlinear system with percentage error. This paper addresses the challenges in modeling and real time implementation of control actuation system for missiles glider applications. As an alternative fuzzy-PID controller is proposed in BLDC motor drive followed by linkage mechanism to actuate fins in missiles and gliders. The proposed system will realize better rise time and less overshoot while operating in extreme nonlinear dynamic system conditions. A mathematical model of BLDC motor is derived in state space form. The complete control actuation system is modeled in MATLAB/Simulink environment and verified by performing simulation studies. A real time prototype of the control actuation is developed with dSPACE-1104 hardware controller and a detailed analysis is carried out to confirm the viability of the proposed system. PMID:26613102

  8. Modeling and Simulation of Control Actuation System with Fuzzy-PID Logic Controlled Brushless Motor Drives for Missiles Glider Applications

    Murali Muniraj


    Full Text Available A control actuation system has been used extensively in automotive, aerospace, and defense applications. The major challenges in modeling control actuation system are rise time, maximum peak to peak overshoot, and response to nonlinear system with percentage error. This paper addresses the challenges in modeling and real time implementation of control actuation system for missiles glider applications. As an alternative fuzzy-PID controller is proposed in BLDC motor drive followed by linkage mechanism to actuate fins in missiles and gliders. The proposed system will realize better rise time and less overshoot while operating in extreme nonlinear dynamic system conditions. A mathematical model of BLDC motor is derived in state space form. The complete control actuation system is modeled in MATLAB/Simulink environment and verified by performing simulation studies. A real time prototype of the control actuation is developed with dSPACE-1104 hardware controller and a detailed analysis is carried out to confirm the viability of the proposed system.

  9. Adaptive Missile Guidance Using GPS

    Pallavi Sharad Rupnar


    Full Text Available The name adaptive means we can guide any missile using GPS in any critical conditions. GPS guided missiles, using the exceptional navigational and surveying abilities of GPS, after being launched, could deliver a warhead to any part of the globe via the interface of the onboard computer in the missile with the GPS satellite system.GPS allows accurate targeting of various military weapons including ICBMs, cruise missiles and precision-guided munitions. Artillery projectiles with embedded GPS receivers able to withstand accelerations of 12,000 G have been developed for use in 155mm.GPS guided weapons, with their technological advances over previous, are the superior weapon of choice in modern days

  10. Infrared Background and Missiles Signature Survey

    D.V. Renuka


    Full Text Available The proliferation of the missile threats in the existing threat scenario for airborne platform is a serious point of consideration for any mission planning. Missile warning system is an electronic warfare support system which gives warning to the pilot when a missile is detected in the scenario. The airborne platform has to be installed with missile warning sensors to give a spherical coverage, so that the sensors can detect the IR intensity variation in the ground scenario. This IR intensity variation has to be further analysed to differentiate the raising missile intensity from the varying background clutter. In order to differentiate the threat from the background clutter, the system should have sufficient background data set for online comparison thereby having less false alarm rate. The efficiency and performance of any missile warning system is validated with respect to its probability of declaration against the false alarm rate. Hence, to realize an efficient functioning of missile warning system, building IR background data base and missile signature database are the primary task. This paper details the methodology to be adapted for the building of tactical missile IR signatures and background data.

  11. Infrared Background and Missiles Signature Survey

    D.V. Renuka


    Full Text Available The proliferation of the missile threats in the existing threat scenario for airborne platform is a serious point of consideration for any mission planning. Missile warning system is an electronic warfare support system which gives warning to the pilot when a missile is detected in the scenario. The airborne platform has to be installed with missile warning sensors to give a spherical coverage, so that the sensors can detect the IR intensity variation in the ground scenario. This IR intensity variation has to be further analysed to differentiate the raising missile intensity from the varying background clutter. In order to differentiate the threat from the background clutter, the system should have sufficient background data set for online comparison thereby having less false alarm rate. The efficiency and performance of any missile warning system is validated with respect to its probability of declaration against the false alarm rate. Hence, to realize an efficient functioning of missile warning system, building IR background data base and missile signature database are the primary task. This paper details the methodology to be adapted for the building of tactical missile IR signatures and background data.Defence Science Journal, 2013, 63(6, pp.611-615, DOI:

  12. Influence of Missile Fusillade Engagement Mode on Operation Efficiency

    BU Xian-jin; REN Yi-guang; SHA Ji-chang


    Shoot efficiency is one of the most important evaluation indexes of the operation efficiency of weapon system. In this paper, based on definitions of the probability and the expected number of missed attacking missiles, the expected numbers of anti-missiles and attacking missiles hit by single anti-missile, fusillade mechanism of multi-missile is analyzed systematically. The weapon operation efficiency in various engagement patterns is also studied. The results show that double missiles fusillade is the most feasible manner for increasing the weapon operation efficiency.

  13. Missile captive carry monitoring using a capacitive MEMS accelerometer

    Hatchell, Brian; Mauss, Fred; Santiago-Rojas, Emiliano; Amaya, Ivan; Skorpik, Jim; Silvers, Kurt; Marotta, Steve


    Military missiles are exposed to many sources of mechanical vibration that can affect system reliability, safety, and mission effectiveness. One of the most significant exposures to vibration occurs when the missile is being carried by an aviation platform, which is a condition known as captive carry. If the duration of captive carry exposure could be recorded during the missile's service life, several advantages could be realized. Missiles that have been exposed to durations outside the design envelop could be flagged or screened for maintenance or inspection; lightly exposed missiles could be selected for critical mission applications; and missile allocation to missions could be based on prior use to avoid overuse. The U. S. Army Aviation and Missile Research Development and Engineering Center (AMRDEC) has been developing health monitoring systems to assess and improve reliability of missiles during storage and field exposures. Under the direction of AMRDEC staff, engineers at the Pacific Northwest National Laboratory have developed a Captive Carry Health Monitor (CCHM) for the HELLFIRE II missile. The CCHM is an embedded usage monitoring device installed on the outer skin of the HELLFIRE II missile to record the cumulative hours the host missile has been in captive carry mode and thereby assess the overall health of the missile. This paper provides an overview of the CCHM electrical and package design, describes field testing and data analysis techniques used to identify captive carry, and discusses the potential application of missile health and usage data for real-time reliability analysis and fleet management.

  14. The Cooperative Ballistic Missile Defence Game

    Evers, L.; Barros, A.I.; Monsuur, H.


    The increasing proliferation of ballistic missiles and weapons of mass destruction poses new risks worldwide. For a threatened nation and given the characteristics of this threat a layered ballistic missile defence system strategy appears to be the preferred solution. However, such a strategy involv

  15. Principles of Guided Missiles and Nuclear Weapons.

    Naval Personnel Program Support Activity, Washington, DC.

    Fundamentals of missile and nuclear weapons systems are presented in this book which is primarily prepared as the second text of a three-volume series for students of the Navy Reserve Officers' Training Corps and the Officer Candidate School. Following an introduction to guided missiles and nuclear physics, basic principles and theories are…

  16. The Cooperative Ballistic Missile Defence Game

    Evers, L.; Barros, A.I.; Monsuur, H.


    The increasing proliferation of ballistic missiles and weapons of mass destruction poses new risks worldwide. For a threatened nation and given the characteristics of this threat a layered ballistic missile defence system strategy appears to be the preferred solution. However, such a strategy

  17. Theater Ballistic Missile Defense Policy, Missions and Programs: Current Status


    destroy its target. A French-Italian program called SAMP/T (Sol-Air Moyenne Portee/ Terrestre ) is being considered for a point defense system; further...Patriot PAC-3 missile. The Multimode Missile includes semi-active track- via -missile guidance, improved propulsion and uses an aimed blast

  18. Impulsive control for hypervelocity missiles

    Magness, R. W.


    A hypervelocity agile interceptor/quickshot is being developed for defense of ballistic missile launch sites. A guidance and control system is required to achieve the missile guidance accuracy necessary for direct target impact. Attitude control systems evaluated for the agile interceptor included aerodynamic controls, thrust vector controls and impulsive motor controls. The solid squib impulsive control motion was selected because of high response rate, low weight and low volume. A baseline motor configuration was designed and a solid propellant squib was developed for use in the control system. Ballistic pendulum and bench tests were conducted with a test impulsive control motor to measure nominal performance, establish the standard deviation of performance, and define requirements to prevent sympathetic ignition. A dynamic control wind tunnel test was also conducted to determine the impulse augmentation due to the impulsive motor jet interaction with the missile boundary layer. The degree and direction of augmentation was measured for variations in Mach number and angle of attack.

  19. Advanced Missile Signature Center

    Federal Laboratory Consortium — The Advanced Missile Signature Center (AMSC) is a national facility supporting the Missile Defense Agency (MDA) and other DoD programs and customers with analysis,...

  20. Hyper Velocity Missiles For Defence

    Faqir Minhas


    Full Text Available The paper reviews the history of technical development in the field of hypervelocity missiles. It highlights the fact that the development of anti-ballistic systems in USA, Russia, France, UK, Sweden, and Israel is moving toward the final deployment stage; that USA and Israel are trying to sell PAC 2 and Arrow 2 to India; and that India’s Agni and Prithvi missiles have improved their accuracy, with assistance from Russia. Consequently, the paper proposes enhanced effort for development in Pakistan of a basic hypersonic tactical missile, with 300 KM range, 500 KG payload, and multi-rolecapability. The author argues that a system, developed within the country, at the existing or upgraded facilities, will not violate MTCR restrictions, and would greatly enhance the country’s defense capability. Furthermore, it would provide high technology jobs toPakistani citizens. The paper reinforces the idea by suggesting that evolution in the field of aviation and electronics favors the development of ballistic, cruise and guided missile technologies; and that flight time of short and intermediate range missiles is so short that its interception is virtually impossible.

  1. The effectiveness of the U.S. missile defense capabilities as a deterrent to the North Korean missile threat

    Gipson, Issac G.


    Over the last five years, America has placed an ever-increasing emphasis on missile defense and currently spends nearly $10 billion annually on its development. The United States' current missile Defense system is integrated; it depends on the cooperation of defensive elements aboard ships, on land, in the air and space. The objective is to provide a layered defense with multiple opportunities to destroy an incoming missile. By investing heavily in missile defense technology, the United ...

  2. 印度导弹武器装备体系发展与前景分析%Analysis of Indian Missile Weapon System Development



    随着国际安全环境的重大变化,印度加紧了其军事战略的调整和军队建设的步伐,大力发展导弹武器体系建设,对周边国家和地区形成了安全威胁.在分析印度军事战略的基础上,重点阐述印度弹道导弹、巡航导弹、防空导弹和导弹防御系统等武器装备体系的建设情况,并分析了其发展趋势和未来前景.%With the tremendous changes of the international security environment, India promotes the military strategy adjustment and the military construction, and pays great attention to the development of missile weapon system, threatening to the security of neighboring countries and regions. Beginning with the Indian military strategy, this paper describes the Indian weapon system construction in depth, such as the ballistic missile, cruise missile, air defense system and ballistic missile defense system .ete. Finally future development trend and prospect are analyzed.

  3. Discrete Deterministic Modelling of Autonomous Missiles Salvos

    Momcilo Milinovic


    Full Text Available The paper deals with mathematical models of sequent salvos battle, of autonomous flight missiles (AFM organized in the groups of combatants. Tactical integration of AFM system distance-controlled weapon is considered by performances of simultaneous approaches on targets, and continual battle models of guerilla and direct fire, are redesigned to the discrete-continual mixed model, for checking missiles sudden, and further salvos, attack effects. Superiority parameters, as well as losses and strengths of full, or the part of salvo battle, for the missiles groups as technology sub-systems combatants’, is expressed by mathematical and simulation examples. Targets engagements capacities of the missiles battle unit, is conducted through designed scenarios and mathematically derived in the research. Model orientated on answers about employment of rapid reaction defending tactics, by distance missiles attacks.Defence Science Journal, Vol. 64, No. 5, September 2014, pp.471-476, DOI:

  4. Missile Captive Carry Monitoring using a Capacitive MEMS Accelerometer

    Hatchell, Brian K.; Mauss, Fredrick J.; Santiago-Rojas, Emiliano; Amaya, Ivan A.; Skorpik, James R.; Silvers, Kurt L.; Marotta, Steve


    Military missiles are exposed to many sources of mechanical vibration that can affect system reliability, safety, and mission effectiveness. One of the most significant exposures to vibration occurs when the missile is being carried by an aviation platform, which is a condition known as captive carry. If the duration of captive carry exposure could be recorded during the missile’s service life, several advantages could be realized. Missiles that have been exposed to durations outside the design envelop could be flagged or screened for maintenance or inspection; lightly exposed missiles could be selected for critical mission applications; and missile allocation to missions could be based on prior use to avoid overuse. The U. S. Army Aviation and Missile Research Development and Engineering Center (AMRDEC) has been developing health monitoring systems to assess and improve reliability of missiles during storage and field exposures. Under the direction of AMRDEC staff, engineers at the Pacific Northwest National Laboratory have developed a Captive Carry Health Monitor (CCHM) for the HELLFIRE II missile. The CCHM is an embedded usage monitoring device installed on the outer skin of the HELLFIRE II missile to record the cumulative hours the host missile has been in captive carry mode and thereby assess the overall health of the missile. This paper provides an overview of the CCHM electrical and package design, describes field testing and data analysis techniques used to identify captive carry, and discusses the potential application of missile health and usage data for real-time reliability analysis and fleet management.

  5. Advanced technology payoffs for future rotorcraft, commuter aircraft, cruise missile, and APU propulsion systems

    Turk, M. A.; Zeiner, P. K.


    In connection with the significant advances made regarding the performance of larger gas turbines, challenges arise concerning the improvement of small gas turbine engines in the 250 to 1000 horsepower range. In response to these challenges, the NASA/Army-sponsored Small Engine Component Technology (SECT) study was undertaken with the objective to identify the engine cycle, configuration, and component technology requirements for the substantial performance improvements desired in year-2000 small gas turbine engines. In the context of this objective, an American turbine engine company evaluated engines for four year-2000 applications, including a rotorcraft, a commuter aircraft, a supersonic cruise missile, and an auxiliary power unit (APU). Attention is given to reference missions, reference engines, reference aircraft, year-2000 technology projections, cycle studies, advanced engine selections, and a technology evaluation.

  6. Diode Pumped Alkaline Laser System: A High Powered, Low SWaP Directed Energy Option for Ballistic Missile Defense High-Level Summary - April 2017

    Wisoff, P. J. [Lawrence Livermore National Lab. (LLNL), Livermore, CA (United States)


    The Diode-Pumped Alkali Laser (DPAL) system is an R&D effort funded by the Missile Defense Agency (MDA) underway at Lawrence Livermore National Laboratory (LLNL). MDA has described the characteristics needed for a Boost Phase directed energy (DE) weapon to work against ICBM-class threat missiles. In terms of the platform, the mission will require a high altitude Unmanned Aerial Vehicle (UAV) that can fly in the “quiet” stratosphere and display long endurance – i.e., days on station. In terms of the laser, MDA needs a high power, low size and weight laser that could be carried by such a platform and deliver lethal energy to an ICBM-class threat missile from hundreds of kilometers away. While both the military and industry are pursuing Directed Energy for tactical applications, MDA’s objectives pose a significantly greater challenge than other current efforts in terms of the power needed from the laser, the low size and weight required, and the range, speed, and size of the threat missiles. To that end, MDA is funding two R&D efforts to assess the feasibility of a high power (MWclass) and low SWaP (size, weight and power) laser: a fiber combining laser (FCL) project at MIT’s Lincoln Laboratory, and LLNL’s Diode-Pumped Alkali Laser (DPAL) system.


    Raluca Mihaela LEVONIAN


    Full Text Available This study aims to investigate Romanian media discourse on the current standing of the relations between Romania and the United States of America in the military fi eld. The main topic investigated is connected to Romania’s decision to host the land-based component of the Balllistic Missile Defense System on its ground, an event which attracted signifi cant media coverage during the year 2011. The corpus analyzed consisted of 37 news and opinion items and reports published on the site of three Romanian newspapers. The main research questions were to assess whether the evaluations of this event were positive or negative, who were the actors issuing these statements and what objects were discussed in association to this event. The results showed that positive evaluations were more common than negative evaluations and that the offi cial stances on this topic formed a very coherent perspective, endorsing the project.

  8. A design proposal of a certain missile tactical command system based on Beidou satellite communication and GPS positioning techniques

    Ma, Jian; Hao, Yongsheng; Miao, Jian; Zhang, Jianmao


    This paper introduced a design proposal of tactical command system that applied to a kind of anti-tank missile carriers. The tactical command system was made up of embedded computer system based on PC104 bus, Linux operating system, digital military map, Beidou satellite communication equipments and GPS positioning equipments. The geographic coordinates was measured by the GPS receiver, the positioning data, commands and information were transmitted real-time between tactical command systems, tactical command systems and command center, by the Beidou satellite communication systems. The Beidou satellite communication equipments and GPS positioning equipments were integrated to an independent module, exchanging data with embedded computer through RS232 serial ports and USB ports. The decision support system software based on information fusion, calculates positioning data, geography information and battle field information synthetically, shows the position of allies and the position of enemy on the military map, and assesses the various threats of different enemy objects, educes a situation assessment and threat assessment.

  9. Acceleration effects on missile aerodynamics

    Gledhill, Irvy MA


    Full Text Available Practical requirements are now arising in which significant acceleration takes place during flight; 5th generation missiles, such as A-Darter, execute turns at 100 g, where g is the acceleration due to gravity, and thrust from propulsion systems may...

  10. Space and Missile Systems Center Standard: Systems Engineering Requirements and Products


    an analytical tool such as master logic diagram , fault tree, event tree, or Ishikawa diagram ). c. MCFA will be updated as necessary to reflect...Figure 3-2. Systems engineering process described by a “Vee” diagram . ............................................. 6 Figure 3-3. Relationship between...increasingly detailed levels and bottom-up recursion during assembly/integration. The recursive nature is further depicted in the “Vee” diagram of Figure

  11. Redesign of the Stabilized Pitch Control System of a Semi-Active Terminal Homing Missile System.


    Instituto Universitario Politechnico, Barquisimeto, Venezuela. s.s. 3 T 950 L. S. Shieh et al. of high order. When a given multivariable system is...1 a). The block elements of the subsequent rows are evaluated by the following matrix Routh algorithm: Hi=AiAi>+, 1-’ for i=1,2,...,2k and k<n rank Ai...A1 (s) and A (8). When n i A n, and rank A,- 1 0 q in eqn. (3 b), the matrix Routh algorithm in eqn. (3 b) cannot be directly applied. The matrix Routh

  12. Gauging the Influence of Technology on Tactical Missiles of the Future(Short Communication

    Mark L. Bundy


    Full Text Available Tactical missiles, carrying kinetic energy, high explosives, or multiple submunitions are an integral part of the current and future US Army weapons inventory. Naturally, the number of missiles that can be stowed on any mobile launch platform depends on the size of the missile. Advances in rocket propulsion efficiency and improvements in guidance systems may make it possible to reduce missile size without a proportionate decrease in effectiveness. A primitive I-DOF computer model is used here to show how advances in missile technology might allow smaller missiles in the future to carry out the mission of today's larger missiles. A scaled-down version of a typical current generation missile is taken as the next generation missile. Hypothetical improvements in this smaller missile are then chosen in four basic areas-propellant impulse, burn time, weight fraction, and aerodynamic drag.-with the effects on lethality reported in a nondimensional format.

  13. 舰载弹炮结合近程武器系统技术研究%Study on Shipped Missile-Gun Integrated Defense Weapon System



    现代高性能反舰导弹是舰艇末端防御的最大威胁,而舰载弹炮结合近程武器系统为舰艇的末端防御提供了一种有效的途径。分析了舰载弹炮结合近程武器系统的作战使用和主要特点,针对海上空袭武器的特点,重点研究了增强系统抗饱和攻击能力的设计方法,并探讨了舰载弹炮结合近程武器系统在现代海战中的使用方向。%Modern high-powered antiship missile is the main threaten of ship,and shipped missile-gun integrated defense weapon system is an effective way to the terminal defense of ship. This paper first analyzes the combat operation and main characteristic of missile-gun integrated defense weapon system,then studies the key factor of designing a system. At last the system usage is discussed in the modern sea war.

  14. The Joint Cruise Missiles Project: An Acquisition History


    his staff at the Air Force ALCM System Project Office. The authors are, of course , solely responsible for the accuracy and interpretation of the...meaning) Sea launched cruise missile (current meaning) SPOC System Project Officers Council SRAM Short range attack missile STCM Supersonic tactical...Council ( SPOC ), com- posed of the directors of the four major missile systems (consisting at that time of the GLCM, ship- and sub-launched SLCM, and the

  15. 导弹预防性检测系统设计%The Design of The System of Missile Precautionary Measurement

    刘洪于; 方洋旺


    导弹贮存期间经历多次测试维修,检测数据繁杂,只有更好利用其现场数据才能更合理预测导弹寿命及检测时间。对此,结合装备失效率曲线,提出三种样本采集方案,设计了一套预防性检测系统,并以威布尔分布为例,进行了仿真验证,结果验证系统的正确性与实用性。%There is a lot of measurement and maintenance during missile storage.Due to the complexity of data test,only by using field data can the lifespan and test time of missiles be better forecasted.To solve the problem,three kinds of data acquisition schemes are given by considering the bathtub curve of disabled probability of equipment.The system of missile precautionary measurement is designed.The simulation experiment based on the data turns out to obey Weibull distribution.The result validates the effectiveness and practicability of the system.

  16. Simulacioni model sistema za upravljanje letom protivbrodske rakete / Model for simulating the flight control system of a antiship missile

    Nebojša N. Gaćeša


    Full Text Available U radu je analiziran program za simulaciju sistema za upravljanje letom protivbrodske rakete sa radarskom glavom za samonavođenje. Analiziran je matematički model rakete, model autopilota i model cilja. Ovakvim pristupom dobijen je rezultat koji omogućava uspostavljanje realnijeg procesa praćenja leta konkretne protivbrodske rakete, budući da upravljanje letom rakete na celoj trajektoriji ima znatne prednosti u odnosu na nevođene projektile, pre svega zbog mogućnosti gađanja pokretnih ciljeva. Simulacioni model upravljanja letom rakete pruža mogućnosti za dalje proučavanje ove klase raketa. / The paper analyzes a program for simulating the flight control of an antiship missile with the radar seeker. The paper analyzes a mathematic missile model an autopilot model and a target model. Thus obtained results enable a more realistic process of flight tracking of a particular antiship missile as the missile guidance along the whole trajectory provides many advantages over unguided projectiles, primarily because of the possibility to fire at moving targets. The flight control simulation model enables further study of this missile class.

  17. Back-stepping active disturbance rejection control design for integrated missile guidance and control system via reduced-order ESO.

    Xingling, Shao; Honglun, Wang


    This paper proposes a novel composite integrated guidance and control (IGC) law for missile intercepting against unknown maneuvering target with multiple uncertainties and control constraint. First, by using back-stepping technique, the proposed IGC law design is separated into guidance loop and control loop. The unknown target maneuvers and variations of aerodynamics parameters in guidance and control loop are viewed as uncertainties, which are estimated and compensated by designed model-assisted reduced-order extended state observer (ESO). Second, based on the principle of active disturbance rejection control (ADRC), enhanced feedback linearization (FL) based control law is implemented for the IGC model using the estimates generated by reduced-order ESO. In addition, performance analysis and comparisons between ESO and reduced-order ESO are examined. Nonlinear tracking differentiator is employed to construct the derivative of virtual control command in the control loop. Third, the closed-loop stability for the considered system is established. Finally, the effectiveness of the proposed IGC law in enhanced interception performance such as smooth interception course, improved robustness against multiple uncertainties as well as reduced control consumption during initial phase are demonstrated through simulations.

  18. Introduction of Women into Titan II Missile Operations.


    areas (weapons system orientation: mnaintenance management. electronics principles , and technical publications. facility systems and missile Sfstents...Management. Electronics Principles . Technical Publications 97.00 2.63 94.04 5.27 2.31 Facility Systems 92.25 4.61 93.2) 5.80 -.62 Missile Systems 96.67 2.90

  19. 空空导弹冗余系统共模失效%Approach of Common Mode Failure Analysis in Redundant System of Air-to-Air Missile

    王丽丽; 周光巍; 王俊华


    为避免空空导弹冗余系统产生共模失效,提高产品可靠性和安全性。在研究共模失效分析方法的基础上,结合空空导弹的研制特点,对某型空空导弹电源组件点火电路冗余系统共模故障进行了定性分析,识别了点火电路中的共模故障,分析了故障原因和耦合因素,并提出了相应的改进措施。%In order to avoiding common mode failure of the air-to-air missile, and improving the reliability and safety of the product, combine the developing character of the air-to-air missile, made a qualitative a- nalysis of the common mode failure in the redundant system of a type air-to-air missile power supply module igniting circuit based on the study of the method of common mode failure analysis, identified the com- mon mode failure of the equipment, analyzed the cause of failure and the coupling factor, put forward improvement measures.

  20. 基于Multi-Agent的防空导弹武器系统模型设计%Design of Multi-Agent Based Model on Air Defense Missile Weapon System

    陈宝印; 栾立秋; 张成斌


    建立科学的结构模型是进行防空导弹武器系统仿真的基础和关键环节.针对防空导弹武器系统的特点,提出了基于Multi-Agent的防空导弹武器系统模型建模方法,设计了防空导弹武器系统模型结构.利用Multi-Agent建模技术,把防空导弹武器系统实体映射成相应的Multi-Agent系统,并以Agent的形式对防空导弹武器系统这一客观复杂系统进行了深刻的认识,为防空导弹武器系统建模仿真奠定了基础.%Forming a scientific system model is the key of Air Defense Missile Weapon System simulation. According to the characters of Air Defense Missile Weapon System, a modeling method of multi-agent based model on Air Defense Missile Weapon System is given. The framework on Air Defense Missile Weapon System is designed. Using the Multi-Agent modeling technology, maps the Air Defense Missile Weapon System entity the corresponding Multi-Agent system, and carries on the profound understanding by the Agent form to Air Defense Missile Weapon System this objective complicated, which will be helpful to realize the modeling simulation on Air Defense Missile Weapon System.

  1. 导弹防御系统中红外光电识别技术分析%Analyses on infrared optoelectronics recognition technology in missile defense system

    吴瑕; 周焰; 崔建; 杨龙坡


    目标识别问题是弹道导弹防御系统中的核心难题之一,针对弹道导弹突防中威胁目标群飞行各阶段呈现出的不同红外特性.介绍了天基红外系统和拦截弹的最新研究进展及其红外目标识别技术手段.在温度测量、测辐射强度、红外成像等关键技术方面,系统地论述了其在反导系统弹道目标识别中所运用的红外光电子学方法与技术,并且就相应的反红外识别手段--红外隐身与红外诱饵,进行了探讨.最后对导弹防御系统中红外目标识别与反识别的研究动向进行了展望,提出了进行导弹防御系统目标识别研究的总体建议.%The target recognition is one of the core difficult problems of ballistic missile defense system. According to the different infrared characteristics of all sorts of dangerous targets in the apiece phases of ballistic missile flying, the newest development and the technical means of infrared target recognition for SBIRS and kinetic kill vehicle were introduced. The means and technologies of infrared optoelectronics applying in target recognition were depicted systematically considering the development of some key technologies, such as infrared temperature measurement, radiant intensity test and infrared imaging. Infrared stealth and infrared decoy technique were also discussed, which were the relevant infrared target counter-recognition means and technologies during ballistic missile attacking. Finally, some new representative developments for infrared target recognition and counter-recognition in ballistics missile defense system were expected, and some general suggestions to develop target recognition in ballistic missile defense system were provided.

  2. Modeling and Simulating Dynamics of Missiles with Deflectable Nose Control

    Gao Yuan; Gu Liangxian; Pan Lei


    This article investigates the dynamic characteristics of deflectable nose missiles with rotary single-channel control. After introduction of effective attack and sideslip angles as well as quasi-body coordinates based on the spin characteristics of the missile's body, an integrated rigid kinetic model of missile with deflectable nose control is set up in the quasi-body coordinates considering the interaction between the missile's nose and body by using rootless multi-rigid-body system dynamics and is linearized. Then an analysis with simulation is conducted to investigate the coupling characteristics between the channels, the influences of nose deflection on the body and the dynamic characteristics of missile's body. The results indicate that various channels of missiles with deflectable nose control are coupled cross-linked; the nose deflection tends to make the body move in the opposite direction and, finally, evidences the correctness and reasonability of the kinetic model proposed by this article.

  3. Letters: Subs, Not Missiles

    Tsipis, Kosta


      In a letter, MIT physicist Kosta Tsipis responds to a column in the August 1988 "Bulletin of the Atomic Scientists" and clarifies his position in regard to the MX and Trident II missile programs...

  4. The Trend of Missile-Gun Combined Weapon System for Aerial Defense%弹炮结合防空武器系统新趋势

    陈薇; 王军


    Since the Kosovo War started to use a form of simple air raids and counter-air raids,a increasing number of wars use air raids to attack the enemy,so how to defense the enemy in the air become more and more important. Missile-Gun combined weapon system not only has a big air defense area but also has a high effective-cost,so it will become the trend of air defense weapon system. This paper describes the structure and classification of Missile-Gun combined weapon system,and analyzes the advantages and disadvantages of the current systems; finally the trend of Missile-Gun combined weapon system is proposed.%自从科索沃战争开创了单纯空袭作战与反空袭作战的先例之后,空袭就成为了战争的焦点,如何更好地抵御空中目标的来袭成为各国战争防御的主题。弹炮结合防空武器系统具有防空区域大、效费比高等优点,是防空武器系统的发展趋势之一。在分析现有典型弹炮结合防空武器系统的基础上,依据弹炮结合武器系统是否共用火控系统将其分为弹炮混编式和弹炮同控式两种形式;随后,结合现代空袭的特点提出了弹炮结合武器系统的发展趋势。

  5. A Study of Age Demographics across the Aviation and Missile Materiel Enterprise


    future Aviation and Missile ME may look like. The Defense Civilian Personnel Data System (DCPDS) Human Resource managers across the Aviation and...Missile ME use the Defense Civilian Personnel Data System (DCPDS) as the warehouse for storing employee information. Each of the five organizations...Aviation and Missile Life Cycle Management Command Public Affairs, 25 April 2016 AVIATION AND MISSILE MATERIEL ENTERPRISE DEMOGRAPHICS 2

  6. 美国空射导弹拦截系统的作战应用分析%Analysis on Operational Applications of USA Air-launched Missile Interception System

    宋文静; 曹泽阳; 张晋; 刘永兰


    Air-launched missile interception system is an interception mean of USA missile defense systems.Its main operational missions are analyzed, including missile defense mission, hypersonic speed missile interception mission in the air,multi-orbital air-craft interception mission and other defense missions.Taking missile defense mission as an example, its operational process is ana-lyzed, thus key links of air-launched missile anti-missile /anti-satellite system are given.Combined with main operational missions and operational process, special influence factors of its operational effectiveness are parsed.Studying on problems of its operational application, is benefit to improve operational effectiveness of the weapon equipment.%空射导弹拦截系统是美国弹道导弹防御体系的拦截手段之一,文中首先分析了空射导弹拦截系统的主要作战任务,包括弹道导弹防御任务、高超声速导弹空中截击任务、跨轨道飞行器拦截任务和其他防御任务;然后,以弹道导弹防御任务为例,对其作战过程进行了分析,进而给出了空射导弹反导/反卫拦截系统作战的关键环节;最后,结合主要作战任务和作战过程,剖析了其作战效能的特殊影响因素. 研究其作战应用问题,有益于提升该武器装备的作战效能.

  7. The P3 Power Generation System for Advanced Missile Defense Applications


    Kansal, J. Hsu, J. Friedman, and M. B. Srivastava, "Design Considerations for Solar Energy Harvesting Wireless Embedded Systems", IEEE...Generator", Proceedings of the Materials Research Society, Perovskite Materials, vol. 718, pp. D10.25.l-7 (2002) A.L. Olson, L.M. Eakins, B.W. Olson, D.F...system in which the P3 system is a bottoming cycle for a mid to high temperature fuel cell will be developed. This option will require a total of two

  8. FMP (Flight Mechanics Panel) Working Group WG-12 on Validation of Missile System Simulation


    maintenance costs for weapon performance simulation programs (2) Fase of software maintenance during development ltem (2) is very important and needs...System simulation studies - if hinge moments have a sensible effect on system performance or if an estimate of overall power consumption during a mission...effects, deterioration of magnetic flux and the dynamics of the power amplifier should not have a sensible effect on the static and cyoamic behavior of

  9. Space and Missile Systems Center Tailoring: Tailoring Instructions for AIAA-S-120-2006


    space system have been included properly. Customer-Furnished Equipment ( CFE ) The contractor’s mass properties records should have a separate...tabulation of all CFE . 4.5 Documentation Use AIAA-S-120-2006 for all paragraphs except as noted below. 20 4.5.1 Mass Properties Control Plan A

  10. GPS轨迹测量系统在导弹飞行试验中的应用%Application of GPS trajectory measurement system in missile flight test

    李东; 黄信安


    In the process of air-to-air missile development,a serial of tethered flight test must be done to improve the capa-bility of capturing and tracking the real goal of missile guidance system. The traditional tethered flight test results in great uncer-tainty for the flight test results because the test personnel on ground can not grasp the dynamic status of the drone aircraft in real time. With GPS widely used in the system,the target aircraft′s position and speed relative to fighter plane are calculated in com-bination the GPS information received from the airborne missile and target GPS pod,and displayed in the data processing soft-ware,so that the test personnel on ground obtain the relevant information of fighter plane and drone aircraft in real time and pro-vide reliable data for the test command. The practical application result shows that this system can greatly improve the success rate and the missile interception probability,and save the time and fund of the test.%空空导弹研制需要一系列空中系留飞行试验,以解决导弹制导系统对真实目标的截获跟踪能力。传统的系留试验由于地面试验人员无法实时掌握靶机和目标机的动态,给飞行试验结果造成了很大的不确定性;本系统利用日益广泛使用的GPS全球定位技术,从载机的导弹产品和目标机GPS吊舱接收下传的GPS信息,实时解算出目标机相对于载机位置、速度等信息,显示在数据处理软件上,从而使地面试验人员实时获取载机和目标机的相关信息,为试验指挥提供了可靠数据;实际应用结果表明,该系统大大提高了系留试验的成功率和导弹截获概率,为飞行试验节约了试验经费和时间,创造了良好的经济效益。

  11. 2005 40th Annual Armament Systems: Guns - Ammunition - Rockets - Missiles Conference and Exhibition. Volume 2: Wednesday


    system SRL 6 24 CTA INTERNATIONAL UK and French Government Collaboration Warrior = VCI EBM = FRES UK TDP Manned Turret Integration...WARRIOR FRES VBCI EBM EMD & PROD’N 25 CTA INTERNATIONAL CTAI Turret Demonstrator Programmes MTIP 4 Tonne Conventional Manned Turret Toutatis 1,5...learned that do not apply 8 Grouping • Sort out those that do not apply • Combine lessons learned into themes – Facilitates comparing Lessons Learns

  12. Tunnel Boring Machine Technology for a Deeply Based Missile System. Volume I, Application Feasibility. Part 2.


    Air Force Weapons Laboratory (NTESG) August 1980 Kirtland AFB, NM 87117 NUMBER OF PAGES 14. MONITORING AGENCY NAME & ADDRESS(il different from...incorporate in selected initial tunnel sections, trial sunport systems lighter than those calculated by existing RSP methods. These could be monitored as part...a pair of steel, 156 lA wide-flanqe (1F) beams, shaped to fit the tunnel opening and bolted toqether at the tunnel crown set on kicker foot blocks

  13. 46th Annual Gun and Missile Systems Conference and Exhibition. Volume 3 - Thursday


    Smith, U.S. Army Benet Laboratories – NON-TRADITIONAL WEAPONS I 11840 - Development of a Large Caliber Naval EM Railgun , Mr. Roger Ellis, Office of...Naval Research 11841 – Electromagnetic Railgun , a Multi-Mission Weapon System, Mr. Alan Kull, General Atomics 11828 - Scalable Gen-Set for Directed Energy...Development of a Large Caliber Naval EM Railgun Mr. Roger Ellis, Office of Naval Research 1:35 PM - 1:55 PM 11725 - Medium Calibre Goes in a New

  14. 46th Annual Gun and Missile Systems Conference and Exhibition. Volume 2. Wednesday


    Smith, U.S. Army Benet Laboratories – NON-TRADITIONAL WEAPONS I 11840 - Development of a Large Caliber Naval EM Railgun , Mr. Roger Ellis, Office of...Naval Research 11841 – Electromagnetic Railgun , a Multi-Mission Weapon System, Mr. Alan Kull, General Atomics 11828 - Scalable Gen-Set for Directed Energy...Development of a Large Caliber Naval EM Railgun Mr. Roger Ellis, Office of Naval Research 1:35 PM - 1:55 PM 11725 - Medium Calibre Goes in a New

  15. 弹道导弹SINS/CNS 组合导航系统建模与性能仿真%System Modeling and Performance Simulation on SINS/CNS Integrated Navigation System for Ballistic Missile

    王鑫; 王新龙


    Combined with the characteristics of ballistic missile and the model error caused by uncer-tain noise characteristics in engineering practice, this paper proposes a SINS/CNS integrated navigation system suitable for ballistic missiles.This system, integrated some characteristics of simple combination models and overall optimal correction combination models, uses the adaptive Kalman filtering to ensure the stability and robustness of the filter.In the simulation, according to the missile trajectory, it establi-shes a reasonable, complete guide star catalog of missile.The simulation illustrates that this navigation scheme can improve the precision of navigation parameters of ballistic missile.%针对弹道导弹在工程实际中噪声特性的不确定性及其引起的模型误差,本文提出了一种适用于弹道导弹的 SINS/CNS 组合导航方案。该方案融合了简单组合模式和基于全面最优校正的组合模式特点,采用自适应卡尔曼滤波来保证滤波的稳定性和鲁棒性,并根据导弹的飞行弹道,建立了合理、完备的弹载导航星表。仿真验证结果表明,该导航方案可以达到全面提高弹道导弹导航参数精度的目的。

  16. 国外舰载防空反导火控系统发展现状%Study on Overseas Development Conditions of Shipboard Aerial Defence Anti-Missile Fire System

    王金云; 王孟军


    论述了国外舰载火控系统的发展状况,介绍了各国防空反导系统中防空导弹、火炮、弹、炮、箭相结合的防御方式及新概念武器发展现状及其特点分析,指出未来防空反导任务中,需在火控技术上采用新的机理(如多传感器信息融合、对机动目标滤波处理、火控解算等),火力配置上采用分层防御,各种武器系统协同作战,实现对来袭导弹有效拦截。%The paper discusses the development conditions of overseas shipboard weapon system, introduces aerial defence missile,gun,missile-gun,missile-rocket integrated defense mode and new concept weapon development status and characteristics analysis. Finally,it is necessary to study new fire control theory(multiple sensors information fusion,maneuvering targets filtering,fire control computation) in the future aerial defence anti-missile task,adopted layered defence mode for fire configuration,all kinds of weapon combination fight. It is available to hold up missile.

  17. Air and Missile Defense Radar (AMDR)


    March 8, 2016 11:04:34 UNCLASSIFIED 4 CAPT Seiko Okano 1333 Isaac Hull Ave , SE Washington, DC 20376-7101 Phone: 202-781-0461 Fax: the combat system. AMDR will be deployed on the Guided Missile Destroyer (DDG) 51 Flight III. AMDR December 2015 SAR March 8, 2016 11:04:34...Abbreviations Ao - Operational Availability CMS - Combat Management System DDG - Guided Missile Destroyer kW - Kilowatt TTL - Training Task List AMDR December

  18. The science, technology, and politics of ballistic missile defense

    Coyle, Philip E.


    America's missile defense systems are deployed at home and abroad. This includes the Groundbased Missile Defense (GMD) system in Alaska and California, the Phased Adaptive Approach in Europe (EPAA), and regional systems in the Middle East and Asia. Unfortunately these systems lack workable architectures, and many of the required elements either don't work or are missing. Major review and reconsideration is needed of all elements of these systems. GMD performance in tests has gotten worse with time, when it ought to be getting better. A lack of political support is not to blame as the DoD spends about 10 billion per year, and proposes to add about 5 billion over the next five years. Russia objects to the EPAA as a threat to its ICBM forces, and to the extensive deployment of U.S. military forces in countries such as Poland, the Czech Republic and Romania, once part of the Soviet Union. Going forward the U.S. should keep working with Russia whose cooperation will be key to diplomatic gains in the Middle East and elsewhere. Meanwhile, America's missile defenses face an enduring set of issues, especially target discrimination in the face of attacks designed to overwhelm the defenses, stage separation debris, chaff, decoys, and stealth. Dealing with target discrimination while also replacing, upgrading, or adding to the many elements of U.S. missiles defenses presents daunting budget priorities. A new look at the threat is warranted, and whether the U.S. needs to consider every nation that possesses even short-range missiles a threat to America. The proliferation of missiles of all sizes around the world is a growing problem, but expecting U.S. missile defenses to deal with all those missiles everywhere is unrealistic, and U.S. missile defenses, effective or not, are justifying more and more offensive missiles.

  19. The science, technology, and politics of ballistic missile defense

    Coyle, Philip E. [Center for Arms Control and Non-Proliferation, Washington, DC (United States)


    America's missile defense systems are deployed at home and abroad. This includes the Groundbased Missile Defense (GMD) system in Alaska and California, the Phased Adaptive Approach in Europe (EPAA), and regional systems in the Middle East and Asia. Unfortunately these systems lack workable architectures, and many of the required elements either don't work or are missing. Major review and reconsideration is needed of all elements of these systems. GMD performance in tests has gotten worse with time, when it ought to be getting better. A lack of political support is not to blame as the DoD spends about $10 billion per year, and proposes to add about $5 billion over the next five years. Russia objects to the EPAA as a threat to its ICBM forces, and to the extensive deployment of U.S. military forces in countries such as Poland, the Czech Republic and Romania, once part of the Soviet Union. Going forward the U.S. should keep working with Russia whose cooperation will be key to diplomatic gains in the Middle East and elsewhere. Meanwhile, America's missile defenses face an enduring set of issues, especially target discrimination in the face of attacks designed to overwhelm the defenses, stage separation debris, chaff, decoys, and stealth. Dealing with target discrimination while also replacing, upgrading, or adding to the many elements of U.S. missiles defenses presents daunting budget priorities. A new look at the threat is warranted, and whether the U.S. needs to consider every nation that possesses even short-range missiles a threat to America. The proliferation of missiles of all sizes around the world is a growing problem, but expecting U.S. missile defenses to deal with all those missiles everywhere is unrealistic, and U.S. missile defenses, effective or not, are justifying more and more offensive missiles.

  20. The analysis of a generic air-to-air missile simulation model

    Kaplan, Joseph A.; Chappell, Alan R.; Mcmanus, John W.


    A generic missile model was developed to evaluate the benefits of using a dynamic missile fly-out simulation system versus a static missile launch envelope system for air-to-air combat simulation. This paper examines the performance of a launch envelope model and a missile fly-out model. The launch envelope model bases its probability of killing the target aircraft on the target aircraft's position at the launch time of the weapon. The benefits gained from a launch envelope model are the simplicity of implementation and the minimal computational overhead required. A missile fly-out model takes into account the physical characteristics of the missile as it simulates the guidance, propulsion, and movement of the missile. The missile's probability of kill is based on the missile miss distance (or the minimum distance between the missile and the target aircraft). The problems associated with this method of modeling are a larger computational overhead, the additional complexity required to determine the missile miss distance, and the additional complexity of determining the reason(s) the missile missed the target. This paper evaluates the two methods and compares the results of running each method on a comprehensive set of test conditions.

  1. Modeling Of Ballistic Missile Dynamics

    Salih Mahmoud Attiya


    Full Text Available Aerodynamic modeling of ballistic missile in pitch plane is performed and the open-loop transfer function related to the jet deflector angle as input and pitch rate, normal acceleration as output has been derived with certain acceptable assumptions. For typical values of ballistic missile parameters such as mass, velocity, altitude, moment of inertia, thrust, moment and lift coefficient show that, the step time response and frequency response of the missile is unstable. The steady state gain, damping ratio and undraped natural frequency depend on the missile parameters. To stabilize the missile a lead compensator must be added to the forward loop.

  2. Stability and Control of Tactical Missile Systems Held in Ankara (Turkey) on 9-12 May 1988


    Ankara. Turkey and for the facilities and personnel which made this meeting possible. Le Panel du Mecanique du Vol tient ii remercier les D6legucs...missile peut 6tre fournie soit par des outils de CAO, soit par des formulations analytiques . L~e premier exemple do calcul pr6sentA eat relatif i doUne mecttudo cone qni rend le ilisposit i d’.tcti vation iso~lastique et qoi supprime la resonance mecanique do basculemeot. Coin

  3. 导弹自动测试系统闭环量传与溯源方法%Closed-loop System of Valuation Transfer and Traceability for Missile Automatic Test System



    Based on the MAP theory,closed-loop system of valuation transfer and traceability are used to missile automatic test system by the transfer standard device for identifying the error of whole test system, and enhanced the calibration ability of missile ATS.%介绍了利用“传递标准”装置对测试系统各参数实施“闭环量传”,以确定测试系统整体参数相对于计量单位工作标准的偏差的方法,实现对测试系统整体参数的校准与评定。

  4. The North Korean Missile Program

    Wright, David


    In recent years, the development of ballistic missiles by North Korea has been a key motivation for US efforts to stem missile proliferation and to develop defenses against intermediate and long-range missiles. In the 1980s, North Korea reverse-engineered short-range Soviet Scud missiles and began to produce and sell them. In 1993, it flight-tested a missile reported to have a range of up to 1,300 kilometers, which would allow it to target most of Japan. In 1998, it launched a multi-stage missile over Japan; it later announced that the launch had been an attempt to place a satellite in orbit. An important question is what these tests imply for its current capability and its possible future missile development. Since North Korea has sold missiles to countries in the Middle East and South Asia and is reported to be assisting Iran's missile development program, understanding its capabilities is relevant to security concerns in several parts of the world. In this talk I will discuss my analysis of the publicly available information about North Korea's missile tests, and my conclusions about possible future developments. This includes estimates of ranges and payloads of its next potential generation of missiles, and comments about their potential military utility.

  5. Current Trends in Tactical Missile Guidance

    S. Vathsal


    Full Text Available The problem of tactical missile guidance is very challenging and has been treated using several basic metlfodologies in the past four decades. Major techniques can be grouped underclassical guidance laws, modern guidance laws, l'aws for manoeuvring targets, predictive guidance for endgame scenario, and guidance laws based on intelligent control methods. Each technique has some advantages and disadvantages while implementing in a practical system. Guidance law selection is dictated by nature of flight profile like boost, midcourse, terminal homing, etc, and also miss-distance and a single-shot kill probability. This paper presents a brief survey of the existing techniques and current trends in tactical missile guidance.

  6. 弹载计算机CPU数字模型系统开发%CPU Numerical Model System of the Embedded Computer in Airborne Missile

    罗阳; 侯俊刚


    提出弹载计算机数字模型系统的研制需求,在此基础上,分析了该系统的功能组成,然后从COFF文件解析、DSP软核、指令解析执行三个方面详细介绍了该系统的具体开发过程,最后给出应用结论。%The studying demand of numerical model system of the embedded computer in airborne missile is adverted in this article. On basis of this, the system composition is analyzed, and the develop- ment process of the numerical model system is introduced particularly in three ways, that is analysis of COFF file, DSP soft core and parsing command execution. Lastly, the applied conclusion is gained.

  7. Missile defence : An overview

    Weimar, P.W.L.


    At the present day, an unparalleled number of international actors, be it national governments or non-state groups, have acquired or are seeking to acquire both weapons of mass destruction and the means to deliver them. Those means of delivery can be Ballistic Missiles that can bridge vast – even

  8. Missile defence : An overview

    Weimar, P.W.L.


    At the present day, an unparalleled number of international actors, be it national governments or non-state groups, have acquired or are seeking to acquire both weapons of mass destruction and the means to deliver them. Those means of delivery can be Ballistic Missiles that can bridge vast – even in

  9. 导弹电源系统故障诊断实验%Experiment of fault diagnosis of missile power supply system

    安若铭; 杨峰; 孔翔; 陈少飞


    For using theory to guide practice, and further understanding of theory in practice, the computer-aided analysis of fault diagnosis experiment of missile power supply system is developed. Firstly, the dummy experimental system is established through Multisim 10. 0. Main fault patterns of power supply system are achieved by the dummy system. Secondly, the experimental hardware system is designed and produced for setting the fault. Thirdly, the diagnosis software is developed by Lab VIEW and VB based on multi-signal diagnosis model. The multi-signal fault diagnosis model is discussed in detail. The experimental procedures are given, and experimental data is processed and analyzed. The fault diagnosis process and the missile power supply system are deeply understood by students based on the experiment.%为了能用理论去指导实践,并在实践中进一步认识理论,开发了由计算机辅助分析的导弹电源系统故障诊断实验.首先,采用Multisim10.0电路仿真软件措建虚拟实验平台,获得电源系统的主要故障模式;然后,设计制造实验硬件平台,供实际设置故障;最后,基于多信号诊断模型,利用LabVIEW和VB开发了诊断软件.详细论述了多信号故障诊断模型的诊断原理,给出了实验步骤,并对实验数据进行了处理和分析.该实验使学生对故障诊断方法和导弹电源系统有了深刻认识和理解.

  10. Influence of seeker disturbance rejection rate on missile guidance system%平台导引头隔离度对导弹制导系统影响

    宋韬; 林德福; 王江


    Spring torque and damping torque are two main factors which cause seeker disturbance rejection rate problems, for studying the influence of seeker disturbance rejection rate on the guidance system of missile, a model of the guidance system which contains seeker disturbance rejection rate parasitical loop was established; the rela-tionship between the disturbance rejection rate and the stabilization of the guidance system was analyzed on basis of the model;under the typical noise input condition of radar seeker, the simulation gave the miss distances of missile corresponding to different seeker disturbance rejection rates. The results show that the guidance system parameters greatly affect the parasitical loop stability zone; the larger the disturbance rejection rate caused by spring torque, following the reduction of the distance between missile and target, the earlier the radiation of the guidance system. The larger the disturbance rejection rate caused by damping torque, the later the radiation of the guidance system;under the condition of seeker noise input, the larger the disturbance rejection rate caused by spring torque, the lar-ger the miss distance. The larger the disturbance rejection rate caused by damping torque, the smaller the miss dis-tance. The conclusion may provide theoretical instruction for the general missile design and the demonstration for the relevant indices of seeker.%弹簧力矩和阻尼力矩是平台导引头产生隔离度问题的主要因素,为了研究平台导引头隔离度对导弹制导系统的影响,建立了包含隔离度寄生回路的制导系统模型;在此模型的基础上,分析了隔离度与制导系统稳定性的关系;在雷达导引头典型噪声输入条件下,仿真得出了不同隔离度时对应的导弹脱靶量。结果表明:制导系统主要参数的变化会引起隔离度寄生回路稳定域的变化;弹簧力矩引起的隔离度越大,随着弹目距离接近制导系统越早

  11. Research on ballistic missile laser SIMU error propagation mechanism

    Wei Shihui; Xiao Longxu


    It is necessary that the laser inertial system is used to further improve the fire accuracy and quick reaction capability in the ballistic missile strapdown inertial navigation system. According to the guidance con-trolling method and the output and error model of ballistic missile laser SIMU, the mathematical model of error propagation mechanism is set up and any transfer environmental function of error coefficient that affects the fire accuracy is deduced. Also, the missile longitudinal/lateral impact point is calculated using MATLAB. These estab-lish the technical foundation for further researching the dispersion characteristics of impact point and reducing the laser guidance error.

  12. Anti-tank missile TV guidance image processing system design%反坦克导弹电视制导图像处理系统设计

    刘光灿; 白廷柱; 黄飞江


    Based on the function demand of the anti-tank missile TV guidance,the hardware of the image processing system, including a video signal pre-process module, a background subtraction circuit, a digital image processing module and other auxiliary modules, is designed. And all the functions of these modules are introduced. The software of the image processing system, including functions like image pre-process, image segmentation, target recognizing and tracking, is also designed. And especially expounded is the multimode threshold image segmentation algorithm and the image target recognizing &tracking algorithm. The experiment result shows the system that we designed can recognize and track anti-tank missile reliably.%根据反坦克导弹电视制导要求,设计了由视频预处理和背景减法电路模块、数字图像处理模块和其他辅助功能模块组成的图像处理系统硬件部分,介绍了这些模块的作用和功能;设计了包含图像预处理、目标分割、目标识别和目标跟踪等功能的图像处理系统软件部分,特别对图像目标的多模阈值分割和识别跟踪处理方法进行了阐述,给出了实验结果.实验结果表明,该系统能可靠识别和跟踪反坦克导弹.

  13. 某车载导弹发射系统振动特性%Vibration characteristics of a vehicular missile launching system

    高星斗; 毕世华; 陈阵


    建立了某多联装车载导弹发射系统多体动力学模型,从理论、仿真计算、试验方面对发射系统的振动特性进行研究,分析计算了整体结构的振动模态,得到发射系统固有频率在3~20 Hz范围内,为车载导弹倾斜发射系统整体结构振动模态试验及动态响应分析提供了重要参考.试验结果与仿真结果的最大相对误差绝对值小于10%,计算结果与模态试验结果吻合较好,验证了建模及分析计算方法的正确性.%The multi-body dynamics model of a multiple missile launcher was built,and its vibration characteristics were studied from three aspects of theory calculation, simulation calculation and test; vibration modes were computed and analyzed. The results show that the natural frequency of launching system is about 3 - 20 Hz, which can also provide an important reference to modal testing and dynamic response analyzing of the whole vehicular missile oblique launching system. As the absolute value of the maximum relative error between results of simulation and test is less than 10% , the calculation results agree well with modal testing results, verifing the correctness of the modeling and analyzing method.

  14. 77 FR 51970 - Renewal of Missile Defense Advisory Committee


    ... configurations for the Ballistic Missile Defense System. The Committee shall be composed of not more than eleven... shall be comprised of no more than seven members. The primary focus of the Subcommittee is to conduct...

  15. Attacking the Cruise Missile Threat


    little warning before a strike. Cruise missiles such as Silkworm and Exocet are designed to fly at “sea-skimming” levels only a few feet above the surface...the SS-N-2 Styx missile, a surface-to-surface antiship cruise missile. Most variants of modern cruise missiles are conversions of the Styx—the Silkworm ...number of Soviet built SS-N-2 Styxes that had been dismounted from boats.23 The Silkworm , the predominant of these variants, is the “Scud” of cruise

  16. Innovation in Aerodynamic Design Features of Soviet Missiles

    Spearman, M. Leroy


    Wind tunnel investigations of some tactical and strategic missile systems developed by the former Soviet Union have been included in the basic missile research programs of the NACA/NASA. Studies of the Soviet missiles sometimes revealed innovative design features that resulted in unusual or unexpected aerodynamic characteristics. In some cases these characteristics have been such that the measured performance of the missile exceeds what might have been predicted. In other cases some unusual design features have been found that would alleviate what might otherwise have been a serious aerodynamic problem. In some designs, what has appeared to be a lack of refinement has proven to be a matter of expediency. It is a purpose of this paper to describe some examples of unusual design features of some Soviet missiles and to illustrate the effectiveness of the design features on the aerodynamic behavior of the missile. The paper draws on the experience of the author who for over 60 years was involved in the aerodynamic wind tunnel testing of aircraft and missiles with the NACA/NASA.

  17. An analysis of the common missile and TOW 2B on the Stryker anti-tank guided missile platform, using the Janus simulation


    Approved for public release; distribution in unlimited. The U.S. Army is beginning to field the first of six Stryker Brigade Combat Teams (SBCTs) and equip the organic Anti-Tank (AT) Company of the Brigade with the LAV III Anti-Tank Guided Missile (ATGM) Platform and the Tube-Launched, Optically-Tracked, Wire-Guided 2B (TOW 2B) missile system. A developmental effort is currently underway to replace the aging TOW 2B and Hellfire missile systems with a common missile that meets both ground...

  18. ARMS CONTROL: U.S. Efforts to Control the Transfer of Nuclear-Capable Missile Technology


    risk of diversion is an important part of its analysis, Commerce focuses its reviews on certain countries that are developing nuclear-capable missiles...ogy to countries developing nuclear-capable missile systems. Our work was conducted in the United States at the Departments of State, Commerce , and...the MTCR in halting the transfer of MTCR-related systems and technology to countries developing nuclear-capable missile systems. The objectives, scope

  19. European Missile Defense and Russia


    most senior level—the only one that matters in Russian decisionmaking cul - ture—is also of significance today and will also be re- ferred to later in... org /missile-defense/us-ballistic-missile-defense/p30607. 9. Email exchange with author, July 2013. 10. “Safeguard,” Washington, DC: Federation of Ameri

  20. System Requirements Analysis and Technological Support for the Ballistic Missile Defense System (BMDS) - FY07 Progress Report


    formal requirement for a distributed-system protocol ( leader election ) operating with non- ideal communication links. The proof-of-concept prototype is OMNeT++ Figure 5 shows the top-level statechart of a leader election (LE) module. The top-level statechart consists of four states, the...component under test using events, time, and data information specified in the component. The likelihood of success of the leader - election requirement

  1. Cruise Missile Attack Are We Prepared


    to be met to make its air and missile defense systems interoperable with others throughout the military because the requirements for SIAP [Single...Single Integrated Air Picture ( SIAP ) and Integrated Fire Control (IFC). SIAP “is the product of fused, near real-time and real-time data from...guidance of the Assistant Secretary of the Army for Acquisition, Logistics, and Technology (ASAALT), the Joint SIAP System Engineering Organization (JSSEO

  2. Passive Acoustic Radar for Detecting Supersonic Cruise Missile

    XIAO Feng; XIAO Hui


    A Passive Acoustic Radar is presented as a necessary complement to electromagnetic wave radar, which will be expected to be an effective means for detecting cruise missiles. Acoustic characteristics of supersonic flying projectiles with diverse shapes are expounded via experiment. It is pointed out that simulation experiment could be implemented using bullet or shell instead of cruise missile. Based on theoretical analysis and experiment, the "acoustic fingerprint" character of cruise missile is illustrated to identify it in a strong noise environment. After establishing a locating mathematical model,the technique of acoustic embattling is utilized to resolve a problem of confirming the time of early-warning, considering the fact that velocity of sound is much slower than that of light. Thereby, a whole system of passive acoustic radar for detecting supersonic cruise missile is formed.

  3. Design and Realization of Embedded Precision Testing System for Air-ship Missile Fire Control System%空舰导弹火控系统嵌入式精度测试仪的设计与实现

    马向玲; 赵安兴; 蔡虎


    Precision test for air-ship missile fire control system is one of the important content for the missile weapon system capability test, which defined the precision of the missile mostly.The precision testing device can keep flying security; improve training level and maintenance quality.The advanced embedded system including ARM hardware and LINUX operating system were used.As recorded data bus standard, ARINC429 formation was followed to realize the precision testing device.The recorded data was transferred through the Ethernet communication interface and was analysis on the ground to judge whether it satisfied the precision or not.%空舰导弹火控系统的精度测试是导弹武器系统测试的重要内容之一,在很大程度上决定了导弹的命中精度,精度测试仪对于保障飞行安全,提高飞行训练水平和机务维护质量都具有十分重要的作用.采用先进的嵌人式系统设计方法,以嵌入式硬件ARM和LINUX嵌入式操作系统为基础,以ARINC429为录取数据总线标准,对精度测试仪进行了设计与实现.利用网络通信,对录取的数据在地面进行分析,并对其是否满足精度指标进行判定,完全满足了航空机载设备的要求.

  4. Sea-Based Ballistic Missile Defense - Background and Issues for Congress


    Aegis ships. The program involved modifying the SM-2 Block IV air-defense missile. The missile, as modified, was called the Block IVA version. The...system was designed to intercept descending missiles endo-atmospherically (i.e., within the atmosphere) and destroy them with the Block IVA missile’s...the SBX radar in Texas.52 SBX underwent sea trials and high- power radiation testing in the Gulf of Mexico in 2005. It was then moved by a heavy

  5. The Future of Theater Missile Defense


    withERINT) 1,500 IVf 74C 1998 3.0 Navy Lower-Tier Defense 1,820 SO4 50* 1999° 3* THAAD(withTMD-GBR) 1,313 80 14 2001e 9.1 AdvaaoedCapabflitylMD Systems...Administration cannot, by itself, provide a sufficient buffer between theater and strategic missile defenses. Other limits must be included. Finally, the

  6. Design of Missile Launch Control System Based on FlexRay Bus%基于FlexRay总线的导弹发射控制系统设计

    毕崇伟; 黄志勇; 齐强


    It is introduced that FlexRay bus technology has strong points of high data transmission speed,high reliability and supporting distributed control system. Based on HCS12 SCM, basic architecture of missile launch control system is presented. The hardware and software of interface circuit are designed by using MFR4200 as controler. The hardware components of interface adapter are studied. Because missile-borne equipment is getting complicate increasingly, missile launch control system is designed on the base of FlexRay bus technology to improve its reliability in real-time.%介绍了FlexRay总线技术具有数据传输速率高、可靠性高及支持分布式控制等优点.以HCS12单片机为核心, 提出了导弹发射控制系统的基本结构.以MFR4200为控制器, 设计了接口电路的硬件和软件.研究了接口适配器的硬件构成.随着弹上设备的日趋复杂, 设计了基于FlexRay总线技术的导弹发射控制系统, 可改善发射控制系统的可靠性, 提高对导弹发射控制的实时性.

  7. Flight testing of the AIM/RIM-7M missile, preflight analysis

    Hicks, W.; Greenberg, E.


    The AIM/RIM-7M missile is the most recent version of the AIM-7 missile series. It is in the preproduction phase and has completed most of the preproduction flight test evaluation. A description is presented of the preflight simulation techniques used, taking into account the value of the techniques in predicting the results of actual flights. The AIM/RIM-7M is a semiactive, radar-guided homing missile with sophisticated onboard digital processing. It may be launched from either an aircraft or a surface system. To a large degree, the AIM/RIM-7M represents problems typical of all guided missiles. The described techniques are directly applicable to radar-guided missiles and generically to all types of guided missiles. Attention is given to simulation bay activities, the anechoic chamber, aspects of RF control, the target array, computer models, aspects of preflight simulations, and the test setup.

  8. The proliferation of aerospace weapons technology: Ballistic missiles and the case of Brazil

    Vossen, Terrence John


    The rationale behind the development of ballistic missile production in Brazil is examined by exploring the political, military, and economic determinants of ballistic missile demand in that country. To ascertain how Brazil developed missile production capabilities, the contributions of aerospace industries in industrialized states, the Brazilian space program, trade between less-developed countries, and illicit trade in missile technology are assessed. It is argued that missile development increasingly became a function of economic as opposed to security considerations, and that technologies transferred from developed country aerospace firms and Brazil's space program were primarily responsible for the creation of production capabilities. It is also contended that the proliferation of missile technology to Brazil was consistent with the workings of a system evident in the aerospace weapons technology market that sustains the horizontal spread of weapons production capabilities.

  9. Application of Pontryagin’s Minimum Principle in Optimum Time of Missile Manoeuvring

    Sari Cahyaningtias


    Full Text Available Missile is a guided weapon and designed to protect outermost island from a thread of other country. It, commonly, is used as self defense. This research presented surface-to-surface missile in final dive manoeuvre for fixed target. Furthermore, it was proposed manoeuvring based on unmanned aerial vehicle (UAV, autopilot system, which needs accuration and minimum both time and thrust of missile while attacking object. This paper introduced pontryagin’s Minimum Principle, which is useable to solve the problem. The numerical solution showed that trajectory of the missile is split it up in three sub-intervals; flight, climbing, and diving. The numerical simulation showed that the missile must climb in order to satisfy the final dive condition and the optimum time of a missile depend on initial condition of the altitude and the terminal velocity

  10. Using NASTRAN to model missile inertia loads

    Marvin, R.; Porter, C.


    An important use of NASTRAN is in the area of structural loads analysis on weapon systems carried aboard aircraft. The program is used to predict bending moments and shears in missile bodies, when subjected to aircraft induced accelerations. The missile, launcher and aircraft wing are idealized, using rod and beam type elements for solution economy. Using the inertia relief capability of NASTRAN, the model is subjected to various acceleration combinations. It is found to be difficult to model the launcher sway braces and hooks which transmit compression only or tension only type forces respectively. A simple, iterative process was developed to overcome this modeling difficulty. A proposed code modification would help model compression or tension only contact type problems.

  11. Research on Life Determination and Extension of Missile Weapon System Based on Multilevel Finite Element%基于多级有限元方法的导弹武器定寿延寿研究

    常新龙; 张有宏; 岳春国; 余堰峰; 刘万雷


    提出了多级有限元的概念,将导弹结构定寿延寿工作划分为3个有限元分析步骤进行,在有限元分析的过程中考虑了导弹结构原始状态、老化缺陷状态及修理/换件的影响,对导弹结构强度及剩余寿命进行了科学准确的评判.利用该理论对含有老化和裂纹等损伤因素的药柱结构质量状态和对出现的裂纹损伤进行修复的效果进行了评价.结果表明,该方法科学合理,可为导弹武器系统定寿延寿工作提供一定的理论参考.%The concept of multilevel finite element was presented. The life determination and extension of missile structure was divided to three finite element analysis steps. In the finite element analysis, the influence of original state, weathering state, and repair or replacement of missile structure was considered. The structural strength and residual life of missile structure was estimated exactly. Using this method, the quality state of grain considering factors such as aging and crack damage and the effect of repair for crack damage were evaluated. The results showed that this method is scientific and can provide a reference for life determination and extension of missile weapon system.

  12. 通用空空导弹ACMI毁伤评估仿真模型%"Hit or Miss" Assessment of Generic Air-to-Air Missile Simulation Model in ACMI System

    张滢; 杨任农; 左家亮


    空空导弹飞行速度快,在系统传输延迟时间内,飞行距离往往大于战斗部的威力半径,难以确定目标机的毁伤情况.可以通过空战演习训练(ACMI)系统能大幅提升空战作战效能,在安全条件下,一般采用仿真模型代替实弹,进行毁伤评估.根据空空导弹飞行力学原理,建立导弹运动方程.为了准确进行毁伤评估,提出了计算导弹与目标最小距离的两种方法,实现延迟时间内完成导弹毁伤评估.最后给出评估的具体条件,建立模型进行仿真.仿真结果证实了模型的合理性和可行性.%Operational efficiency in the air combat can be greatly improved by introducing ACMI system for training. Considering the aspects of money and safety, it is the "Hit or Miss" assessment that uses the missile simulation models instead of the real ones. However, As a result of the high speed of the air-to-air missile, its flying distance within the transmission time is usually beyond the explosive range, which makes it difficult to assess. Firstly, the equation is set up in this paper, according to the theory of missile flight mechanics. Then, two methods which calculate the closest approach between missile and target aircraft are presented to accomplish the assessment within the transmission time. By listing several conditions, the "Hit or Miss" assessment of the missile model is established,and the simulation experiments prove its rationality and usefulness.

  13. 48 CFR 225.7016 - Restriction on Ballistic Missile Defense research, development, test, and evaluation.


    ... 48 Federal Acquisition Regulations System 3 2010-10-01 2010-10-01 false Restriction on Ballistic Missile Defense research, development, test, and evaluation. 225.7016 Section 225.7016 Federal Acquisition... Acquisition 225.7016 Restriction on Ballistic Missile Defense research, development, test, and evaluation. ...

  14. Joint Air-to-Ground Missile (JAGM)


    Navy. The JAGM mission is to develop the next generation of aviation launched fire and forget missiles to replace the HELLFIRE laser and Longbow...EMD contract to develop the next generation of aviation launched missiles to replace the HELLFIRE laser and Longbow radar missiles . JAGM December 2015...Selected Acquisition Report (SAR) RCS: DD-A&T(Q&A)823-355 Joint Air-to-Ground Missile (JAGM) As of FY 2017 President’s Budget Defense Acquisition

  15. Large Scale Software System Design of the Missile Minder AN/TSQ-73 Using the ADA Programming Language.


    line of the graphic. Thus, a two-lined graph could be used to re resent ten levels of abstraction -lined9 system 99and a three-lined graph 9 funtion ...of module interdependence, called tightly coupled, errors or changes in any part of the system will resonate or ripple through the entire system... magnetic tape devices (if not -- initialized for svstem bootstrap), displaw consoles, D-5 -- auxiliarw read-outs, status disPlaw Panels, etc

  16. Remote control missile model test

    Allen, Jerry M.; Shaw, David S.; Sawyer, Wallace C.


    An extremely large, systematic, axisymmetric body/tail fin data base was gathered through tests of an innovative missile model design which is described herein. These data were originally obtained for incorporation into a missile aerodynamics code based on engineering methods (Program MISSILE3), but can also be used as diagnostic test cases for developing computational methods because of the individual-fin data included in the data base. Detailed analysis of four sample cases from these data are presented to illustrate interesting individual-fin force and moment trends. These samples quantitatively show how bow shock, fin orientation, fin deflection, and body vortices can produce strong, unusual, and computationally challenging effects on individual fin loads. Comparisons between these data and calculations from the SWINT Euler code are also presented.

  17. Discussion of the target-missile control scheme with supersonic speed at minimum altitude


    An antiship missile with supersonic speed at minimum altitude is an effective weapon to break through a defense line. The former Soviet Union was a leader in this field since it had developed several kinds of antiship missiles which obtained supersonic speed at minimum altitudes. To counter this kind of missile,many countries have been developing corresponding antimissiles. For the purpose of verifing the antimissile missile's effectiveness in intercepting antiship missiles, a target-missile is needed. A target-missle is cheaper and can imitate the main characteristics of antiship missiles with supersonic speed at minimum altitude. In this paper, the control scheme of a target missile flying with supersonic speed at minimum altitude is studied. To counter the problem of hedgehopping over the sea, a control scheme utilizing a SINS + altimeter was proposed.In this scheme, both the quick response ability of altitude control and the anti-jamming problem were considered. A simulation experiment shows that when an integrated altitude control system is used, the anti-disturbance ability of the integrated altitude is good and the response speed of altitude control system can be dramatically improved.

  18. Flexible missile autopilot design studies with PC-MATLAB/386

    Ruth, Michael J.


    Development of a responsive, high-bandwidth missile autopilot for airframes which have structural modes of unusually low frequency presents a challenging design task. Such systems are viable candidates for modern, state-space control design methods. The PC-MATLAB interactive software package provides an environment well-suited to the development of candidate linear control laws for flexible missile autopilots. The strengths of MATLAB include: (1) exceptionally high speed (MATLAB's version for 80386-based PC's offers benchmarks approaching minicomputer and mainframe performance); (2) ability to handle large design models of several hundred degrees of freedom, if necessary; and (3) broad extensibility through user-defined functions. To characterize MATLAB capabilities, a simplified design example is presented. This involves interactive definition of an observer-based state-space compensator for a flexible missile autopilot design task. MATLAB capabilities and limitations, in the context of this design task, are then summarized.

  19. Missile Defense: DOD’s Report Provides Limited Insight on Testing Options for the Ground-based Midcourse Defense System


    Cochran Ranking Member Subcommittee on Defense Committee on Appropriations United States Senate The Honorable Howard P. " Buck " McKeon Chairman The...System Component Mission Location Ground Based Interceptor (GBI) The interceptor consists of a silo-based, three-stage booster stack and a “hit-to

  20. Design of Recording System for Air-to-Air Missile Based on Flash Chip%基于 Flash 芯片的弹载记录系统设计



    针对弹载记录系统大容量、高速率数据的记录需求,设计了一种基于Flash芯片的弹载记录系统。该系统以FPGA芯片为控制核心,通过并行总线操作、流水线操作等技术实现数据的高速存储,并利用下载软件的多线程功能实现数据的快速下载。具有存储速率高、可靠性高、扩展性好等优点。%In order to meet the requirement of recording system used in air-to-air missile such as large capacity and high rate data , the design method of recording system for air-to-air missile based on flash chip is introduced .The system takes the FPGA chip as the control core , through the parallel bus op-eration, pipeline operation and other technologies to achieve high-speed data storage , and the download software is used to achieve the fast download of data .This system has the advantages of high storage rate , high reliability and good expansibility .

  1. Trajectory Optimization Design for Morphing Wing Missile

    Ruisheng Sun; Chao Ming; Chuanjie Sun


    This paper presents a new particle swarm optimization ( PSO) algorithm to optimize the trajectory of morphing⁃wing missile so as to achieve the enlargement of the maximum range. Equations of motion for the two⁃dimensional dynamics are derived by treating the missile as an ideal controllable mass point. An investigation of aerodynamic characteristics of morphing⁃wing missile with varying geometries is performed. After deducing the optimizing trajectory model for maximizing range, a type of discrete method is put forward for taking optimization control problem into nonlinear dynamic programming problem. The optimal trajectory is solved by using PSO algorithm and penalty function method. The simulation results suggest that morphing⁃wing missile has the larger range than the fixed⁃shape missile when launched at supersonic speed, while morphing⁃wing missile has no obvious range increment than the fixed⁃shape missile at subsonic speed.

  2. Terrain Contour Matching (TERCOM): A Cruise Missile Guidance Aid

    Golden, Joe P.


    The Cruise Missile is guided by an inertial guidance system aided by an updating technique called Terrain Contour Matching (TERCOM). Chance-Vought first proposed the terrain correlation technique in the late 1950's. Since that time TERCOM has evolved into a reliable, accurate, all weather, day and night method of position fixing and updating for cruise missiles. A brief history of TERCOM development will be presented giving results where possible. A description of TERCOM and how is works will be discussed. A snapshot of the present TERCOM status and future planned developments will be addressed.

  3. Robust missile feedback control strategies

    Trottemant, E.J.; Scherer, C.W.; Weiss, M.; Vermeulen, A.


    The nature of the missile interception problem with two noncooperative players leads to the field of differential games. Introducing nonlinear uncertain models can potentially lead to nonexistence of game theoretic equilibrium strategies, computationally intractable problems, and/or highly reduced p

  4. 高超声速反舰导弹作战效能指标体系研究%Operational Effectiveness Criteria System of Hypersonic Anti-ship Missile

    王少平; 董受全; 李晓阳; 沈振华


    分析了包括高超声速反舰导弹在内的高超声速武器的发展现状,明确了高超声速反舰导弹的基本定义和不同的分类方式,以及高超声速反舰导弹飞行弹道分段标准和分段名称,概括总结了高超声速反舰导弹主动段、惯性段、再入滑翔段和下压段等四个弹道阶段的任务和特点,建立了以射击精度等四项效能指标为一级指标的作战效能指标体系,并对效能指标的具体含义及分析方法进行了说明。%Development status of hypersonic weapon is analyzed, which includes hypersonic anti⁃ship missile. Basic defini⁃tion, different classification, sub⁃standard and names of variable trajectory of hypersonic anti⁃ship missile are specified. The tasks and characteristics of boost phase, reentry glide trajectory, inertial phase and pressurizing⁃down phase are summarized. The operational effectiveness criteria system is proposed,which includes four first grade indexes, firing accuracy of anti⁃ship missile, for example. Specific meaning and analysis methods of operational effectiveness indexes are introduced.

  5. 防空导弹武器系统通用火控软件设计与实现%General Design and Accomplishment of Firepower Control Software in Air Defense Missile Weapon System



    针对不同防空导弹武器系统的火控软件之间不能互用的现状,分析了火控系统各主要功能模块之间的接口关系,提出了火控软件通用化设计的思路,并用C++实现了该设计.火控软件的通用化设计值碍将来防空导弹能武器系统火控软件的标准化设计和编程借鉴.%s :Contrasting the status of no interoperability in firepower control softwares among different aerial defense missile weapon system, the interface relation of functional module in firepower control system is analyzed.And the idea of general design of firepower control software is put forward.Furthermore, the idea is realized by using C++ programming.The general design of firepower control software is worth used for reference in the standard design and programming of future aerial defense missile weapon system.

  6. Modelling cavitating flow around underwater missiles

    Fabien Petitpas


    Full Text Available The diffuse interface model of Saurel et al. (2008 is used for the computation of compressible cavitating flows around underwater missiles. Such systems use gas injection and natural cavitation to reduce drag effects. Consequently material interfaces appear separating liquid and gas. These interfaces may have a really complex dynamics such that only a few formulations are able to predict their evolution. Contrarily to front tracking or interface reconstruction method the interfaces are computed as diffused numerical zones, that are captured in a routinely manner, as is done usually with gas dynamics solvers for shocks and contact discontinuity. With the present approach, a single set of partial differential equations is solved everywhere, with a single numerical scheme. This leads to very efficient solvers. The algorithm derived in Saurel et al. (2009 is used to compute cavitation pockets around solid bodies. It is first validated against experiments done in cavitation tunnel at CNU. Then it is used to compute flows around high speed underwater systems (Shkval-like missile. Performance data are then computed showing method ability to predict forces acting on the system.

  7. Joint Air-to-Surface Standoff Missile (JASSM)


    Defense Program ICE - Independent Cost Estimate IOC - Initial Operational Capability Inc - Increment JROC - Joint Requirements Oversight Council $K...penetrating warhead with a robust blast fragmentation capability. The missiles employ an IIR seeker system to attack fixed, point targets requiring precision

  8. 22 CFR 121.16 - Missile Technology Control Regime Annex.


    ... missile systems, see § 121.1, Cat. VIII (a), target drones and reconnaissance drones (see § 121.1, Cat... (see § 121.1, Cat. IV(h)); (b) Reentry vehicles (see § 121.1, Cat. IV(g)), and equipment designed or modified therefor, as follows, except as provided in Note (1) below for those designed for...

  9. Joint Counterair and Theater Missile Defense Doctrine to Defend against Unmanned Aerial Vehicles and Cruise Missiles in Asymmetric Warfare


    state lasers, and a megawatt-class Chemical Oxygen Iodine Laser (COIL) to detect, track, target, and destroy ballistic missiles shortly after launch... disproportionate cost tradeoff between threat weapon systems and the proposed interceptors. With a price tag of over $1M per interceptor such as Patriot

  10. Missile vascular injuries: 19-year experience.

    Ahanger, Abdul Gani; Wani, Mohd Lateef; Lone, Reyaz Ahmad; Singh, Shyam; Hussain, Zahur; Mir, Ishtiyak A; Irshad, Ifat; Ashraf, Hakeem Zubair; Dar, Abdul Majeed; Lone, Ghulam Nabi; Bhat, Mohammad Akbar; Sharma, Mukand Lal


    Missile vascular injuries have reached an epidemic proportion in Kashmir valley since the eruption of militancy. The present study was undertaken to analyze the mode, pattern, presentation, and management of missile vascular injuries. A retrospective study of patients with missile vascular injury from January 1990 to October 2008 was undertaken. Five hundred eighty patients with missile vascular injury were studied. All patients with vascular injury due to causes other than missiles were excluded from the study. Most of the patients were treated by interpositional saphenous vein graft or end-to-end anastomosis. The most common complication was wound infection (22.7%) followed by graft occlusion (3.8%). The amputation rate was 3.3% and was higher in patients with a delay of >6 hours to revascularization and associated fractures. Missile vascular injury requires prompt resuscitation and revascularization. Preoperative angiography is seldom necessary. Doppler study may sometimes be needed to aid in the diagnosis.

  11. Electro-chemical batteries for guided missiles

    H. S. Jaggi


    Full Text Available Electro-chemical batteries owing to their simplicity and ease of stowage form one of the sources of electrical power inside a missile. However, all batteries are not suited for this application. This article describes the special features required of a missile borne battery pack and discusses the characteristics of various types of batteries available today in the world. Conclusions have been drawn as to the most suitable types of batteries for missile applications.

  12. Countering Air and Missile Threats


    carrying the CMs. (2) SLCMs and ground-launched cruise missiles ( GLCMs ) present opportunities for detection as well as challenges for surveillance...if possible, and engage them before they can navigate to their targets. (6) Training patterns or identifiable launch sequence events for GLCMs are...rarely observed or practiced in an overt environment. Consequently, the probability is small for conclusively identifying a GLCM TEL using current

  13. Soviet debate on missile defense

    Parrott, B.


    Although the Strategic Defense Initiative (SDI) is meant to cope with the danger of a Soviet nuclear attack, the recent US debate over SDI has paid surprisingly little attention to Soviet views of ballistic missile defense. Despite the existence of a substantial body of pertinent scholarship, the debate has failed to take adequate account of major changes in Soviet ballistic missile defense policy since the mid-1960s. It has also neglected the links between current Soviet military policy and broader Soviet political and economic choices. The Soviets regard SDI not as a novel undertaking to reduce the risks of nuclear war but as an extension of the geopolitical competition between the superpowers. This competition has been dominated in the 1980s, in the Soviet view, by sharply increased US assertiveness and the decline of detente. Viewing SDI as a manifestation of these general trends, Soviet decision makers find the prospect of an unregulated race in ballistic missile defenses and military space technologies deeply unsettling. The deterioration of superpower relations has raised serious doubts in Moscow about the wisdom of Soviet external policy during the 1970s and has provoked sharp internal differences over policy toward the US. Already highly suspicious of the Reagan administration, the elite is united by a general conviction that SDI is an American gambit that may ultimately undercut past Soviet strategic gains and pose a grave new threat to Soviet security. 14 references.

  14. Missile Electro-Optical Countermeasures Simulation Laboratory

    Federal Laboratory Consortium — This laboratory comprises several hardware-in-the-loop missile flight simulations designed specifically to evaluate the effectiveness of electro-optical air defense...

  15. Evaluation of Operational Capability for Surface-to-Air Missile Weapon System Based on Neural Network%基于神经网络的地空导弹武器系统作战能力评估

    李国宏; 孙健; 夏伟鹏; 康红霞


    The limitations of evaluation method of operational capability for surface-to-air missile weapon system are analyzed in the light of the characteristics of its operational use in this paper. The index system for evaluating the operational capability of surface-to-air weapon system according to the principle of setting the index system. Through analysis of the structure and characteristics of artificial neural network,the neural network model used to evaluate the operational capability of surface-to-air missile weapon system. This model needs not to determine the strict quantitative relations between different factors,overcome the negative influences of man-made factors.%根据地空导弹武器系统的作战使用特点,分析了评估其作战能力方法的局限性.根据指标体系设置的原则,建立了地空导弹武器系统作战能力评价指标体系.通过分析人工神经网络的结构和特点,设计了评估地空导弹武器系统作战能力的神经网络模型.该模型不需要确定各因素之间严格的定量关系,克服了以往由于人为因素所造成的负面影响.最后通过实际应用,说明该方法简便易行,准确可靠.

  16. Research on the Dynamic Recombining Algorithm About the Multiple Missiles Cooperative Attacking Net Combat System%多弹协同攻击网络化作战系统动态重组算法研究

    王君; 朱永文; 崔颢; 梁文波


    The combat thinking is put forward,which is to set up multiple missiles cooperative attacking net combat system based on the dynamic founded net with many remote range air-to-air missiles.And the dynamic founding net system's topology relation finding algorithm is realized by using the searching method in chart theory and defining the application layer data message,which is also used to study the dynamic founding net system's recombining algorithm and to convert the topology relation to the nothing orientation chart Abstractively.By research on dynamic recombining problem with chart theory tools,some reference is provided for new type of air-to-air missiles' cooperative attacking net combat system when the system member node is destroyed in battle field or something wrong is with the communication system.%提出了利用多枚远程空空导弹在空中动态组网,构建多弹协同攻击的网络化作战系统的作战思想.利用图论中的搜索方法、定义应用层数据报文实现动态组网系统的拓扑关系发现算法,并利用拓扑关系发现算法研究了动态组网系统的动态重组算法,将动态组网系统拓扑关系抽象成图论中的无向图,利用图论工具来研究系统成员节点战损与通信故障情况下动态重组问题,为新一代空空导弹协同攻击网络化作战系统的研究提供一定的参考.

  17. 小型弹用电动舵系统中永磁同步交流电机应用技术研究%Research on the technique of PMSM application on minitype electromechanical actuation systems of missiles



    PMSM has been applied in high-power/high precision electromechanical actuation systems widely because of its excellent performance. The technique development of embedded digital systems and power electronics and the advance of digital techniques on missiles build the conditions of PMSM applied in electromeehanical actuation systems of missiles. The high power electromeehanical actuation systenis are demanded more necessarily along with the electrical power transmission technique in aircraft. The paper sets up the model about the control and drive for PMSM, designs the project of the electromechanical actuation system that PMSM is applied, and makes a simulation.%在大功率、高精度伺服系统中,永磁同步交流电机凭借优异的性能应用越来越广泛,嵌入式数字系统和电力电子技术的发展和导弹数字化程度的提高,给永磁同步交流电机应用到导弹电动舵系统中提供了条件。随着飞行器功率电传技术发展,对大功率电动舵系统需求日益突出,本文建立了永磁同步交流电机驱动控制模型,设计了采用永磁同步交流电机的电动舵系统方案,进行了仿真分析。

  18. Infrared ship/decoy/missile encounter model

    Morin, Josee; Reid, Francoise; Morin, Andre


    Simulations of missile-ship-countermeasures engagements are used to determine the effective ways of defending a ship against infrared-guided missile threats. This paper describes one type of simulation that models the engagement of a ship deploying IR decoys by an infrared-guided seeker-head missile. This model was developed to assess the efficiency of IR decoys in protecting ships against these missiles. The simulation, Missile Infrared Decoy And Ship (MIDAS), is composed of three major blocks, the infrared scene generation, the seeker simulation and the missile dynamics simulation. The infrared scene generation block produces a three-dimensional IR scene from the target ship and flare models and transforms it into the two-dimensional IR image viewed by the seeker. The seeker simulation block is based on a generic conical scan seeker which uses a crossed-detector array for target detection. It processes the IR image to select a target and generates a steering command. The missile dynamics block computes the changes in missile trajectory according to the seeker steering command. The computations performed by each of the three blocks are explained in detail.

  19. Design and Analysis of Information Flow in Missile Control System Based on 1553B Protocol%基于1553B协议的导弹控制系统信息流设计探讨

    陈亮; 刘丽霞; 刘经宇


    553B bus, with feature of reliability, real time and openness, is applied widely in the field of Aerospace. The defects of the bus, which include the limitation of data rate and transmission efficiency, and that the design of information flow is not standardized, restrict its broadness and depth of applications in the future Aerospace. In response to these issues, we redefine the data word in 1553B messages and achieve the organic combination of the 1553B messages, which meets the demand of large data transmission in the missile control system. And we analyze the design of information flow of the missile control system based on a typical bus topology.%1553B总线技术具有可靠性、实时性、开放性等特点,在航天领域中得到了广泛地应用;但其在总线传输速率、大数据量传输效率等方面的局限性,以及在具体应用实践中信息流编排的不规范性,严重制约了其在未来航天等领域的应用广度和深度;针对上述问题,从工程实践出发,对1553B协议定义的消息进行规范化处理,实现了原有消息的有机组合,以适应导弹控制系统信息流设计的需求,并以一典型导弹控制系统总线拓扑结构为模型进行了信息流设计的初步分析.

  20. BTT autopilot design for agile missiles with aerodynamic uncer tainty

    Yueyue Ma; Jie Guo; Shengjing Tang


    The approach to the synthesis of autopilot with aerody-namic uncertainty is investigated in order to achieve large maneu-verability of agile missiles. The dynamics of the agile missile with reaction-jet control system (RCS) are presented. Subsequently, the cascade control scheme based on the bank-to-turn (BTT) steering technique is described. To address the aerodynamic un-certainties encountered by the control system, the active distur-bance rejection control (ADRC) method is introduced in the autopi-lot design. Furthermore, a compound control er, using extended state observer (ESO) to online estimate system uncertainties and calculate derivative of command signals, is designed based on dynamic surface control (DSC). Nonlinear simulation results show the feasibility of the proposed approach and validate the robust-ness of the control er with severe unmodeled dynamics.

  1. Adaptive Autopilot Design for Missile Systems with Aerodynamics Uncertainties%带有气动参数不确定性的导弹自动驾驶仪设计



    The autopilot design for a class of nonlinear missile systems with aerodynamics uncertainies is presented. First of all, an uncertain nonlinear mathematical model is constructed for the missile in the pitch plane. Then, using adaptive robust control theory and backstepping technology, an adaptive robust control scheme is proposed. The term of control fin detection angle is considered in the attack angle channel and removing the assumption of attack angle. Simulation results with the Mach value of 2. 5、 1.8、 3.0 verify the effectiveness of the control law.%针对一类不确定导弹系统,考虑系统中存在气动参数不确定性,研究其自动驾驶仪的设计问题;由导弹俯仰面的力学模型及气动参数的多项式模型,考虑舵偏角为控制输入建立二阶导弹系统模型,基于自适应控制得到导弹自动驾驶仪的设计方法,使得闭环系统稳定且攻角快速跟踪指令信号;文章充分考虑系统模型攻角通道中存在舵偏项的影响且不需假设导弹攻角为小量,使得系统模型更具有一般性;仿真中马赫数分别取为2.5、1.8、3.0并考虑50%的参数摄动,结果表明文章设计的自动驾驶仪指令跟踪精度高,鲁棒性强.

  2. Design for Super-short-range Low-cost Intercept Missile of Active Protection System%超近程低成本主动防护系统拦截导弹设计

    李富贵; 夏群利; 郭龙昌


    针对末端近距防御的特殊需求,研究了低成本主动防护系统拦截导弹设计方法.分析了拦截导弹的总体设计方案,利用工程算法和CFD平台设计优化了拦截导弹的气动外形,研究了侧向喷流干扰并提出了抑制措施,提出了拦截导弹控制资源分配方案并设计了非线性控制策略.建立了六自由度拦截对抗模型,利用蒙特卡洛方法分析了设计方法的有效性和鲁棒性.研究结果表明,在简易制导条件下,采用轨控脉冲发动机非线性操纵方式可满足拦截导弹的总体需求.%To satisfy terminal short-distance defense requirement,design methods for low-cost intercept missile of active protection system were presented.The general scheme was analyzed,and project methods and CFD platform were used to design and optimize the airframe of missile.The disturbance of lateral jet was simulated and analyzed,and the restrained approach was derived.Then the control resources arrangement was presented,which was suited with nonlinear control measures.Six-DOF intercept model was established,and the validity and robustness of previous design method were tested by Monte-Carlo simulation.The result shows that under the conditions of simple guidance,utilizing divert pulse motor in a nonlinear way can satisfy the general requirements.

  3. HOMA: Israel’s National Missile Defense Strategy (Abridged Version)


    developed by Tadiran Electronics Systems), and the Hazelnut Tree launcher control center.28 Each battery is designed to track and counter —14 enemy...Communications center, (4) HAZELNUT TREE fire control center, (5) GREEN PINE radar antenna, (6) Radar control center, (7) Radar power unit, (8) Radar...cooling unit. A battery has four launch vehicles with six ready missiles each, a Tadiran Citron Tree launch control centre, a Hazelnut Tree fire

  4. Missile trajectory shaping using sampling-based path planning

    Pharpatara, Pawit; Pepy, Romain; Hérissé, Bruno; Bestaoui, Yasmina


    International audience; This paper presents missile guidance as a complex robotic problem: a hybrid non-linear system moving in a heterogeneous environment. The proposed solution to this problem combines a sampling-based path planner, Dubins' curves and a locally-optimal guidance law. This algorithm aims to find feasible trajectories that anticipate future flight conditions, especially the loss of manoeuverability at high altitude. Simulated results demonstrate the substantial performance imp...

  5. 77 FR 46413 - 36(b)(1) Arms Sales Notification


    ... will be Raytheon Corporation in Tewksbury, Massachusetts; and Lockheed Martin Missiles and Fire Control... that might reduce weapon system effectiveness or be used in the development of a system with similar...

  6. Robust Hybrid Control for Ballistic Missile Longitudinal Autopilot

    WAEL Mohsen Ahmed; QUAN Quana


    This paper investigates the boost phase's longitudinal autopilot of a ballistic missile equipped with thrust vector control.The existing longitudinal autopilot employs time-invariant passive resistor-inductor-capacitor (RLC) network compensator as a control strategy,which does not take into account the time-varying missile dynamics.This may cause the closed-loop system instability in the presence of large disturbance and dynamics uncertainty.Therefore,the existing controller should be redesigned to achieve more stable vehicle response.In this paper,based on gain-scheduling adaptive control strategy,two different types of optimal controllers are proposed.The first controller is gain-scheduled optimal tuning-proportional-integral-derivative (PID) with actuator constraints,which supplies better response but requires a priori knowledge of the system dynamics.Moreover,the controller has oscillatory response in the presence of dynamic uncertainty.Taking this into account,gain-scheduled optimal linear quadratic (LQ) in conjunction with optimal tuning-compensator offers the greatest scope for controller improvement in the presence of dynamic uncertainty and large disturbance.The latter controller is tested through various scenarios for the validated nonlinear dynamic flight model of the real ballistic missile system with autopilot exposed to external disturbances.

  7. Countermeasure effectiveness against an intelligent imaging infrared anti-ship missile

    Gray, Greer J.; Aouf, Nabil; Richardson, Mark; Butters, Brian; Walmsley, Roy


    Ship self defense against heat-seeking anti-ship missiles is of great concern to modern naval forces. One way of protecting ships against these threats is to use infrared (IR) offboard countermeasures. These decoys need precise placement to maximize their effectiveness, and simulation is an invaluable tool used in determining optimum deployment strategies. To perform useful simulations, high-fidelity models of missiles are required. We describe the development of an imaging IR anti-ship missile model for use in countermeasure effectiveness simulations. The missile model's tracking algorithm is based on a target recognition system that uses a neural network to discriminate between ships and decoys. The neural network is trained on shape- and intensity-based features extracted from simulated imagery. The missile model is then used within ship-decoy-missile engagement simulations, to determine how susceptible it is to the well-known walk-off seduction countermeasure technique. Finally, ship survivability is improved by adjusting the decoy model to increase its effectiveness against the tracker.

  8. Assessment of Containment Structures Against Missile Impact Threats

    LI Q M


    In order to ensure the highest safety requirements,nuclear power plant structures (the containment structures,the fuel storages and transportation systems) should be assessed against all possible internal and external impact threats.The internal impact threats include kinetic missiles generated by the failure of high pressure vessels and pipes,the failure of high speed rotating machineries and accidental drops.The external impact threats may come from airborne missiles,aircraft impact,explosion blast and fragments.The impact effects of these threats on concrete and steel structures in a nuclear power plant are discussed.Methods and procedures for the impact assessment of nuclear power plants are introduced.Recent studies on penetration and perforation mechanics as well as progresses on dynamic properties of concrete-like materials are presented to increase the understanding of the impact effects on concrete containment structures.

  9. Potential applications of video disc technology to missile guidance

    Ormsby, C. C.; Long, H. S.


    An assessment of video disk data storage technology suggests the possibility of a missile-borne data storage system providing real-time access to a data base consisting of approximately 10 to the 11th bits, with readout rates of up to 200 Mbits/sec and average frame access time of 2-3 sec. The Direct Read After Write (DRAW) technology currently under development will also provide a data recording capability of 10 to the 7th - 10 to the 8th bits/sec. Five cruise missile applications of this technology are discussed: (1) Terrain Contour Matching (TERCOM) data base guidance; (2) target signature data base guidance; (3) terrain/obstacle files navigation; (4) preprogrammed route storage navigation; and (5) reconnaissance data recording.

  10. Design and Simulation of TF and TA Controller for Missile

    ZHA Xu; GUANG Cheng-qi; CUI Ping-yuan; LIU Yong-cai


    A nonlinear terrain following(TF) and terrain avoidance(TA) controller is proposed for missile control systems.Based on classical TF algorithm (adaptive angle method), a new method for TF controller is proposed by using angle of attack. A method of obtaining terrain outline data from digital elevation map (DEM) for TF control is discussed in order to save store space. A TA algorithm is proposed by using bank-to-turn technique. The block control model, which is suitable for backstepping design, is given for nonlinear model of missile. Making full use of the characteristics of the system and combining block control principle and backstepping technique, a robust controller design method is proposed. Uncertainties in every sub-block are allowed, and can be canceled by using the idea of nonlinear damping. It is proved that the state tracking errors are converged to a neighborhood of the origin exponentially. Finally, nonlinear six-degree-of-freedom simulation results for the missile model are presented to demonstrate the effectiveness of the proposed control law.

  11. Design of a missile servo stabilization platform control system based on TMS320F2812%基于TMS320F2812的弹载伺服稳定平台控制系统设计



    文章介绍了弹载伺服稳定平台功能及控制要求,分析了平台控制系统组成及工作原理,说明了系统核心器件、传感器及伺服电机的选型方案,通过基于TMS320F2812高性能DSP的控制系统硬件、软件设计,完成伺服稳定平台控制系统设计。试验结果表明,该弹载伺服稳定平台各项指标满足设计要求,设计方法正确、有效。%This paper introduces the function and the control requirements of missile servo stabilization platform control system, analyses the composition and working principle of the platform control system, illustrates the selection scheme of the main electric circuit chips, sensors and servo motor. Through the hard ware and the soft ware design which based on the high-performance DSP chip TMS320F2812,fulfills the servo stabilization platform control system design. The experiment results indicates that the designed platform implements all the system design specifications, the design method which introduced is correct and effective.

  12. Missile Servo System Fault Diagnosis Method Based on Sliding Mode Variable Structure%基于滑模变结构的导弹伺服机构故障诊断

    黄岳; 马震; 刘丙杰


    According to uncertainty and nonlinear characteristic of missile servo system, a sensor fault diagnosis proposal for a class of nonlinear system is presented. The studied uncertain nonlinear system is with unknown input disturbance. First, a controller is designed based on sliding mode variable structure theory. A design of state observation also based on sliding mode variable structure theory but by use of a specific equivalent control methodology follows. Then, by means of adaptive method, the fault identification which can restructure the faults is studied. The results of some numerical simulations on an artillery position servo system verify the validity of the proposed approaches.%针对导弹伺服机构的不确定非线性特点,提出了一种基于滑模变结构的传感器故障诊断方案.首先给出一种基于滑模变结构的控制器设计方法,然后利用滑模变结构中的等值控制方法设计了状态观测器,再利用自适应方法实现了对故障的重构.最后将提出的方法在导弹伺服系统中应用,表明了该方法的有效.

  13. DDG-1000 Missile Integration: A Case Study


    Effectiveness (Pk) ‐ Platform  Environment ‐ Interface Definition Requirements Flow Interface  Definition Legend Figure 28. DDG-1000 Requirements Flow (from...development specifications and gaps that still exist in requirements. 71 Legacy Missile Requirements Legend DDG1000 Missile...Office Consolidates Programs, Cuts Costs.” Sea Power, Navy League of the United States, Arlington VA. February 2004. Accessed July 2013. http

  14. Attacking the Theater Mobile Ballistic Missile Threat


    and Record, �Theater Ballistic Missile Defense and US Contingency Operations,� 13. 43Greg Myre, Associated Press, �De Klerk Reveals South African...possession). ____. Briefing, subject: �WarBreaker.� 17 December 1992. Myre, Greg. Associated Press. �De Klerk Reveals South African Nuclear...April�3 May 1992, 1,44. Ordway, Frederick I. III and Ronald C. Wakeford. International Missile and Spacecraft Guide. New York: McGraw

  15. Ballistic Missile Defense. Past and Future


    and deployed. These are the two big questions of the anti-ballistic missile ( ABM ) debate. It must be emphasized that the extreme polarization of the opposing positions that have been taken. Consider this statement: “The whole ABM question touched off so intense...earlier that same year by the Washington Post and ABC News11 reported that 80 percent of the American population was in favor of building a missile

  16. The Research of Missile Temperature Acquisition System Based on a Platinum Resistance%基于A类铂电阻的弹体温度采集系统研究

    朱杰; 郭涛


    为了提高导弹弹体温度的测量精度,提出了一种新型的基于A类铂电阻的多点采集温度传感器的设计方案.该系统采用高精度恒流源减小铂电阻功耗,四线制和对称组装式数据放大电路来减小温度漂移.五阶低通滤波器MAX280滤波后的信号经A/D转换与数字电位器X9241相连,通过AT89S52控制数字电位器调整输出的零点漂移,再采用最小二乘法进行分段拟合.经试验验证,在-50℃~400℃的温度范围内,误差<0.05℃,目前以本电路为核心的测量与控制系统已实际应用于某导弹系统装备.%In order to improve the missile temperature measurement precision, a kind of multi-point acquisition temperature sensor based on a platinum resistance was put forward. Constant current source was used to reduced power consumption of precision platinum, the temperature drift was reduced by four wire system and symmetric assembled data amplifier circuit. The signal was filtered by five order low-pass filter MAX280, was put to A/D conversion, and was connected through X9241. AT89S52 controlled to adjust the output of the zero drift, the least square method was used in the segmented range. Experiments show that the temperature error is less than 0. 05 t between the temperature range of - 50 ℃ ~ 400 ℃. At present, the circirt as the core temperature measurement and control system has been used in a missile system.

  17. Analysis of the influence of launching platform navigation error on the strapdown inertial navigation system of anti ship missile%发射平台导航误差对反舰导弹捷联惯导系统影响分析



    建立动基座条件下反舰导弹捷联惯导系统误差传播方程,分析发射平台导航参数误差对导弹惯导定位误差的影响,得出了相关的结论。研究结果可以为武器试验鉴定工作提供支撑。%Based onthe error propagation equation of the strapdown inertial navigation system of the anti ship missile under the condition of moving base,the influence of the navigation parameters of the launching platform on the positioning error of missile inertial navigation system is analyzed, and the related conclusion is drawn.The results of the study can provide support for the weapon test and appraisal work.

  18. Changing law of launching pitching angular velocity of rotating missile

    Liu Guang; Xu Bin; Jiao Xiaojuan; Zhen Tiesheng


    In order to provide accurate launching pitching angular velocity (LPAV) for the exterior trajectory optimization design, multi-flexible body dynamics (MFBD) technology is presented to study the changing law of LPAV of the rotating missile based on spiral guideway. An MFBD virtual prototype model of the rotating missile launching system is built using multi-body dynamics modeling technology based on the built flexible body models of key components and the special force model. The built model is verified with the frequency spectrum analysis. With the flexible body contact theory and nonlinear theory of MFBD technology, the research is conducted on the influence of a series of factors on LPAV, such as launching angle change, clearance between launching canister and missile, thrust change, thrust eccentricity and mass eccentricity, etc. Through this research, some useful values of the key design parameters which are difficult to be measured in physical tests are obtained. Finally, a simplified mathematical model of the changing law of LPAV is presented through fitting virtual test results using the linear regression method and verified by physical flight tests. The research results have important significance for the exterior trajectory optimization design.

  19. Variable centroid control scheme over hypersonic tactical missile

    Yl; Yan(易彦); ZHOU; Fengqi(周凤岐)


    This paper presents a brand-new tactical missile control scheme--variable centroid vector control according to the international highlight in the field of missile control and the research status of hypersonic missile control in China. Four critical problems related with the new control method are included: improving phase control in the spinning missile single-channel control; establishing variable centroid controlled spinning missile attitude dynamics equations; analyzing variable centroid control strategies and analyzing the stability of the controlled missile and implementing robust control. The achievements and results obtained are valuable and helpful to the theoretical explorations and engineering applications.

  20. Variable centroid control scheme over hypersonic tactical missile

    Yi, Yan; Zhou, Fengqi


    This paper presents a brand-new tactical missile control scheme—variable centroid vector control according to the international highlight in the field of missile control and the research status of hypersonic missile control in China. Four critical problems related with the new control method are included: improving phase control in the spinning missile single-channel control; establishing variable centroid controlled spinning missile attitude dynamics equations; analyzing variable centroid control strategies and analyzing the stability of the controlled missile and implementing robust control. The achievements and results obtained are valuable and helpful to the theoretical explorations and engineering applications.

  1. 空空导弹数字舵机软件串行加载系统设计%Design of Software Serial Loading System for Air-to-Air Missile Digital Control Actuator

    刘鹏; 朱沛洪; 陶小亮


    During modifying software of air-to-air missile digital control actuator , a serial loading sys-tem using serial communication interface loading program is designed to avoid disassembling production repeatedly . Software serial loading realizes via serial asynchronous communication with ROM of TMS320LF2407 chip-self.Practical applications prove that the system can load soft expediently and fast , and can avoid disassembling production and improve producing efficiency .%在数字舵机软件修改时,为了避免空空导弹产品反复拆装,保证导弹的可靠性,设计了一套利用产品串行通信接口加载程序的串行加载系统。针对控制芯片TMS320 LF2407,利用芯片自带的ROM,采用串行异步通信方式实现软件串行加载。实际应用表明,该系统可以方便、快捷地进行舵机软件加载,避免了反复拆装产品,提高了生产效率。

  2. Year 2000 small engine technology payoffs in cruise missiles

    Singh, B.; Benstein, E. H.


    A study has been conducted for advanced small (450-850 pounds thrust) gas turbine engines for a subsonic strategic cruise missile application, using projected year-2000 technology. Engine performance and configuration analyses were performed for two and three spool turbofan and propfan engine concepts. Mission and Life Cycle Cost (LCC) analyses were performed in which the candidate engines were compared to the baseline engine over a prescribed mission. The advanced technology engines reduced system LCC up to 41 percent relative to the baseline engine. The critical aerodynamic materials and mechanical systems necessary for turbine engine technology were identified.

  3. Control Design and Implementation for Missiles with Blended Lateral Jets and Aerodynamic Control Systems%导弹直接侧向力与气动力复合控制设计与实现

    马克茂; 赵辉; 张德成


    针对带有姿控式直接侧向力/气动力复合控制系统导弹的控制律设计问题,建立了俯仰平面内姿态控制系统的数学模型,应用非线性系统理论对模型进行了分析,在此基础上建立了进行控制系统设计的简化模型.基于滑模变结构控制理论进行了复合控制律设计,并分别考虑气动力控制和直接侧向力控制的特点对所设计的控制律进行了实现.所设计的复合控制系统在进行快速攻角指令跟踪的同时,可以有效节省姿控发动机的使用数量.仿真结果说明了所提出方法的有效性.%For the controller design of missiles with blended lateral jets and aerodynamic control systems, the mathematical model of attitude control system in the pitch plane is canstructed. and some nonlinear system theory is applied to analyze the characteristics of the attitude control model. In view of the above , a simplified model is built for control system design. A blended control law is designed hy applying sliding-mode variable structure control theory, and the implementation of the controller is discussed based on the respective characteristics of lateral jet control and aerodynamic control. By using the proposed control law. fast tracking of angle-of-attack is realized. and the consumption of laleral jets is greatly reduced as well. Simulation results show the effectiveness of the proposed design.

  4. Digital Simulation of Kill Probability on Shipborne Weapon System Against Missile Target%舰炮武器系统对导弹目标毁伤概率的数字仿真

    李云超; 冯元伟


    Taking antimissile shipbome gun weapon system as a prototype, based on the operational process of this weapon system, and by using dynamic accuracy test data of naval gun tracing real object,a mathematical model of dynamic accuracy test calculating kill probability is constructed to simulate kill probability of shipborne gun system by directly hitting against missile targets, which realizes this simulation calculation. The simulation result is similar to that of actual effect of firing. Results show that the way of the simulation can carry out dynamic accuracy calculating kill probability and provide basis for decision making for the scheme of firing tests and supply reference for fire efficiency' s evaluation and effectiveness assessment of shipborne gun weapon system.%以某型反导舰炮武器系统为原型,通过分析舰炮武器系统反导作战过程,利用靶场舰炮武器系统的动态精度试验数据,建立了动态精度计算毁伤概率的数学模型,模拟了舰炮武器系统对导弹目标着发射击的毁伤概率,实现了毁伤概率的仿真计算,仿真结果与实弹射击结果接近.结果表明,应用这种方法,可以实现动态精度预估毁伤概率,为射击试验方案制定提供决策依据,也可以为舰炮武器系统射击效力的鉴定和效能评估提供参考.

  5. Integrated Guidance and Control of Homing Missiles Against Ground Fixed Targets

    Hou Mingzhe; Duan Guangren


    This paper presents a scheme of integrated guidance and autopilot design for homing missiles against ground fixed targets. An in- tegrated guidance and control model in the pitch plane is formulated and further changed into a normal form by nonlinear coordinate transformation. By adopting the sliding mode control approach, an adaptive nonlinear control law of the system is designed so that the missile can hit the target accurately with a desired impact attitude angle. The stability analysis of the closed-loop system is also con- ducted. The numerical simulation has confirmed the usefulness of the proposed design scheme.

  6. Simulation Study on the Feasibility of Gun-Launched Missile Against Attack Helicopters

    王狂飙; 张天桥


    The feasibility of providing the tank a limited anti-helicopterability with gun-launched missile is studied. A type of simulation model of gun-launched missile against attack helicopters is established. The simulation and the parameter optimization of missile control system under various circumstances are done. The gun-launched missile can directly hit the helicopters in the typical tracks, all the missdistances are less than 1 m and the maximum overload is less than available overload. Gun-launched missile is a feasible choice for tanks against attack helicopters.%研究通过炮射反坦克导弹赋予坦克有限反武装直升机能力的可行性.建立了一种炮射导弹与武装直升机对抗的仿真模型,并在各种情况下进行了系统仿真与导弹控制系统参数优化.经参数优化的炮射导弹在给定的武装直升机各种航迹下,均可直接命中,脱靶量均小于1m,最大过载不超过可用过载.仿真结果表明炮射导弹是坦克对抗武装直升机的一种可行的选择.

  7. Use of noise attenuation modeling in managing missile motor detonation activities.

    McFarland, Michael J; Watkins, Jeffrey W; Kordich, Micheal M; Pollet, Dean A; Palmer, Glenn R


    The Sound Intensity Prediction System (SIPS) and Blast Operation Overpressure Model (BOOM) are semiempirical sound models that are employed by the Utah Test and Training Range (UTTR) to predict whether noise levels from the detonation of large missile motors will exceed regulatory thresholds. Field validation of SIPS confirmed that the model was effective in limiting the number of detonations of large missile motors that could potentially result in a regulatory noise exceedance. Although the SIPS accurately predicted the impact of weather on detonation noise propagation, regulators have required that the more conservative BOOM model be employed in conjunction with SIPS in evaluating peak noise levels in populated areas. By simultaneously considering the output of both models, in 2001, UTTR detonated 104 missile motors having net explosive weights (NEW) that ranged between 14,960 and 38,938 lb without a recorded public noise complaint. Based on the encouraging results, the U.S. Department of Defense is considering expanding the application of these noise models to support the detonation of missile motors having a NEW of 81,000 lb. Recent modeling results suggest that, under appropriate weather conditions, missile motors containing up to 96,000 lb NEW can be detonated at the UTTR without exceeding the regulatory noise limit of 134 decibels (dB).

  8. Comparison of different lateral acceleration autopilots for a surface-to-surface missile

    Danilo V. Ćuk


    Full Text Available This paper presents a comparison of three lateral acceleration autopilots for a surface-to-surface missile: three-loop conventional acceleration autopilot, and gamma-dot and three-loop acceleration autopilot based upon the inverse-dynamic control. The surface-to-surface missile motion is described by nonlinear differential equations whose parameters change rapidly over a very wide range due to variable velocity and altitude. The requirement for the accurate controlling of the missile in such an environment represents a challenge for the autopilot designer. The brief review of the calculation of the autopilot gains is given using the concept of the 'point' stability for the linear time-varying system with 'frozen' dynamic coefficients. The method of the inverse-dynamic control is presented in the next section for two types of the autopilots: gamma-dot and acceleration autopilot. Both of them require the design of the estimators for the variables used as inputs to the control law. Finally, six-degree-of-freedom simulation results of the missile response to the demanded command on the typical ballistic trajectory are presented. The comparison of three autopilots considers the steady state errors and the sensitivity of the response to the highly variable environment. It was shown that the inverse-dynamic control can be very effective in the controlling of the surface-to-surface missile.

  9. The new politics of missile proliferation

    Karp, A. [Old Dominion Univ., Norfolk, VA (United States)


    The author addresses the most consequential proliferation battle of the 1990s which occurred in Washington over the interpretation of the long-term threat to the United States from ballistic missiles. In the early 1970s, the stabilization of the US-Soviet strategic relationship led to new disputes over the other side`s future intentions, seen most graphically in Western debates over the implications of the Soviet SS-18 and SS-20 missile programs. Today, in much the same way, proliferation politics has matured to the point that surprises are few and the most challenging problem is anticipating the more distant future. Washington`s ballistic missile proliferation battle was sparked by National Intelligence Estimate (NIE) 95-19, entitled {open_quotes}Emerging Threats to North America During the Next 15 Years,{close_quotes} released by the National Intelligence Council in November 1995. This document updated the evidence of regional missile programs reviewed in a similar report issued in 1993, and recapitulated the previous finding that {open_quotes}No country, other than the major declared nuclear powers, will develop or otherwise acquire a ballistic missile in the next 15 years that could threatened the contiguous 48 states or Canada.{close_quotes} The new report confirmed what several other studies of missile proliferation had already established: that besides the five nuclear-weapon states (the United States, Russia, China, France and Britain), only India, Israel and Japan are in a position to develop an ICBM during the foreseeable future, and while all have relevant capabilities, none are undertaking the steps necessary to develop an actual ICBM.

  10. EFP Warhead Missile Fuze Analysis and Simulation

    LI Wei; FAN Ning-jun; WANG Zheng-jie


    The explosive formed penetrator(EFP)warhead missile projects the blast fragments in one direction normal to the missile longitudinal axis.Through analyzing on the two restrictions of EFP warhead explosion:trajectory restriction and attitude requirement,the concept of fuse time-delay tolerance is presented to be the measurement of the time of the EFP warhead explosion.The calculation models of fuze time-delaY tolerance under two restrictions are provided.Some crucial parameters playing important roles in calculation under attitude requirements are simulated.The simulation results show that the engagement plane angle,roll rate and warhead attack standoff influence the tolerance dramatically.

  11. Reserve lithium-thionyl chloride battery for missile applications

    Planchat, J. P.; Descroix, J. P.; Sarre, G.

    A comparative performance study has been conducted for silver-zinc, thionyl chloride, and thermal batteries designed for such missile applications as ICBM guidance system power supplies. Attention is given to each of the three candidates' conformity to requirements concerning mechanical configuration, electrochemical design, electrolyte reservoir, external case, and gas generator. The silver-zinc and Li-SOCl2 candidates employ similar cell configurations and yield comparable performance. The thermal battery is found to be incapable of meeting battery case temperature-related requirements.

  12. Thermal Battery As A Power Sources In Guided Missiles

    S. S. Singh


    Full Text Available The battery based on low melting eutectic salt mixture electrolyte is thermally activated by raising the temperature of the electrolyte to its melting point. The battery is capable of discharging at very high rates for short duration. The battery employs a combination of elements with low electronegativity and capable of giving higher electrode potentials such as Ca or Mg as anode, a wide variety of eutectic salt electrolytes and various oxides, sulphates, silicates, phosphates, chromates as cathode depolarizers. Only those thermally activated systems which find application as potential power sources in guided missiles are reviewed.

  13. Rationale for wind-borne missile criteria for DOE facilities

    McDonald, J R; Murray, R


    High winds tend to pick up and transport various objects and debris, which are referred to as wind-borne missiles or tornado missiles, depending on the type of storm. Missiles cause damage by perforating the building envelope or by collapsing structural elements such as walls, columns or frames. The primary objectives of this study are as follows: (1) to provide a basis for wind-borne or tornado missile criteria for the design and evaluation of DOE facilities, and (2) to provide guidelines for the design and evaluation of impact-resistant missile barriers for DOE facilities The first objective is accomplished through a synthesis of information from windstorm damage documentation experience and computer simulation of missile trajectories. The second objective is accomplished by reviewing the literature, which describes various missile impact tests, and by conducting a series of impact tests at a Texas Tech University facility to fill in missing information.

  14. NATO and U.S. Ballistic Missile Defense Programs: Divergent or Convergent Paths?


    making framework. It is common for TMD systems to be developed and deployed via bilateral negotiations. The only TMD project that has been subject to...sol-air moyenne portée- terrestre , that is, a ground based surface- to-air medium-range missile. 52 “Aster 30 SAMP/T – Surface-to-Air Missile Platform...alone rather than via a joint development with Alliance members that have expressed interest. Additionally, some European members of the Alliance

  15. Key considerations in infrared simulations of the missile-aircraft engagement

    Willers, MS


    Full Text Available of these details are investigated in Section 6. The tactical missile system used against aircraft includes several subsystems: airframe, flight control, fuze, propulsion, telemetry, data link, warhead and seeker.4 The seeker of an imaging IR missile provides...:// on 12/19/2012 Terms of Use: /7 dual mode detectors view a scene in two separate bands of the spectrum. The seeker compares the spectral distribution ratio of the various targets in the field of view to a predefined threshold. If a...

  16. Health assessment for Fairchild Semiconductor Corporation Proposed National Priorities List Site, Intel Corporation National Priorities List Site, Raytheon Company National Priorities List Site, Mountain View, California, Region 9. CERCLIS No. CAD095989778. Final report


    The Fairchild Semiconductor Corporation, the Intel Corporation, and the Raytheon Company each have a facility located approximately 3 miles south of San Francisco Bay in Mountain View, California. The Intel and Raytheon facilities are on the National Priorities List (NPL) while the Fairchild facility is a proposed NPL site. Within the one-half square mile area containing the three sites, 37 potential and two inferred sources of contamination have been identified. The major contaminants for the three sites include trichloroethene, 1,1,1-trichloroethane, 1,1-dichloroethene, 1,2-dichloroethene, 1,1-dichloroethane, chloroform, tetrachloroethene, 1,2-dichlorobenzene, trichlorotrifluoroethane (Freon 113), and vinyl chloride. These contaminants are attributed to the sites and have been found primarily in the ground water and subsurface soil on the sites and in ground water off the sites. Contaminant concentrations in surface soils were within the normal range of background values. Volatile organic compounds (VOCs) have been found in surface water west of the study area in Stevens Creek, an intermittent stream. The source of these contaminants is suspected to be treated ground water that has been pumped from the Fairchild and Raytheon sites and discharged to Stevens Creek under a permit.




    Full Text Available A Statistical report of 912 battle casualtiesadmitted in a special unit of the neurological surgery department during 49 months of the recent war was given. Methods of their evaluation, operative categories, management poli¬cies including techniques of Missile and bullet removal, and their complications were discussed.

  18. Cruise missiles should not stop START

    Tsipis, K.


    A method for verifying a cruise-missile agreement that would be acceptable to the military, industrial, and intelligence communities in both nations must be as unintrusive as possible, while remaining immune to cheating of any significance. This is the goal of the technical solutions outlined here. The elements of a verification regime described do not require routine, intrusive, on-site visits to naval vessels, aircraft, air bases, or weapons magazines where missiles may be stored. They do not interfere with the operational readiness of the missiles, and they protect legitimate military secrets of the inspected nation. If supported by competent national technical means of verification such as those both sides already employ, with a small number of on-site challenge inspections, a combination of technical solutions and procedures such as these could be effective. They would adequately safeguard the national security and sovereignty of the participating nations while providing policymakers with the option of a treaty that limits the number of long-range nuclear cruise missiles or eliminates them completely. As discussed, there are problems that remain to be addressed, but they should not be allowed to block a U.S.-Soviet agreement significantly reducing strategic nuclear arsenals.

  19. Integrated Air and Missile Defense (IAMD)


    IBCS. The cruise missile surrogate, an MQM-107 Drone Target, flew a low altitude trajectory against an asset defended by an Army IAMD task force...FY 2048 The difference in the acquisition quantity of 443 and the sustainment quantity of 427 is due to 16 RDT&E prototypes that are not to be

  20. Minimum variation guidance laws for interceptor missiles

    Weiss, M.; Shima, T.


    This paper introduces a new approach to guidance law design using linear quadratic optimal control theory, minimizing throughout the engagement the variation of the control input as well as the integral control effort. The guidance law is derived for arbitrary order missile dynamics and target maneu

  1. 考虑动态接触参数的某型导弹发射动力学分析%Analysis of Launch Dynamics of Missile System Considering Dynamic Contact Parameters

    刘馨心; 徐宏斌; 张亮亮; 褚福磊


    To study the launch dynamics characteristics of an anti tank missile system, dynamic contact stiffness, damping coefficient and penetration were calculated based on the elasticity theory. Many movements were obtained through numerical simulation by dynamic software ADAMS,and the effects of temperature,direction aiming angle and damping characteristics on the initial disturbance were discussed. The simulation results show that the initial disturbances are bigger under low temperature,and the damping coefficient greater than 300 N.s/rad is better,and increasing contact parameter of the ground helps reduce the initial disturbances.%为研究某型号反坦克导弹系统的发射动力学特性,基于弹性理论计算了接触变形模型的动态接触参数,通过多体系统动力学软件ADAMS对该模型进行了仿真分析,并重点讨论了温度、初始方位瞄准角、阻尼特性以及地面接触参数对初始扰动的影响.仿真结果表明,它们对初始扰动均有影响,低温发射下的初始扰动大,阻尼器阻尼系数以大于300N.s/rad为佳,增大地面接触参数有利于减小初始扰动.

  2. Data fusion control and guidance of surface-to-air missile under the complex circumstance based on neural-net technology

    Zhou Deyun; Zhou Feng


    Under the complicated electromagnetism circumstance,the model of data fusion control and guidance of surface-to-air missile weapon systems is established.Such ways and theories as Elman-NN,radar tracking and niter's data fusion net based on the group method for data-processing (GMRDF) are applied to constructing the model of data fusion.The highly reliable state estimation of the tracking targets and the improvement in accuracy of control and guidance are obtained.The purpose is optimization design of data fusion control and guidance of surface-to-air missile weapon systems and improving the fighting effectiveness of surface-to-air missile weapon systems.

  3. Protivoklopni vođeni projektili zapadne Evrope, Izraela i Indije / Anti-tank guided missiles of western Europe, Israel and India

    Goran M. Lazić


    Full Text Available Protivoklopni vođeni projektili namenjeni su za uništavanje teško-oklopljenih tenkova, kao i drugih oklopnih vozila. Ovaj rad nudi istorijsko-tehnički pregled (razvoj projektila kroz generacije i osnovni podaci vezani za borbeno-operativno dejstvo ovih projektila ovog tipa naoružanja koje poseduju zemlje zapadne Evrope, Izraela i Indije. Pored osnovnih podataka navode se i cene nekih projektila ponaosob, kao i tendencije razvoja u ovoj grani naoružanja. / Anti-tank guided missiles are designed to hit and destroy heavily armored tanks and other armored fighting vehicles. This review offers a historical and technical overview (development of missiles throughout generations and basic data about combat and operational actions of this type of weapons in Western Europe, Israel and India. The review also offers prices of some missiles and tendencies of development in this branch. Anti-tank guided missiles are primarily designed to destroy armoured tanks as well as other armoured vehicles. Anti-tank guided systems differ in size, from small ones (shoulder-launched missile weapons carried by a single person to complex weapon systems (crewserved, vehicle-mounted and airborne systems. The first generation of anti-tank guided missiles is a manually guided MCLOS (Manual Command to Line of Sight projectile requiring an operator to guide and steer it to a target by a joystick. Vickers vigilant is a British anti-tank wire-guided missile, produced in 1956. The Bantam (Bofors Anti-Tank Missile or Robot 53 (RB 53 is a Swedish anti-tank wire-guided missile, produced in 1963. Cobra is a German - Swiss product which entered the operational use in 1956. It was replaced by Cobra 2000 and Mamaba systems, which are anti-tank guided missiles of the first generation, but with improved guidance and electronics. ENTAC (Engin téléguidé anti-char or MGM Petronor-32A is a French anti-tank wire-guided missile, widely spread and still in the operational use in many

  4. Wide-FOV FPAs for a shipboard distributed aperture system

    Gulbransen, David J.; Black, Stephen H.; Childs, A. C.; Fletcher, Christopher L.; Johnson, Scott M.; Radford, William A.; Venzor, Gregory M.; Sienicki, J. P.; Thompson, A. D.; Griffith, J. H.; Buell, Aimee A.; Vilela, M. F.; Newton, Michael D.; Takken, Edward H.; Waterman, James R.; Krapels, Keith A.


    The Navy faces an ever evolving threat scenario, ranging from sub-sonic sea skimming cruise missiles to newer, unconventional threats such as that experienced by the USS Cole. Next generation naval technology development programs are developing "stealthy" ships by reducing a ships radar cross section and controlling electromagnetic emissions. To meet these threat challenges in an evolving platform environment, ONR has initiated the "Wide Aspect MWIR Array" program. In support of this program, Raytheon Vision Systems (RVS) is developing a 2560 X 512 element focal plane array, utilizing Molecular Beam Epitaxially grown HgCdTe on silicon detector technology. RVS will package this array in a sealed Dewar with a long-life cryogenic cooler, electronics, on-gimbal power conditioning and a thermal reference source. The resulting sub system will be a component in a multi camera distributed aperture situation awareness sensor, which will provide continuous surveillance of the horizon. We will report on the utilization of MWIR Molecular Beam Epitaxial HgCdTe on Silicon material for fabrication of the detector arrays. Detector arrays fabricated on HgCdTe/Si have no thermal expansion mismatch relative to the readout integrated circuits. Therefore large-area focal plane arrays (FPAs) can be developed without concern for thermal cycle reliability. In addition these devices do not require thinning or reticulation like InSb FPAs to yield the high levels of Modulation Transfer Function (MTF) required by a missile warning sensor. HgCdTe/Si wafers can be scaled up to much larger sizes than the HgCdTe/CdZnTe wafers. Four-inch-diameter HgCdTe/Si wafers are currently being produced and are significantly larger than the standard 1.7 inch x 2.6 inch HgCdTe/CdTe wafers. The use of Si substrates also enables the use of automated semiconductor fabrication equipment.

  5. Space radiation studies at the White Sands Missile Range Fast Burst Reactor

    Delapaz, A.


    The operation of the White Sands Missile Range Fast Burst Reactor is discussed. Space radiation studies in radiobiology, dosimetry, and transient radiation effects on electronic systems and components are described. Proposed modifications to increase the capability of the facility are discussed.

  6. Navy Aegis Ballistic Missile Defense (BMD) Program: Background and Issues for Congress


    developments in Australia, Japan , and South Korea. 93 Justin Doubleday, “MDA Looking to Integrate European Allies into Missile Defense Architecture ...12 Japan ................................................................................................................................. 12 Other...building, or are planning to build Aegis-equipped ships include Japan , South Korea, Australia, Spain, and Norway.2 Aegis BMD System3 Aegis ships

  7. Design of Attitude Control System Based on μ-Synthesis for Morphing Wing Cruise Missile%可变翼巡航导弹μ综合姿态控制系统设计

    舒营恩; 郭建国; 周军


    The existing cruise missiles are applied to certain specific missions. The smart morphing cruise missile can morph configuration to adapt to different missions. As morphing wings, dynamics and control characteristics of missile become complex. In order to improve robust performance of the cruise missile, the multi-body dynamic model of morphing cruise missile based on morphing wings, parameter uncertainties and structure uncertainties can be considered by using μ—synthesis. The three—channel robust attitude control law for an example missile was designed. The simulation results show that the designed based on μ- synthesis controller has not only good dynamic performance , but also excellent robust stability and robust performance.%研究巡航导弹稳定性优化控制问题,针对面对称可变翼巡航导弹,利用μ综合方法设计了导弹的姿态控制系统.常规巡航导弹执行任务特点单一,可变翼巡航导弹可以通过改变气动外形实现多任务飞行.然而随着弹翼的变化导致导弹的动力学模型与控制特性更为复杂,为了提高可变翼巡航导弹的鲁棒性能,结合弹翼的变化策略构建可变翼导弹的多体动力学模型,综合考虑控制对象的参数不确定性和结构不确定性,采用μ综合方法设计了算例的三通道控制系统并进行了仿真.仿真结果表明,μ综合姿态控制系统不仅具有良好的动态特性,而且对参数不确定性具有良好的鲁棒稳定性.

  8. Adaptive block dynamic surface control for integrated missile guidance and autopilot

    Hou Mingzhe; Liang Xiaoling; Duan Guangren


    A novel integrated guidance and autopilot design method is proposed for homing missiles based on the adaptive block dynamic surface control approach.The fully integrated guidance and autopilot model is established by combining the nonlinear missile dynamics with the nonlinear dynamics describing the pursuit situation of a missile and a target in the three-dimensional space.The integrated guidance and autopilot design problem is further converted to a state regulation problem of a time-varying nonlinear system with matched and unmatched uncertainties.A new and simple adaptive block dynamic surface control algorithm is proposed to address such a state regulation problem.The stability of the closed-loop system is proven based on the Lyapunov theory.The six degrees of freedom (6DOF) nonlinear numerical simulation results show that the proposed integrated guidance and autopilot algorithm can ensure the accuracy of target interception and the robust stability of the closed-loop system with respect to the uncertainties in the missile dynamics

  9. Estimation filters for missile tracking with airborne laser

    Clemons, T. M., III; Chang, K. C.


    This paper examines the use of various estimation filters on the highly non-linear problem of tracking a ballistic missile during boost phase from a moving airborne platform. The aircraft receives passive bearing data from an IR sensor and range data from a laser rangefinder. The aircraft is assumed to have a laser weapon system that requires highly accurate bearing information in order to keep the laser on target from a distance of 100-200 km. The tracking problem is made more difficult due to the changing acceleration of the missile, especially during stage drop-off and ignition. The Extended Kalman Filter (EKF), Unscented Kalman Filter (UKF), 'bootstrap' Particle Filter (PF), and the Gaussian Sum Particle Filter (GSPF) are explored using different values for sensor accuracy in bearing and range, and various degrees of uncertainty of the target and platform dynamic. Scenarios were created using Satellite Toolkit © for trajectories from a Southeast Asia launch with associated sensor observations. MATLAB © code modified from the ReBEL Toolkit © was used to run the EKF, UKF, PF, and GSPF sensor track filters. Mean Square Error results are given for tracking during the period when the target is in view of the radar and IR sensors. This paper provides insight into the accuracy requirements of the sensors and the suitability of the given estimators.

  10. Centralized interception coalition formation method in networked air defense missile systems%网络化防空导弹体系集中式拦截联盟形成方法

    唐苏妍; 朱一凡; 葛伟; 李群


    Centralized interception coalition, which focuses on the method to allocate the targets, shooters and guidance sensors in order to maximize the effectiveness of the system, is one of the new problems in Networked Air Defense Missile Systems. According to the operational context, a constrained optirnization model was proposed for the problem and the particle swarm optimization algorithm was chosen to solve the model. To solve the local optimization problem of the algorithm, the creative thinking was introduced into particles from the cognitive psychology aspects. It is considered that creative thinking can improve the cognitive capability of particles to prevent the premature convergence problem. Based on the classical four-phase model in creative thinking process, a framework of creative thinking based particle swarm optimization algorithm was provided by adapting the evolution model. According to discrete characteristics of the problem, a discrete strategy was designed by setting the coding rules and the operation rules for particles' velocity and position. Experimental results show that the proposed algorithm has priority in solution quality and convergence rate.%集中式拦截联盟(CIC)形成是网络化防空导弹体系(NADMS)中的新问题,旨在确定目标、火力节点以及制导节点三者之间的最优匹配关系,以使得体系整体作战效能最大.根据问题背景,建立了CIC的约束优化问题模型,并选择收敛速度较快的粒子群优化(PSO)算法对模型进行求解.针对PSO的局部收敛问题,从认知心理学角度将人类特有的创造性思维(CT)引入粒子速度更新公式中,通过提升单个粒子的搜索能力来提高整个群体的寻优质量.基于CT过程经典的四阶段模型构建了算法框架,改进了PSO的速度更新公式.根据CIC问题特点,制定了编码策略及相关变量的离散化运算规则.实验结果证明了算法在CIC问题求解质量和收敛速度方面的优越性.

  11. Ballistic Missile Silo Door Monitoring Analysis



    This paper compares the cost and effectiveness of several potential options that may be used to monitor silo-based ballistic missiles. Silo door monitoring can be used to verify that warheads removed to deactivate or download silo-based ballistic missiles have not been replaced. A precedent for monitoring warhead replacement using reentry vehicle on site inspections (RV-OSIs) and using satellites has been established by START-I and START-II. However, other monitoring options have the potential to be less expensive and more effective. Three options are the most promising if high verification confidence is desired: random monitoring using door sensors; random monitoring using manned or unmanned aircraft; and continuous remote monitoring using unattended door sensors.

  12. Ballistic Missile Defense: New Plans, Old Challenges

    Elizabeth Zolotukhina


    Full Text Available On September 17, 2009—the 70th anniversary of the Soviet invasion of Poland in 1939 that marked the beginning of World War II—the Obama Administration announced its intention to shelve plans for the U.S. Ballistic Missile Defense (BMD that had been developed under former President George W. Bush. Pointing to a new intelligence assessment, President Obama argued that his predecessor's plan to deploy an X-band radar station outside of Prague, Czech Republic, and 10 two-stage interceptor missiles in Poland would not adequately protect America and its European allies from the Iranian threat and reiterated his opposition to utilizing unproven technology in any European BMD architecture.

  13. Reliability Simulation for a Missile Tank Under Random Loading


    This paper presents a Monte-Carlo simulation method to calculate intensity relia- bility for a missile tank under random loading. The cumulative damage mathematical mod- el is established, and it adopts a direct simulation method to present random loading and o-riginal intensity for a missile tank. It can effectively predict intensity reliability for a missile tank in the environment of transport and flight.

  14. Theater Missile Defenses and U.S. Foreign Policy


    and Joseph Rotblat (London: Macmillan Press, 1987), p. 171. 11 dowry " to alleviate European fears of being left defenseless as the U.S. retreated behind...surface missile, the design of which came from reverse-engineering of U.S. Nike-Hercules surface-to-air missiles. 59 India could be on the verge of...indigenous production with the testing of its Privthi missile. India has also demonstrated successful development of an indigenous space launch capacity

  15. On the Dynamic Stability of a Missile

    K.C. Sharma


    Full Text Available The P-method given by Parks and Pritchard has been used to discuss the stability behaviour of a missile in free flight. General stability criteria for aerodynamic stabilisation have been obtained for slowly varying coefficients. The effect of pressure gradient on the stability of a coasting rocket has been explicitly examined. It is observed that the positive Magnus moment parameter ensures stability whereas a negative moment parameter would enhance the requirements of a larger stability margin.

  16. Sustainability Of The 21M Missile Maintainer


    considering alternative career field models for missile maintenance officers. Benefits can include discovering lessons learned and best practices to improve...entire ICBM community in mitigating today’s problems and securing the confidence of the service and public. Introduction Mission failure has...which are applied to an alternative ICBM career field model . The paper closes in offering conclusions and recommendations about improving the health

  17. The Evolution of the Cruise Missile


    device as a target in operations with the cartier Ranger in August, 1938. These and subqueat practice sessions revealed shockingly poor US Navy... market within a very short time." TIhe author speculated that the device could destroy an entire town as far as 100 miks away with no loss te the...downed 72.8 percent of the 125 missiles observed. Nevertheless, one flying bomb hit Smithfield Market on 8 March, causing 233 casualties.61 In all, the

  18. Absolute and contrast infrared signatures from missile noses

    Tofani, Alessandro


    The infrared radiant intensity and radiative contrast produced by the aerodynamic and solar heating of missile noses have been obtained by computer simulating the corresponding temperature distributions and by taking into account the effects of both atmosphere (absorption and self-emission) and target geometry (distance, aspect and elevation angles). Six target classes have been considered, including cruise missiles, air-to-air and surface-to-surface missiles, and ballistic missiles. The comparison between radiative quantities in the 3 to 5 μm and S to 12 μm atmospheric transmittance windows gives the optimum spectral band for target detection in each point of its trajectory.

  19. 基于任务的潜用导弹武器系统保障性仿真评价%Simulation evaluation research on supportability of missile weapon system based on mission

    衡辉; 魏勇; 王新华; 杨迎化


    The defects existed in the traditional research of supportability were analyzed,some new evaluation indexes,including operational availability,operational readiness,mission completion success probability,were advanced,and the simulation model was established based on mission.Taking the operational mission,the structure and maintenance process as the foundation,a kind of simulating principle of missile weapon system was set up based on mission by using the theory of Monte-Carlo,Discrete Event and so on.The maintenance support simulation experiment was analyzed by an example.The evaluative parameters of mission capability on duty and support capabilities were acquired 、 Results of its application show that the method is feasible,can offer the decision for useful department and managing department.%分析传统保障性评价存在的缺陷,提出基于任务的使用可用度、战备完好率及任务成功率3个评价指标,建立相应的仿真统计模型.以使用任务、系统结构、维修保障过程分析为基础,引用离散事件、蒙特卡洛等理论建立一种基于任务的保障性评价仿真原理.通过一个实例对导弹武器系统的维修保障仿真试验进行分析,得出了导弹武器系统的执行任务能力和保障能力评价参数.仿真表明该方法是可行的,可为使用、维修保障部门评价装备的任务成功性和战备完好性等提供理论依据和方法支持.

  20. A Direct Interception Missile Assignment Model in Firepower Planning of Double-Layer Anti-Missile Combat%直接分配到弹的双层反导火力规划模型

    李龙跃; 刘付显; 杨国哲; 赵麟锋


    Firepower application is one of the core problem in anti-missile power construction,Firepower Planning of double-layer anti-missile combat in terminal phase is a Nondeterministic polynomial hard Mod-eling question.We analysis the problem,when to assign the interception missiles to the targets and give the model assumptions;Then we establish the direct interception missile assignment model in firepower planning of double-layer anti-missile combat This model break the research which targets only can be as-signed to the weapon system or fire units in the past,assigned the interception missiles to ballistic missiles one by one,it's a new idea about firepower planning.%反导作战火力运用是反导力量建设的核心内容之一,末段双层反导火力规划是一个复杂的不确定多约束条件优化问题,对火力规划进行了问题分析、弹-目分配时机分析和模型假设;分2个阶段建立了直接分配到弹的末段双层反导火力规划模型,模型重点考虑拦截目标与拦截弹杀伤时间窗口的对应关系,建立起武器系统拦截弹与来袭目标的弹-目对应分配关系,提供一种新的、快速的双层反导火力规划方法。

  1. Geohydrology of the High Energy Laser System Test Facility site, White Sands Missile Range, Tularosa Basin, south-central New Mexico

    Basabilvazo, G.T.; Nickerson, E.L.; Myers, R.G.


    The Yesum-HoHoman and Gypsum land (hummocky) soils at the High Energy Laser System Test Facility (HELSTF) represent wind deposits from recently desiccated lacustrine deposits and deposits from the ancestral Lake Otero. The upper 15-20 feet of the subsurface consists of varved gypsiferous clay and silt. Below these surfidai deposits the lithology consists of interbedded clay units, silty-clay units, and fine- to medium-grained quartz arenite units in continuous and discontinuous horizons. Clay horizons can cause perched water above the water table. Analyses of selected clay samples indicate that clay units are composed chiefly of kaolinire and mixed-layer illite/ smectite. The main aquifer is representative of a leaky-confined aquifer. Estimated aquifer properties are: transmissivity (T) = 780 feet squared per day, storage coefficient (S) = 3.1 x 10-3, and hydraulic conductivity (K) = 6.0 feet per day. Ground water flows south and southwest; the estimated hydraulic gradient is 5.3 feet per mile. Analyses of water samples indicate that ground water at the HELSTF site is brackish to slightly saline at the top of the main aquifer. Dissolved-solids concentration near the top of the main aquifer ranges from 5,940 to 11,800 milligrams per liter. Predominant ions are sodium and sulfate. At 815 feet below land surface, the largest dissolved-solids concentration measured is 111,000 milligrams per liter, which indicates increasing salinity with depth. Predominant ions are sodium and chloride.

  2. Passive FOG IMU for short-range missile application: from qualification toward series production

    Trommer, Gert F.; Mueller, R.; Opitz, S.


    An inertial measurement unit (IMU) with angular rate, angular increment and linear acceleration measurement systems for short range missile application is described. It consists of a three axis fiber optic gyroscope (FOG) cluster, three linear vibrating beam accelerometers and an electronics device for signal evaluation and data transmission via a serial transputer link. The FOG cluster is realized by means of a passive all-fiber open loop configuration. Due to the inherent optical phase shift of 3 by 3 couplers, completely passive operation near the quadrature point is achieved without the need for a non- reciprocal optical phase modulation in the fiber loop. Basing on that concept more than 50 rugged IMUs have been built for implementation into a short range air to air missile. Verification tests for flight clearance with stresses simulating air carriage and missile free flight environments have been computed. The operation under extreme vibration and shock environments without the use of vibration isolator fixings due to very tight requirements on data time delay has been demonstrated. The first telemetered missile firings have been performed successfully. The line- setup for large quantity series production is progressing. The implementation of the workstations for the integration of the IMU is finished. The production equipment for calibration and acceptance testing of IMUs in parallel allowing for a rate of more than 150 unit per month has been installed and will be operational in autumn this year.

  3. Backstepping design of missile guidance and control based on adaptive fuzzy sliding mode control

    Ran Maopeng; Wang Qing; Hou Delong; Dong Chaoyang


    This paper presents an integrated missile guidance and control law based on adaptive fuzzy sliding mode control. The integrated model is formulated as a block-strict-feedback nonlinear system, in which modeling errors, unmodeled nonlinearities, target maneuvers, etc. are viewed as unknown uncertainties. The adaptive nonlinear control law is designed based on backstepping and sliding mode control techniques. An adaptive fuzzy system is adopted to approximate the coupling nonlinear functions of the system, and for the uncertainties, we utilize an online-adaptive control law to estimate the unknown parameters. The stability analysis of the closed-loop system is also conducted. Simulation results show that, with the application of the adaptive fuzzy sliding mode control, small miss distances and smooth missile trajectories are achieved, and the system is robust against system uncertainties and external disturbances.

  4. 用于导弹逼近告警的“日盲”紫外光学系统设计%Design of solar-blind UV optical system for missile approach warning

    陈宇; 宋玉龙; 霍富荣


    紫外告警技术在军事应用中扮演着重要的角色。基于“日盲”紫外光学系统的最佳工作波段240~280 nm ,设计了一款用于导弹逼近告警的光学系统。为提高系统接收的紫外辐射能、扩展系统探测范围以及简化系统结构,系统中采用了非球面和二元衍射光学元件。系统中含有5片透镜,其焦距为50 mm,视场角为43°。探测器采用ANDOR公司的iKon-L 936型CCD,其像元大小为13.5μm×13.5μm,有效成像面积为27.6 mm×27.6 mm。系统优化后,最大RMS半径仅为11μm左右,远小于像元尺寸。超过86%来自物方各视场的紫外辐射会聚在半径为6.75μm的圆内。像质表明,所设计的系统能够满足“日盲”紫外光学系统的工作条件。若减小焦距,则系统的视场角可进一步增大。%Ultraviolet (UV) warning technology is playing a very important roll in the field of military application. Based on the optimal working waveband of solar-blind UV optical system from 240 nm to 280 nm, an optical system was designed for missile approach warning. To enhance the received light energy, expand the detection range and simplify the system structure, aspheric surfaces and binary elements were adopted in the system. Only five elements were used to realize the focal length 50 mm and field of view (FOV) 43 degrees. iKon-L 936 from ANDOR company was selected as the UV detector, which has pixel size 13.5μm×13.5μm and active image area 27.6 mm×27.6 mm. After optimization, the maximum RMS radius is only about 11 microns, which is much less than pixel size of the detector and more than 86% of the light energy from each FOV is converged within the circle of radius 6.75 microns. The image quality shows the designed system can meet the working requirements of solar-blind UV optical system. If the focal length can be decreased, the FOV of the system can be enlarged further.

  5. New digital-input transmitter for missile telemetry

    Rieger, J. L.; Woodworth, P. H.

    It is pointed out that telemetry for aircraft and missiles has been in use by the military and its suppliers since the 1950's, using a variety of frequencies and formats. However, the techniques used in airborne telemetry have changed as a consequence of advances in electronic technology. Use of digital pulse-code modulation instead of the analog time-sampled pulse-amptitude modulation (PAM) produced by an analog commutator has advantages in noise performance in instances where the telemetry link is performing near the threshold of noise. The present investigation is concerned with a digital-input transmitter which accepts binary format directly from a TTL source and has applicability in both standard telemetry and encrypted systems. Attention is given to telemetry modulation systems, data encryption requirements, the modulation interface, and transmitter characteristics.

  6. Joint FCRC Utah-Nevada Missile System


    surveyprcdes f. -Wrked with the local NX staff and BIM to develop an efficient and economically feasible nechanism to transfer public land to private...private sector devt induced by MX. b. Ensure that-land will be available in- time to complete impact mitigation capital constrution projects prior to

  7. An Analysis of Theater Missile Defense Systems.


    Ave. Fort Leavenworth, KS, 66027-1352 LTC John M. Rogers University of Kentucky College of Law Lexington, KY, 40506-0048 Naval War College Library ...Both President Clinton and the Chairman of the Joint Chiefs of Staff General John Shailikashvili have stated the country and the military are...1977), 84. 2 1William J. Durch, The ABM Treaty and Western Security (Cambridge: Ballinger Publishing, 1988), 36. 22Ibid., 8. 23Ernest J. Yanarella, The


    prepared concurrently with this report are available from the Defense Documentation Center, and the respective titles are ’Composite Thermal...on the particle distribution, time-temperature- cristobalite behavior and physical properties of pure fused silica, and fabrication of SCFS radome

  9. Trident II (D-5) Sea Launched Ballistic Missile UGM 133A (Trident II Missile)


    on quality training and unscheduled down time on the rocket motor precision drilling machine . Trident II Missile December 2015 SAR March 17, 2016...chocks, Third Stage (TS) dollies and TS Motor Supports and completion of machining and welding for Aerospike Protective Caps; 2) Early delivery of

  10. Common Ada Missile Packages. Phase 2. (CAMP-2). Volume 2. 11th Missile Demonstration


    bii t Ui< «i > i martial Sanaor Aaaaaibly 11th Miaaila Syatam Figure 1. 11th Missile Hardware Design TABLE 2. PROCESSORS AND THEIR FUNCTIONS...ualng Two Value Aretangant Coaputa Wander Ailauth Angle ualng Two Value Aretangant SUBTOTALS 132 14» 20 »003 North »olntlng HaTlgatlon » arta Coaputa

  11. Aerodynamic performances of cruise missile flying above local terrain

    Ahmad, A.; Saad, M. R.; Che Idris, A.; Rahman, M. R. A.; Sujipto, S.


    Cruise missile can be classified as a smart bomb and also Unmanned Aerial Vehicle (UAV) due to its ability to move and manoeuvre by itself without a pilot. Cruise missile flies in constant velocity in cruising stage. Malaysia is one of the consumers of cruise missiles that are imported from other nations, which can have distinct geographic factors including their local terrains compared to Malaysia. Some of the aerodynamic performances of missile such as drag and lift coefficients can be affected by the local geographic conditions in Malaysia, which is different from the origin nation. Therefore, a detailed study must be done to get aerodynamic performance of cruise missiles that operate in Malaysia. The effect of aerodynamic angles such as angle of attack and side slip can be used to investigate the aerodynamic performances of cruise missile. Hence, subsonic wind tunnel testings were conducted to obtain the aerodynamic performances of the missile at various angle of attack and sideslip angles. Smoke visualization was also performed to visualize the behaviour of flow separation. The optimum angle of attack found was at α=21° and side slip, β=10° for optimum pitching and yawing motion of cruise missile.

  12. A History of Polish Anti-Missile Defenses


    tanks, 1,750 armored personnel carriers, transport 11 aircraft, helicopters, and several naval craft.ŕ The WOPK provided air space management and...targets which included missile-related threats.90 Comunnication was an integral part of missile warning. Since Poland’s WOPK was part of the PVOS, Warsaw

  13. Ballistic Missile Defense Review Report


    attack, including through more aggressive denial and deception practices as well as a shift to mobile systems.  Some states are also developing...Avionics Upgrade/Obsolescence Program ( FAU /OP). The Department will also emphasize proven capabilities by requesting funding for additional GMD... practical solutions to emerging challenges, solutions that involve all elements of national power. In addition, by working with allies and partners to

  14. CT analysis of missile head injury

    Besenski, N. [Dept. of Radiology, Zagreb Univ. Hospital Rebro (Croatia); Jadro-Santel, D. [Dept. of Neuropathology, Zagreb Univ. Hospital Rebro (Croatia); Jelavic-Koic, F. [Dept. of Radiology, General Hospital Sveti Duh, Zagreb (Croatia); Pavic, D. [Dept. of Neuropathology, Zagreb Univ. Hospital Rebro (Croatia); Mikulic, D. [Zagreb School of Medicine (Croatia); Glavina, K. [Dept. of Radiology, Clinical Hospital, Osijek (Croatia); Maskovic, J. [Dept. of Radiology, Clinical Hospital, Split (Croatia)


    Between August 1991 and December 1992, CT was performed in 154 patients who had suffered missile head injury during the war in the Republic of Croatia. In 54% CT was performed 1-24 h after injury, and in 27% follow-up CT was also obtained. The wounds were penetrating, tangential or perforating (45%, 34% and 21%, respectively). Haemorrhage was the most frequent lesion in the brain (84%). Follow-up CT evolution of haemorrhage, oedema, cerebritis, abscess, secondary vascular lesions, necrosis, encephalomalacia and hydrocephalus. The most dynamic changes occurred 7-14 days after injury. In 14% of cases, deep cerebral lesions were found in the corpus callosum, septum pellucidum periventricular region and pons, although bone and shell fragments were in a different part of the brain parenchyma. Such lesions were found in penetrating injuries only. CT proved very useful for assessing the extent and type of lesions. Although different mechanisms of brain damage in missile head injury are known, here they are, to the best of our knowledge, shown for the first time by CT. (orig.)



    The applied problems of SINS/GPS integration navigation system existing in midcourse guidance of air-to-air missiles have been investigated recently. In comparison with those investigations existing in current publications, a new tightly coupled SINS/GPS integration navigation system for air-to-air missiles, based on the decorrelated pseudo-range approach, is presented in this paper. Because of high jamming and dynamic of air-to-air missiles, inertial velocity aiding GPS receiver is used to provide a more accurate, jam-resistant measurement for midcourse guidance systems. A tracking error estimator is designed to distinguish the correlation that existed between pseudo-range measurements and inertial information. It is found better to regard inertial velocity aiding errors as the noise of which statistical properties are unknown. So using mixed Kalman/minimax filtering theory, one can obtain the new tracking error estimator with simple and robust algorithm through constructing a composite filter consisting of two parts: Kalman filter for the noise of known statistics and minimax filter for the unknown. In order to ensure this simple estimator stability, a new method is proposed to choose its parameters, based on Khargonekars work. Moreover, it is demonstrated that the given method also ensures the proposed estimator optimality. All the work mentioned above is involved in the tightly coupled SINS/GPS integration midcourse system design in which a set of low-accuracy inertial components is shared by SINS and autopilot. Simulation results of a certain type of air-to-air missile are presented. Due to decorrelation by the tracking error estimator, only small white noise of pseudo-range measurements remains. So it is shown that application of the new midcourse guidance system results in better guidance accuracy, higher jam-resistance.

  16. Research on the Robustness of an Adaptive PID Control of a Kind of Supersonic Missile

    Gangling Jiao


    Full Text Available In this study, the dynamic characteristic of missile system is viewed as a two-loop system, such as inner loop and outer loop and we design an adaptive PID control strategy for the pitch channel linear model of supersonic missile. The robustness of a double PID controller is analyzed by changing the aerodynamic coefficients. The control law is testified to be stable even the aerodynamic coefficients are changed between 0.7 and 1.7 times of its standard value and the control effect is compared with the sliding mode control strategy. Also the advantage and defect of both control strategy are summarized at the end of this study.

  17. A Study on Missile Reentry Control Based on the Method of Feedback Linearization

    LIU Yu-xi; ZHOU Jun; ZHOU Feng-qi


    In the process of missile large attack angle reentry, there exist nonlinear, strong coupling uncertainty and multiinput-multi-output (MIMO) in the movement equations, so the traditional small disturbance faces difficulties. For such situations, the method of feedback linearization is adopted to control the complex system, and the control method based on the fuzzy adaptive nonlinear dynamic inversion decoupling control of missile is proposed in the paper. According to the principle of time-scale separation, the system is separated into fast loop and slow loop, the method of dynamic inversion is applied to them, and the method of adaptive fuzzy approach is adopted to compensate for the uncertainty of the fast loop.The simulation results denote the control method in the paper has a better tracing characteristic and robustness.

  18. Results from Sandia National Laboratories/Lockheed Martin Electromagnetic Missile Launcher (EMML).

    Lockner, Thomas Ramsbeck; Skurdal, Ben (Lockheed Martin MS2, Baltimore, MD); Gaigler, Randy (Lockheed Martin MS2, Baltimore, MD); Basak, L (Lockheed Martin MS2, Baltimore, MD); Root, G (Lockheed Martin MS2, Baltimore, MD); Aubuchon, Matthew S.; Turman, Bobby N.; Floyd, Mendel D. (Lockheed Martin MS2, Baltimore, MD)


    Sandia national laboratories (SNL) and lockheed martin MS2 are designing an electromagnetic missile launcher (EMML) for naval applications. The EMML uses an induction coilgun topology with the requirement of launching a 3600 lb. missile up to a velocity of 40 m/s. To demonstrate the feasibility of the electromagnetic propulsion design, a demonstrator launcher was built that consists of approximately 10% of the propulsion coils needed for a tactical design. The demonstrator verified the design by launching a 1430 lb weighted sled to a height of 24 ft in mid-December 2004 (Figure 1). This paper provides the general launcher design, specific pulsed power system component details, system operation, and demonstration results.

  19. Indirect robust control of agile missile via Theta-D technique

    Di Zhou


    Full Text Available An agile missile with tail fins and pulse thrusters has continuous and discontinuous control inputs. This brings certain difficulty to the autopilot design and stability analysis. Indirect robust control via Theta-D technique is employed to handle this problem. An acceleration tracking system is formulated based on the nonlinear dynamics of agile missile. Considering the dynamics of actuators, there is an error between actual input and computed input. A robust control problem is formed by treating the error as input uncertainty. The robust control is equivalent to a nonlinear quadratic optimal control of the nominal system with a modified performance index including uncertainty bound. Theta-D technique is applied to solve the nonlinear optimal control problem to obtain the final control law. Numerical results show the effectiveness and robustness of the proposed strategy.

  20. A Low-Visibility Force Multiplier: Assessing China’s Cruise Missile Ambitions


    and ballistic missile force will be far less effective than its numbers would indicate. 18 Forensic data may not have been collected and analyzed for...and ballistic missiles; some has focused on Chinese efforts to develop an antiship ballistic missile that might tar- get U.S. aircraft carriers. One...electronically scanned array AIP air-independent propulsion ARM antiradiation missile ASAT antisatellite ASBM antiship ballistic missile ASCM antiship

  1. ASTEROFF: A Computer Code to Deflect NEOs by Missiles shot from L1 and L3 (Earth-Moon)

    Maccone, C.

    We develop the mathematical theory for an automatic, space-based system to deflect NEOs by virtue of missiles shot from the Earth-Moon L1 and L3 Lagrangian Points. A patent application has been filed for the relevant code, dubbed ASTEROFF (= Asteroids OFF !). This code was already implemented, and a copyright for it was registered. In a paper published in Acta Astronautica, Vol. 50, No. 3, pp. 185-199 (2002), this author proved mathematically the following theorem (hereafter called the ``confocal conics theorem''): ``Within the sphere of influence of the Earth, any NEO could be hit by a missile at just an angle of 90 degrees, was the missile shot from Lagrangian Points L1 or L3 of the Earth-Moon system, rather than from the surface of the Earth''. As a consequence, the hitting missile would have move along a ``confocal ellipse'' (centered at the Earth) uniquely determined by the NEO's incoming hyperbola. Based on the above theorem, the author further shows in this paper that: The proposed defense system would be ideal to deflect NEOs that are small, i.e. less than one kilometer in diameter. Small NEOs are just the most difficult ones to be detected early enough and to such an orbital accuracy to be positively sure that they are indeed hazardous. The traditional theory of Keplerian orbits can successfully be applied to get an excellent first-order approximation of the (otherwise unknown) mathematical formulae of the energy/momentum requested to achieve the NEO deflection. Many engineering details about the missiles shot from L1 and L3, however, still have to be implemented into our simulations, partly because they are classified. Was one missile not enough to deflect the NEO completely, it is a great advantage of the ``confocal conics'' used here that the new, slightly deflected NEO's hyperbola would certainly be hit at nearly 90 degrees by another and slightly more eccentric elliptical missile trajectory. A sufficient number of missiles could thus be launched in a

  2. Ballistic Missile Defense in the European Theater: Political, Military and Technical Considerations


    in a ground-based system, called the Sol-Air Moyen Portee/ Terrestre (SAMP/T) that uses the Aster 15 and the Aster 30 missiles with a range of up to...development processes “ via a spiral pathway culminating in an operator-in-the- 107 COL Tim Polaske Chief...Reentry Vehicle SAMP/T Sol-Air Moyen Portee/ Terrestre SBI Space Based Interceptor SBIRS Space Based Infrared Satellite SHAPE

  3. TOW Missile Pallet MIL-STD-1660 Tests


    0 DTICS ELECTE FEB 2 19941 FINAL REPORT C U ow AUGUST 1993 (V V Lfl3 NNE REPORT NO. 93-23 TOW MISSILE PALLET MIL- STD -1660 TESTS Prepared for...TITLE gOnakde Secwir Casaftedon) TOW Missile Pallet MIL- STD -1660 Tests 12. PERSONAL AUTHOR(S) Jason B. Solberg 13s. TYPE OF REPORT 13b. TIME COVERED...and Engineering Center (ARDEC) to test the TOW missile pallet. This report contains the procedures, results, and recommendations from the MIL- STD

  4. Aerodynamic heating of ballistic missile including the effects of gravity

    S N Maitra


    The aerodynamic heating of a ballistic missile due to only convection is analysed taking into consideration the effects of gravity. The amount of heat transferred to the wetted area and to the nose region has been separately determined, unlike A Miele's treatise without consideration of gravity. The peak heating ratesto the wetted area and to the nose of the missile are also investigated. Finally four numerical examples are cited to estimate the errors, in heat transfers and heating ratesto both wetted area and nose region of the missile, arising out of neglecting the gravitational forces.

  5. Analysis of Rocket, Ram-Jet, and Turbojet Engines for Supersonic Propulsion of Long-Range Missles. II - Rocket Missile Performance

    Huff, Vearl N.; Kerrebrock, Jack


    The theoretical performance of a two-stage ballistic rocket mis having a centerbody and two parallel boosters was investigated for J oxygen and ammonia-fluorine propellants. Both power-plant and missi parameters were optimized to give minimum cost on-the basis of the analysis for a range of 5500 nautical miles. After optimum values were found, each parameter was varied independently to determine its effect on performance of the missile. The missile using the ammonia-fluorine propellant weighs about one half as much as a missile using JP4-oxygen. Based on an expected unit cost of fluorine in quantity production, the ammonia-fluorine missile has a substantially lower relative cost than a JP4-oxygen missile. Optimum chamber pressures for both propellant systems and for both the centerbody and boosters were between 450 and 600 pounds per square inch. High design altitudes for the exhaust nozzle are desirable for both the centerbody and boosters. For the centerbody, the design altitude should be between 45,000 and 60,000 feet, with the value for ammonia-fluorine lower than that for JP4-oxygen. For the boosters, the design altitude should be 20,000 to 30,000 feet, with the value for the ammonia-fluorine. missile higher.

  6. Terrain-aided navigation of an unpowered tactical missile using autopilot-grade sensors

    Longenbaker, W. E.


    The feasibility of applying a terrain-aided navigation concept (Sandia Inertial Terrain-Aided Navigation, or SITAN) to an unpowered tactical missile (USAF GBU-15) is considered. The brief flight time and predictable missile flight path dynamics lead to the definition of a velocity-based strap-down navigation algorithm that uses the existing autopilot-grade sensors. The navigation states are corrected by means of the error estimates of a Kalman filter. The filter makes use of frequent radar altimeter measurements and terrain slope information (derived from an on-board digitized map) to provide essentially continuous position updating. Covariance analysis and Monte Carlo simulation techniques are then applied to predict system performance. Results are obtained showing that the accuracy of this weapon/guidance combination is sufficient to defeat airfields with area munitions.

  7. Using Fractional-order Piλ Dμ Controller for Control of Aerodynamic Missile

    ZHANG Bang-chu; ZHU Ji-hong; PAN Shu-shan; WANG Shao-feng


    A new type of PID controller is introduced and some properties are given. The novelty of the proposed controller consists in the extension of derivation and integration order from integer to non-integer order. The PIλDμ controller generally has three advantages when compared to the integerl-order controller: the first is that it has more degrees of freedom in the model; the second is that it has a memory in model, the memory insure the history and its impact to present and future, the third is it ensures the stability of missile. This approach provides a more flexible tuning strategy and therefore an easier achieving of control requirements. Flight dynamic model of an aerodynamic missile is taken into account in implementing the PIλDμ controller. Simulation results show that the PIλDμ controller is not sensitive to the changes of control parameters and the system parameters. Also, the controller has more flexible structure and stronger robustness.

  8. Regional Joint-Integrated Air and Missile Defense (RF-IAMD): An Operational Level Integrated Air and Missile Defense (IAMD) Command and Control (C2) Organization


    the Naval Air and Missile Defense Command (NAMDC). NAMDC then began training field grade officers through a Weapons and Tactics Instructor ( WTI ...49 Integrated Air and Missile Defense (IAMD) Weapons and Tactics Instructor ( WTI ), Naval Air and Missile...and Missile Defense (IAMD) Weapons and Tactics Instructor ( WTI ). Accessed April 28, 2015.

  9. A new guidance law for a tactical surface-to-surface missile

    Danilo V. Ćuk


    Full Text Available Modern tactical surface-to-surface missiles, equipped with strapdown inertial navigation systems, achieve very good accuracy compared with free-flight rockets. The probable range dispersion mainly depends on instruments errors and longitudinal disturbances such as rocket motor total-impulse deviation as well as differences between the estimated and actual values of the axial force and head wind. This paper gives an extension of the correlated velocity concept for surface-to-surface missiles without a thrust-terminating mechanism. The calculated parameters of the correlated velocity are stored into the memory of an onboard guidance computer. On the basis of the correlated velocity concept, the modified proportional navigation with the adjustment of the time-to-go of the missile to the target was proposed. It is shown that the new guidance law can compensate for the longitudinal disturbances of different levels successfully. The effectiveness of the proposed guidance method was confirmed by means of the calculated probable range and lateral dispersion for the anticipated disturbances in the guidance system.

  10. The Study of Tactical Missile's Airframe Digital Optimization Design

    LUO Zhiqing; QIAN Airong; LI Xuefeng; GAO Lin; LEI Jian


    Digital design and optimal are very important in modern design. The traditional design methods and procedure are not fit for the modern missile weapons research and development. Digital design methods and optimal ideas were employed to deal with this problem. The disadvantages of the traditional missile's airframe design procedure and the advantages of the digital design methods were discussed. A new concept of design process reengineering (DPR) was put forward. An integrated missile airframe digital design platform and the digital design procedure, which integrated the optimization ideas and methods, were developed. Case study showed that the design platform and the design procedure could improve the efficiency and quality of missile's airframe design, and get the more reasonable and optimal results.

  11. Vortex development on slender missiles at supersonic speeds

    Allen, J. M.; Dillenius, M. F. E.


    A theoretical and experimental effort has been made to develop a vortex-prediction capability on circular and noncircular missiles at supersonic speeds. Predicted vortex patterns are computed by two linear-theory computer codes. One calculates the strengths and initial locations of the vortices, and the other calculates their trajectories. A short color motion picture has been produced from the calculations to illustrate the predicted vortex patterns on a typical missile. Experimental vapor-screen photographs are presented to show the longitudinal development of the vortices on a fin-control missile. Comparisons are made between these data and the predicted vortices to assess the accuracy of the theory. The theory appears to be fairly accurate in predicting the number, locations, and relative strengths of individual vortices which develop over the missile, but cannot predict vortex sheets or diffuse vorticity whenever they occur.

  12. Revolution in military affairs, missile defence and weapons in space ...

    Revolution in military affairs, missile defence and weapons in space: the US ... 1991 Gulf War that captured the imagination of military planners and policy makers, ... Firstly, very few countries have the financial and technological capability to ...

  13. Analysis and improvement of missile three-loop autopilots

    Lin Defu; Fan Junfang; Qi Zaikang; Mou Yu


    characteristics from a two-loop autopilot with PI compensator.Both the two-loop and three-loop topologies can stabilize a static unstable missile.However,the finite actuator resource is the crucial factor dominating autopilot function.

  14. Design and Manufacturing Process for a Ballistic Missile

    Zaharia Sebastian Marian


    Full Text Available Designing a ballistic missile flight depends on the mission and the stress to which the missile is subject. Missile’s requests are determined by: the organization of components; flight regime type, engine configuration and aerodynamic performance of the rocket flight. In this paper has been developed a ballistic missile with a smooth fuselage type, 10 control surfaces, 8 directional surfaces for cornering execution, 2 for maneuvers of execution to change the angle of incidence and 4 stabilizers direction. Through the technology of gluing and clamping of the shell and the use of titanium components, mass of ballistic missile presented a significant decrease in weight and a structure with high strength.

  15. Density Models for Velocity Analysis of Jet Impinged CEDM Missile

    Jo, Won Ho; Kang, Tae Kyo; Cho, Yeon Ho; Chang, Sang Gyoon; Lee, Dae Hee [KEPCO EnC, Daejeon (Korea, Republic of)


    A control element drive mechanism (CEDM) can be a potential missile in the reactor head area during one of the postulated accidents. The CEDM is propelled by the high speed water jet discharged from a broken upper head nozzle. The jet expansion models to predict the missile velocity have been investigated by Kang et al. The previous work of Kang et al. showed a continuous increase in missile velocity as the CEDM missile travels. But it is not natural in that two phase flow from the nozzle break exit tends to disperse and the thrust force on the missile decreases along the distance of the travel. The jet flow also interacts with the air surrounding itself. Therefore, the density change has to be included in the estimation of the missile velocity. In this paper, two density change models of the water jet are introduced for the jet expansion models along with the distance from the nozzle break location. The first one is the direct approximation model. Two density approximation models are introduced to predict the CEDM missile velocity. For each model, the effects of the expanded jet area were included as the area ratio to the exit nozzle area. In direct approximation model, the results have showed rapid decrease in both density and missile velocity. In pressure approach model, the density change is assumed perfectly proportional to the pressure change, and the results showed relatively smooth change in both density and missile velocity comparing to the direct approximation model. Using the model developed by Kang et al.., the maximum missile velocity is about 4 times greater comparing to the pressure approach model since the density is constant as the jet density at the nozzle exit in their model. Pressure approach model has benefits in that this model adopted neither curve fitting nor extrapolation unlike the direct approximation model, and included the effects of density change which are not considered in the model developed by Kang et al. So, this model is

  16. Application of Computer Graphics to Performance Studies of Missile Warheads

    K. Rama Rao


    Full Text Available Intercept geometry of target aircraft and missiles play an important role in determining the effectiveness of the warhead. Factors such as fragment spatial distribution profile, damage capabilities, target and missile characteristics have been considered and visualised through computer graphics and optimum intercept intercept angles have been arrived. Computer graphics has proved to be an important tool to enhance perception and conceptual design capabilities in the design environment.

  17. Patriot Advanced Capability-3 Missile Segment Enhancement (PAC-3 MSE)


    sustainment reliability will exceed 20 hours MTBCMF. Will be demonstrated during Post Deployment Build -8 and Radar Digital Processor- Configuration...Technology and Logistics) PAC-3 MSE December 2015 SAR March 21, 2016 09:42:58 UNCLASSIFIED 4 COL John M. Eggert Lower Tier Project Office Building 5250...PAC-3 MSE) is a high velocity, hit-to-kill, surface -to-air missile capable of intercepting and destroying Tactical Ballistic Missiles (TBM) and air

  18. Missile Defense Acquisition: Failure Is Not An Option


    missile over Japan into the sea.1With the nation already possessing weapons of mass destruction (WMD), the test launch signaled their intention to...Korea stunned the world in 1998 with the launch of a Taepo Dong-1 ballistic missile over Japan into the sea.4With the nation already possessing nuclear...acquisition agility. MDA’s BMDS acquisition strategy must be timely, flexible, and agile or risk irrelevance. BMDS Layered Architecture Since the NMD

  19. The expectation of applying IR guidance in medium range air-to-air missiles

    Li, Lijuan; Liu, Ke


    IR guidance has been widely used in near range dogfight air-to-air missiles while radar guidance is dominant in medium and long range air-to-air missiles. With the development of stealth airplanes and advanced electronic countermeasures, radar missiles have met with great challenges. In this article, the advantages and potential problems of applying IR guidance in medium range air-to-air missiles are analyzed. Approaches are put forward to solve the key technologies including depressing aerodynamic heating, increasing missiles' sensitivity and acquiring target after launch. IR medium range air-to-air missiles are predicted to play important role in modern battle field.

  20. 一种导弹防空视景仿真系统设计与Vega实现%Design and Realization of Scene Simulation System for Missile Defense Based on Vega

    张继山; 程文娟; 陆文骏


    虚拟现实技术是目前国内外仿真界研究的热点之一,而视景仿真技术是其核心技术。利用Vega软件,研究了防空导弹发现并截击飞机的视景仿真过程,研究了点击式图形环境Lynx和Vega软件的开发方法,对类似问题的研究提供了帮助。%The technique of Virtual Reality is one of hot points in domestic and international simulation field, which studies simulation boundary. And technique of scene simulation is a core technique. By using Vega software, a complete guided missile is discovered and cutting the process of the shot airplane is designed, and the click type sketch environment of Lynx with the Vega software development method is also researched. It's helpful for similar problem.

  1. Cooled and uncooled infrared detectors for missile seekers

    Fraenkel, Rami; Haski, Jacob; Mizrahi, Udi; Shkedy, Lior; Shtrichman, Itay; Pinsky, Ephi


    Electro-optical missile seekers pose exceptional requirements for infrared (IR) detectors. These requirements include: very short mission readiness (time-to-image), one-time and relatively short mission duration, extreme ambient conditions, high sensitivity, fast frame rate, and in some cases small size and cost. SCD is engaged in the development and production of IR detectors for missile seeker applications for many years. 0D, 1D and 2D InSb focal plane arrays (FPAs) are packaged in specially designed fast cool-down Dewars and integrated with Joule-Thomson (JT) coolers. These cooled MWIR detectors were integrated in numerous seekers of various missile types, for short and long range applications, and are combat proven. New technologies for the MWIR, such as epi-InSb and XBn-InAsSb, enable faster cool-down time and higher sensitivity for the next generation seekers. The uncooled micro-bolometer technology for IR detectors has advanced significantly over the last decade, and high resolution - high sensitivity FPAs are now available for different applications. Their much smaller size and cost with regard to the cooled detectors makes these uncooled LWIR detectors natural candidates for short and mid-range missile seekers. In this work we will present SCD's cooled and uncooled solutions for advanced electro-optical missile seekers.

  2. Missile launch detection electric field perturbation experiment. Final report

    Kane, R.J.; Rynne, T.M.


    The Lawrence Livermore National Laboratory and SARA Inc. participated in the ATMD missile launch activities that occurred at WSMR during January 1993. LLNL and SARA deployed sensors for monitoring of basic phenomena. An attempt was made to measure perturbations of the earth geo-potential during the launch of a Lance missile. The occurrence of the perturbation is expected from the conducting body of the missile and the exhaust plume. A set of voltage-probe antennas were used to monitor the local electric field perturbation from the launch at ranges of approximately 1 km. Examination of the data acquired during the launch period failed to show identifiable correlation of the field variations with the launch event. Three reasons are ascribed to this lack of event data: (1) The electric field potential variations have a limited spatial correlation length - the fields measured in one region have little correlation to measurements made at distances of a kilometer away. The potential variations are related to localized atmospheric disturbances and are generally unpredictable. A value for the spatial correlation length is also not known. (2) The conductivity of the plume and missile body are not adequate to produce a field perturbation of adequate magnitude. Phenomena related to the exhaust plume and missile may exist and be outside of the collection range of the equipment employed for these measurements. (3) The presence of 60 Hz power line noise was of sufficient magnitude to irreversibly contaminate measurements.

  3. Asia-Pacific Missile Defense Cooperation and the United States 2004-2005: A Mixed Bag


    in cooperating with the United States on various missile defense -related programs. Such close friends and allies as South Korea and Taiwan have made...many local opponents of missile defense argue that the missile threat to Australia is quite low, particularly as North Korea does not yet possess any...2004 in cooperating with the United States. Overall, South Korea does not appear to regard the North Korean missile threat as very likely. Based on

  4. Design of Ground Test Equipment for Missile Weapon System Based on Nested State Machine Model%基于嵌套式状态机模型的导弹武器系统地面监测系统设计

    陈尧; 张靖; 尹明


    Working mechanism of state machine and its application in LabVIEW are introduced in detail according to basic principle of state machine. Combined with the development of ground test equipment for missile weapon system and multi-state system, the idea of nested state machine is presented. It is proved in project practice that the framework of nested state machine can be used to develop large-scale test system, making its complicated logical relationship more clear, and improving the expansibility, reusability and maintainability of software system greatly.%通过引入状态机的基本原理, 详细介绍了状态机的工作机理及其在LabVIEW中的实现方法.结合对炮射导弹武器系统地面监测系统的开发, 针对多状态系统, 提出了嵌套式状态机的设计思想.实践证明, 采用嵌套式状态机的架构模式开发大型测试系统可使复杂程序的逻辑关系更清晰, 极大地增强了软件系统的可扩展性、可重用性和可维护性.


    KANGGuo-hua; LIUJian-ye; ZHUYan-hua; XIONGZhi


    Considering the domestic single navigation system of the ballistic missile, a new filter method is presented. The method integrates the information of the strapdown star tracker (SST) attitude, the position and the velocity of a high speed GPS with a strapdown inertial navigation system (SINS) information into one filter, thus improving the precision of the attitude, the velocity, and the position. Finally, the GPS/SST/SINS simulation platfornt is designed. Simulation results demonstrate that the filter is robust and reliable, and the precision rises to the comparative level abroad.

  6. Application of Extended Kalman Filter to Tactical Ballistic Missile Re-entry Problem

    Bhowmik, Subrata


    The objective is to investigate the advantages and performance of Extended Kalman Filter for the estimation of non-linear system where linearization takes place about a trajectory that was continually updated with the state estimates resulting from the measurement. Here tactile ballistic missile Re-entry problem is taken as a nonlinear system model and Extended Kalman Filter technique is used to estimate the positions and velocities at the X and Y direction at different values of ballistic coefficients. The result shows that the method gives better estimation with the increase of ballistic coefficient.

  7. 76 FR 63541 - Design-Basis Hurricane and Hurricane Missiles for Nuclear Power Plants


    ...-2010-0288] Design-Basis Hurricane and Hurricane Missiles for Nuclear Power Plants AGENCY: Nuclear... Hurricane Missiles for Nuclear Power Plants.'' This regulatory guide provides licensees and applicants with... hurricane and design-basis hurricane-generated missiles that a nuclear power plant should be designed...

  8. High performance infrared fast cooled detectors for missile applications

    Reibel, Yann; Espuno, Laurent; Taalat, Rachid; Sultan, Ahmad; Cassaigne, Pierre; Matallah, Noura


    SOFRADIR was selected in the late 90's for the production of 320×256 MW detectors for major European missile programs. This experience has established our company as a key player in the field of missile programs. SOFRADIR has since developed a vast portfolio of lightweight, compact and high performance JT-based solutions for missiles. ALTAN is a 384x288 Mid Wave infrared detector with 15μm pixel pitch, and is offered in a miniature ultra-fast Joule- Thomson cooled Dewar. Since Sofradir offers both Indium Antimonide (InSb) and Mercury Cadmium Telluride technologies (MCT), we are able to deliver the detectors best suited to customers' needs. In this paper we are discussing different figures of merit for very compact and innovative JT-cooled detectors and are highlighting the challenges for infrared detection technologies.

  9. Roll-pitch-yaw autopilot design for nonlinear time-varying missile using partial state observer based global fast terminal sliding mode control

    Ahmed Awad; Wang Haoping


    The acceleration autopilot design for skid-to-turn (STT) missile faces a great challenge owing to coupling effect among planes, variation of missile velocity and its parameters, inexistence of a complete state vector, and nonlinear aerodynamics. Moreover, the autopilot should be designed for the entire flight envelope where fast variations exist. In this paper, a design of inte-grated roll-pitch-yaw autopilot based on global fast terminal sliding mode control (GFTSMC) with a partial state nonlinear observer (PSNLO) for STT nonlinear time-varying missile model, is employed to address these issues. GFTSMC with a novel sliding surface is proposed to nullify the integral error and the singularity problem without application of the sign function. The pro-posed autopilot consisting of two-loop structure, controls STT maneuver and stabilizes the rolling with a PSNLO in order to estimate the immeasurable states as an output while its inputs are missile measurable states and control signals. The missile model considers the velocity variation, gravity effect and parameters’ variation. Furthermore, the environmental conditions’ dynamics are mod-eled. PSNLO stability and the closed loop system stability are studied. Finally, numerical simula-tion is established to evaluate the proposed autopilot performance and to compare it with existing approaches in the literature.

  10. Roll-pitch-yaw autopilot design for nonlinear time-varying missile using partial state observer based global fast terminal sliding mode control

    Awad Ahmed


    Full Text Available The acceleration autopilot design for skid-to-turn (STT missile faces a great challenge owing to coupling effect among planes, variation of missile velocity and its parameters, inexistence of a complete state vector, and nonlinear aerodynamics. Moreover, the autopilot should be designed for the entire flight envelope where fast variations exist. In this paper, a design of integrated roll-pitch-yaw autopilot based on global fast terminal sliding mode control (GFTSMC with a partial state nonlinear observer (PSNLO for STT nonlinear time-varying missile model, is employed to address these issues. GFTSMC with a novel sliding surface is proposed to nullify the integral error and the singularity problem without application of the sign function. The proposed autopilot consisting of two-loop structure, controls STT maneuver and stabilizes the rolling with a PSNLO in order to estimate the immeasurable states as an output while its inputs are missile measurable states and control signals. The missile model considers the velocity variation, gravity effect and parameters’ variation. Furthermore, the environmental conditions’ dynamics are modeled. PSNLO stability and the closed loop system stability are studied. Finally, numerical simulation is established to evaluate the proposed autopilot performance and to compare it with existing approaches in the literature.

  11. Evaluation of Impact Force of Missile Filled with Fluid

    Lee, Hyuk-Kee [Hyundai, Yongin (Korea, Republic of); Kim, Seung-Eock [Sejong University, Seoul (Korea, Republic of)


    In this paper, the effect of the fluid on the impact force was evaluated using the commercial software LS-DYNA. In order to verify the proposed finite element (FE) models, the impact force and impulse of the missiles filled with the fluid (wet missile) were investigated, and the analysis results were compared with the force plate tests conducted by VTT laboratory in Finland. A parametric study was performed to evaluate the impulse as per the position filled with the fluid and the impact velocity. The impulses of the wet missiles obtained from the parametric study were compared with those calculated by the modified Riera function. The effect of the fluid on the impact force was evaluated in this study. Based on this study, the following conclusions have been obtained: (1) The impulse/momentum ratios of the wet missiles filled with fluid in the front part were larger than those filled with fluid in the middle part. The difference was 5.5%, 5.3%, 6.2%, 3.8%, 2.9% and 1.0% for the impact velocities of 100 m/s, 110 m/s, 120 m/s, 130 m/s, 140 m/s, and 150 m/s, respectively. (2) The impulse/momentum ratios of the wet missiles by the FE analysis was larger than those by the modified Riera function up to 23.1% and 20.8%, respectively, when the fluid was filled in the front and middle parts. The modified Riera function underestimated the impulses of the wet missiles.

  12. Heat Transfer Between a Missile's Combustion Chamber and the Warhead

    赵永涛; 张奇; 白春华; 闫华


    Under higher temperatures the charge within a warhead will be subjected to physical and chemical changes, which will influence the security of the warhead launching process. In this paper the problem is studied adopting finite difference method for the case of a rocket-powered missile. Temperature distribution tables are given through quadrature experiments, and the results fit the actual measured values very well. The results also show that to ensure the launching security of rocket-powered missiles having warhead charge critical temperature close to about 60 ℃, the designer can select appropriate heat insulation structural parameters.

  13. Robust control for snake maneuver design of missile

    Kun, Ya; Chen, Xin; Li, Chuntao


    For the performance of missile with high Mach number and strongly nonlinear dynamics, this paper uses robust control to design maneuver controller. Robust servomechanism linear quadratic regulator (RSLQR) control is used to form the inner loop and proportional-plus-integral (PI) control is used to provide yawing tracking with no error. Contrast simulations under three types of deviation have been done to confirm robustness of the RSLQR-plus-PI control. Simulation results shows that RSLQR-plus-PI control would resist the disturbance and maintain the properties of the controller, guarantee the robustness and stability of missile more effectively than pure PI control.

  14. Consolidation of data base for Army generalized missile model

    Klenke, D. J.; Hemsch, M. J.


    Data from plume interaction tests, nose mounted canard configuration tests, and high angle of attack tests on the Army Generalized Missile model are consolidated in a computer program which makes them readily accessible for plotting, listing, and evaluation. The program is written in FORTRAN and will run on an ordinary minicomputer. It has the capability of retrieving any coefficient from the existing DATAMAN tapes and displaying it in tabular or plotted form. Comparisons of data taken in several wind tunnels and of data with the predictions of Program MISSILE2 are also presented.

  15. Research on image fusion of missile team based on multi-agent cooperative blackboard model

    Sen, Guo; Munan, Li

    The target of cooperative engagement of missile teams is to furthest improve hit rate of target according to communication and cooperation among missiles. In this paper the problems of image fusion between missile teams in complex combat environment was analyzed, after which an muti-agent blackboard cooperative model was presented and a public information platform of missile team is built according to this model. Through these, the fusion of images taken from muti-sensor of missiles can be realized and the hit rate of attacking target will be improved. At last, an simulation experiment were performed, and the feasibility of the method is proved by simulation experiment.

  16. The vulnerability of laser warning systems against guided weapons based on low power lasers

    Al-Jaberi, Mubarak


    Laser assisted weapons, such as laser guided bombs, laser guided missiles and laser beam-riding missiles pose a significant threat to military assets in the modern battlefield. Laser beam-riding missiles are particularly hard to detect because they use low power lasers. Most laser warning systems produced so far can not detect laser beam-riding missiles because of their weak emissions which have signals less than 1% of laser range finder power . They are even harder to defeat because current ...

  17. Method of Designing Missile Controller Based on Multi-Objective Optimization

    LIN Bo; MENG Xiu-yun; LIU Zao-zhen


    A method of designing robust controller based on genetic algorithm is presented in order to overcome the drawback of manual modification and trial in designing the control system of missile. Specification functions which reflect the dynamic performance in time domain and robustness in frequency domain are presented,then dynamic/static performance, control cost and robust stability are incorporated into a multi-objective optimization problem. Genetic algorithm is used to solve the problem and achieve the optimal controller directly.Simulation results show that the controller provides a good stability and offers a good dynamic performance in a large flight envelope. The results also validate the effectiveness of the method.

  18. The Joint Cruise Missiles Project: An Acquisition History--Appendixes


    21 TERCOM and Terrain Following Operation.......................22 DMA/JCMPO Organizational Interactions...50 MRASM (AGM-1091) Test Program................................52 Cruise Missile TERCOM and Survivability Flight package TEL Transporter erector launcher T&E Test and evaluation TEMP Test and evaluation master plan TERCOM Terrain contour matching UFC Unit

  19. CMC occasional papers : a missile stability regime for South Asia.

    Khan, Feroz Hassan (Pakistan Army, Islamabad, Pakistan); Vannoni, Michael Geoffrey; Rajen, Gaurav (Gaia Research Consulting, Albuquerque, NM)


    India and Pakistan have created sizeable ballistic missile forces and are continuing to develop and enlarge them. These forces can be both stabilizing (e.g., providing a survivable force for deterrence) and destabilizing (e.g., creating strategic asymmetries). Missile forces will be a factor in bilateral relations for the foreseeable future, so restraint is necessary to curtail their destabilizing effects. Such restraint, however, must develop within an atmosphere of low trust. This report presents a set of political and operational options, both unilateral and bilateral, that decreases tensions, helps rebuild the bilateral relationship, and prepares the ground for future steps in structural arms control. Significant steps, which build on precedents and do not require extensive cooperation, are possible despite strained relations. The approach is made up of three distinct phases: (1) tension reduction measures, (2) confidence building measures, and (3) arms control agreements. The goal of the first phase is to initiate unilateral steps that are substantive and decrease tensions, establish missiles as a security topic for bilateral discussion, and set precedents for limited bilateral cooperation. The second phase would build confidence by expanding current bilateral security agreements, formalizing bilateral understandings, and beginning discussion of monitoring procedures. The third phase could include bilateral agreements limiting some characteristics of national missile forces including the cooperative incorporation of monitoring and verification.

  20. Health Management and Service Life for Air Force Missiles


    prediction of performance will be conducted DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited. PA# TBD 24 • Empiricism ...Strategic Missile A&S Approach Overview Empiricism DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited. PA# TBD...Extrapolation Simulated Data 25 • Empiricism cannot always predict future state • Mechanistic method enables enhanced predictions • Mechanistic will not be

  1. Controlling The Spread of Land-Attack Cruise Missiles.


    Debate in the ’New’ European Community," Arms Control Today 23, no. 2 (March 1993): 12. 38 Controlling the Spread of Land-Attack Cruise Missiles...of temperature, pressures or atmosphere in autoclaves or hydro- claves when used for the production of composites or partially processed composites

  2. A robust approach to the missile defence location problem

    Bloemen, A.A.F.; Evers, L.; Barros, A.I.; Monsuur, H.; Wagelmans, A.P.M.


    This paper proposes a model for determining a robust defence strategy against ballistic missile threat. Our approach takes into account a variety of possible future scenarios and different forms of robustness criteria, including the well-known absolute robustness criterion. We consider two problem

  3. White Sands Missile Range 2011 Drinking Water Quality Report


    acerca de su agua potable . Haga que alguien lo traduzca para usted, o hable con alguien que lo entienda. Main Post White Sands Missile Range 2011...standards. What is This Water Quality Report? Este informe contiene informacion importante acerca de su agua potable . Haga que alguien lo traduzca

  4. A Prototype Fibre Optic Gyroscope for Missile Guidance Applications,

    This paper describes the design of a prototype fibre optic gyro, which is intended for missile guidance applications. Important design constraints...beam-splitter. Serrodyne phase ramps are impressed on the light propagating round the fibre optic sensor coil connected to the integrated optics chip

  5. Preliminary Airworthiness Evaluation of the AH-1S (Modernized Cobra) with the HELLFIRE, TOW, and Stinger Missiles Installed


    Evaluation (PAE) was to obtain limited handling qualities and performance data on the AH-IS(MC) with an in-house developed integrated HELLFIRE, TOW, and... integration of the HELLFIRE, TOW and Stinger missile systems for weapons firing. The three evaluations resulted in a logical progression of flight...testing in a cost effective manner. If at any timc the results of an evaluacion were unacceptable, the program could hive been stopped with minimum cost

  6. Analysis of the Dryden Wet Bulb GLobe Temperature Algorithm for White Sands Missile Range

    LaQuay, Ryan Matthew


    In locations where workforce is exposed to high relative humidity and light winds, heat stress is a significant concern. Such is the case at the White Sands Missile Range in New Mexico. Heat stress is depicted by the wet bulb globe temperature, which is the official measurement used by the American Conference of Governmental Industrial Hygienists. The wet bulb globe temperature is measured by an instrument which was designed to be portable and needing routine maintenance. As an alternative form for measuring the wet bulb globe temperature, algorithms have been created to calculate the wet bulb globe temperature from basic meteorological observations. The algorithms are location dependent; therefore a specific algorithm is usually not suitable for multiple locations. Due to climatology similarities, the algorithm developed for use at the Dryden Flight Research Center was applied to data from the White Sands Missile Range. A study was performed that compared a wet bulb globe instrument to data from two Surface Atmospheric Measurement Systems that was applied to the Dryden wet bulb globe temperature algorithm. The period of study was from June to September of2009, with focus being applied from 0900 to 1800, local time. Analysis showed that the algorithm worked well, with a few exceptions. The algorithm becomes less accurate to the measurement when the dew point temperature is over 10 Celsius. Cloud cover also has a significant effect on the measured wet bulb globe temperature. The algorithm does not show red and black heat stress flags well due to shorter time scales of such events. The results of this study show that it is plausible that the Dryden Flight Research wet bulb globe temperature algorithm is compatible with the White Sands Missile Range, except for when there are increased dew point temperatures and cloud cover or precipitation. During such occasions, the wet bulb globe temperature instrument would be the preferred method of measurement. Out of the 30

  7. Identifying Governance Best Practices in Systems-of-Systems Acquisition


    Hellfire missiles and a 30mm cannon (“Marines to Deploy,” 2010). Some kits also carried a ramp-mounted release system for “Gunslinger” precision...factors. The relationship between the acquisition organization and the external environment has a material effect on how acquisition efforts are...Walker, 2010). However, the office transitioned to PEO Missiles and Space in May 2011 as the Army began consolidating its air and missile defense C2

  8. What to Do About That Pack of Wolves at the Door: A Binational Organization and Acquisitions Approach to Homeland Cruise Missile Defense


    Russia’s desire for increased military power to counter US primacy. In order to codify the ways and means to this end, Russian President Vladimir Putin ...5 Russia ... Russia have enjoyed a largely uncontested duopoly on cruise missile employment, these increasingly accurate and lethal systems have proliferated widely

  9. CMDS System Integration and IAMD End-to-End Laboratory

    Federal Laboratory Consortium — The Cruise Missile Defense Systems (CMDS) Project Office is establishing a secure System Integration Laboratory at the AMRDEC. This lab will contain tactical Signal...

  10. Developing Effective Adaptive Missile Crews and Command and Control Teams for Air and Missile Defense Systems


    understanding of team roles and interdependencies; an adaptive network of roles; and a self-learning system—differentiate effective teams from a simple...aggregation of individuals. Effective teams work together toward common goals, learn as a group, and adjust their intra- team roles to reflect changing

  11. Missile Defense: Ballistic Missile Defense System Testing Delays Affect Delivery of Capabilities


    space objects. It also added two capabilities, expected in December 2020, to assess intercepts from space and improve discrimination. Amid this...contributions to this report were LaTonya Miller, Assistant Director, Helena Johnson, Anh Nguyen, Wiktor Niewiadomski, Steven B. Stern, Brian Tittle, Hai Tran

  12. 42nd Annual Armament Systems: Gun and Missile Systems


    Reduced Caliber WARHEAD : • Penetrates building structures such as – Double brick Walls – Clay Walls – Timber and Sand Bags Bunker • 400 g explosives of...Prototype Demo Planned May 07 • LRIP Quantity Planned 3rdQ FY07 SOCOM GPK • Expanded Requirements • ARDEC LRIP underway Sculpted Transparent Armor • Curved

  13. Sliding mode control for an aerodynamic missile based on backstepping design

    Wenjin GU; Hongchao ZHAO; Changpeng PAN


    In order to solve the mismatched uncertainties of a class of nonlinear systems,a control method of sliding mode control (SMC) based on the backstepping design is proposed.It introduces SMC in to the last step of backstepping design to modify the backstepping algorithm.This combination not only enables the generalization of the backstepping design to be applied to more general nonlinear systems,but also makes the SMC method become effective in solving the mismatched uncertainties.The SMC based on the backstepping design is applied to the flight control system design of an aerodynamic missile.The control system is researched through simulation.The simulation results show the effectiveness of the proposed control method.

  14. Computer simulation of absolute and contrast infrared signatures from missile noses

    Tofani, Alessandro


    A computer simulation was performed to obtain an estimate of the infrared radiant intensity and radiative contrast produced by missile noses. The temperature distribution on the nose was computed by taking into account the effects of aerodynamic and solar heating, sky irradiance, and radiative cooling. The corresponding absolute and contrast signatures were obtained by considering the influence of both atmosphere and target geometry, for six target classes, including cruise missiles, tactical ballistic missiles, and air-to-air and surface-to-surface missiles. Both radiant intensity and radiative contrast were computed as a function of missile altitude or missile distance for all targets. A comparison of radiative quantities in the 3- to 5-micron and 8- to 12-micron bands shows that usually the spectral region that gives the strongest signal is not the one that gives the highest contrast.

  15. Peeling the onion: an heuristic overview of hit-to-kill missile defense in the 21st century

    LaCroix, Len; Kurzius, Shelby


    Researchers engaged in the development of infrared detector technologies may well benefit from a broader understanding of their products from the perspective of the end-user. An appreciation of how this technology is to be used by system designers, many of whom possess only a rudimentary understanding of quantum physics, is highly germane. Answers to questions like: "What device technology will be employed," "How will the device be used?" and "What are the impacts on signal-to-noise?" are of critical importance. In this paper, some of the fundamentals of hit-to-kill missile defense technology are examined in a largely non-mathematical context. From its "Star Wars" inception during the Reagan administration, to today"s Missile Defense Agency, the core requirement of missile defense has not changed - find the threat and destroy it before it reaches its destination. This fundamental requirement, while conceptually straightforward, is extraordinarily difficult to satisfy, and is almost exclusively dependent on our ability to detect and designate a relatively small, very fast-moving, room-temperature object, at great distances, and usually in a severe environment of shock and vibration further clouded by error and uncertainty. With an obvious bias toward passive IR detection and associated focal plane array characteristics, the flight of a fictitious interceptor is followed from launch to impact. At various points along the interceptor"s trajectory, a "peel the onion" approach is utilized to expose increasingly detailed layers of behavior, including the eventual release of the kinetic kill vehicle, and its autonomous flight to a body-to-body impact with its target. Various sources of error and their impact on the success of the mission are examined, and an overall understanding of the key features of the infrared seeker and its critical role in missile defense are ultimately developed.

  16. Using GPU convolutions to correct optical distortion in closed-loop real-time missile simulations

    Fronckowiak, Thomas, Jr.


    U.S. Army Aviation and Missile Research, Development and Engineering Center (AMRDEC) has long been a leader in in-band high fidelity scientific scene generation. Recent efforts to harness and exploit the parallel power of the Graphics Processor Unit (GPU), for both graphics and general purpose processing, have been paramount. The emergence of sophisticated image generation software packages, such as the Common Scene Generator (CSG) and the Joint Signature Image Generator (JSIG), have lead to a sharp increase in the performance of digital simulations and signal injection and projection systems in both tactical and strategic programs. One area of missile simulations that benefits from this technology is real-time modeling of optical effects, such as seeker dome distortion, glint, blurring effects, and correcting for facility misalignment and distortion. This paper discusses the on-going research of applying convolution filters to the GPU multi-pass rendering process to compensate for spatial distortion in the optical projection path for synthetic environments.

  17. The Control of Asymmetric Rolling Missiles Based on Improved Trajectory Linearization Control Method

    Huadong Sun


    Full Text Available According to motion characteristic of an asymmetric rolling missile with damage fin, a three-channel controlled model is established. The controller which is used to realize non-linear tracking and decoupling control of the roll and angle motion is introduced based on an improved trajector y linearization control method. The improved method is composed of the classic trajectory linearization control method and a compensation control law. The classic trajectory linearization control method is implemented in the time-scale separation principle. The Lipschitz non-linear state observer systematically obtained by solving the linear matrix inequality approach is provided to estimate state variables and unknown parameters, and then the compensation control law utilizing the estimated unknown parameters improves the TLC method. Simulation experiments show that the adaptive decoupling control ensure tracking performance, and the robustness and accuracy of missile attitude control are ensured under the condition of the system parameters uncertainty, random observation noise and external disturbance caused by damage fin.

  18. Industrial-hygiene-survey report of Martin Marietta Missile and Electronics Group, Orlando, Florida, April 25-27, 1988

    Piacitelli, G.; Votaw, D.M.; Krishnan, E.R.


    A walk-through survey was made of the Martin Marietta Missile and Electronics Group, Orlando, Florida to evaluate worker exposure, protective equipment, and engineering controls used to reduce employee exposures to 2-methoxyethanol (2-ME), 2-methoxyethyl acetate (2-MEA), 2-ethoxyethanol (2-EE), and 2-ethoxyethyl-acetate (2-EEA). The facility was involved in the design, development, and production of missile and electro-optical systems used for aircraft and naval combat weapons programs. Of 38 field samples collected for each of the four target ethylene glycol ethers, only nine samples indicated the presence of any of the compounds and one sample indicated more than one to be present. Some skin protection was afforded by gloves, but the workers wore only ordinary street clothes and no respirators. Peak exposures to 2-EEA in the Hellfire area occurred during the spray painting of missiles. The authors recommend that local exhaust ventilation be installed at work stations in the Patriot area and that impermeable coveralls be given to workers in the Hellfire and Patriot areas.

  19. Informationization Design of New Generation Antitank Missile Weapon%新一代反坦克导弹武器信息化设计

    何亚娟; 孙亚平; 王小永; 王琨


    In order to improve the design level of anti-tank missile weapon in informationization warfare, a method of informative design of indirect aiming anti-tank missile weapon system is proposed. Based on the purpose and criterion of informative design, informative design flow of anti-tank missile weapon is presented. The design content of information system of anti-tank missile weapon is described in detail form 8 aspects. Simulation results show the advantage of this design method such as short design assessment cycle, clear and reasonable design flow, rapid reaction and strong resilience.%为了提高信息化战争中反坦克导弹武器系统的设计水平,提出了一种间瞄反坦克导弹武器系统信息化设计方法,以信息化设计的目的、设计准则为依据,给出了反坦克导弹武器系统信息化设计流程,从8个方面详细论述了反坦克导弹武器系统信息化设计的内容.仿真结果表明:该设计评估周期短,设计流程清晰、合理、反应迅速、抗毁性强.

  20. A Predictive Explicit Guidance Scheme for Ballistic Missiles

    N. Prabhakar


    Full Text Available A new approach to the design of ballistic missile guidance is presented in this paper. The proposed method uses the missile model to predict the likely impact point at every guidance cycle and apply course corrections based on the predicted impact point (PIP deviations. The algorithm also estimates the in-flight thrust variation from nominal and accordingly updates the model to reduce the uncertainty in the prediction of the impact point. The performance of the algorithm is tested through 6-DOF simulation. The simulation results show excellent performance of the proposed guidance scheme in nominal & off nominal cases.Defence Science Journal, 2013, 63(5, pp.456-461, DOI:

  1. Discrete Sliding Mode Control for Hypersonic Cruise Missile

    Yong Hua Fan


    Full Text Available A discrete variable structure control (DVSC with sliding vector is presented to track the velocity and acceleration command for a hypersonic cruise missile. In the design an integrator is augmented to ensure the tracking with zero steady-state errors. Furthermore the sliding surface of acceleration is designed using the error of acceleration and acceleration rate to avoid the singularity of control matrix. A proper power rate reaching law is utilized in this proposal; therefore the state trajectory from any initial point can be driven into the sliding surface. Besides, in order to validate the robustness of controller, the unmolded dynamic and parameter disturbance of the missile are considered. Through simulation the proposed controller demonstrates good performance in tracking velocity and acceleration command.

  2. External Peer Review Report on the Missile Defense Agency Office of Internal Review


    No. DODIG-2015-123 M A Y 1 4 , 2 0 1 5 External Peer Review Report on the Missile Defense Agency Office of Internal Review Report Documentation...3. DATES COVERED 00-00-2015 to 00-00-2015 4. TITLE AND SUBTITLE External Peer Review Report on the Missile Defense Agency Office of Internal... REVIEW SUBJECT: External Peer Review Report on the Missile Defense Agency Office of Internal Review (Report No. DODIG-2015-123) Attached is the

  3. Long-Range Ballistic Missile Defense in Europe


    and another transportable radar to be deployed in a country closer to Iran (which was never publicly identified). Deployment of the GMD European...former Polish President Lech Walesa and former Czech Prime Minister Mirek Topolanek criticized the Obama administration’s policy toward the region.4...the Pacific missile test range, would have been refurbished and transported to a fixed site at a military training base in the Czech Republic. The

  4. 1997 Report to the Congress on Ballistic Missile Defense.


    be modified to the Block IVA TBMD configuration. This area defense program will provide a lower-tier or endoatmospheric intercept capability. The...and ADCP completed operational testing and evaluation at White Sands Missile Range, New Mexico . A successful TMD demonstration was conducted as part of...UOES FY 99) Sea Lower PAC-3 Configuration Three (FUE FY 99) Navy Theater Wide TBMD AEGIS With SM-2 Block IVA (FUE FY 02; UOES Software

  5. The U.S. Navy and the Cuban Missile Crisis


    floor of 1,200 feet, the Guidelines were photographed at Bahia Honda, Havana, La Coloma, Mariel, Matanzas , San Julian, and Cienfuegos. Photography of the...a sharp warning might deter the Soviets from deploying ballistic missiles to Cuba, but unwilling to go public with the evidence 68 available to date...p. 4; "United States Air Force Security Service: Performance During the Cuban Crisis, April- December 1962," n.d., NSACF, pp. 12, 68 ; "Air Force

  6. Open Architecture as an Enabler for FORCEnet Cruise Missile Defense


    battlespace via the FORCEnet information network. Current capability gaps include a lack of common configuration and Fire Control Quality ( FCQ ...connectivity among platforms that is needed to achieve and maintain a robust cruise missile defense. FCQ is defined as data obtained with the sufficient...platform, or a combination of the two. With Fire Control Quality ( FCQ ) threat data from a remote sensor, the remote unit can initiate a launch

  7. Analyzing and designing object-oriented missile simulations with concurrency

    Randorf, Jeffrey Allen


    A software object model for the six degree-of-freedom missile modeling domain is presented. As a precursor, a domain analysis of the missile modeling domain was started, based on the Feature-Oriented Domain Analysis (FODA) technique described by the Software Engineering Institute (SEI). It was subsequently determined the FODA methodology is functionally equivalent to the Object Modeling Technique. The analysis used legacy software documentation and code from the ENDOSIM, KDEC, and TFrames 6-DOF modeling tools, including other technical literature. The SEI Object Connection Architecture (OCA) was the template for designing the object model. Three variants of the OCA were considered---a reference structure, a recursive structure, and a reference structure with augmentation for flight vehicle modeling. The reference OCA design option was chosen for maintaining simplicity while not compromising the expressive power of the OMT model. The missile architecture was then analyzed for potential areas of concurrent computing. It was shown how protected objects could be used for data passing between OCA object managers, allowing concurrent access without changing the OCA reference design intent or structure. The implementation language was the 1995 release of Ada. OCA software components were shown how to be expressed as Ada child packages. While acceleration of several low level and other high operations level are possible on proper hardware, there was a 33% degradation of 4th order Runge-Kutta integrator performance of two simultaneous ordinary differential equations using Ada tasking on a single processor machine. The Defense Department's High Level Architecture was introduced and explained in context with the OCA. It was shown the HLA and OCA were not mutually exclusive architectures, but complimentary. HLA was shown as an interoperability solution, with the OCA as an architectural vehicle for software reuse. Further directions for implementing a 6-DOF missile modeling

  8. Joint Air-to-Surface Standoff Missile (JASSM)


    Retrieval Dev Est - Development Estimate DoD - Department of Defense DSN - Defense Switched Network Econ - Economic Eng - Engineering Est...Missile Reliability (KSA) (CPD para 6.2.8) 4th Lot .91 4th Lot. 91 IOT &E .80 4th Lot .85 IOT &E .95 4th Lot .91 JASSM December 2013 SAR April 16, 2014 17...Acronyms and Abbreviations CPD - Capability Production Document IOT &E - Initial Operational Test and Evaluation KPP - Key Performance Parameter KSA - Key

  9. Quadrennial Defense Review and Ballistic Missile Defense Review


    global defense posture 3 BMDR Highlights • Outlines a strategy and policy framework to – Defend the homeland against limited ballistic missile attack...abroad – Collaborate closely with allies and partners – Pursue a cooperative and tailored global defense posture – Strengthen US civilian in 2010 – QDR and BMDR released February 1, 2010 – Nuclear Posture Review to be released this spring – Space Posture Review, with Director of

  10. Decoupling Control Method Based on Neural Network for Missiles

    ZHAN Li; LUO Xi-shuang; ZHANG Tian-qiao


    In order to make the static state feedback nonlinear decoupling control law for a kind of missile to be easy for implementation in practice, an improvement is discussed. The improvement method is to introduce a BP neural network to approximate the decoupling control laws which are designed for different aerodynamic characteristic points, so a new decoupling control law based on BP neural network is produced after the network training. The simulation results on an example illustrate the approach obtained feasible and effective.

  11. Iranian Ballistic Missile Threat and a Phased, Adaptive Approach for Missile Defense in Europe: Perceptions, Policies and Scenarios


    critical challenges that endanger peace. The institute has offices in New York, Brussels and Moscow. In May 2009, EWI published a report titled...Program: Treading Water in Shark -Infested Seas,” The Heritage Foundation, April 8, 2010, Defense-Program-Treading-Water-in- Shark -Infested-Seas. 129 Ibid. 57 an ICBM until 2020 (using the SM-3 Block

  12. Missiles for Asia The Need for Operational Analysis of U.S. Theater Ballistic Missiles in the Pacific


    attack a skilled TEL force. During the Gulf War, Iraqi TELs were able to continue firing TBMs at Israel , Saudi Arabia, and Bahrain despite a concerted...1, 2015: family-of-stealthy-cruise-missiles-014343/ Binnie, Jeremy, “ Israel , Syria...Secretary of the Army and was conducted within the RAND Arroyo Center’s Strategy, Doctrine, and Resources Program. RAND Arroyo Center, part of the RAND

  13. Õhutõrjerelvade ost võib tuua suure teadusinvesteeringu või tellimuse / Hannes Krause

    Krause, Hannes


    Õhutõrjerelvade riigihankele kutsutud relvatootjad peavad tegema ka pakkumise Eesti teaduskeskustelt või kaitsetööstuselt mitmesaja miljoni krooni eest toodete või teenuste ostmise kohta. Vastuostu põhimõtet rakendatakse Eestis esimest korda, hankel on kutsutud osalema relvatootjad MBDA Missile Systems ja Raytheon Company

  14. Õhutõrjerelvade ost võib tuua suure teadusinvesteeringu või tellimuse / Hannes Krause

    Krause, Hannes


    Õhutõrjerelvade riigihankele kutsutud relvatootjad peavad tegema ka pakkumise Eesti teaduskeskustelt või kaitsetööstuselt mitmesaja miljoni krooni eest toodete või teenuste ostmise kohta. Vastuostu põhimõtet rakendatakse Eestis esimest korda, hankel on kutsutud osalema relvatootjad MBDA Missile Systems ja Raytheon Company

  15. Impact of coupling of lateral movement on missile stability margin%侧向运动耦合对导弹稳定裕度的影响

    郭广明; 罗琴


    各通道间无耦合是工程上导弹控制系统设计的一个基本假设,但随着飞行速度及机动性的提高,导弹各通道间的气动与运动学耦合已不能忽略.以面对称导弹为研究对象,依据小扰动理论,通过建立偏航与滚转通道之间的耦合运动方程,定量分析了通道耦合对导弹控制系统稳定裕度的影响,所得结论可为面对称导弹的工程设计提供参考.%Abstract:No coupling between each channel is a basic assumption of the missile control system design on engineering,but with the flight speed and the mobility increased,aerodynamic and kinematic coupling between each channel of the missile can not be neglected.With plane symmetry missile as the research object,based on small perturbation theory and by establishing some coupled equations of motion between yaw and roll channels,this paper analyzes quantitatively the influence of channel coupling on stability margin.The conclusions can provide a reference for the engineering design of the plane symmetry missile.

  16. Interception Times Model and Simulation of Surface to Air Missile%地空导弹反导作战拦截次数计算模型及仿真

    吕超; 王光辉; 迟玉玮


    Based on studying the process of surface to air missile weapon system intercepting incoming targets, the interception rate model of surface to air missile is built by analyzing the depth of surface to air missile launching zone. The model can calculate the times of surface to air missile weapon system intercepting a single incoming target in the anti-block area. The simulation results reveal how the targets with different characteristics ( speed, altitude, route shortcut) influence the times of surface to air missile weapon system intercepting incoming targets.%在分析地空导弹武器系统拦截来袭目标过程的基础上,通过分析地空导弹发射区纵深建立了地空导弹武器系统可拦截次数模型.利用该模型可计算地空导弹武器系统对单个来袭目标在杀伤区内的拦截次数.仿真结果揭示了地空导弹武器系统在不同目标特性(速度、高度、航路捷径)下对目标的可拦截次数的影响.

  17. The Apache Longbow-Hellfire Missile Test at Yuma Proving Ground: Ecological Risk Assessment for Missile Firing

    Jones, Daniel Steven [ORNL; Efroymson, Rebecca Ann [ORNL; Hargrove, William Walter [ORNL; Suter, Glenn [U.S. Environmental Protection Agency; Pater, Larry [ERDC-CERL


    A multiple stressor risk assessment was conducted at Yuma Proving Ground, Arizona, as a demonstration of the Military Ecological Risk Assessment Framework. The focus was a testing program at Cibola Range, which involved an Apache Longbow helicopter firing Hellfire missiles at moving targets, M60- A1 tanks. This paper describes the ecological risk assessment for the missile launch and detonation. The primary stressor associated with this activity was sound. Other minor stressors included the detonation impact, shrapnel, and fire. Exposure to desert mule deer (Odocoileus hemionus crooki) was quantified using the Army sound contour program BNOISE2, as well as distances from the explosion to deer. Few effects data were available from related studies. Exposure-response models for the characterization of effects consisted of human "disturbance" and hearing damage thresholds in units of C-weighted decibels (sound exposure level) and a distance-based No Observed Adverse Effects Level for moose and cannonfire. The risk characterization used a weight-of-evidence approach and concluded that risk to mule deer behavior from the missile firing was likely for a negligible number of deer, but that no risk to mule deer abundance and reproduction is expected.

  18. Research on Missile Separation Design Techniques%导弹分离设计技术研究

    郭凤美; 余梦伦


    Separation system is an important subsystem of the missile. Its design is one of the keys of the missile system design and also a key process which affects the success of the missile flight. From the view of engineering practice, the design principles, design methods and test methods of separation system is researched and summarized. With respect to stage separation design technique, the requirements of coordination, environmental compatibility for separation system design and a method for separation sequence optimal design are proposed. Also some issues about separation system design which should be paid attention to are pointed out, providing some reference to the engineering design of separation system.%分离系统是导弹的一个重要分系统,分离系统设计是导弹总体设计的关键之一,也是影响导弹飞行成败的关键环节。从工程实际的角度,对分离系统设计原则、设计方法和试验方法等进行研究总结,围绕级间分离设计技术,提出分离系统设计协调性、环境适应性等要求和分离时序优化设计方法,并指出分离系统设计需关注的几个问题,对分离系统工程设计具有一定的参考意义。

  19. 高超声速巡航导弹攻防对抗仿真研究%Study about Hypersonic Cruise Missile Combat Engagement Simulation

    郑祥品; 王志刚


    在当前复杂作战环境下,对导弹武器系统进行攻防对抗研究是非常有必要的.针对攻防对抗这一复杂的动态过程,建立了高超声速巡航导弹攻防对抗仿真模型.并在此模型中,分别给出了结果评判模型、作战环境模型和对抗仿真模型.并根据所建立的仿真模型,计算出高超声速巡航导弹的突防概率.仿真算例结果表明,减小高超声速巡航导弹的雷达反射截面积RCS和增大高超声速巡航导弹的巡航速度是提高其突防效能的重要手段.%During current complex combat conditions, investigation of combat engagement of a new technology missile weapon system is necessary. Aimed at the complex dynamic course of combat engagement, a framework for hypersonic cruise missile combat engagement simulation is established. The combat engagement models of offensive side and defensive side are established in this framework, as well as combat environment models and damage probability of the hypersonic cruise missile are computed. Finally, penetration effectiveness of the hypersonic cruise missile is given. The results show that reducing the RCS and increasing the cruise velocity of the hypersonic cruise missile are two important approaches to improve the penetration effectiveness.

  20. Zero-sum versus nonzero-sum differential game approach to missile guidance

    Trottemant, E.J.; Vermeulen, A.; Weiss, M.


    New developments and improvements on evasive missiles have led to a situation in which the current missile guidance laws have difficulties to intercept maneuvering targets. The nature of the interception problem with 2 non-cooperative players leads to the field of differential games. Recent studies

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

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


    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

  2. Missile Sites, Former missile field for Whiteman., Published in 2005, 1:12000 (1in=1000ft) scale, Whiteman Air Force Base.

    NSGIC GIS Inventory (aka Ramona) — This Missile Sites dataset, published at 1:12000 (1in=1000ft) scale, was produced all or in part from Field Survey/GPS information as of 2005. It is described as...

  3. Simulation Analysis of Wave Effect on Exceeding Water Gesture and Load of Submarine Launched Missile

    Ke Zhao


    Full Text Available In this study, we have a research on wave action on the submarine launched missile water trajectory and gesture angles during the process between launch and exit from water. Infinite water depth plane wave was used as the wave model, mathematics models of missile exceeding water under different wave conditions were established based on ideal potential flow theory. The flow field velocity potential was obtained by solving the Laplace equation, thus can obtain missile surface pressure. Considering free surface effects, simple Green’s function was introduced to solve boundary value problems. Three-dimensional Fortran program and finite software ABAQUS were combined to complete the fluid-structure interaction simulation. The rules that wave level and phases effects on submarine-launched missile were finally obtained, which shows wave affect cannot be neglected. Simulation methods and results of this study have a certain reference value for the submarine-launched missile launching.


    Mu Jianchun; Zhang Tieguang


    Impact tests at both normal and oblique angles of incidence were .conducted on thin mild tubes using a moderate size of 90° conical-nosed missiles. Tne minimum impact speed that generated cracks through the thickness of the wall, termed the speed for rupture, was measured, and various modes of rupture were identified. For a thin tube hit by a missile at a normal angle of obliquity at the speed for rupture, the contact region spreads across the nose of the missile, and the transverse shear deformation is predominant in the final failure process. If the angle of obliquity is 30°, the missile pierces a hole through the wall of the tube. At the speed for rupture, the kinetic energy of the missile for oblique angle 30° is only about 45 % that required for plugging at a normal angle of obliquity.

  5. Designing Integrated Fuzzy Guidance Law for Aerodynamic Homing Missiles Using Genetic Algorithms

    Omar, Hanafy M.

    The Fuzzy logic controller (FLC) is well-known for robustness to parameter variations and ability to reject noise. However, its design requires definition of many parameters. This work proposes a systematic and simple procedure to develop an integrated fuzzy-based guidance law which consists of three FLC. Each is activated in a region of the interception. Another fuzzy-based switching system is introduced to allow smooth transition between these controllers. The parameters of all the fuzzy controllers, which include the distribution of the membership functions and the rules, are obtained simply by observing the function of each controller. Furthermore, these parameters are tuned by genetic algorithms by solving an optimization problem to minimize the interception time, missile acceleration commands, and miss distance. The simulation results show that the proposed procedure can generate a guidance law with satisfactory performance.

  6. Adaptive Sliding Mode BTT Autopilot for Cruise Missiles with Variable-Swept Wings

    Wei-Ming Li; Rui-Sheng Sun; Hong-Yang Bai; Peng-Yun Liu


    In this paper, an adaptive sliding mode method was proposed for BTT autopilot of cruise missiles with variable-swept wings. To realize the whole state feedback, the roll angle, normal overloads and angular rates were considered as state variables of the autopilot, and a parametric sliding mode controller was designed via feedback linearization. A novel parametric adaptation law was put forward to estimate the nonlinear time-varying parameter perturbations in real time based on Lyapunov stability theory. A sliding mode boundary layer theory was adopted to smooth the discontinuity of control variables and eliminate the control chattering. The simulation was presented for the roll angle and overload commands tracking in different configuration schemes. The results indicated that the controlled system has robust dynamic tracking performance in condition of the large-scale aerodynamic parametric variety resulted from variable-swept wings.

  7. Ballistic missile precession frequency extraction by spectrogram's texture

    Wu, Longlong; Xu, Shiyou; Li, Gang; Chen, Zengping


    In order to extract precession frequency, an crucial parameter in ballistic target recognition, which reflected the kinematical characteristics as well as structural and mass distribution features, we developed a dynamic RCS signal model for a conical ballistic missile warhead, with a log-norm multiplicative noise, substituting the familiar additive noise, derived formulas of micro-Doppler induced by precession motion, and analyzed time-varying micro-Doppler features utilizing time-frequency transforms, extracted precession frequency by measuring the spectrogram's texture, verified them by computer simulation studies. Simulation demonstrates the excellent performance of the method proposed in extracting the precession frequency, especially in the case of low SNR.

  8. Renewable Energy Opportunities at White Sands Missile Range, New Mexico

    Chvala, William D.; Solana, Amy E.; States, Jennifer C.; Warwick, William M.; Weimar, Mark R.; Dixon, Douglas R.


    The document provides an overview of renewable resource potential at White Sands Missile Range (WSMR) based primarily upon analysis of secondary data sources supplemented with limited on-site evaluations. The effort was funded by the U.S. Army Installation Management Command (IMCOM) as follow-on to the 2005 DoD Renewable Energy Assessment. This effort focuses on grid-connected generation of electricity from renewable energy sources and also ground source heat pumps (GSHPs) for heating and cooling buildings, as directed by IMCOM.

  9. Minimum Ballistic Factor Problem of Slender Axial Symmetric Missiles

    V. B. Tawakley


    Full Text Available The problem of determining the geometry of slender, axisymmetric missiles of minimum ballistic factor in hypersonic flow has been solved via the calculus of variations under the assumptions that the flow is Newtonian and the surface averaged skin-friction coefficient is constant. The study has been made for conditions of given length and diameter, given diameter and surfacearea, and given surface area and length. The earlier investigations/sup 8/ where only regular shapes were determined has been extended to cover those class of bodies which consist of regular shapes followed or preceded by zero slope shapes.

  10. Cost Effective Regional Ballistic Missile Defense


    Defense Agency, Huntsville, AL; Chief, Materiel Fielding Team ( Automotive ), Materiel Fielding and Training Directorate, TACOM Life Cycle Management...Executive Office Ground Combat Systems, Detroit Arsenal, Michigan; Training With Industry Officer, EADS North America, Huntsville, Alabama; and Product...identify the ways and means to counter this imbalance or risk future erosion of our military effectiveness, diminished allied confidence, and unnecessarily

  11. Environmental Assessment for Conventional Strike Missile Demonstration


    transmitters; maximum 900 Watt radio frequency pulse Power Up to five lithium ion and lithium thionyl chloride batteries , each weighing between 1 and 30 lb...coolant, oil, and hydraulic fluid. Additional lead-acid or lithium batteries on the barges would power control systems and sensors. No other fuels...and other marine species. If any of the PDV lithium battery electrolytes enter the water, wave action and currents would rapidly dilute the

  12. Air-to-Air Missile Vector Scoring


    Authorized licensed use limited to: Air Force Institute of Technology. Downloaded on April 19,2010 at 19:40:39 UTC from IEEE Xplore . Restrictions apply...all three cases the azimuth angle estimation is based on two receive antennas and the monopulse technique. 1-4244-1 539-X/08/$25.00 ©2008 IEEE ...December 2005. 4. Blackman, Samuel. “Multiple Hypothesis Tracking for Multiple Target Tracking”. IEEE Aerospace and Electronic Systems Magazine, 19:5–18

  13. Improvement of Intercept Probability Algorithm for Anti-ship Missile Based on Search Theory%Improvement of Intercept Probability Algorithm for Anti-ship Missile Based on Search Theory

    汪新刚; 谢晓方; 李雪


    Traditional intercept probability model has some drawbacks and can not meet the demands of command and control system. Aiming at this problem, a new calculation method based on search theory, terminal control area distribution function of antl-ship missile, target distribution function and missile's radar scan feature is proposed, Under the condition of common target distribution, an intercept probability model for present point attacking is determined. The simulation verifies its effectiveness and establishes the selecting model for aiming point when enemy ships evade in high speed.

  14. 导弹攻防对抗仿真中偶极子云建模和仿真%Modeling and Simulation of Chaff Cloud in Missile Attack-Defense Confrontation

    颜如祥; 宦国杨; 方冰


    Principles of chaff clouds thrown by missiles are analyzed in the simulation of missile attack-defense confrontation. The flight path model of chaff clouds is built and effects of chaff clouds are researched. The modeling and simulation technologies give a guidance for building simulation system of the missile attack-defense confrontation.%从导弹攻防对抗仿真角度分析了弹道导弹抛撒偶极子云的工作原理,继而建立了偶极子云飞行轨迹模型。同时研究了偶极子云的作用效果。该建模和仿真技术对建立导弹攻防对抗仿真系统具有指导意义。

  15. Missile-Borne SAR Raw Signal Simulation for Maneuvering Target

    Weijie Xia


    Full Text Available SAR raw signal simulation under the case of maneuver and high-speed has been a challenging and urgent work recently. In this paper, a new method based on one-dimensional fast Fourier transform (1DFFT algorithm is presented for raw signal simulation of maneuvering target for missile-borne SAR. Firstly, SAR time-domain raw signal model is given and an effective Range Frequency Azimuth Time (RFAT algorithm based on 1DFFT is derived. In this algorithm, the “Stop and Go” (SaG model is adopted and the wide radar scattering characteristic of target is taken into account. Furthermore, the “Inner Pulse Motion” (IPM model is employed to deal with high-speed case. This new RFAT method can handle the maneuvering cases, high-speed cases, and bistatic radar cases, which are all possible in the missile-borne SAR. Besides, this raw signal simulation adopts the electromagnetic scattering calculation so that we do not need a scattering rate distribution map as the simulation input. Thus, the multiple electromagnetic reflections can be considered. Simulation examples prove the effectiveness of our method.

  16. AIM-120 Advanced Medium Range Air-to-Air Missile (AMRAAM)


    Selected Acquisition Report (SAR) RCS: DD-A&T(Q&A)823-185 AIM-120 Advanced Medium Range Air-to-Air Missile (AMRAAM) As of FY 2017 President’s...17, 2013 Program Information Program Name AIM-120 Advanced Medium Range Air-to-Air Missile (AMRAAM) DoD Component Air Force Joint Participants...December 2015 SAR March 23, 2016 16:04:24 UNCLASSIFIED 5 Mission and Description The Advanced Medium Range Air-to-Air Missile (AMRAAM) AIM-120

  17. Analysis Of The Infrared Emission Due To Aerodynamic Heating Of Missile Domes

    Tofani, Alessandro


    A computer simulation of head-on infrared emission from missile noses has been performed. Both cruise missiles and tactical ballistic missiles were considered; results indicate a strong dependence of the emitted radiation on physical and geometrical properties of aerodynamic surfaces, flow character in the boundary layer and atmospheric characteristics. The model allows to give an order-of-magnitude estimate of radiant intensity in the 8-12 μm and 3-5 μm spectral bands and to determine their relative merits as far as the target detection is concerned.

  18. Guide for Transitioning Army Missile Systems From Development to Production.


    WIdea" -tif tesi ~pelss..wih ol as prgdois 9$ qwsltv,~pgst~o ow up$u)~ wih.. h risk 0l be atpre~edi It should Include participation by individuial f srim... Paso PrT40 404"ie V w bility to mst a uflitary contnency. Theyv ar nonIm2 b3s type qW$’esst, W$ are "pos to jwlt In W., Wot4.3 P0W f duo tion. 2boy W

  19. Environmental Impact Statement: Peacekeeper Missile System Deactivation and Dismantlement


    goldenrod (Solidago sp.), and death camus (Zygadenus elegans). Shrub species occur on rocky slopes at higher elevations within the deployment area...Federal Lands Highway Projects Office, Lakewood, CO. November. Thuman, Albert and Richard Miller, 1976. Secrets of Noise Control. 2nd ed. Atlanta

  20. Occupational Survey Report. Missile Systems Maintenance AFSC 411XOA



  1. A Computer Aided Statistical Covariance Program for Missile System Analysis


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  2. 46th Annual Gun and Missile Systems Conference and Exhibition


    OFAC Regulations • Barclays (2010): $474 million • Lloyds (2009): $350 million • Credit Suisse (2009): $536 million • ANZ (2009...with the correct credit card or form of payment, as a $25 fee will be applied to registrations switching credit cards or forms of payment...Any U.S. Government employee paying with U.S. Government check or credit card will be tax exempt (with supporting documentation as required by some

  3. Future Operational Scenario for Antitank Guided Missile Systems

    A.P.J. Abdul Kalam


    Full Text Available Discusses latest type of explosive reactive armour (ERA and active armour for defeating ERA that contains a slab of relatively less sensitive explosive sandwiched between two metal plates and attached to the main armour to be protected.

  4. Missile Systems Maintenance, AFSC 411XOB/C.



  5. Space and Missile Systems Center Standard: Software Development


    Ergonomic requirements for office work with visual display terminals (VDTs) – Part 11, Guidance on usability, ISO 9241-11:1998, 15 March 1998. McGarry...of tests to determine whether those criteria have been met. Source: Adapted from (IEEE 610.12) Test activity suspension. A temporary interruption

  6. Joint FCRC Utah-Nevada MX Missile System.


    248. 1 41300 ECPT LEASE 2,100.00 2.282.76 182.7 41400 ECP1 EXPENSE 168.90 168.9 41500 TELEPFCNE PEG 1,050.00 1,451.66 401.6 41600 TELEPFCNE L G... deta ii ed iist-inj of[ pastJ work erfrdprob.l~eiii en- csI- (Ied, futr wol ln /l and e. VIC>; Lpe 1 are dHiscus.,eclkio A deCAa ileo] ni i.-i rt iye

  7. Robust and Adaptive Guidance and Control Laws for Missile Systems


    Englewood Cliffs, NJ: Prentice-Hall, 1988. positive real lemma are developed in Sections II and HI using optimal [111 R. S. Varga . Matrix Iterative...testing certain Math, 1987. square matrices for positive definiteness related to the generalized [14] F. Alvarado , "Parallel solution of transient

  8. Advanced Technology Demonstrator for IR Imaging Missile Warning System


    13 Figure 9: Paraglider ...but also mountains, towers, other flying platform and e.g. paratroopers/ paragliders . Some of these objects have no plume, this excludes UV-devices for...Figure 9: Paraglider - The device also has to have the ability to recognize these a.m. objects, so it has to be an imaging device with intelligent image

  9. Missile Liquid Propellant Systems Maintenance. AFS 445X1.


    Ic w. z ’.7 -CX c 666. 0 at be1 I. t- .0G z *U U : O WAC .0 a -1 atft I I6. I 1 1 :6 ki IA -K 0 64 C’ 6*9 td . cc of Liw2 0 I ft .m W" , z, P2 iz w an...NW & ; -- ’e o -h - P 0x 3 1.. 1e -&1- a a- at4 . ,, 0 = S.c U’, W L42-9’I.4 w -29 2 l -"j0I la. ’*12, 04b0-- I 2l -c w aIS z j 0 1-: 0KK Z I IN hi

  10. Competition Among Near-Substitutable Systems


    Standoff Land Attack Missile-Expanded Response 11 September 2012 10  Similar GPS midcourse /IR terminal guidance ; both missiles use the same...1 The Limits of Competition in Defense Acquisition Defense Acquisition University Research Symposium, September 2012 Keywords Weapon System...distribution unlimited 13. SUPPLEMENTARY NOTES Presented at The Limits of Competition in Defense Acquisition, Defense Acquisition University Research

  11. Impact angle constrained three-dimensional integrated guidance and control for STT missile in the presence of input saturation.

    Wang, Sen; Wang, Weihong; Xiong, Shaofeng


    Considering a class of skid-to-turn (STT) missile with fixed target and constrained terminal impact angles, a novel three-dimensional (3D) integrated guidance and control (IGC) scheme is proposed in this paper. Based on coriolis theorem, the fully nonlinear IGC model without the assumption that the missile flies heading to the target at initial time is established in the three-dimensional space. For this strict-feedback form of multi-variable system, dynamic surface control algorithm is implemented combining with extended observer (ESO) to complete the preliminary design. Then, in order to deal with the problems of the input constraints, a hyperbolic tangent function is introduced to approximate the saturation function and auxiliary system including a Nussbaum function established to compensate for the approximation error. The stability of the closed-loop system is proven based on Lyapunov theory. Numerical simulations results show that the proposed integrated guidance and control algorithm can ensure the accuracy of target interception with initial alignment angle deviation and the input saturation is suppressed with smooth deflection curves. Copyright © 2016 ISA. Published by Elsevier Ltd. All rights reserved.

  12. Next Generation Operational Control System (OCX)


    UNCLASSIFIED 5 Mission and Description The Global Positioning System (GPS) is a space-based positioning, navigation, and timing distribution system, which...operates through weather and electromagnetic environments (jamming, spoofing, etc.). GPS supports both civil and military users in air, space, sea, and...a complex incentive structure; and high government personnel turnover. The Program Office and Raytheon have worked to address the root causes

  13. Assessment of equipment operation network capability based on the anti-missile operation loops%基于反导作战环的装备作战网络能力评估

    芦荻; 商慧琳


    考虑到以往装备体系的研究方法忽略了装备之间的配合关系,基于网络科学思想,建立反导作战网络模型。阐明了反导作战能力生成机制,并基于此提出了反导装备体系作战网络能力评估方法,最后通过示例对所提出的建模和评估方法进行展示,证明了该方法的可行性和有效性。%Considering the interactions between equipment that have been neglected in the earlier research on equipment system-of-systems, an exploration based on networks science is conducted. The paper presents a model of anti-missile operation network and illustrates the generation progress of anti-missile operation capability, based on which a capability assessment method of anti-missile equipment system-of-systems is examined. An example of anti-missile operation network is demonstrated to illuminate the feasibility and validity of the proposed method.

  14. A Game-Theoretic History of the Cuban Missile Crisis

    Frank C. Zagare


    Full Text Available This study surveys and evaluates previous attempts to use game theory to explain the strategic dynamic of the Cuban missile crisis, including, but not limited to, explanations developed in the style of Thomas Schelling, Nigel Howard and Steven Brams. All of the explanations were judged to be either incomplete or deficient in some way. Schelling’s explanation is both empirically and theoretically inconsistent with the consensus interpretation of the crisis; Howard’s with the contemporary understanding of rational strategic behavior; and Brams’ with the full sweep of the events that define the crisis. The broad outlines of a more general explanation that addresses all of the foundational questions associated with the crisis within the confines of a single, integrated, game-theoretic model with incomplete information are laid out.

  15. Ballistic Missile Warhead Recognition based on Micro-Doppler Frequency

    Sun Hui-Xia


    Full Text Available To elucidate the spinning-precession signatures of ballistic warhead, the model of spinning precessionfor ballistic missile warhead is established and the mathematics of micro-Doppler signatures caused by spinning-precession is derived. Then the micro-Doppler features are analysed using high-resolution time-frequencytransform, and the model predictions match the experimental data well. Based on  different mass of warheadsand decoys, the feature, which can reflect the mass of the targets, is extracted from the time-frequency plane,proving a new method for recognising warheads and discriminating these from decoys. Finally the validityof the feature extracted in this study is verified by computer simulations even with low signal-to-noise ratio.Defence Science Journal, 2008, 58(6, pp.705-709, DOI:

  16. Ogive Nose Hard Missile Penetrating Concrete Slab Numerical Simulation Approach

    Qadir Bux


    Full Text Available Great demand exists for more efficient design to protect delicate and serious structures such as nuclear plants, Power plants, Weapon Industries, weapons storage places, water retaining structures, & etc, against impact of kinetic missiles generated both accidentally and deliberately such as dynamic loading, incident occurs in nuclear plants, terrorist attack, Natural disasters like tsunami and etc., in various impact and blast scenarios for both civilian and military activities. In many cases, projectiles can be treated as rigid bodies when their damage and erosion are not severe. Due to the intricacy of the local impact damages, investigations are generally based on experimental data. Conclusions of the experimental observations are then used to guide engineering models. Local damages studies normally fall into three categories, i.e. empirical formulae based on data fitting, idealised analytical models based on physic laws and numerical simulations based on computational mechanics and material models. In the present study, 2D asymmetrical numerical simulation have done on concrete slab against the impact of  ogive nose hard missile of 26.90mm and 76.20mm diameter with CRH ratio 2.0 and 6.0 respectively, for penetration by using Concrete Damaged Plasticity Model, and ABAQUS/Explicit dynamic analysis in ABAQUS. It is found that the strains/stresses are induced in the concrete slab and a very nicely propagation of the stresses inside the  concrete slab in the form of waves, which is a clear indication for vibrations of the concrete. The lack of failure criterion in concrete damaged plasticity model does not allow the removal of elements during the analyses. This means that spalling, scabbing, and perforation cannot be modelled with the Concrete Damage Plasticity Model. The penetration depth results shows that the deeper penetration requires higher critical impact kinetic energies, and comparison shows the simulation results are more accurate

  17. Technologies for Future Precision Strike Missile Systems (les Technologies des futurs systemes de missiles pour frappe de precision)


    guidage de précision et de guidage optimal. Les technologies des capteurs GPS/INS avec une évaluation de l’intégration à coût modéré du matériel...technologies des autodirecteurs avec une évaluation des autodirecteurs actifs et passifs à ondes millimétriques et infrarouges. Les technologies

  18. Robust Graded Sliding Mode Tracking Control for Low Speed Spinning Ballistic Missiles

    ZHOU Jun; WANG Zhi; ZHOU Feng-qi


    The nonlinear dynamic model of spinning ballistic missiles is established during the first boosting phase of the missile. Based on the conventional backstepping sliding mode control and the assumption of a two time-scale separation of missile dynamics, a graded sliding mode controller is designed with two sub-sliding surfaces which have invariability to external disturbances and parameter perturbations, and a matrix which comprises three first order low pass filters is introduced to prevent "explosion of terms". Owing to the upper bounds of the uncertainties are difficult to obtain in advance,adaptive laws are introduced to estimate the values of the uncertainties in real-time. Eventually, the numerical simulation results given to show the proposed controller can ensure the steady flight of missiles.

  19. Radar signal analysis of ballistic missile with micro-motion based on time-frequency distribution

    Wang, Jianming; Liu, Lihua; Yu, Hua


    The micro-motion of ballistic missile targets induces micro-Doppler modulation on the radar return signal, which is a unique feature for the warhead discrimination during flight. In order to extract the micro-Doppler feature of ballistic missile targets, time-frequency analysis is employed to process the micro-Doppler modulated time-varying radar signal. The images of time-frequency distribution (TFD) reveal the micro-Doppler modulation characteristic very well. However, there are many existing time-frequency analysis methods to generate the time-frequency distribution images, including the short-time Fourier transform (STFT), Wigner distribution (WD) and Cohen class distribution, etc. Under the background of ballistic missile defence, the paper aims at working out an effective time-frequency analysis method for ballistic missile warhead discrimination from the decoys.

  20. A Terminal Guidance Law Based on Motion Camouflage Strategy of Air-to-Ground Missiles

    Chang-sheng Gao


    Full Text Available A guidance law for attacking ground target based on motion camouflage strategy is proposed in this paper. According to the relative position between missile and target, the dual second-order dynamics model is derived. The missile guidance condition is given by analyzing the characteristic of motion camouflage strategy. Then, the terminal guidance law is derived by using the relative motion of missile and target and the guidance condition. In the process of derivation, the three-dimensional guidance law could be designed in a two-dimensional plane and the difficulty of guidance law design is reduced. A two-dimensional guidance law for three-dimensional space is derived by bringing the estimation for target maneuver. Finally, simulation for the proposed guidance law is taken and compared with pure proportional navigation. The simulation results demonstrate that the proposed guidance law can be applied to air-to-ground missiles.

  1. Missile injuries to the external genitalia: a five year experience in Maiduguri, North Eastern Nigeria

    Hassan Mohammed Dogo


    Conclusions: Genital missile injuries are on the increase with militarization of civilian population. Goals of treatment still remain cosmesis, preservation of erectile and voiding function. [Int J Res Med Sci 2016; 4(7.000: 2964-2966

  2. Seeing 2020: America’s New Vision for Integrated Air and Missile Defense


    the U.S. Army Air Corps began Operation Crossbow, the Anglo-American bombing campaign against Adolf Hitler’s V-1 and V-2 missile forces and of war and its weapons matured, the development of improved propulsion, guidance, and payloads in guns, artillery, rockets, mortars , aircraft...range of threats to include short- and intermediate-range ballistic missiles, bombers, and tactical weapons such as artillery, rockets, and mortars

  3. Six-Degree-of-Freedom Digital Simulations for Missile Guidance and Control

    Yongjie Xu


    Full Text Available Six-degree-of-freedom ballistic trajectory model can be used to verify design indicators, performance parameters, and correctness so they have been put forward in the missile argumentation and design process. Mathematical simulation is the basis of late semiphysical simulation and field firing testing, and it can greatly reduce the field shooting test time, which shortens the missile test cycle and so reduces costs.

  4. Defense Science Board Task Force on Defense Strategies for Advanced Ballistic and Cruise Missile Threats


    REPORT OF THE DEFENSE SCIENCE BOARD TASK FORCE ON Defense Strategies for Advanced Ballistic and Cruise Missile Threats January 2017 Office of... Science Board (DSB). The DSB is a Federal Advisory Committee established to provide independent advice to the Secretary of Defense. Statements, opinions... Science Board Task Force on Defense Strategies for Advanced Ballistic and Cruise Missile Threats completed its information-gathering in February 2016

  5. The Impact on Strategic Stability of Ballistic Missile Defense in Eastern Europe


    the final chapter of the Eastern European missile defense saga has yet to be written, this study can contribute to the field of knowledge even at...Canada at the USSR Academy of Sciences. This publication is invaluable in examining how strategic stability was viewed at the twilight of the Cold...the Czech Republic are carrying out deliberations and how Russia is reacting to each particular new wrinkle in the missile defense saga ; and

  6. A Strategic Conversation about National Missile Defense (Strategic Studies Quarterly, Winter 2008)


    they were “producing missiles like sausages .” These quotes, and the overall tone of Reagan’s speech, indicate the specific historical context in this article . LeFevre.indd 108 10/30/08 1:18:22 PM A Strategic Conversation about National Missile Defense Strategic  Studies article /0,9171,923443,00.html. 3. National Intelligence Council, “Iran: Nuclear Intentions and Capabilities,” National Intel- ligence

  7. Robust sliding mode control with ESO for dual-control missile

    Wei Shang; Shengjing Tang; Jie Guo; Yueyue Ma; Yuhang Yun


    This paper proposes a novel composite dual-control by combing the integral sliding mode control (ISMC) method based on the finite time convergence theory with extended state observer (ESO) for a tracking problem of a missile with tail fins and reaction-jet control system (RCS). First, the ISMC method based on finite time convergence is utilized to design the control law of tail fins and the pulse control of RCS for the dual-control system, ensuring the system with rapid response and high accuracy of tracking. Then, ESO is employed for the estimation of aerodynamic disturbances influenced by the airflow of thruster jets. With the characteristic of high accuracy estimation of ESO, the chattering free tracking performance of the attack angle command and the robustness of the control law are achieved. Meanwhile, the stability of the dual-control system is analyzed based on finite time convergence stability theorem and Lyapunov’s theorem. Final y, numerical sim-ulations demonstrate the effectiveness of the proposed design.

  8. Cooperative Monitoring Center Occasional Paper/9: De-Alerting Strategic Ballistic Missiles

    Connell, Leonard W.; Edenburn, Michael W.; Fraley, Stanley K.; Trost, Lawrence C.


    This paper presents a framework for evaluating the technical merits of strategic ballistic missile de-alerting measures, and it uses the framework to evaluate a variety of possible measures for silo-based, land-mobile, and submarine-based missiles. De-alerting measures are defined for the purpose of this paper as reversible actions taken to increase the time or effort required to launch a strategic ballistic missile. The paper does not assess the desirability of pursuing a de-alerting program. Such an assessment is highly context dependent. The paper postulates that if de-alerting is desirable and is used as an arms control mechanism, de-alerting measures should satisfy specific cirteria relating to force security, practicality, effectiveness, significant delay, and verifiability. Silo-launched missiles lend themselves most readily to de-alerting verification, because communications necessary for monitoring do not increase the vulnerabilty of the weapons by a significant amount. Land-mobile missile de-alerting measures would be more challenging to verify, because monitoring measures that disclose the launcher's location would potentially increase their vulnerability. Submarine-launched missile de-alerting measures would be extremely challlenging if not impossible to monitor without increasing the submarine's vulnerability.

  9. 基于TOPSIS的战区高层反导威胁评估%Threat Assessment of the High Altitude Area Ballistic Missile Defense Based on TOPSIS

    范学渊; 邢清华; 黄沛; 王小光


    Firstly, the characteristics of the high altitude area ballistic missile defense' s threat assessment are analyzed. Then the threat assessment's model index system is set up and quantitated, such as launch position of tactical ballistic missile (TBM) , forecasting impact point, range and so on. Finally, the theory of technique for order preference by similarity to idea solution (TOPSIS) based on weight of entropy is used to compute the model. The result shows that the threat assessment' s model and the algorithm is effective and useful for developing the battle manage of the high altitude area ballistic missile defense ' s.%在分析战区高层反导威胁评估特点的基础上,建立了以来袭TBM发射点、预测落点、射程等为核心的战区高层反导威胁评估模型指标体系并进行了相应的量化,然后利用基于熵值权重确定的TOPSIS理论对模型进行求解.通过实例证明所提出的战区高层反导威胁评估模型和算法的有效性,对研究美军的战区高层反导武器系统具有一定的借鉴意义.

  10. Surgical treatment of tibial nonunion after wounding by high velocity missile and external fixators: A case report


    Introduction. The missiles of modern firearms can cause severe fractures of the extremity. High velocity missile fractures of the tibia are characterized by massive tissue destruction and primary contamination with polymorphic bacteria. Treatment of these fractures is often complicated by delayed healing, poor position healing, nonhealing and bone tissue infection. Case Outline. We present the management of tibial nonunion after wounding by high velocity missile and primary treatment by...

  11. Fast pattern recognizer for autonomous target recognition and tracking for advanced naval attack missiles

    Hastbacka, Al


    A FPR System under development for the Naval Air Warfare Center, China Lake, CA is funded under a SBIR, Phase II contract as an automatic target recognizer and tracker candidate for Navy fast-reaction, subsonic and supersonic, stand-off weapons. The FPR will autonomously detect, identify, correlate, and track complex surface ship and land based targets in hostile, high-clutter environments in real time. The novel FPR system is proven technology that uses an electronic implementation analogous to an optical correlator system, where the Fourier transform of the incoming image is compared against known target images stored as matched filter templates. FPR demonstrations show that unambiguous target identification is achievable in a ninety-five percent fog obscuration for over ninety-percent of target images tested. The FPR technology employs an acoustic dispersive delay line (DDL) to achieve ultra-fast image correlations in 90 microseconds or 11,000 correlations per second. The massively scalable FPR design is capable of achieving processing speeds of an order of magnitude faster using available ASIC technology. Key benefits of the FPR are dramatically reduced power, size, weight, and cost with increased durability, robustness, and performance - which makes the FPR ideal for onboard missile applications.

  12. Real-time simulation of missile efflux plasma based on Vega Prime & OpenGL%Vega Prime结合OpenGL的导弹尾焰实时模拟

    李威; 杨峰; 程咏梅; 杨衍波


    It researches missile operational system simulation experiment, in view of the problem that when using Vega Prime' s particle system module for the simulation of missile efflux plasma which is moving with high speed, the particles are discrete that impact the simulation visualization effect. In order to solve the missile efflux plasma simulation problem, it proposes the solution that using Vega Prime together with OpenGL. It models the missile efflux plasma based on the particle system principle, applies OpenGL into Vega Prime according to the event issued subscription mechanism of Vega Prime. The efflux plasma that simulated by the proposed method is shape lifelike and sporty. It meets the demands of the instantaneity and authenticity in the simulation and solves the defect of simulating missile efflux plasma by Vega Prime.%研究基于Vega Prime的导弹作战系统仿真实验,针对使用Vega Prime的粒子特效模拟高速飞行导弹尾焰会出现尾焰不连续而影响仿真可视化效果的问题,提出将Vega Prime与OpenGL相结合的方法.基于粒子系统基本原理,对导弹尾焰进行建模;依据Vega Prime的事件发布订阅机制将OpenGL引入到Vega Prime中.模拟的尾焰形态逼真,动感十足,满足仿真实时性与真实性要求,解决了Vega Prime模拟导弹尾焰存在缺陷的问题.

  13. Adjoint analysis of mixed continuous/discrete systems in simulink

    Bucco, D.; Weiss, M.


    The adjoint simulation method is a well established and efficient tool for gaining insight and understanding of key parameters affecting the behaviour and performance of a guided missile homing system. Traditionally, the method has been employed by various missile companies during the preliminary an

  14. Adjoint analysis of mixed continuous/discrete systems in simulink

    Bucco, D.; Weiss, M.


    The adjoint simulation method is a well established and efficient tool for gaining insight and understanding of key parameters affecting the behaviour and performance of a guided missile homing system. Traditionally, the method has been employed by various missile companies during the preliminary

  15. Time-cooperative distributed guidance law design for multi-missiles%多导弹时间协同分布式导引律设计

    马国欣; 张友安


    To achieve the cooperative attack against a same target for multi-missiles, an approach to design the time-cooperative distributed guidance law is proposed, which is applicable to the situation with or without angular constraint. With each missile subsystem as a homogeneous network node, the time-cooperative guidance model for multi-missiles is built, which takes each missile’s time-to-go plus designated bias as the outputs. The distributed control scheme of the system is designed to reduce the difference among the outputs of subsystems. The communication topology condition to guarantee the time-cooperativeness of multi-missiles is given by analyzing the features of the homing guidance of missile with consideration of the convergence condition of the general cooperative control system. Finally, simulation results show the effectiveness of the proposed approach.%为了实现多导弹协同攻击同一目标,提出一种时间协同分布式导引律设计方法,该方法对于无角度约束和有角度约束的情况均适用。首先,以各导弹子系统作为网络同构节点建立了多导弹时间协同制导模型,该模型以各导弹剩余时间信息附加预定偏置量为输出;然后,以调整子系统间输出误差为目的,设计了系统的分布式控制方案,并结合一般协同控制系统的收敛性条件,分析了导弹寻的导引的特殊性,给出了保证多导弹时间协同的通信拓扑条件;最后,通过仿真结果验证了所提出方法的有效性。

  16. 美军舰空导弹协同制导技术及其能力分析%Analysis of Cooperative Guidance Technology of US Navy Ship-to-Air Missile and Its Capability

    王国田; 王航宁; 石章松


    介绍了美军舰空导弹协同制导的发展概况。阐述了标准6导弹的协同制导作战流程,分析了舰空导弹协同制导技术的能力,以及实现协同制导的关键技术。协同制导为舰空导弹实现超视距拦截创造了条件,可提高系统的作战效能和可靠性。%The development survey of US navy ship-to-air missiles cooperative guidance was introduced in this paper.The cooperative guidance operational flowchart of SM-6 missile was presented.The capabilities of the cooperative guidance technology for ship-to-air missile and main key technologies for its implement were analyzed.The cooperative guidance would create the conditions for beyond-visual-range interception of ship-to-air missile,which could improve the combat effectiveness and reliability of the weapon system.

  17. China and ballistic missile defense: 1955 to 2002 and beyond

    Brad, Roberts


    China's opposition to U.S. ballistic missile defense was forcefully articulated officially and unofficially between 1991 and 2001. Vociferous opposition gave way to near silence following U.S. ABM Treaty withdrawal, raising a question about precisely whether and how China will respond to future U.S. deployments in both the political and military-operational realms. To gauge likely future responses, it is useful to put the experience of the 1991-2001 period into historical context. China's attitudes toward BMD have passed through a series of distinct phases since the beginning of the nuclear era, as China has been concerned alternately with the problems of strategic defense by both the Soviet Union and United States (and others) around its periphery. Throughout this era it has also pursued its own strategic defense capabilities. There are important elements of continuity in China's attitudes concerns about the viability of its own force and about strategic stability. These suggest the likelihood of significant responses to U.S. BMD even in the absence of sharp rhetoric. (author)

  18. Missile Design PC Trap: An Improved PC Trap for Tactical Missile Design


    0000 TPZ =-.8229 TVEL = 584.8 APX =-3.487 APY =-3.487 APZ =-1.646 AVEL = 510.5 MPX =-3.487 MPY =-3.487 MPZ =-1.646 MVEL = 510.5 ATRX = 3.487 ATRY...APX =-1.826 APY =-1.826 APZ =-1.254 AVEL = 510.5 MPX = 2.725 MPY =-.3295E-02 MPZ =-.8237 MVEL = 1181. ATRX = 4.555 ATRY = 1.826 ATRZ = .4308 ATRR...velocity in wind axes coordinate system) [kts or m/sec]. ATRX : This is the X-axis component of the launching aircraft to target relative range in the

  19. Signature analysis of ballistic missile warhead with micro-nutation in terahertz band

    Li, Ming; Jiang, Yue-song


    In recent years, the micro-Doppler effect has been proposed as a new technique for signature analysis and extraction of radar targets. The ballistic missile is known as a typical radar target and has been paid many attentions for the complexities of its motions in current researches. The trajectory of a ballistic missile can be generally divided into three stages: boost phase, midcourse phase and terminal phase. The midcourse phase is the most important phase for radar target recognition and interception. In this stage, the warhead forms a typical micro-motion called micro-nutation which consists of three basic micro-motions: spinning, coning and wiggle. This paper addresses the issue of signature analysis of ballistic missile warhead in terahertz band via discussing the micro-Doppler effect. We establish a simplified model (cone-shaped) for the missile warhead followed by the micro-motion models including of spinning, coning and wiggle. Based on the basic formulas of these typical micro-motions, we first derive the theoretical formula of micro-nutation which is the main micro-motion of the missile warhead. Then, we calculate the micro-Doppler frequency in both X band and terahertz band via these micro-Doppler formulas. The simulations are given to show the superiority of our proposed method for the recognition and detection of radar micro targets in terahertz band.

  20. Wind Tunnel Experimental Investigation on the Aerodynamic Characteristics of the Multifin Rockets and Missiles


    The transonic-supersonic wind tunnel experiment on the aerodynamics of the rockets and missiles that have four, six, eight flat or wrap-around fins is introduced. The experimental results show, while M∞<2.0, with the increase of the fins' number, the derivative of lift coefficient is increasing, the pressure center is shifting backwards, and the longitudinal static stability is augmenting. On the contrary, while the Mach number exceeds a certain supersonic value, the aerodynamic effectiveness of the eight-fin missiles would be lower than that of the six-fin missiles. For the low speed short-range missiles, by adopting six, eight or ten flat fins configuration, the lift effectiveness can be greatly increased, the pressure center can be shifted backwards, the static and dynamic stability can be obviously enhanced. For the high speed long-range large rockets and missiles launched from multi-tube launcher, the configuration adopting more than six fins can not be useful for increasing the stability but would make the rolling rate instable during the flight.

  1. An evaluation method for tornado missile strike probability with stochastic correction

    Eguchi, Yuzuru; Murakami, Takahiro; Hirakuchi, Hiromaru; Sugimoto, Soichiro; Hattori, Yasuo [Nuclear Risk Research Center (External Natural Event Research Team), Central Research Institute of Electric Power Industry, Abiko (Japan)


    An efficient evaluation method for the probability of a tornado missile strike without using the Monte Carlo method is proposed in this paper. A major part of the proposed probability evaluation is based on numerical results computed using an in-house code, Tornado-borne missile analysis code, which enables us to evaluate the liftoff and flight behaviors of unconstrained objects on the ground driven by a tornado. Using the Tornado-borne missile analysis code, we can obtain a stochastic correlation between local wind speed and flight distance of each object, and this stochastic correlation is used to evaluate the conditional strike probability, QV(r), of a missile located at position r, where the local wind speed is V. In contrast, the annual exceedance probability of local wind speed, which can be computed using a tornado hazard analysis code, is used to derive the probability density function, p(V). Then, we finally obtain the annual probability of tornado missile strike on a structure with the convolutional integration of product of QV(r) and p(V) over V. The evaluation method is applied to a simple problem to qualitatively confirm the validity, and to quantitatively verify the results for two extreme cases in which an object is located just in the vicinity of or far away from the structure.

  2. Strategic culture and ballistic missile defense: Russia and the United States. Master's thesis

    Becker, M.D.


    This thesis examines U.S. and Russian history and current policy debates to advance understanding of: (1) the strategic cultures of these nations, particularly with respect to BMD policies in the recent past; and (2) whether and how their strategic cultures and approaches to BMD are changing and how that may affect future strategic BMD developments and the status of the ABM Treaty. The development of BMD strategies, including policies concerning the ABM Treaty, within the framework of the established American and Russian strategic cultures is studied, with due attention to the Soviet experience and legacy in the Russian case. U.S. strategic culture does not seem to have changed significantly with the end of the Cold War, but U.S. BMD priorities have been redefined to reflect a higher priority attached to regional and theater-level defenses. It is apparent that the Soviet experience did have a significant impact on Russian strategic culture. Faced with major changes in its international status, domestic political-military arrangements, and scope of national security concerns, Russian strategic culture is nonetheless moving beyond the old Soviet culture. Future Russian policies regarding the transfer of BMD technology, sharing early warning data, and participating in a global protective system are heavily dependent on domestic political developments. United States, Russia, USSR, Strategic culture, Ballistic missile defense, National strategy, Nuclear strategy, Strategic defense, ABM Treaty, Arms control, Strategic stability.

  3. A Study of the Effects of Sensor Noise and Guidance Laws on SAM Effectiveness Against Cruise Missiles


    k guidance acceleration command vector xviii THIS PAGE INTENTIONALLY LEFT BLANK xix EXECUTIVE SUMMARY Cruise missile (CM) technology is...Germany, Netherlands, UK, Denmark Turkey, Romania, Poland, and Spain ) contributed to the Maritime Theatre Missile Defence Forum to obtain an impressive

  4. 77 FR 64564 - Implementation of Regulatory Guide 1.221 on Design-Basis Hurricane and Hurricane Missiles


    ... COMMISSION Implementation of Regulatory Guide 1.221 on Design-Basis Hurricane and Hurricane Missiles AGENCY....221 on Design-Basis Hurricane and Hurricane Missiles.'' The purpose of this ISG is to supplement the guidance regarding the application of Regulatory Guide 1.221, ``Design-Basis Hurricane and...

  5. Guidance Law and Neural Control for Hypersonic Missile to Track Targets

    Wenxing Fu


    Full Text Available Hypersonic technology plays an important role in prompt global strike. Because the flight dynamics of a hypersonic vehicle is nonlinear, uncertain, and highly coupled, the controller design is challenging, especially to design its guidance and control law during the attack of a maneuvering target. In this paper, the sliding mode control (SMC method is used to develop the guidance law from which the desired flight path angle is derived. With the desired information as control command, the adaptive neural control in discrete time is investigated ingeniously for the longitudinal dynamics of the hypersonic missile. The proposed guidance and control laws are validated by simulation of a hypersonic missile against a maneuvering target. It is demonstrated that the scheme has good robustness and high accuracy to attack a maneuvering target in the presence of external disturbance and missile model uncertainty.

  6. A Direct Multiple Shooting Method for Missile Trajectory Optimization with The Terminal Bunt Manoeuvre

    S. Subchan Subchan


    Full Text Available Numerical solution of constrained nonlinear optimal control problem is an important field in a wide range of applications in science and engineering. The real time solution for an optimal control problem is a challenge issue especially the state constrained handling. Missile trajectory shaping with terminal bunt manoeuvre with state constaints is addressed. The problem can be stated as an optimal control problem in which an objective function is minimised satisfying a series of constraints on the trajectory which includes state and control constraints. Numerical solution based on a direct multiple shooting is proposed. As an example the method has been implemented to a design of optimal trajectory for a missile where the missile must struck the target by vertical dive. The qualitative analysis and physical interpretation of the numerical solutions are given.

  7. Improved manufacturing techniques for rf and laser hardening of missile domes, phase 1

    Pawlewicz, W. T.; Mann, I. B.; Martin, P. M.; Hays, D. D.; Graybeal, A. G.


    The adaptation of an existing Pacific Northwest Laboratory (PNL) optical coating capability developed for high power fusion laser applications to the case of RF and laser hardening of plastic missile domes used by US Army (MICOM) is reported. RF hardening of Hellfire and Copperhead 1.06 micron missile domes by use of transparent conductive Indium Tin Oxide (ITO) coatings is demonstrated. The project involved adaptation of a coating material and process developed for flat glass components used in fusion lasers to the case of hemispherical or conical heat sensitive plastic domes used on laser guided missiles. Specific ITO coating property goals are an electrical sheet resistance of 10 ohms/square, a coated dome transmission of 80% or more at 1.06 micron wavelength (compared to 90% for a bare dome), and good adhesion. The sheet resistance goal of 10 ohms/square was expected to result in an RF attenuation of 30 dB at the frequencies of importance.

  8. A method for simulating the atmospheric entry of long-range ballistic missiles

    Eggers, A J , Jr


    It is demonstrated with the aid of similitude arguments that a model launched from a hypervelocity gun upstream through a special supersonic nozzle should experience aerodynamic heating and resulting thermal stresses like those encountered by a long-range ballistic missile entering the earth's atmosphere. This demonstration hinges on the requirements that model and missile be geometrically similar and made of the same material, and that they have the same flight speed and Reynolds number (based on conditions just outside the boundary layer) at corresponding points in their trajectories. The hypervelocity gun provides the model with the required initial speed, while the nozzle scales the atmosphere, in terms of density variation, to provide the model with speeds and Reynolds numbers over its entire trajectory. Since both the motion and aerodynamic heating of a missile tend to be simulated in the model tests, this combination of hypervelocity gun and supersonic nozzle is termed an atmosphere entry simulator.

  9. Autopilot Design Method for the Blended Missile Based on Model Predictive Control

    Baoqing Yang


    Full Text Available This paper develops a novel autopilot design method for blended missiles with aerodynamic control surfaces and lateral jets. Firstly, the nonlinear model of blended missiles is reduced into a piecewise affine (PWA model according to the aerodynamics properties. Secondly, based on the equivalence between the PWA model and mixed logical dynamical (MLD model, the MLD model of blended missiles is proposed taking into account the on-off constraints of lateral pulse jets. Thirdly, a hybrid model predictive control (MPC method is employed to design autopilot. Finally, simulation results under different conditions are presented to show the effectiveness of the proposed method, which demonstrate that control allocation between aerodynamic control surfaces and lateral jets is realized by adjusting the weighting matrix in an index function.

  10. Missile Defense Agency Ballistic Missile Defense System (BMDS): Programmatic Environmental Impact Statement. Volume 1 Final BMDS PEIS


    dwarfed shrubs and miniature wildflowers adapted to a short growing season. Species resident in arctic tundra have evolved adaptations peculiar to high...strong northeast winds, the likelihood of pollutants remaining in the ambient air is low. Heavy industrial activities, high automobile traffic, and...bodies. Some perennial surface waters could be impacted following a flight termination. However, the probability of any individual water body, spring

  11. Missile Defense Agency Ballistic Missile Defense System (BMDS): Programmatic Environmental Impact Statement. Volume 2. Appendices A - J


    18 wedding parties and a hotels full of journalists. In 19 other words, you honored military gentlemen have trouble... Hawaiian language translator? 4 MR. BONNER: I don’t think we’ve provided for 5 one, unfortunately. 6...21 actually discriminating against native Hawaiians in 22 doing so. 23 As William Eiler has said in other

  12. Missile Defense Agency Ballistic Missile Defense System (BMDS): Programmatic Environmental Impact Statement. Volume 3 Appendices K - N


    K.2.1 Castor Rachel DC_M0217 K.2.1 Cathcart Mary DC_M4026 UCS K.2.1 Caton Barney DC_M1750 UCS K.2.1 Catrambone Natalie DC_M3934 UCS K.2.1 Caturegli...professional and nonprofit groups who specialize in public health, emergency response, sewage treatment, landfills , water, environment, toxicology, science...nonprofit groups who specialize in public health, emergency response, sewage treatment, landfills , water, environment, toxicology, science, medicine

  13. Software and Systems Test Track Architecture and Concept Definition


    Raytheon, the Embedded Systems Consortium for Hybrid and Embedded Research ( ESCHER ) Research Institute, Vanderbilt University, and the University of...Stuart ESCHER PM: Larry Rohrbough UC Berkeley Co-PI: Prof. Shankar Sastry Tech Lead: Dr. Jonathan Sprinkle Vanderbilt Co-PI: Dr. Ted Bapty Advisor: Dr...Andrew Vandivort contributed greatly to the development of the SWTT CONOPS, and Don Wilson provided strategic technology leadership. From ESCHER

  14. Genetic Algorithms, Neural Networks, and Time Effectiveness Algorithm Based Air Combat Intelligence Simulation System

    曾宪钊; 成冀; 安欣; 方礼明


    This paper introduces a new Air Combat Intelligence Simulation System (ACISS) in a 32 versus 32 air combat, describes three methods: Genetic Algorithms (GA) in the multi-targeting decision and Evading Missile Rule Base learning, Neural Networks (NN) in the maneuvering decision, and Time Effectiveness Algorithm (TEA) in the adjudicating an air combat and the evaluating evading missile effectiveness.

  15. 2005 8th Annual Systems Engineering Conference Volume 3 - Wednesday presentations


    Engineering, Inc. Systems Modeling Language Systems Modeling Language (SysML) Overview & Update, Rick Steiner, Raytheon Company Data Management Support for...template” – Ensure language in contracts – Determine how to verify SE compliance • Exit Criteria: – List of all targeted contracts – SE an are evaluated and analyzed early in the acqusition process. 10SEC-8 Integrated Product and Process Development Design Development Manufacturing

  16. Pacific Missile Range Facility Intercept Test Support. Environmental Assessment/Overseas Environmental Assessment


    Portable hair dryer 86 to 77 At 1 foot Vacuum cleaner 85 to 78 At 5 feet Long range airplane 80 to 70 Inside Conversation 60 Typical suburban...missile unstable, causing it to tumble and fall to the earth prior to reaching populated areas. Other strategies to cause a vehicle to tumble may also

  17. A Three-Pronged Strategy to Solve the Problem of Long-Range Missile Proliferation


    One example is Brazil and its Sonda space launch vehicle (SLV) program. This SLV program, and others like it, are potentially dangerous to the U.S...because as a non-adherent to the MTCR, Brazil may transfer Sonda technology to rogue states or build offensive missiles capable of striking the U.S

  18. Treatment of open tibial fracture with bone defect caused by high velocity missiles: a case report.

    Golubović, Zoran; Vukajinović, Zoran; Stojiljković, Predrag; Golubović, Ivan; Visnjić, Aleksandar; Radovanović, Zoran; Najman, Stevo


    Tibia fracture caused by high velocity missiles is mostly comminuted and followed by bone defect which makes their healing process extremely difficult and prone to numerous complications. A 34-year-old male was wounded at close range by a semi-automatic gun missile. He was wounded in the distal area of the left tibia and suffered a massive defect of the bone and soft tissue. After the primary treatment of the wound, the fracture was stabilized with an external fixator type Mitkovic, with convergent orientation of the pins. The wound in the medial region of the tibia was closed with the secondary stitch, whereas the wound in the lateral area was closed with the skin transplant after Thiersch. Due to massive bone defect in the area of the rifle-missile wound six months after injury, a medical team placed a reconstructive external skeletal fixator type Mitkovic and performed corticotomy in the proximal metaphyseal area of the tibia. By the method of bone transport (distractive osteogenesis), the bone defect of the tibia was replaced. After the fracture healing seven months from the secondary surgery, the fixator was removed and the patient was referred to physical therapy. Surgical treatment of wounds, external fixation, performing necessary debridement, adequate antibiotic treatment and soft and bone tissue reconstruction are essential in achieving good results in patients with the open tibial fracture with bone defect caused by high velocity missiles. Reconstruction of bone defect can be successfully treated by reconstructive external fixator Mitkovic.

  19. 78 FR 9768 - Bureau of International Security and Nonproliferation Imposition of Missile Sanctions on Two...


    ... of International Security and Nonproliferation Imposition of Missile Sanctions on Two Chinese Foreign.... SUMMARY: A determination has been made that two foreign persons in China have engaged in activities that...) . Accordingly, the following sanctions are being imposed on these foreign persons for two years: (A) Denial of...

  20. Military aircraft and missile technology at the Langley Research Center: A selected bibliography

    Maddalon, D. V.


    A compilation of reference material is presented on the Langley Research Center's efforts in developing advanced military aircraft and missile technology over the past twenty years. Reference material includes research made in aerodynamics, performance, stability, control, stall-spin, propulsion integration, flutter, materials, and structures.

  1. 76 FR 4322 - Availability of the Fiscal Year 2009 Missile Defense Agency Services Contracts Inventory Pursuant...


    ... of the Secretary Availability of the Fiscal Year 2009 Missile Defense Agency Services Contracts... United States Code as amended by the National Defense Authorization Act for Fiscal Year 2008 (NDAA 08... Procurement and Acquisition Policy, Office of Strategic Sourcing (DPAP/SS) will make available to the public...

  2. 78 FR 42430 - Revisions to the Export Administration Regulations Based on the 2012 Missile Technology Control...


    ... (Definitions of Terms as Used in the Export Administration Regulations) by amending the definition of the term... Definitions of terms as used in the Export Administration Regulations (EAR). * * * * * Payload... Administration Regulations Based on the 2012 Missile Technology Control Regime Plenary Agreements AGENCY:...


    A cross-sectional survey of two fleet ballistic missile submarine crews revealed no remarkable oral health factors. A close relationship was found...effects of FBM submarine service on oral health could be demonstrated; however, in view of the isolated nature of the FBM patrols great stress needs to

  4. The Effects of Fleet Ballistic Missile Submarine Patrols on Oral Health

    Maintenance of optimum oral health for Fleet Ballistic Missile submarine personnel is a continuing effort. Information is required concerning oral ... health status and patrol effects on this status. Ninety-one crew members of the USS JOHN MARSHALL (SSBN 611 (Gold)) were evaluated predeployment, during

  5. Joint Theater Missile Defense in Taiwan: Protecting United States Interests and Friends


    people in a disproportionately short period and where the consequences of its release overwhelms local responders. 67 APPENDIX A CHINESE BALLISTIC...2004, Ballistic Missile Defense. Airborne Laser The Airborne Laser (ABL) consists of a high-energy, chemical oxygen iodine laser (COIL) mounted

  6. Theoretical and Experimental Methods in the Solution of Missile Nonlinear Roll Problems


    directed towvard improving the science of free flight missile dynamics by investigating the nonlinear rolling motion phenomena *exhibitcd by firned ...3 3 Schematic of Basic Finner Model ......................... 7 4 Induced Rolling Moment vs Roll Orientation Angle for Basic Finner Model Measured in...28 27 Rotational Characteristics of Cruciform Rectangular Fins ....... ............................. 29 28 Wind Tunnel Model (Naval Academy

  7. Dynamic attack zone of air-to-air missile after being launched in random wind field

    Hui Yaoluo; Nan Ying; Chen Shaodong; Ding Quanxin; Wu Shengliang


    A new concept is presented for air-to-air missile which is dynamic attack zone after being launched in random wind field. This new concept can be used to obtain the 4-dimensional (4-D) information regarding the dynamic envelope of an air-to-air missile at any flight time aimed at different flight targets considering influences of random wind, in the situation of flight fighters coop-erated with missiles fighting against each other. Based on an air-to-air missile model, some typical cases of dynamic attack zone after being launched in random wind field were numerically simulated. Compared with the simulation results of traditional dynamic envelope, the properties of dynamic attack zone after being launched are as follows. The 4-D dynamic attack zone after being launched is inside traditional maximum dynamic envelope, but its forane boundary is usually not inside tra-ditional no-escape dynamic envelope;Traditional dynamic attack zone can just be reliably used at launch time, while dynamic envelope after being launched can be reliably and accurately used dur-ing any flight antagonism time. Traditional envelope is a special case of dynamic envelope after being launched when the dynamic envelope is calculated at the launch time;the dynamic envelope after being launched can be influenced by the random wind field.

  8. Synthesis of robust feedback missile control strategies by using LMI techniques

    Trottemant, E.J.; Weiss, M.; Vermeulen, A.


    Robust programming, and more specific LMI techniques, have proven to be an extremely effective tool for the synthesis of missile guidance laws. The advantage of this model-based approach is that a large class of uncertainties can be taken into account and a robust guidance law is obtained. In this p

  9. Optimal linear-quadratic missile guidance laws with penalty on command variability

    Weiss, M.; Shima, T.


    This paper proposes a new approach to the derivation of homing guidance laws for interceptor missiles that makes use of linear-quadratic optimal control in a different manner than the traditional approaches. Instead of looking only for the minimization of the miss distance and the integral square of

  10. 75 FR 20520 - Revisions to the Export Administration Regulations Based on the 2009 Missile Technology Control...


    ... turbo-compound engines. Accordingly, turbo-compound engines are not meant to be included within the... describe these engines. Additionally, turbo- compound engines are not a missile proliferation concern. This... December 10, 2009 (74 FR 65662). DATES: Effective Date: This rule is effective: April 20, 2010....

  11. 75 FR 28587 - Taking and Importing Marine Mammals; Taking Marine Mammals Incidental to Missile Launch...


    ... incidents (e.g., search-and-rescue, fire-fighting, adverse weather conditions), which may require... mission objectives; (2) the Navy must limit launch activities during other pinniped pupping seasons... launch trajectory necessary to meet mission objectives; (3) the Navy must not launch missiles from...

  12. Determination of an Achievable Materiel Availability for the Joint Air-to-Ground Missile


    to meet applied TAT metrics (use of FedEx, DHL , etc.). Sup- ply chain variances emerge under organic support, which are out of the control of the...can be a low priority, will vary depending on the mode and frequency of trips. Missiles in particular cannot be shipped commercially (FedEx, DHL etc

  13. 75 FR 58365 - Taking and Importing Marine Mammals; Taking Marine Mammals Incidental to Missile Launch...


    .... Placement of the cameras would cause minimal disturbance to pinnipeds and would focus on a subgroup of... forward looking infrared (FLIR) HS-324 Command thermal imaging cameras for nighttime monitoring of pinnipeds before, during, and after each missile launch. Previously, no cameras were available for...

  14. Near Term Command and Control of Homeland Air and Missile Defense


    grounded the aircraft prior to take off. Special Operations forces might be best suited to eliminate a terrorist cell with minimal collateral 32 damage. We...Review. 27 March 2002. HAER No. ND-9 (Excerpt from Historic American Engineering Record,) Safeguard Ballistic Missile Defense Center ( BMDC ). Heller

  15. Conventional Prompt Global Strike and Long Range Ballistic Missiles: Background and Issues


    Christopher P. Caves, “Subs May Serve Attack, Guided Missile Functions,” Navy Times, October 15, 2011, dual -use...preliminary results show that the HTV-2 achieved controlled flight in the atmosphere before telemetry was lost nine minutes after liftoff. 72 Media

  16. Conventional Prompt Global Strike and Long-Range Ballistic Missiles: Background and Issues


    2011/10/navy- dual -use-submarines-attack-guided-missile-101511w/ 46 U.S. Department of Defense, Major Budget Decisions Briefing From the Pentagon...According to DARPA, its preliminary results show that the HTV-2 achieved controlled flight in the atmosphere before telemetry was lost nine minutes after

  17. Research on Guidance Law for Cooperative Attack of Multiple Missiles%多导弹协同作战制导律研究

    王晓芳; 郑艺裕; 林海


    To enhance the penetration and hitting capacity of anti-ship missiles attacking the target cooperatively,a cooperative guidance law composed of a cooperative range-to-go guidance law and a guidance law making line-of-sight (LOS)angle-rate approach zero was proposed.The desired range-to-go was designed based on current range-to-go of each missile.Then the nonlinear relative motion model between missile and target on the basis of proportional navigation guidance law was built,and it was divided into a fast subsystem and a slow subsystem according to the time-scale separation method.Feedback linearization of two subsystems was realized based on dynamic inverse system theory.The guidance law that made multiple missiles’range-to-go approach and keep the desired range-to-go was designed adopting linear system theory.To ensure missiles to hit target precisely,another guidance law was proposed based on the finite time control theory,which made the angle-rate of LOS of every missile approach zero quickly in finite time while the range-to-go decreased gradually.Simulation results show that adopting the cooperative guidance law can make multiple missiles fly to the target synchronously and hit the target almost at the same time, and the cooperation of range-to-go and impact time are realized effectively.%为了增强多枚反舰导弹协同作战时的突防和打击能力,提出了一种由弹目距离协同制导律和视线角速度收敛制导律两部分组成的多导弹协同制导律。综合多枚导弹的弹目距离信息,设计了期望弹目距离。基于比例导引律建立了导弹目标相对运动非线性模型,采用时标分离原理将其分为快变子系统和慢变子系统,然后采用动态逆系统理论将2个子系统反馈线性化,基于线性系统理论设计了能够实现多弹弹目距离趋于期望弹目距离的制导律。为了保证各导弹顺利地协同攻击目标,在飞行末段,采用有限时间控制理论

  18. 基于共生仿真的巡航导弹协同作战研究%Research on symbiotic simulation based cruise missile collaborative engagement

    吴红; 杨峰; 王维平


    In order to response to complex and diverse battlefield environment, cruise missile needs to carry out task through dynamic collaboration. Nowadays, domestic and international researches which focus on cruise missile collaborative engagement have presented some dynamic cooperative modes, but all they have several drawbacks to some extent. Because of this, this paper puts forward a limited autonomy of central control of distributed collaboration, designs system business logic and analyzes system function in detail, then uses it as the background to carry out system architecture design of remote control collaboration based on symbiotic simulation.%为了应对体系对抗过程中复杂多变的战场环境,巡航导弹需通过动态协同执行作战任务.目前,国内外在巡航导弹协同作战的研究过程中,提出了几种动态协同模式,但都在一定程度上存在局限性.基于此,首先提出有限中央控制的分布式自主协同,对其系统业务逻辑进行了详细的设计和系统功能进行了详细的分析,并以此为背景开展基于共生仿真的远程控制协同系统体系结构设计.

  19. Assembly Area Trouble Shooting Manual -- Missile Guidance Set AN/DPW-11. Guided Missile Test Set AN/DSM-12. Guided Missile Electrical Test Set M22. (NIKE-AJAX Antiaircraft Guided Missile System)


    dilfcrt’llt from•) ... S•JI>PLIE.,.ENT ARY NOTE S Research performed by HumRRO Division t\\o. 5, El Paso , Texas (nO\\\\ llumRRO ~es t e rn Oivision...El Paso Office) under \\~ork Unit ~l~l~lR\\IN, ~lai ntcnance Profi ·icncy and Its Relation to Training Procedures for Guided ~fissile Pcr~onne i...8217 mi rnm 0011« Qimi*i Ml • •••• «■Ml PUTI M m uu fM MIM lU IM oucia Itni TESI SIUCTM J wssiu mr«t ( »SSIll CUMIll » \\ 0 M in 111

  20. NATO Network Enabled Capability (NNEC) challenges: Why NATO Air Command and Control System (ACCS) might be a good case?


    Picture ( RAP ), Air Tasking Order (ATO), Air Coordination order (ACO), etc. 2. Non Functional: providing all other functionalities, e.g. IA/security...IBM, BEA, Raytheon, etc.), fielded national systems, NATO systems and prototypes (Euro Fighter, ICC, JADOCS, JCOP, JTS, MUSIC , NE-3A, Nor BFTS...instance, the RAP and FFT dissemination to internal as well as to external entities. The approach will be of benefit to ACCS and NATO C3 in the future

  1. Influence of transverse reinforcement on perforation resistance of reinforced concrete slabs under hard missile impact

    Orbovic, Nebojsa, E-mail:; Sagals, Genadijs; Blahoianu, Andrei


    This paper describes the work conducted by the Canadian Nuclear Safety Commission (CNSC) related to the influence of transverse reinforcement on perforation capacity of reinforced concrete (RC) slabs under “hard” missile impact (impact with negligible missile deformations). The paper presents the results of three tests on reinforced concrete slabs conducted at VTT Technical Research Centre (Finland), along with the numerical simulations as well as a discussion of the current code provisions related to impactive loading. Transverse reinforcement is widely used for improving the shear and punching strength of concrete structures. However, the effect of this reinforcement on the perforation resistance under localized missile impact is still unclear. The goal of this paper is to fill the gap in the current literature related to this topic. Based on similar tests designed by the authors with missile velocity below perforation velocity, it was expected that transverse reinforcement would improve the perforation resistance. Three slabs were tested under almost identical conditions with the only difference being the transverse reinforcement. One slab was designed without transverse reinforcement, the second one with the transverse reinforcement in form of conventional stirrups with hooks and the third one with the transverse reinforcement in form of T-headed bars. Although the transverse reinforcement reduced the overall damage of the slabs (the rear face scabbing), the conclusion from the tests is that the transverse reinforcement does not have important influence on perforation capacity of concrete slabs under rigid missile impact. The slab with T-headed bars presented a slight improvement compared to the baseline specimen without transverse reinforcement. The slab with conventional stirrups presented slightly lower perforation capacity (higher residual missile velocity) than the slab without transverse reinforcement. In conclusion, the performed tests show slightly

  2. Study on Emergency Measures for Nuclear Accident of Missile Nuclear Weapon%导弹核武器核事故应急有关问题研究

    高桂清; 毕义明


    The major task, characteristics, organizing and commending, and resource manipulation of the emergency measures for nuclear accident of missile nuclear weapon are probed into. The measures may be considered as a complex system engineering involving system of organization, personnel, equipment, technique and scientific theory, so on. Relevant problems of emergency measures are deliberately studied referring the practical situations. The results could provide the theoretical guidance to emergency measures for nuclear accident of missile nuclear weapon.%对导弹核武器核事故应急的主要任务、特点、组织指挥以及力量运用等问题进行了探讨,导弹核武器核事故的应急问题是一项涉及体制、人员、装备、技术、科学理论等方面的复杂系统工程,笔者结合实际,有针对性的研究了事故应急有关的问题,可为导弹核武器核事故应急提供理论指导。

  3. The Implementation of BTT Missile Neural Network Direct Inverse Control Algorithm Based on FPGA%BTT导弹神经网络直接逆控制算法的FPGA实现研究

    马建伟; 王志鹏; 刘忠


    Regarding the nonlinear strong coupling characteristics of missile model in BTT missile control system, an inverse missile model is built by combining neural network with inverse system. Taking the pitch channel for instance, the structure of BP neural network inverse control algorithm is designed. And the Verilog HDL is used to implement each module of BP neural network and then realized in FPGA. According to the comparison of the implementation of neural network inverse control methods between FPGA and general computer software, the scheme can meet requirement of the BTT missile control algorithm for computing speed. The performance of neural network hardware implementation is also analyzed in this paper.%针对BTT导弹控制系统中导弹模型的非线性和强耦合的特点,应用逆7系统和神经网络相结合的方法建立了导弹的逆模型.并以俯仰通道为例,设计了逆控制算法的BP神经网络结构,采用Verilog HDL编写了BP神经网络各个功能模块,并将其在FPGA上实现.通过神经网络逆控制算法在FPGA硬件实现和通用计算机上软件实现的对比,表明该方案能够满足BTT导弹对控制算法运算速度的要求.文中还对硬件实现神经网络的性能进行了分析.

  4. Cooperative Monitoring Center Occasional Paper/4: Missile Control in South Asia and the Role of Cooperative Monitoring Technology

    Kamal, N.; Sawhney, P.


    The succession of nuclear tests by India and Pakistan in May 1998 has changed the nature of their missile rivalry, which is only one of numerous manifestations of their relationship as hardened adversaries, deeply sensitive to each other's existing and evolving defense capabilities. The political context surrounding this costly rivalry remains unmediated by arms control measures or by any nascent prospect of detente. As a parallel development, sensible voices in both countries will continue to talk of building mutual confidence through openness to avert accidents, misjudgments, and misinterpretations. To facilitate a future peace process, this paper offers possible suggestions for stabilization that could be applied to India's and Pakistan's missile situation. Appendices include descriptions of existing missile agreements that have contributed to better relations for other countries as well as a list of the cooperative monitoring technologies available to provide information useful in implementing subcontinent missile regimes.

  5. Integrated guidance and control design for missile with terminal impact angle constraint based on sliding mode control

    Peng Wu; Ming Yang


    Aimed at the guidance requirements of some missiles which attack targets with terminal impact angle at the terminal point,a new integrated guidance and control design scheme based on variable structure control approach for missile with terminal impact angle constraint is proposed.First,a mathematical model of an integrated guidance and control model in pitch plane is established,and then nonlinear transformation is employed to transform the mathematical model into a standard form suitable for sliding mode control method design.A sufficient condition for the existence of linear sliding surface is given in terms of linear matrix inequalities(LMIs),based on which the corresponding reaching motion controller is also developed.To verify the effectiveness of the proposed integrated design scheme,the numerical simulation of missile is made.The simulation results demonstrate that the proposed guidance and control law can guide missile to hit the target with desired impact angle and desired flight attitude angle simultaneously.

  6. Raytheon, Estonia agree to cyber pact / Zachary Fryer-Biggs

    Fryer-Biggs, Zachary


    USA ettevõte on valmis tegema Eestiga koostööd kübervõimekuse arendamisel. Kaitseministeeriumi asekantsleri Mikk Marrani sõnul on Eesti ja USA kaitsetööstuselane koostöö Eesti strateegilistes huvides

  7. Raytheon, Estonia agree to cyber pact / Zachary Fryer-Biggs

    Fryer-Biggs, Zachary


    USA ettevõte on valmis tegema Eestiga koostööd kübervõimekuse arendamisel. Kaitseministeeriumi asekantsleri Mikk Marrani sõnul on Eesti ja USA kaitsetööstuselane koostöö Eesti strateegilistes huvides

  8. Ballistic Missile Defense: Actions Needed to Address Implementation Issues and Estimate Long-Term Costs for European Capabilities


    forces, and allies against inbound threat missiles. In December 2011, DOD deployed the initial phase of a revised approach for Europe, with...the United States, U.S. forces, and allies around the world against inbound threat missiles. In 2009, the President announced a revised approach for...allocating resources. In addition, we reviewed the Army’s regulation on Integrated Logistic Support, which includes guidance on business-case analysis

  9. A study of the motion and aerodynamic heating of ballistic missiles entering the earth's atmosphere at high supersonic speeds

    Allen, H Julian; Eggers, A J , Jr


    A simplified analysis of the velocity and deceleration history of ballistic missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer.

  10. Research of Short-range Missile Motion in Terms of Different Wind Loads

    A. N. Klishin


    Full Text Available When modeling the aircraft motion it is advisable to choose a particular model of the Earth, depending both on the task and on the required accuracy of calculation. The article describes various models of the Earth, such as the flat Earth with a plane-parallel field of gravity, spherical and non-rotating Earth with a plane-parallel field of gravity, spherical and non-rotating Earth with a central gravitational field, spherical and non-rotating Earth, taking into account the polar flattening of the Earth, spherical Earth based compression and polar daily rotation. The article also considers the influence of these models on the motion of the selected aircraft.To date, there is technical equipment to provide highly accurate description of the Earthshape, gravitational field, etc. The improved accuracy of the Earth model description results in more correct description of the trajectory and motion parameters of a ballistic missile. However, for short ranges (10-20 km this accuracy is not essential, and, furthermore, it increases time of calculation. Therefore, there is a problem of choosing the optimal description of the Earth parameters.The motion in the model of the Earth, which takes into account a daily rotation of the planet and polar flattening, is discussed in more detail, and the geographical latitude impact on coordinates of the points of fall of a ballistic missile is analyzed on the basis of obtained graphs.The article individually considers a problem of the wind effect on the aircraft motion and defines dependences of the missile motion on the parameters of different wind loads, such as wind speed and height of its action.A mathematical model of the missile motion was built and numerically integrated, using the Runge-Kutta 4th order method, for implementation and subsequent analysis.Based on the analysis of the calculation results in the abovementioned models of the Earth, differences in impact of these models on the parameters of the

  11. Comparison of head-steered and aircraft-fixed infrared imagery for employing the AGM-65 Maverick missile

    Osgood, Robert K.; Wells, Maxwell J.; Meador, Douglas P.


    Eight veteran USAF fighter pilots, experienced with AGM-65 Maverick air-to-ground missiles, flew a night, low-level ground attack mission in a flight simulator equipped with a helmet-mounted display (HMD). The mission was performed by delivering five Maverick missiles against ground vehicles using either an aircraft-fixed forward-looking infrared (FLIR) sensor image on a head-up display (HUD) or a head-steered FLIR as the missile aiming device. Additionally, the pilots employed their weapons by two methods: fixing and launching missiles singly or in varying numbers (multiple method). The purpose of the experiment was to determine what, if any, advantage there is to employing the AGM-65 using the HMD FLIR image to slew the missile seeker onto the target versus the conventional method of using the FLIR image displayed on the HUD. With a head-steered sensor (and fixing and launching weapons singly) subjects released their weapons quicker (14.6 second interval between launches vs. 17.1 sec.), at a higher altitude (1739 feet vs. 1603 ft.), and slightly farther from the target (3.42 nautical miles vs. 3.37 nm). Furthermore, data indicated the pilots looked farther off-boresight when searching for and locking the weapon onto a target, thereby more effectively using the full field-of-regard of the missile seeker. The participants also contributed their opinions of the advantages and disadvantages of the two mechanizations.

  12. 基于二阶滑模控制的驾束制导导弹一体化制导系统设计%Integrated Guidance-Control System for Beam-riding Guidance Missiles Based on Second Order Sliding Mode Control

    周军; 王婷


    针对驾束制导导弹,运用超扭曲二阶滑模控制理论,提出了一种一体化制导控制算法.通过充分考虑目标不确定因素以及控制回路未建模状态,建立了一体化制导控制回路的四阶状态方程.运用该状态方程的转移矩阵,重新定义了零能脱靶量(ZEM),使其不再需要估计剩余时间,并将此作为滑模切换面,设计了一体化超扭曲二阶滑模制导律.通过对目标的拦截仿真,结果表明制导线偏差可在有限时间内收敛到零,从而验证了选择新定义的ZEM作为制导律的滑模切换面是有效的.数字仿真结果也表明了该一体化设计方法明显优于不考虑控制回路的传统制导律设计方法.%An Integrated Guidance-Control(IGC) law is proposed , using the super-twisting second order Sliding Mode Control(SMC) method, for the beam-riding guidance missiles . The fourth order state equation for integrated guidance and control loop was formulated taking into consideration the target uncertainties and control loop dynamics. Based on the transition matrix of the state equation, the zero-effort miss (ZEM) was redefined without calculating the time-to-go. By choosing the ZEM as a single sliding surface, the integrated super-twisting second order sliding mode guidance law was obtained. Simulation results show that ZEM and guidance range error could converge to zero in a finite time almost without any overshoot. The advantages of the integrated guidance are also validated by comparing with the conventional guidance without considering control loop.

  13. 基于灰色物元分析法的导弹装备采办风险评估%Risk Assessment of Missile Equipment Acquisition Based on Grey Matter Element Analysis

    曹翊天; 李彦彬; 吴振亚; 张斯嘉


    This paper established the assessment index system of missile equipment acquisition risk problems. It used grey theory and matter element analysis to build up the grey matter element analysis model for evaluating the risk for certain missile equipment. Then it gives the correlation coefficients of total acquisition risk with each evaluating grey-group and concluded assessment conclusion according to principle of maximum degree of membership. Finally,it verifies the feasibility of model and put forward suggestions for missile equipment acquisition.%对于导弹装备存在的采办风险问题,建立了导弹装备采办的评估指标体系。灰色理论与物元分析法相结合,构建了灰色物元模型,对某型导弹采办风险进行了评估,得出总的采办风险与各个评估灰类的关联系数,用最大隶属度原则得出评估结论。用实例验证了该模型的可行性,并对导弹装备的采办提出相应建议。

  14. 基于多目标灰色决策的地空导弹选型研究%Research on Surface to Air Missile Type Selection Based on Multi-criteria Gray Decision-making

    崔建鹏; 辛永平; 刘肖健


    Aiming at the type selection of surface to air missile and synthetically considering the cost and holistic efficiency,the model of multi-criteria gray decision-making for the type selection of surface to air missile is established using the multi-criteria gray decision-making method of gray system theory.The model is analyzed and calculated,and then the optimal decision is worked out.The example can prove that the method of multi-criteria gray decision-making is a reasonable and feasible method,it can be used as a quantitative analysis means to the type selection of surface to air missile.%针对地空导弹选型这一问题,综合考虑地空导弹武器系统的成本及整体效能,运用灰色系统理论中的多目标灰色决策方法建立了地空导弹武器系统选型的多目标灰色决策模型。对此模型进行分析和计算,并做出了最优决策。通过实例分析,证明这是一种合理、可行的分析方法,为地空导弹选型研究提供了一种定量分析的依据。

  15. Battlefield De-Confliction Sensor And Information System

    Breckinridge, James B.


    A battlefield de-confliction and assessment sensor system architecture is described that uses a hyper-spectral imaging spectomerer instrument onboard a robitc aerial vehicle (UAV) to identify, characterize,and track missiles and aircraft.

  16. 3D-Route Planning Method to Realize Missile Cruise Flight

    WANG Zheng-jie; FAN Chen; ZHU Qun-Min; TANG Wei


    In order to increase the aircraft's survival in the flight mission, it is necessary to carry out flight mission planning, which includes TF/TA\\+2(terrain following/terrain avoidance/threat avoidance).An approach to 3D-route planning based on A* heuristic search algorithm was selected to determine the routes of fiber optic guidance missile's cruise segment.The cost function was discussed, which was mainly related to the physical obstacle, threat exposure, and aircraft performance characteristics.The digital map techniques were presented, which included setting "no-go" area according to fiber's safety requirement.The optimal or the sub-optimal route was obtained, while the cost function constraints were satisfied and the stored terrain obtained from a real terrain was digitized.The algorithm is validated through simulation and can fulfill the route planning task which focuses on the cruise segment of fiber optic guidance missile.

  17. A distributed cooperative guidance law for salvo attack of multiple anti-ship missiles

    Zhang Youan


    Full Text Available The consensus problem of impact time is addressed for multiple anti-ship missiles. A new distributed cooperative guidance law with the form of biased proportional navigation guidance (BPNG is presented. The proposed guidance law employs the available measurements of relative impact time error as the feedback information to achieve the consensus of impact time among missiles and, by exploiting the special structure of the biased cooperative control term, it can handle the seeker’s field-of-view (FOV constraint. The proposed scheme ensures convergence to consensus of impact time under either fixed or switching sensing/communication network, and the topological requirements are less restrictive than those in the existing results. Numerical examples are provided to illustrate the effectiveness of the proposed guidance law.

  18. A distributed cooperative guidance law for salvo attack of multiple anti-ship missiles

    Zhang Youan; Wang Xingliang; Wu Huali


    The consensus problem of impact time is addressed for multiple anti-ship missiles. A new distributed cooperative guidance law with the form of biased proportional navigation guidance (BPNG) is presented. The proposed guidance law employs the available measurements of relative impact time error as the feedback information to achieve the consensus of impact time among mis-siles and, by exploiting the special structure of the biased cooperative control term, it can handle the seeker’s field-of-view (FOV) constraint. The proposed scheme ensures convergence to consensus of impact time under either fixed or switching sensing/communication network, and the topological requirements are less restrictive than those in the existing results. Numerical examples are provided to illustrate the effectiveness of the proposed guidance law.

  19. Comparative Analysis of Guidance Algorithms for the Hyper Velocity Missile and AFTI/F-16


    latest Kalman Filter modeling tools to the problem of guiding this missile to a target. Capps and Nelson assumed a smart missile, with "a proportional...N \\ r~,sin(S)I Nx /4 p1M. rt rioi r.Di PIc2 i_e IM rm rM BIm Figure 3-7 Pursuit Algorithm Geometry From Figure 3-7 it is seen that: r, sin (8) (1...algorithm does. 4-25 101 I-\\ - - 00 I-’ c 4 o. 0) 000 < L L Z 0) LL zo 0 C!) * . 0 .D 0 0 ~ cu r- mn T CItI I’ II II I I I CUj 0 0) CD r- CD I) W m N ~ 4-2E

  20. Design and Simulation of BTT Missile with High-Aspect-Ratio Wing Robust H∞ Autopilot

    CUI Sheng-wang; LIU Li; MA Chun-yan


    For the strong coupling among the channels of bank-to-turn (BTT) missile with high-aspect-ratio wing,an autopilot is designed with a two loop control structure robust autopilot design methods.By the inner loop design,the question of pole-zero cancellation is solved,and the stabilization of structured uncertainty is achieved.Through the outer loop of H∞ controller design,the flying performance and robustness can be guaranteed.The nonlinear simulation results show that the autopilot designed has perfect time domain response,and can suppress bad influence of the inertial and kinematics couplings.It can make the missile fly stably in the large flying areas.The control is very effective.

  1. Crisis Stability and Long-Range Strike: A Comparative Analysis of Fighters, Bombers, and Missiles


    affordable as we advance further into the 21st century. In fact , the risks in some confrontations may be comparable to what the United States expe- rienced...confrontation between nuclear- armed superpowers at the height of the Cold War. Given the immense stakes for both sides and the fact that it was resolved...and a secret promise to remove U.S. Jupiter missiles from Turkey. While this case is informative, and much has been made of it in previous crisis

  2. Prediction of Target Travel During Missile Time of Flight. A Computer Simulation


    the second program, the subject had to decide if a gap between two covered areas was wide enough for a missile to be fired successfully. Functional...Program Display During "Time to Decide"....... . ............ 7 4. Gap Program Display ,howing Covered Areas and Dot Track ... .......... 7 5. Gap...18 17. SD of Decision Time As a Funcion of Target Speed and Relative Gap Size ....... .............................. 19 18. Mean Decision

  3. China and Proliferation of Weapons of Mass Destruction and Missiles: Policy Issues


    Machinery and Electric Equipment Import and Export Co. - Wha Cheong Tai Co. - China Shipbuilding Trading Co. - CPMIEC - China Aero-Technology Import...Equipment Import Export Co. - CMEC Machinery and Electrical Import Export Co. - China Machinery and Electric Equipment Import Export Co. - Wha Cheong...ballistic missiles) September 23, 2004 for two years - Liaoning Jiayi Metals and Minerals Co. - Q.C. Chen - Wha Cheong Tai Co. Ltd. - Shanghai

  4. Another Brick in the Wall: The Israeli Experience in Missile Defense


    the launch- ing of preemptive campaigns that would swiftly move the battles to the territory its enemies. The country did start cooperating with the...Israeli leaders opted for offensive doctrines, enabling the launching of preemptive campaigns that would swiftly move the battles to the territory meant for Israeli analysts was that Saddam Hussein was using Scud missiles to strike Tehran as new means of compellence. This is now cor

  5. Deep intracerebral (basal ganglia) haematomas in fatal non-missile head injury in man.

    Adams, J H; Doyle, D.; Graham, D I; Lawrence, A E; McLellan, D R


    Deep intracerebral (basal ganglia) haematomas were found post mortem in 63 of 635 fatal non-missile head injuries. In patients with a basal ganglia haematoma, contusions were more severe, there was a reduced incidence of a lucid interval, and there was an increased incidence of road traffic accidents, gliding contusions and diffuse axonal injury than in patients without this type of haematoma. Intracranial haematoma is usually thought to be a secondary event, that is a complication of the ori...

  6. Navy Ohio Replacement (SSBN[X]) Ballistic Missile Submarine Program: Background and Issues for Congress


    Missile Submarine Program Congressional Research Service F. Woolf , discusses the SSBN(X) as an element of future U.S. strategic nuclear forces in the...Report RL33640, U.S. Strategic Nuclear Forces: Background, Developments, and Issues, by Amy F. Woolf . 3 In the designations SSN, SSGN, SSBN, and SSBN(X...missions than do SSN operations. For more on the Navy’s SSNs and SSGNs, see CRS Report RL32418, Navy Virginia (SSN-774) Class Attack Submarine

  7. Treatment of open tibial fracture with bone defect caused by high velocity missiles: A case report

    Golubović Zoran


    Full Text Available Introduction .Tibia fracture caused by high velocity missiles is mostly comminuted and followed by bone defect which makes their healing process extremely difficult and prone to numerous complications. Case Outline. A 34-year-old male was wounded at close range by a semi-automatic gun missile. He was wounded in the distal area of the left tibia and suffered a massive defect of the bone and soft tissue. After the primary treatment of the wound, the fracture was stabilized with an external fixator type Mitkovic, with convergent orientation of the pins. The wound in the medial region of the tibia was closed with the secondary stitch, whereas the wound in the lateral area was closed with the skin transplant after Thiersch. Due to massive bone defect in the area of the rifle-missile wound six months after injury, a medical team placed a reconstructive external skeletal fixator type Mitkovic and performed corticotomy in the proximal metaphyseal area of the tibia. By the method of bone transport (distractive osteogenesis, the bone defect of the tibia was replaced. After the fracture healing seven months from the secondary surgery, the fixator was removed and the patient was referred to physical therapy. Conclusion. Surgical treatment of wounds, external fixation, performing necessary debridement, adequate antibiotic treatment and soft and bone tissue reconstruction are essential in achieving good results in patients with the open tibial fracture with bone defect caused by high velocity missiles. Reconstruction of bone defect can be successfully treated by reconstructive external fixator Mitkovic. [Projekat Ministarstva nauke Republike Srbije, br. III 41017 i br. III 41004

  8. Electromagnetic pulse (EMP): Exposure of missile 56 in EMP simulator sapiens

    Dikvall, T.


    The effects on the electric field caused by the object (missile) in the SAPIENS electromagnetic pulse simulator were studied. A noticeable effect on the field strength is noted close to the object, due to the characteristics of the field. This effect also appears in real electromagnetic pulse environments. During these tests 200 pulses were distributed with good accuracy of reproduction. The SAPIENS is an outdoor device and tests carried out in winter show that weather has very little influence on results.

  9. Non-Slender Missile Geometries of Minimum Ballistic Factor via Calculus of Variations

    Manak Singh


    Full Text Available The problem of determining the geometry of non-slender axisymmetric missile of minimum ballistic factor in hypersonic flow has been solved via calculus of variation under the assumption that the flow is Newtonian and the surface averaged skin friction coefficient is constant. The study has been made for conditions of given diameter and surface area. The results obtained have been compared with those obtained by the method of gradient technique.

  10. Complaint Regarding the Use of Audit Results on a $1 Billion Missile Defense Agency Contract


    our scope and methodology. See Appendix B for the sequence of events. Background Missile Defense Agency MDA is a research , development, and...a $2.07 billion cost-plus-fixed/award-fee1 proposal submitted by a DoD contractor for the Ground-Based Midcourse Defense (GMD) Core Completion...negotiated, DCAA discontinued its audit of the GMD proposal. MDA Did Not Consider the DCAA Preliminary Audit Results DFARS Procedures, Guidance , and

  11. Navy Aegis Ballistic Missile Defense (BMD) Program: Background and Issues for Congress


    many ships will be available; and how the alphabet- soup of U.S. and international commanders will work together in a crisis. [Admiral Mark...meeting outside of missile defense,” Campbell said during a Nov. 3 interview with Aviation Week. These include providing weapons and manpower for...would seem a natural mission for the Army to fund and field the land-based SM-3 mission as the lead service. Campbell notes that the Army has 10

  12. Application of fleet ballistic missile components/designs for expendable launch vehicles

    Grizzell, Norman E.

    This paper describes the orbital performance and configuration attributes of an expendable launch vehicle (ELV) derived from flight-qualified components. Representative logistical and programmatic data are also provided. The backbone of the ELV program described is the cost-effective use of proven Fleet Ballistic Missile components/designs coupled with other high confidence 'off-the-shelf' equipment. The ELV defined can place over a thousand pounds (1000 lb) of spacecraft (payload) into Low Earth Orbit.

  13. A qualitative analysis of future air combat with 'fire and forget' missiles

    Shinar, J.; Davidovitz, A.


    A set of previous examples have demonstrated that the two-target game formulation is adequate for modeling air-to-air combat between two aggressively motivated fighter aircraft. The present paper describes such an engagement between two aircraft of different speed but equipped with the same 'fire and forget' type guided missiles. The results of the analysis suggest a new concept of air combat tactics for future scenarios.


    Joelien Pretorius


    American plans for Missile Defence (MD) and the weaponisation of space should be analysed in the larger framework of the contemporary Revolution in Military Affairs (RMA).1 Soviet military analysts have written about this revolution from as early as the 1970s, but it was the application of information age technology (IT) in the 1991 Gulf War that captured the imagination of military planners and policy makers, especially in the US. The US is actively pursuing an RMA, conceptualised as integra...

  15. Echoes That Never Were: American Mobile Intercontinental Ballistic Missiles, 1956-1983


    the remains of three old launch facilities now surrounded by the ubiquitous ice plant and sweet-smelling wildflowers of the California chaparral...1956-1983 Steven Anthony Pomeroy Doctor of Philosophy, May 11, 2006 (M.A., California State University, 1994) (B.A., Pennsylvania State University...the humanities from the California State University. He has had extensive experience in missile and space launch operations, education, training

  16. Ground Based Free Electron Laser Technology Integration Experiment, White Sands Missile Range, New Mexico


    would preclude interference with televisions , radios and computer equipment operated in the area around WSMR. Warning signs will be posted at the...canadensis mexicana ); (2) black-tailed prairie dog (Cynonmys ludovicianus); (3) Colorado chipmunk (Eutamias quadrivittatus australis); (4) White Sands GBFEL TIE equipment, it could disturb local television and radio receivers. Since the GBFEL TIE will be located on White Sands Missile Range (WSMR

  17. Focal Plane Array Sensor for Imaging Infrared Seeker of Antitank Guided Missile

    A.V.R. Warrier


    Full Text Available Technological issues and Processes for fabrication of mercury cadmium telluride detector arrays, charge coupled device readout arrays and integration of these into a focal plane array sensor have been discussed. Mini arrays of 16 X 16 size have been realised and tested to prove the technology and process schedule with a view to scaling up this for larger arrays to be used in the antitank guided missile.

  18. Storage Reliability Missile Materiel Program. Storage Reliability Summary Report. Volume 2. Electromechanical Devices


    these factors places great im- portance on selecting missile materiels which are capable of performing reliably in each of the environments. The... great variety of special features and construction, are available. Latching and time delay are common features, and the reed construction has advantages...represents a reliability study performed under contract to RADC in 1974. This source identified the type and quality grades for the devides , however

  19. The Unauthorized Movement of Nuclear Weapons and Mistaken Shipment of Classified Missile Components: An Assessment


    nonnuclear warhead cruise missiles in the storage structures even though visually recognizing the difference between nuclear and nonnuclear requires...ratification on that promise. Michelle Spencer, Aadina Ludin, and Heather Nelson 38 House? There is a response to that stimuli or lack of stimuli ...Encouraging teamwork  Responsibility. Former Chairman of the Joint Chiefs of Staff General Maxwell D. Taylor stated, ―One expects a military

  20. Environmental Assessment (EA): Proposed Missile Storage Improvements, Utah Test and Training Range


    Prevention Plan TTU Thermal Treatment Unit UAC Utah Administrative Code US United States (of America ) USAF United States Air Force USC United States Code...activities. Wider roads and new missile storage facilities would create a minor loss of habitat, displacing reptiles , avian species, and mammals. The...Photography Guidelines, National Park Service, 2011. US 2010: Treaty Between the United States of America and the Russian Federation on Measures for the

  1. Development of Empirical Prediction Formula for Penetration of Ogive Nose Hard Missile into Concrete Targets

    Ahmad M.A. Zaidi


    Full Text Available Problem statement: Concrete is basic construction material used for most of structures. However, the typical vital structures have to be designed as self-protective such as nuclear plants, power plants, weapon industries, weapons storage places and water retaining structures, against any threats like natural disaster tragedy incident or intentionally produced by horrible incidents such as dynamic loading, incident occurs in nuclear plants, terrorist attack, missile attack tsunami and etc. Approach: In modern science, the impact energies are crucial way to study the local impact effects on concrete structures. Results: The way in which the kinetic energy is distributed through the concrete target is also noteworthy in determining its response, with the influence of dimensional analysis of the non dimensional numbers. This study is concentrate on development of empirical formula for predicting penetration depth of ogive nose hard missile in to the concrete structures, with the effects of different CRH ratios of missile (CRH = 2.0, CRH = 3.0, CRH = 4.5, CRH = 6.0 based on critical impact energies, by using curve fitting dimensional analysis of non-dimensional numbers. Conclusions/Recommendations: For the verification, the proposed developed empirical formula was compared with other established formulae such as Modified NDRC formula, Hughes formula, ACE formula, UKAEA formula. It is expected that the outcome of the proposed formulae can be applied in design recommendations and design procedures, especially for determining the dynamic reaction of the target to foil penetration in terms of critical impact kinetic energy.

  2. Improved manufacturing techniques for RF and laser hardening of missile domes. Phase I. Technical report

    Pawlewicz, W.T.; Mann, I.B.; Martin, P.M.; Hays, D.D.; Graybeal, A.G.


    This report summarizes key results and accomplishements during the first year of a Manufacturing Methods and Technology project to adapt an existing Pacific Northwest Laboratory (PNL) optical coating capability developed for high-power fusion-laser applications to the case of rf and laser hardening of plastic missile domes used by the US Army (MICOM). The primary objective of the first year's work was to demonstrate rf hardening of Hellfire and Copperhead 1.06-micron missile domes by use of transparent conductive Indium Tin Oxide (ITO) coatings. The project thus involved adaptation of a coating material and process developed for flat glass components used in fusion lasers to the case of hemispherical or conical heat-sensitive plastic domes used on laser-guided missiles. Specific ITO coating property goals were an electrical sheet resistance of 10 Ohms/square, a coated-dome transmission of 80% or more at 1.06 micron wavelength (compared to 90% for a bare dome), and good adhesion. The sheet resistance goal of 10 Ohms/square was expected to result in an rf attenuation of 30 dB at the frequencies of importance.

  3. Raman studies for stockpile reliability of missiles by detecting degradation of propellant stabilizers

    Farley, Carlton; Kassu, Aschalew; Mills, Jonathan; Bibb, Jonathan; Curley, Michael; Ruffin, Paul; Sharma, Anup; Rice, Jeremy; McDonald, Brian


    The objective of this study is to demonstrate a sensitive Raman technique for sensing degradation of propellant stabilizers like MNA and 2-NDPA that are commonly used in some missiles. The functionality of missiles and rockets are often evaluated by being fired or decomposed at routine time-intervals after prolonged storage. However, these destructive testing techniques for determining long-term rocket motor aging and shelf-life are extremely costly. If successful, the Raman technique could be utilized to determine the health of propellant stabilizers without dismantling the missiles as is commonly done at present. Raman technique is to measure concentrations of propellant stabilizers between 0.1-2% in glycerin. Two different lasers at 785 nm and 532 nm are used for developing this technique. A secondary objective is to develop a theoretical model that predicts temperature as a function of time and position inside the cylindrical storage container of MNA or 2-NDPA stabilizer. This model can help in understanding the thermal degradation of propellant stabilizers.

  4. Missile target interaction analysis of B747 aircraft using hydro code LSDYNA

    Lee, Kyoung Soo; Hong, Jung Wuk [KAIST, Daejeon (Korea, Republic of)


    After the 11 September 2011, we newly recognized the importance of intentional aircraft impact on national critical infrastructure such as tall buildings, military facilities, and nuclear power plants. A lot of research has been performed to measure the capability of current nuclear power plants to withstand unusual impact loadings. As a result, Nuclear Regulatory Commission (NRC) concluded that the impact of a large, commercial aircraft is a beyond design basis event (BDBE). In this paper, we demonstrate the assessment of the impact load of large, commercial B747 aircraft by using the so called missile target interaction analysis method. The results of impact force is compared with the reported impact force time histories of B747. To perform the missile target interaction analysis, an FE mesh model of B747 is developed. Rigid wall impact tests are performed numerically using commercial Hydro code LS DYNA with FE model of B747 to demonstrate the accuracy and applicability of the rigorous missile target interaction analysis.

  5. Upper and lower extremity nerve injuries in pediatric missile wounds: a selective approach to management.

    Stoebner, Andrew A; Sachanandani, Neil S; Borschel, Gregory H


    Nerve injuries from missile and gunshot wounds often produce significant disability, and their management is controversial. The role of the surgeon in cases of missile wounds with neurologic deficits is not well defined. Enhancing the trauma team's ability to recognize treatable nerve injuries will lead to improved outcomes. Further, raising awareness of the time-sensitive nature of these injuries will also improve results in these cases. We reviewed a consecutive series of 17 pediatric patients with peripheral nerve injuries caused by missile and gunshot wounds in a tertiary care children's hospital. We examined the indications for surgery, presence of associated injuries, mechanisms of injury, demographic characteristics and clinical outcomes. Urban victims were significantly more likely to have been intentionally assaulted than rural or suburban victims and they were also less likely to have completed follow-up care. High-energy weapons were more likely to require surgery compared with low-energy weapons. Patients presenting with tendon injuries were more likely to have a high-grade nerve injury requiring surgery. Patients presenting with tendon lacerations or high-energy mechanisms were significantly more likely to require surgery. Early exploration should be undertaken in cases where transection is likely to have occurred. Early decompression of common entrapment sites distal to repairs or injuries should be performed. Because follow-up is poor in this population, treatment should be prompt and thorough.

  6. Study on the Analytical Behaviour of Concrete Structure Against Local Impact of Hard Missile

    Ahmad Mujahid Ahmad Zaidi


    Full Text Available Concrete is basic construction material used for almost all kind of structure. However, in the majority essential structures such as nuclear plants, Power plants, Weapon Industries, weapons storage places, water retaining structures like dams, highways barriers, bridges, & etc., concrete structures have to be designed as self-protective structure which can afford any disaster or consciously engendered unpleasant incidents such as incident occurs in nuclear plants, incident in any essential industry, terrorist attack, Natural disasters like tsunami and etc missile attack, and local impact damage generated by kinetic missiles dynamic loading (steel rods, steel pipes, turbine blades, etc.. This paper inquisitively is paying attention on verdict of the recent development in formulating analytical behavior of concrete and reinforced concrete structures against local impact effect generated by hard missile with and without the influence of dimensional analysis based on dominant non-dimensional parameters, various nose shape factors at normal and certain inclined oblique angles. The paper comprises the analytical models and methods for predicting penetration, and perforation of concrete and reinforced concrete. The fallout conquer from this study can be used for making design counsel and design procedures for seminal the dynamic retort of the concrete targets to foil local impact damage.

  7. System Analysis and Design of a Low-Cost Micromechanical Seeker System


    acting as a shutter , periodically blocking out the noise during the time that the laser designation signal is not emitted. So, to account for the...g-tolerance for the thesis application. 48 Aero -thermodynamic Heating The system designer must also be sure that the aero -thermodynamic...munition is similar to other missile geometries. The temperature due to aero - thermodynamic heating at the outer surface of the missile nose is calculated

  8. 导弹虚拟战场环境设计与实现%Design and Implementation of A Missile's Virtual Battlefield Environment

    赵海龙; 李佳泽; 郑重; 李朋飞


    为给某型导弹部队提供一个全新的演习、训练和战前要素熟悉平台,文中通过VC++6.0和该实验室自行开发的软件Deep Eye平台设计和实现了导弹虚拟战场环境演示系统.首先根据系统分析对系统整体结构进行了模块化设计,然后从场景生成和效果实现两方面对各模块进行开发,先后建立了天空模型、地形背景模型、战场实体模型,并对地形匹配、航迹规划、特殊效果实现、视点变换、交互接口设计等关键技术做了研究,最后实现了适合于导弹作战的虚拟战场环境模型.结果表明,该设计方案可行,仿真效果良好.%To give a certain type of missile units for a new exercise,training and pre-war elements familiar platform,the missile's virtual battlefield environment demo system is designed and achieved on VC++6.0 and Deep Eye in this paper. The system overall structure is a-dopted modular design according to the system analysis, and then from two aspects of the modular design scene generation and effect each module is developed,has established a model of the sky,the terrain background model,battlefield solid model and the key technology such as terrain matching,path planning,special effects to achieve, the focus transformation and interactive interface are researched. At last,achieve a suitable model of the virtual battlefield environment for missile combat. The results shows that the design scheme is feasible and the simulation result is good.

  9. Study on Method for Simultaneously Tracking and Classifying Ballistic Missile in Boost and Post-boost Phase%弹道导弹助推段同时跟踪和类型识别算法研究

    陈映; 程臻; 文树梁


    It is meaningful to tracking ballistic missile in boost phase precisely by forward ground-based radar for the whole antimissile defensive system. The paper presents a new method to track ballistic missile in boost and post-boost phase based on prior database. At first, the paper extracts characteristic dynamic parameters of ballistic missile, and analyzes the sensitivities of these parameters and gives a time invariant dynamic model with parameters; then the paper simulates the performance for tracking ballistic missile in boost and post-boost phase with IMM and IUF algorithm. Compared with other dynamic models and algorithms, this new method has much higher tracking precision and by calculating the model transition prohabilities, it can classify the ballistic missiles and indicates the burnout time accurately. The simulation results validate the new method.%前置地基雷达跟踪助推段弹道导弹对整个反导防御系统有着重要意义.本文提出了一种以情报数据库为先验知识的弹道导弹助推段及后助推段跟踪方法.首先从动力学角度提取导弹助推段飞行的特征参量,并对参量的敏感度进行了分析,给出了一种参变的助推段弹道导弹时不变运动模型.然后结合交互式多模型(IMM)和迭代无敏滤波(IUF)算法进行助推段及后助推段弹道导弹跟踪仿真.与采用其他的运动模型和滤波算法相比,该方法能实现对弹道导弹助推段及后助推段更高精度的跟踪,同时结合情报数据库通过计算模型转移概率可完成导弹类型初判别,并准确指示导弹关机时刻.文章通过仿真验证了该算法的有效性.

  10. On a New Six Degree of Freedom Modelling Method for Homing Missiles and its Application for Design/Analysis

    R. N. Bhattacherjee


    Full Text Available Development of an accurate six-degree-of-freedom (6-DOF simulation model for homing missiles incorporating seeker servosystem detailed modelling is reported. A new modelling concept for seeker servosystem simulation, the Newtonian equivalent model (NEM has been evolved, where body motion coupling is modelled through forces and moments transformed to the seeker. The NEM-based modelling of seeker head and its integration in 6-DOF has been discussed. In the presence of body coupling, the simulation model for seeker tracking or pointing error, gimbal angles and inertial line of sight (LOS rates as measured by the seeker mounted rate gyros have been obtained through the new modelling method. A novel method of obtaining optimum pitch and yaw LOS rates for proportional navigation (PN guidance mechanisation is formulated based on synthesised sight line rates measured in the seeker inner gimbal axis. This new method has been validated through simulation studies using the 6-DOF model developed and by comparing the results with those obtained by the conventional method of generating LOS rates for PN guidance. Other important applications of the 6-DOF model discussed are guidance and control design validation/tuning seeker feedforward compensation design tuning of switchover point from open-loop to closed-loop PN guidance. Importance of the detailed 6-DOF simulation model as the ultimate performance evaluation tool for the weapon system in terms of both terminal performance and adequacy of seeker field of view, gimbal angle freedom, etc. has been brought out.

  11. Buying for Armageddon: Factors influencing post-World War II weapons purchases since the Cuban Missile Crisis

    Boies, J.L.


    The central problem of this study is the role that the economy and economic interests play in decisions about US weapons-systems acquisition. Despite a voluminous literature discussing the formation of military policy, journalistic accounts of business influence on military policy dominate the literature. A notable exception to this pattern is Griffin, Devine, and Wallace's use of time-series data on military expenditures to assess Baran and Sweezy's thesis that military expenditures are necessary to the good health of the monopoly sector of the US economy. Using similar techniques and an expanded data set, the effect of business political action and major economic forces on the quantity and types of weapons purchased since the Cuban Missile Crisis are investigated. Findings indicate that defense contractor rates of profit have a positive relationship to procurement expenditures of most types. This is opposite of the effect posited by most of the literature. Elite political mobilization, measured by the activity of the Committee on the Present Danger, a group at the core of the New Right Social Movement, has a positive effect on expenditures.

  12. Computer program for post-flight evaluation of the control surface response for an attitude controlled missile

    Knauber, R. N.


    A FORTRAN IV coded computer program is presented for post-flight analysis of a missile's control surface response. It includes preprocessing of digitized telemetry data for time lags, biases, non-linear calibration changes and filtering. Measurements include autopilot attitude rate and displacement gyro output and four control surface deflections. Simple first order lags are assumed for the pitch, yaw and roll axes of control. Each actuator is also assumed to be represented by a first order lag. Mixing of pitch, yaw and roll commands to four control surfaces is assumed. A pseudo-inverse technique is used to obtain the pitch, yaw and roll components from the four measured deflections. This program has been used for over 10 years on the NASA/SCOUT launch vehicle for post-flight analysis and was helpful in detecting incipient actuator stall due to excessive hinge moments. The program is currently set up for a CDC CYBER 175 computer system. It requires 34K words of memory and contains 675 cards. A sample problem presented herein including the optional plotting requires eleven (11) seconds of central processor time.

  13. U.S.S.R. disposed of nuclear mini reactors for missiles; L'URSS disposait de minireacteurs nucleaires pour missiles

    Kempf, H


    A Byelorussian savant, Vassili Nesterenko, reveals that Moscow had developed, in the eighties years very light and mobile reactors to supply steps of fire of its missiles. The Chernobylsk accident has stopped this project. The realizations of these nuclear plants were called Pamir. In 200, it was question to launch again this project but for civil applications. In 2002, the Russian Minister of Atomic Energy has launched the idea of floating nuclear power plants that could be installed in the region of Arkhangelsk (North west of russia) and on the river banks of Tchoukotka (North east of the Siberia). The nuclear power plants would be constituted of two 35 MW reactors coming from ice-breakers and would cost 180 millions dollars. They would be installed on a big barge anchored near the coast. But this project has risen numerous notices because of their insufficient safety. (N.C.)

  14. Missile Defense: Opportunity to Refocus on Strengthening Acquisition Management


    defense operations, see the battle develop, and manage networked sensors and weapon systems. Ground-based Midcourse Defense (GMD) A ground-based...However, this retest also failed in December 2010 due to the effects of vibration on the kill vehicle’s guidance system. As a result of these...the life cycle— research and development, procurement, military construction, GAO-13-432. 15Pub. L. No. 110-181, § 223(g), repealed by Pub. L. No

  15. 基于引用Petri网的导弹攻防对抗仿真研究%Research on missile confrontation simulation based on reference Petri net

    唐硕; 禹磊


    Missile confrontation system is a complex and dynamic system with both sides interacting with each other. Especially,engagement level simulation will contain more objects and interaction. Petri net is a powerful graphical tool describing complex system with the feature of concurrence,distribution and uncertainty. Objected-oriented Petri net is formed by combining traditional Petri net with objected-orien-ted technology. Reference net is one of the objected-oriented Petri net,which has many excellent characteristics. This paper applies the basic theory of reference net,explores its application in the missile confrontation simulation,and realizes one confrontation simulation instance.%导弹攻防对抗是一个攻防双方相交互的复杂动态系统,尤其对于交战级仿真,会涉及到更多的对象及其交互.Petri网是一种图形化的描述,具有并发、分布、不确定性等特征的复杂系统的有力工具,通过将传统Petri网理论同面向对象技术相结合,形成了面向对象Petri网.引用Petri网作为具有面向对象特征的Petri网的一种,具有更多优良的特性.应用引用网的基本理论,探讨了引用网在导弹对抗仿真中的应用,完成了一个攻防对抗算例的仿真研究.

  16. 多平台对AAM协同制导交接班模型%Multi-P latform Cooperative Guidance Model for Anti-aircraft Missile

    雷宇曜; 姜文志; 朱伟; 张声


    This article provides a detailed analysis of the components of anti⁃aircraft missile system and engagement flow. It gives some definition and concept of cooperative guidance. The AAWS ( Anti⁃aircraft Weapon System) for AAM ( Anti⁃air⁃craft Missile) cooperative guidance model is established. It contains concept model of system, coordinate transaction model, errors model and radar tracking probability model. Radom errors are simulated. The Monte⁃Carlo method is used to have the relationship between errors and cooperative guidance ship probability. The reliable of cooperative guidance model is proved by simulation, which established in this paper. The results of error analysis can be used for precision controlling.%通过对协同制导交接班的类型进行分析,建立了防空武器系统对AAM( Anti⁃aircraft Missile)协同制导交接班的坐标转换模型、误差模型及雷达截获概率模型。通过模拟产生随机误差,利用Monte⁃Carlo方法进行计算,得出不同误差源对协同制导交接班概率影响的定量关系。实验结果证明了所建模型的有效性,误差分析结论可作为协同制导交接班精度控制的依据。

  17. Missile Defense: Assessment of DODs Reports on Status of Efforts and Options for Improving Homeland Missile Defense


    locked into the original suppliers. Conversely, an open system, such as a personal computer , allows system components to be added, removed, modified...Express, Discover Card, MasterCard, Visa, check, or money order. Call for additional information. Connect with GAO on Facebook , Flickr, Twitter, and

  18. Synergetic Optimization of Missile Shapes for Aerodynamic and Radar Cross-Section Performance Based on Multi- objective Evolutionary Algorithm



    A multiple-objective evolutionary algorithm (MOEA) with a new Decision Making (DM) scheme for MOD of conceptual missile shapes was presented, which is contrived to determine suitable tradeoffs from Pareto optimal set using interactive preference articulation. There are two objective functions, to maximize ratio of lift to drag and to minimize radar cross-section (RCS) value. 3D computational electromagnetic solver was used to evaluate RCS, electromagnetic performance. 3D Navier-Stokes flow solver was adopted to evaluate aerodynamic performance. A flight mechanics solver was used to analyze the stability of the missile. Based on the MOEA, a synergetic optimization of missile shapes for aerodynamic and radar cross-section performance is completed. The results show that the proposed approach can be used in more complex optimization case of flight vehicles.

  19. Navy Air-Launched Missile Operating and Support Cost Estimating Model


    same manner as the previous oneexcept that half of the missile poundage is shipped in dromedary units. All routes are calculated with Dual Driver...Protective Service. Dromedary Rate Min. Wt. Security Rate Factor Origin % ($/cwt) (thous.of ibs) ( )t. GIC NWS Yorktown 50.0 38.63 2,500 21.84 60.47 30.24...ll I I IIII • I I N i l ll II Hium-+ ii[ii~ i 1j 78 The preceding calculation refers only to the rates for the poundage shipped in dromedary units. To

  20. Boost-Phase ballistic missile trajectory estimation with ground based radar

    Tang Yuyan; Huang Peikang


    A conditional boost-phase trajectory estimation method based on ballistic missile (BM) information database and classification is developed to estimate and predict boos-phase BM trajectory. The main uncertain factors to describe BM dynamics equation are reduced to the control law of trajectory pitch angle in boost-phase. After the BM mass at the beginning of estimation, the BM attack angle and the modification of engine thrust denoting BM acceleration are modeled reasonably, the boost-phase BM trajectory estimation with ground based radar is well realized. The validity of this estimation method is testified by computer simulation with a typical example.