WorldWideScience

Sample records for airplanes

  1. 77 FR 50644 - Airworthiness Directives; Cessna Airplane Company Airplanes

    Science.gov (United States)

    2012-08-22

    ... 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... Directives; Cessna Airplane Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... certain Cessna Airplane Company Model 525 airplanes equipped with certain part number (P/N)...

  2. Mars Gashopper Airplane Project

    Data.gov (United States)

    National Aeronautics and Space Administration — The Mars Gas Hopper Airplane, or "gashopper" is a novel concept for propulsion of a robust Mars flight and surface exploration vehicle that utilizes indigenous CO2...

  3. The Bristol "Badminton" Airplane

    Science.gov (United States)

    1926-01-01

    The Bristol Badminton, Type 99 airplane has a radial aircooled engine (a Bristol Jupiter 9 cylinder 450 HP.) and three fuel tanks. It is a single seat biplane weighing 1,840 lbs. empty and 2,460 lbs. loaded.

  4. Prospect of ultralight airplanes development

    Directory of Open Access Journals (Sweden)

    Adam KONICZEK

    2015-09-01

    Full Text Available The article presents characteristic of ultralight airplanes, rules and current interest of them. The purpose is to determine prospect of ultralight airplanes development on the basis of Civil Aviation Authority statistics analysis and trend of aviation market.

  5. Flatulence on airplanes

    DEFF Research Database (Denmark)

    Pommergaard, Hans-Christian; Burcharth, Jakob; Fischer, Anders;

    2013-01-01

    Flatus is natural and an invariable consequence of digestion, however at times it creates problems of social character due to sound and odour. This problem may be more significant on commercial airplanes where many people are seated in limited space and where changes in volume of intestinal gases......, due to altered cabin pressure, increase the amount of potential flatus. Holding back flatus on an airplane may cause significant discomfort and physical symptoms, whereas releasing flatus potentially presents social complications. To avoid this problem we humbly propose that active charcoal should be...... airplanes, by using a methane breath test or to alter the fibre content of airline meals in order to reduce its flatulent potential. We conclude that the use of active charcoal on airlines may improve flight comfort for all passengers....

  6. Flatulence on airplanes

    DEFF Research Database (Denmark)

    Pommergaard, Hans C; Burcharth, Jakob; Fischer, Anders;

    2013-01-01

    Flatus is natural and an invariable consequence of digestion, however at times it creates problems of social character due to sound and odour. This problem may be more significant on commercial airplanes where many people are seated in limited space and where changes in volume of intestinal gases...... airplanes, by using a methane breath test or to alter the fibre content of airline meals in order to reduce its flatulent potential. We conclude that the use of active charcoal on airlines may improve flight comfort for all passengers....

  7. 14 CFR 36.7 - Acoustical change: Transport category large airplanes and jet airplanes.

    Science.gov (United States)

    2010-01-01

    ... airplanes and jet airplanes. 36.7 Section 36.7 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... § 36.7 Acoustical change: Transport category large airplanes and jet airplanes. (a) Applicability. This section applies to all transport category large airplanes and jet airplanes for which an acoustical...

  8. 14 CFR 23.3 - Airplane categories.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Airplane categories. 23.3 Section 23.3... STANDARDS: NORMAL, UTILITY, ACROBATIC, AND COMMUTER CATEGORY AIRPLANES General § 23.3 Airplane categories. (a) The normal category is limited to airplanes that have a seating configuration, excluding...

  9. Differential equations in airplane mechanics

    Science.gov (United States)

    Carleman, M T

    1922-01-01

    In the following report, we will first draw some conclusions of purely theoretical interest, from the general equations of motion. At the end, we will consider the motion of an airplane, with the engine dead and with the assumption that the angle of attack remains constant. Thus we arrive at a simple result, which can be rendered practically utilizable for determining the trajectory of an airplane descending at a constant steering angle.

  10. Airplane Upset Training Evaluation Report

    Science.gov (United States)

    Gawron, Valerie J.; Jones, Patricia M. (Technical Monitor)

    2002-01-01

    Airplane upset accidents are a leading factor in hull losses and fatalities. This study compared five types of airplane-upset training. Each group was composed of eight, non-military pilots flying in their probationary year for airlines operating in the United States. The first group, 'No aero / no upset,' was made up of pilots without any airplane upset training or aerobatic flight experience; the second group, 'Aero/no upset,' of pilots without any airplane-upset training but with aerobatic experience; the third group, 'No aero/upset,' of pilots who had received airplane-upset training in both ground school and in the simulator; the fourth group, 'Aero/upset,' received the same training as Group Three but in addition had aerobatic flight experience; and the fifth group, 'In-flight' received in-flight airplane upset training using an instrumented in-flight simulator. Recovery performance indicated that clearly training works - specifically, all 40 pilots recovered from the windshear upset. However few pilots were trained or understood the use of bank to change the direction of the lift vector to recover from nose high upsets. Further, very few thought of, or used differential thrust to recover from rudder or aileron induced roll upsets. In addition, recovery from icing-induced stalls was inadequate.

  11. 75 FR 39804 - Airworthiness Directives; The Boeing Company Model 757 Airplanes, Model 767 Airplanes, and Model...

    Science.gov (United States)

    2010-07-13

    ... airplanes. That NPRM was published in the Federal Register on March 13, 2008 (73 FR 13483). That NPRM... ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), and (3) Will... Model 757 Airplanes, Model 767 Airplanes, and Model 777-200 and -300 Series Airplanes AGENCY:...

  12. 14 CFR 121.605 - Airplane equipment.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane equipment. 121.605 Section 121.605..., FLAG, AND SUPPLEMENTAL OPERATIONS Dispatching and Flight Release Rules § 121.605 Airplane equipment. No person may dispatch or release an airplane unless it is airworthy and is equipped as prescribed in §...

  13. 14 CFR 125.93 - Airplane limitations.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane limitations. 125.93 Section 125.93...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Airplane Requirements § 125.93...

  14. 14 CFR 125.75 - Airplane flight manual.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane flight manual. 125.75 Section 125... Airplane flight manual. (a) Each certificate holder shall keep a current approved Airplane Flight Manual or... approved Airplane Flight Manual or the approved equivalent aboard each airplane it operates. A...

  15. Supersonic airplane study and design

    Science.gov (United States)

    Cheung, Samson

    1993-01-01

    A supersonic airplane creates shocks which coalesce and form a classical N-wave on the ground, forming a double bang noise termed sonic boom. A recent supersonic commercial transport (the Concorde) has a loud sonic boom (over 100 PLdB) and low aerodynamic performance (cruise lift-drag ratio 7). To enhance the U.S. market share in supersonic transport, an airframer's market risk for a low-boom airplane has to be reduced. Computational fluid dynamics (CFD) is used to design airplanes to meet the dual constraints of low sonic boom and high aerodynamic performance. During the past year, a research effort was focused on three main topics. The first was to use the existing design tools, developed in past years, to design one of the low-boom wind-tunnel configurations (Ames Model 3) for testing at Ames Research Center in April 1993. The second was to use a Navier-Stokes code (Overflow) to support the Oblique-All-Wing (OAW) study at Ames. The third was to study an optimization technique applied on a Haack-Adams body to reduce aerodynamic drag.

  16. 78 FR 72834 - Airworthiness Directives; SOCATA Airplanes

    Science.gov (United States)

    2013-12-04

    ... 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... Directives; SOCATA Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT... (AD) for SOCATA Model TBM 700 airplanes. This proposed AD results from mandatory...

  17. 78 FR 46536 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-08-01

    ... Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... B4-600R series airplanes. This proposed AD was prompted by reports of cracks found in the bottom...

  18. 14 CFR 125.355 - Airplane equipment.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane equipment. 125.355 Section 125.355...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Flight Release Rules § 125.355...

  19. 78 FR 40057 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-07-03

    ... Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... A321 series airplanes. This proposed AD was prompted by reports of certain sliding windows that...

  20. Error Analysis of Determining Airplane Location by Global Positioning System

    OpenAIRE

    Hajiyev, Chingiz; Burat, Alper

    1999-01-01

    This paper studies the error analysis of determining airplane location by global positioning system (GPS) using statistical testing method. The Newton Rhapson method positions the airplane at the intersection point of four spheres. Absolute errors, relative errors and standard deviation have been calculated The results show that the positioning error of the airplane varies with the coordinates of GPS satellite and the airplane.

  1. 14 CFR 21.5 - Airplane or Rotorcraft Flight Manual.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Airplane or Rotorcraft Flight Manual. 21.5... CERTIFICATION PROCEDURES FOR PRODUCTS AND PARTS General § 21.5 Airplane or Rotorcraft Flight Manual. (a) With each airplane or rotorcraft that was not type certificated with an Airplane or Rotorcraft Flight...

  2. Visual servoing of an airplane for auto-landing

    OpenAIRE

    Bourquardez, O.; Chaumette, François

    2007-01-01

    International audience In this paper, a visual servoing scheme is proposed to control an airplane during its landing. A linearized model of the airplane dynamics and decoupled visual features are used to build the control scheme. A desired trajectory which takes into account the airplane dynamic is designed. Coupling this trajectory and the control law enables the airplane to join its desired path. Then the airplane is controlled to follow the glide path, realize the flare manoeuvre and fi...

  3. 14 CFR 121.331 - Supplemental oxygen requirements for pressurized cabin airplanes: Reciprocating engine powered...

    Science.gov (United States)

    2010-01-01

    ... pressurized cabin airplanes: Reciprocating engine powered airplanes. 121.331 Section 121.331 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIR CARRIERS AND... pressurized cabin airplanes: Reciprocating engine powered airplanes. (a) When operating a reciprocating...

  4. Installing paparazzi autopilot into a model airplane

    OpenAIRE

    Ojala, Allan

    2010-01-01

    This Bachelor degree study explores the open source Autopilot “Paparazzi” that was installed into a model airplane. The aim for this was to get the model airplane to fly short flight and study what difficulties there are in a project like this. The field of UAV research is innovative and number of companies selling ready UAV products is growing, also many education institutes and amateurs are making their own implementations of UAVs. Paparazzi autopilot is a complete system of hardware a...

  5. 77 FR 2238 - Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

    Science.gov (United States)

    2012-01-17

    ... (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not... Industries PC-6 airplanes, Fairchild Heli Porter PC-6 airplanes, or Fairchild-Hiller Corporation...

  6. 14 CFR 125.407 - Maintenance log: Airplanes.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Maintenance log: Airplanes. 125.407 Section... Maintenance log: Airplanes. (a) Each person who takes corrective action or defers action concerning a reported... record the action taken in the airplane maintenance log in accordance with part 43 of this chapter....

  7. 14 CFR 121.303 - Airplane instruments and equipment.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane instruments and equipment. 121.303... Airplane instruments and equipment. (a) Unless otherwise specified, the instrument and equipment... airspeed limitation and item of related information in the Airplane Flight Manual and pertinent...

  8. 14 CFR 125.91 - Airplane requirements: General.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane requirements: General. 125.91... AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Airplane...

  9. 14 CFR 61.159 - Aeronautical experience: Airplane category rating.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Aeronautical experience: Airplane category... Transport Pilots § 61.159 Aeronautical experience: Airplane category rating. (a) Except as provided in... certificate with an airplane category and class rating must have at least 1,500 hours of total time as a...

  10. 14 CFR 121.161 - Airplane limitations: Type of route.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane limitations: Type of route. 121... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Aircraft Requirements § 121.161 Airplane... specifications, no certificate holder may operate a turbine-engine-powered airplane over a route that contains...

  11. 14 CFR 121.570 - Airplane evacuation capability.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane evacuation capability. 121.570... REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Operations § 121.570 Airplane evacuation capability. (a) No person may cause an airplane carrying passengers to be moved on the surface, take off,...

  12. 14 CFR 23.71 - Glide: Single-engine airplanes.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Glide: Single-engine airplanes. 23.71... AIRWORTHINESS STANDARDS: NORMAL, UTILITY, ACROBATIC, AND COMMUTER CATEGORY AIRPLANES Flight Performance § 23.71 Glide: Single-engine airplanes. The maximum horizontal distance traveled in still air, in nautical...

  13. 14 CFR 121.141 - Airplane flight manual.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane flight manual. 121.141 Section 121... REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Manual Requirements § 121.141 Airplane flight manual. (a) Each certificate holder shall keep a current approved airplane flight manual for each type...

  14. 78 FR 61161 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-10-03

    ...-247-AD; Amendment 39-17602; AD 2013-19-20] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for certain The Boeing Company Model DC-10-10 and MD-10-10F airplanes... MLG and consequent damage to airplane structure, which could adversely affect the airplane's...

  15. 77 FR 50054 - Airworthiness Directives; Cessna Aircraft Company Airplanes

    Science.gov (United States)

    2012-08-20

    ... Directives; Cessna Aircraft Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... certain Cessna Aircraft Company Models 172R and 172S airplanes. This proposed AD was prompted by reports... tube assembly and the airplane structure; and adjustment as necessary. We are proposing this AD...

  16. 78 FR 42417 - Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

    Science.gov (United States)

    2013-07-16

    ... during production could reduce the structural integrity of the airplane. We are issuing this AD to... faulty rivets installed in the airframes during production could reduce the structural integrity of the airplane. We are issuing this AD to ensure the structural integrity of the airplane. (f) Actions...

  17. Headache attributed to airplane travel (“airplane headache”: first italian case

    OpenAIRE

    Mainardi, Federico; Lisotto, Carlo; Palestini, Claudia; Sarchielli, Paola; Maggioni, Ferdinando; Zanchin, Giorgio

    2007-01-01

    A new form of headache, whose attacks seem to be stereotyped, has been recently reported; because of the peculiarity of its onset, strictly related to airplane travel, the name of “Airplane headache” was proposed. A total of 7 cases have been published. Here we present the first Italian one. Furthermore the revision of the clinical characteristics of each patient leads us to propose provisional diagnostic criteria.

  18. Performance Comparison of the Optimized Inverted Joined Wing Airplane Concept and Classical Configuration Airplanes

    Directory of Open Access Journals (Sweden)

    Sieradzki Adam

    2016-09-01

    Full Text Available The joined wing concept is an unconventional airplane configuration, known since the mid-twenties of the last century. It has several possible advantages, like reduction of the induced drag and weight due to the closed wing concept. The inverted joined wing variant is its rarely considered version, with the front wing being situated above the aft wing. The following paper presents a performance prediction of the recently optimized configuration of this airplane. Flight characteristics obtained numerically were compared with the performance of two classical configuration airplanes of similar category. Their computational fluid dynamics (CFD models were created basing on available documentation, photographs and some inverse engineering methods. The analysis included simulations performed for a scale of 3-meter wingspan inverted joined wing demonstrator and also for real-scale manned airplanes. Therefore, the results of CFD calculations allowed us to assess the competitiveness of the presented concept, as compared to the most technologically advanced airplanes designed and manufactured to date. At the end of the paper, the areas where the inverted joined wing is better than conventional airplane were predicted and new research possibilities were described.

  19. 78 FR 66861 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-11-07

    ... required repetitive inspections to check the play of the eye-end of the piston rod of the elevator servo... piston rod of the elevator servo controls, which could result in failure of the elevator servo-control... replacing certain retraction brackets of the main landing gear; and revising the airplane flight...

  20. Computing Airplane Stopping Distance: Applications of Derivatives.

    Science.gov (United States)

    Tylee, J. Louis

    1997-01-01

    Presents two real world applications that use derivatives and are related to computing the distance required to stop an airplane. Examines the curve-fitting techniques used to develop an equation for braking force and develops equations for the deceleration and speed. (DDR)

  1. Two-stroke-cycle engines for airplanes

    Science.gov (United States)

    Jalbert, J

    1926-01-01

    Now that the two-stroke-cycle engine has begun to make its appearance in automobiles, it is important to know what services we have a right to expect of it in aeronautics, what conditions must be met by engines of this type for use on airplanes and what has been accomplished.

  2. 78 FR 8054 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-02-05

    ...-07, Amendment 39-13741 (69 FR 44592, July 27, 2004). For airplanes on which Airbus Modification 5106...-07, Amendment 39-13741 (69 FR 44592, July 27, 2004). That AD required actions intended to address an... (69 FR 44592, July 27, 2004), the manufacturer has done a reassessment of the previous...

  3. 78 FR 78705 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-12-27

    ..., Amendment 39-16526 (75 FR 75878, December 7, 2010). Except for airplanes on which Airbus Modification 34804... publications listed in this AD as of January 11, 2011 (75 FR 75878, December 7, 2010). ADDRESSES: You may... 14, 2013 (78 FR 28152), and proposed to supersede AD 2010-24-07, Amendment 39-16526 (75 FR...

  4. Operation peculiarities of airplane brake systems

    Directory of Open Access Journals (Sweden)

    В. Г. Докучаев

    1999-09-01

    Full Text Available Analyzed is the loading of airplane brake systems. Complex methods are proposed for investi­gation of highly loaded brake systems. The results of investigation of the influence of various factors on technical condition of friction units are given

  5. 78 FR 78694 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-12-27

    ..., Amendment 39-16068 (74 FR 62208, November 27, 2009)), whichever occurs first. (B) For airplanes on which... as of December 14, 2009 (74 FR 62208, November 27, 2009). ADDRESSES: You may examine the AD docket on... products. The NPRM was published in the Federal Register on May 8, 2013 (78 FR 26716), and proposed...

  6. 78 FR 70207 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-11-25

    ... (FR) 41 and FR 46, on one A300-600 aeroplane a crack was detected in the area 2 of the foot of frame... INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane.... SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part...

  7. 78 FR 78294 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-12-26

    ... INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane...-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data... specified products. The MCAI states: During Final Assembly Line tests on an A330 aeroplane, the...

  8. Developing aircraft photonic networks for airplane systems

    DEFF Research Database (Denmark)

    White, Henry J.; Brownjohn, Nick; Baptista, João;

    2013-01-01

    Achieving affordable high speed fiber optic communication networks for airplane systems has proved to be challenging. In this paper we describe a summary of the EU Framework 7 project DAPHNE (Developing Aircraft Photonic Networks). DAPHNE aimed to exploit photonic technology from terrestrial comm...

  9. 76 FR 65419 - Airworthiness Directives; SOCATA Airplanes

    Science.gov (United States)

    2011-10-21

    ... identified in this proposed AD, contact SOCATA--Direction des Services--65921 Tarbes Cedex 9--France... deflection, Socata's analysis shows that the airplane is still capable of achieving its published cross wind... distribution of power and responsibilities among the various levels of government. For the reasons...

  10. 14 CFR 129.25 - Airplane security.

    Science.gov (United States)

    2010-01-01

    ... security. Foreign air carriers conducting operations under this part must comply with the applicable security requirements in 49 CFR chapter XII. ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane security. 129.25 Section...

  11. 77 FR 14679 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-03-13

    ... service information was approved for IBR on IBR June 24, 2002 (67 FR 35425, May 20, 2002). (i) Airbus... asymmetry during landing, with controllability and deceleration consequences. We are issuing this AD to prevent thrust asymmetry conditions which could result in loss of control of the airplane during...

  12. Perturbed Motion of Airplane and Safe Store Separation

    Directory of Open Access Journals (Sweden)

    S. C. Raisinghani

    1984-07-01

    Full Text Available A method is presented to predict the perturbed motion of an airplane following stores jettisoning. The mass, moment of inertia, forces, and moments acting on the airplane are suitable split into contributions from the stores and the rest of the airplane parts. The seperation of stores is assumed to result in a step change of mass, moment of intertai, forces, and moments contributed by stores. The resulting set of perturbed state equations of motion are solved for two illustrative airplane stroes combination. A criterion is evolved to qualitatively indicate locations for safe store separation. It is suggested that the present method be used to predict airplane perturbed motion following stores separation for a given airplane store combination and results be used in conjunction with store trajectory analysis for finally declaring a store location as safe unsafe.

  13. 78 FR 21700 - Aviation Rulemaking Advisory Committee Meeting on Transport Airplane and Engine Issues

    Science.gov (United States)

    2013-04-11

    ... Engine Issues AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of public meeting...) Transportation Airplane and Engine (TAE) Subcommittee to discuss transport airplane and engine issues. DATES:...

  14. 77 FR 40699 - Aviation Rulemaking Advisory Committee Teleconference on Transport Airplane and Engine Issues

    Science.gov (United States)

    2012-07-10

    ... Airplane and Engine Issues AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of public... Committee (ARAC) to discuss transport airplane and engine (TAE) issues. DATES: The teleconference...

  15. Experimental test of airplane boarding methods

    CERN Document Server

    Steffen, Jason H

    2011-01-01

    We report the results of an experimental comparison of different airplane boarding methods. This test was conducted in a mock 757 fuselage, located on a Southern California soundstage, with 12 rows of six seats and a single aisle. Five methods were tested using 72 passengers of various ages. We found a significant reduction in the boarding times of optimized methods over traditional methods. These improved methods, if properly implemented, could result in a significant savings to airline companies.

  16. 78 FR 21854 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-04-12

    ... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation... Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice... certain The Boeing Company Model 747-400 and -400F series airplanes. This proposed AD was prompted by...

  17. 78 FR 25905 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-05-03

    ... airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November... fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746... Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4)...

  18. 78 FR 59304 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-09-26

    ... Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will... Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This proposed AD was...

  19. Variable-Structure Control of a Model Glider Airplane

    Science.gov (United States)

    Waszak, Martin R.; Anderson, Mark R.

    2008-01-01

    A variable-structure control system designed to enable a fuselage-heavy airplane to recover from spin has been demonstrated in a hand-launched, instrumented model glider airplane. Variable-structure control is a high-speed switching feedback control technique that has been developed for control of nonlinear dynamic systems.

  20. 78 FR 30243 - Airworthiness Directives; Eclipse Aerospace, Inc. Airplanes

    Science.gov (United States)

    2013-05-22

    ... Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will... Directives; Eclipse Aerospace, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... all Eclipse Aerospace, Inc. Model EA500 airplanes equipped with Avio, Avio with ETT, or Avio NG...

  1. 78 FR 65171 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-10-31

    ... new airworthiness directive (AD) for certain The Boeing Company Model 747-400 series airplanes. This... carrying capacity, resulting in a possible decompression event. DATES: This AD is effective December 5..., contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC...

  2. 78 FR 7647 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Science.gov (United States)

    2013-02-04

    ... trunnions will lead to a disconnect of the horizontal stabilizer and subsequent loss of the aeroplane...-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a report that the safe life... stabilizer and subsequent loss of controllability of the airplane. DATES: This AD becomes effective March...

  3. 78 FR 22439 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-04-16

    ... Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The existing... around the galley service doorway hinge cutouts, add inspections of certain repaired structure at...

  4. 77 FR 45518 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-08-01

    ... Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC- 9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes... the wing structure not supporting the limit load condition, which could lead to loss of...

  5. 78 FR 49906 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-08-16

    ...-026-AD; Amendment 39-17527; AD 2013-15-11] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for all The Boeing Company Model 727 airplanes. This AD was prompted... structure and result in loss of airplane control due to lack of horizontal stabilizer support. DATES:...

  6. 77 FR 37795 - Airworthiness Directives; Dassault Aviation Airplanes

    Science.gov (United States)

    2012-06-25

    ... combination with other system failures, could lead to loss of controllability of the airplane. DATES: This AD... failure mode of TVS diodes used on PDCU or GCU cards in the PPDB, which, in combination with other system... combination with other system failures, could lead to loss of controllability of the airplane. (f)...

  7. 78 FR 42727 - Airworthiness Directives; the Boeing Company Airplanes

    Science.gov (United States)

    2013-07-17

    ... electrical power to the IFE systems and certain circuit breakers through a utility bus switch, and doing... airplanes, doing an inspection of the electrical power control panel for a certain part number, and corrective action if necessary; and for certain other airplanes, installing a new electrical power...

  8. 14 CFR 121.189 - Airplanes: Turbine engine powered: Takeoff limitations.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplanes: Turbine engine powered: Takeoff... Limitations § 121.189 Airplanes: Turbine engine powered: Takeoff limitations. (a) No person operating a turbine engine powered airplane may take off that airplane at a weight greater than that listed in...

  9. Detection of a poorly resolved airplane using SWIR polarization imaging

    Science.gov (United States)

    Dahl, Laura M.; Shaw, Joseph A.; Chenault, David B.

    2016-05-01

    Polarization can be used to detect manmade objects on the ground and in the air, as it provides additional information beyond intensity and color. Skylight can be strongly polarized, so the detection of airplanes in flight requires careful consideration of the skylight degree and angle of polarization (DoLP, AoP). In this study, we detect poorly resolved airplanes (>= 4 pixels on target) in flight during daytime partly cloudy and smoky conditions in Bozeman, Montana. We used a Polaris Sensor Technologies SWIR-MWIR rotating imaging polarimeter to measure the polarization signatures of airplanes and the surrounding skylight from 1.5 to 1.8 μm in the short-wave infrared (SWIR). An airplane flying in a clear region of partly cloudy sky was found to be 69% polarized at an elevation angle of 13° with respect to the horizon and the surrounding skylight was 4-8% polarized (maximum skylight DoLP was found to be 7-14% at an elevation angle of 50°). As the airplane increased in altitude, the DoLP for both airplane and surrounding sky pixels increased as the airplane neared the band of maximum sky polarization. We also observed that an airplane can be less polarized than its surrounding skylight when there is heavy smoke present. In such a case, the airplane was 30-38% polarized at an elevation angle of 17°, while the surrounding skylight was approximately 40% polarized (maximum skylight DoLP was 40-55% at an elevation angle of 34°). In both situations the airplane was most consistently observed in DoLP images rather than S0 or AoP images. In this paper, we describe the results in detail and discuss how this phenomenology could detect barely resolved aircrafts.

  10. Simulation of Dynamics of a Flexible Miniature Airplane

    Science.gov (United States)

    Waszak, Martin R.

    2005-01-01

    A short report discusses selected aspects of the development of the University of Florida micro-aerial vehicle (UFMAV) basically, a miniature airplane that has a flexible wing and is representative of a new class of airplanes that would operate autonomously or under remote control and be used for surveillance and/or scientific observation. The flexibility of the wing is to be optimized such that passive deformation of the wing in the presence of aerodynamic disturbances would reduce the overall response of the airplane to disturbances, thereby rendering the airplane more stable as an observation platform. The aspect of the development emphasized in the report is that of computational simulation of dynamics of the UFMAV in flight, for the purpose of generating mathematical models for use in designing control systems for the airplane. The simulations are performed by use of data from a wind-tunnel test of the airplane in combination with commercial software, in which are codified a standard set of equations of motion of an airplane, and a set of mathematical routines to compute trim conditions and extract linear state space models.

  11. Fuzzy Logic Decoupled Longitudinal Control for General Aviation Airplanes

    Science.gov (United States)

    Duerksen, Noel

    1996-01-01

    It has been hypothesized that a human pilot uses the same set of generic skills to control a wide variety of aircraft. If this is true, then it should be possible to construct an electronic controller which embodies this generic skill set such that it can successfully control difference airplanes without being matched to a specific airplane. In an attempt to create such a system, a fuzzy logic controller was devised to control throttle position and another to control elevator position. These two controllers were used to control flight path angle and airspeed for both a piston powered single engine airplane simulation and a business jet simulation. Overspeed protection and stall protection were incorporated in the form of expert systems supervisors. It was found that by using the artificial intelligence techniques of fuzzy logic and expert systems, a generic longitudinal controller could be successfully used on two general aviation aircraft types that have very difference characteristics. These controllers worked for both airplanes over their entire flight envelopes including configuration changes. The controllers for both airplanes were identical except for airplane specific limits (maximum allowable airspeed, throttle lever travel, etc.). The controllers also handled configuration changes without mode switching or knowledge of the current configuration. This research validated the fact that the same fuzzy logic based controller can control two very different general aviation airplanes. It also developed the basic controller architecture and specific control parameters required for such a general controller.

  12. Fuzzy Logic Decoupled Lateral Control for General Aviation Airplanes

    Science.gov (United States)

    Duerksen, Noel

    1997-01-01

    It has been hypothesized that a human pilot uses the same set of generic skills to control a wide variety of aircraft. If this is true, then it should be possible to construct an electronic controller which embodies this generic skill set such that it can successfully control different airplanes without being matched to a specific airplane. In an attempt to create such a system, a fuzzy logic controller was devised to control aileron or roll spoiler position. This controller was used to control bank angle for both a piston powered single engine aileron equipped airplane simulation and a business jet simulation which used spoilers for primary roll control. Overspeed, stall and overbank protection were incorporated in the form of expert systems supervisors and weighted fuzzy rules. It was found that by using the artificial intelligence techniques of fuzzy logic and expert systems, a generic lateral controller could be successfully used on two general aviation aircraft types that have very different characteristics. These controllers worked for both airplanes over their entire flight envelopes. The controllers for both airplanes were identical except for airplane specific limits (maximum allowable airspeed, throttle ]ever travel, etc.). This research validated the fact that the same fuzzy logic based controller can control two very different general aviation airplanes. It also developed the basic controller architecture and specific control parameters required for such a general controller.

  13. Rapid Airplane Parametric Input Design(RAPID)

    Science.gov (United States)

    Smith, Robert E.; Bloor, Malcolm I. G.; Wilson, Michael J.; Thomas, Almuttil M.

    2004-01-01

    An efficient methodology is presented for defining a class of airplane configurations. Inclusive in this definition are surface grids, volume grids, and grid sensitivity. A small set of design parameters and grid control parameters govern the process. The general airplane configuration has wing, fuselage, vertical tail, horizontal tail, and canard components. The wing, tail, and canard components are manifested by solving a fourth-order partial differential equation subject to Dirichlet and Neumann boundary conditions. The design variables are incorporated into the boundary conditions, and the solution is expressed as a Fourier series. The fuselage has circular cross section, and the radius is an algebraic function of four design parameters and an independent computational variable. Volume grids are obtained through an application of the Control Point Form method. Grid sensitivity is obtained by applying the automatic differentiation precompiler ADIFOR to software for the grid generation. The computed surface grids, volume grids, and sensitivity derivatives are suitable for a wide range of Computational Fluid Dynamics simulation and configuration optimizations.

  14. Buffet characteristics of the F-8 supercritical wing airplane

    Science.gov (United States)

    Deangelis, V. M.; Monaghan, R. C.

    1977-01-01

    The buffet characteristics of the F-8 supercritical wing airplane were investigated. Wing structural response was used to determine the buffet characteristics of the wing and these characteristics are compared with wind tunnel model data and the wing flow characteristics at transonic speeds. The wingtip accelerometer was used to determine the buffet onset boundary and to measure the buffet intensity characteristics of the airplane. The effects of moderate trailing edge flap deflections on the buffet onset boundary are presented. The supercritical wing flow characteristics were determined from wind tunnel and flight static pressure measurements and from a dynamic pressure sensor mounted on the flight test airplane in the vicinity of the shock wave that formed on the upper surface of the wing at transonic speeds. The comparison of the airplane's structural response data to the supercritical flow characteristics includes the effects of a leading edge vortex generator.

  15. A numerical study of airplanes flying in proximity

    OpenAIRE

    Porter, David B.

    1993-01-01

    Approved for public release; distribution is unlimited During an emergency such as an unsafe landing gear indication, a second aircraft is often used to perform an airborne visual inspection of the landing gear. The chase airplane may be quite dissimilar in size and wing loading and consequently experience unexpected aerodynamic forces and moments caused by the other airplane. A numerical study of the inherent danger involved with the aerodynamic interaction of aircraft flying in proximity...

  16. Mathematical model of induced flow on the airplane vertical tail

    Science.gov (United States)

    Rotaru, Constantin; Cîrciu, Ionicǎ; Edu, Raluca Ioana

    2016-06-01

    In this paper is presented a mathematical model of the flow around the vertical tail of an airplane, based on the general elements of the aerodynamic design, with details leading to the separate formulation of the Fourier coefficients in the series solution of the Prandtl's lifting-line equation. Numerical results are obtained in Maple soft environment, for a standard configuration of an airplane geometry. The results include the discussion of the vortex model for the sidewash gradient on the vertical stabilizer.

  17. Measured Engine Installation Effects of Four Civil Transport Airplanes

    Science.gov (United States)

    Senzig, David A.; Fleming, Gregg G.; Shepherd, Kevin P.

    2001-01-01

    The Federal Aviation Administration's Integrated Noise Model (INM) is one of the primary tools for land use planning around airports. The INM currently calculates airplane noise lateral attenuation using the methods contained in the Society of Automotive Engineer's Aerospace Information Report No. 1751 (SAE AIR 1751). Researchers have noted that improved lateral attenuation algorithms may improve airplane noise prediction. The authors of SAE AIR 1751 based existing methods on empirical data collected from flight tests using 1960s-technology airplanes with tail-mounted engines. To determine whether the SAE AIR 1751 methods are applicable for predicting the engine installation component of lateral attenuation for airplanes with wing-mounted engines, the National Aeronautics and Space Administration (NASA) sponsored a series of flight tests during September 2000 at their Wallops Flight Facility. Four airplanes, a Boeing 767-400, a Douglas DC-9, a Dassault Falcon 2000, and a Beech KingAir, were flown through a 20 microphone array. The airplanes were flown through the array at various power settings, flap settings, and altitudes to simulate take-off and arrival configurations. This paper presents the preliminary findings of this study.

  18. Simple Electromagnetic Modeling of Small Airplanes: Neural Network Approach

    Directory of Open Access Journals (Sweden)

    P. Tobola

    2009-04-01

    Full Text Available The paper deals with the development of simple electromagnetic models of small airplanes, which can contain composite materials in their construction. Electromagnetic waves can penetrate through the surface of the aircraft due to the specific electromagnetic properties of the composite materials, which can increase the intensity of fields inside the airplane and can negatively influence the functionality of the sensitive avionics. The airplane is simulated by two parallel dielectric layers (the left-hand side wall and the right-hand side wall of the airplane. The layers are put into a rectangular metallic waveguide terminated by the absorber in order to simulate the illumination of the airplane by the external wave (both of the harmonic nature and pulse one. Thanks to the simplicity of the model, the parametric analysis can be performed, and the results can be used in order to train an artificial neural network. The trained networks excel in further reduction of CPU-time demands of an airplane modeling.

  19. Revolution in airplane construction? Grob G110: The first modern fiber glass composition airplane shortly before its maiden flight

    Science.gov (United States)

    Dorpinghaus, R.

    1982-01-01

    A single engine two passenger airplane, constructed completely from fiber reinforced plastic materials is introduced. The cockpit, controls, wing profile, and landing gear are discussed. Development of the airframe is also presented.

  20. 75 FR 65052 - Consensus Standards, Standard Practice for Maintenance of Airplane Electrical Wiring Systems

    Science.gov (United States)

    2010-10-21

    ... TRANSPORTATION Federal Aviation Administration Consensus Standards, Standard Practice for Maintenance of Airplane... Practice for Maintenance of Airplane Electrical Wiring Systems (Standard Practice) as an acceptable means... FAA finds the standards to be acceptable methods and procedures for maintenance of electrical...

  1. The estimation of airplane performance from wind tunnel tests on conventional airplane models

    Science.gov (United States)

    Warner, Edward P; Ober, Shatswell

    1925-01-01

    Calculations of the magnitude of the correction factors and the range of their variations for wind tunnel models used in making aircraft performance predictions were made for 23 wind tunnel models. Calculated performances were compared with those actually determined for such airplanes as have been built and put through flight test. Except as otherwise noted, all the models have interplane struts and diagonal struts formed to streamwise shape. Wires were omitted in all cases. All the models were about 18 inches in span and were tested in a 4-foot wind tunnel. Results are given in tabular form.

  2. 14 CFR Appendix B to Part 121 - Airplane Flight Recorder Specification

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane Flight Recorder Specification B... REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Pt. 121, App. B Appendix B to Part 121—Airplane... airplanes that can demonstrate the capability of deriving either the control input on control movement...

  3. 14 CFR 125.175 - Protection of other airplane components against fire.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Protection of other airplane components... CERTIFICATION AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD... Requirements § 125.175 Protection of other airplane components against fire. (a) Except as provided...

  4. 14 CFR 121.409 - Training courses using airplane simulators and other training devices.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Training courses using airplane simulators... Program § 121.409 Training courses using airplane simulators and other training devices. (a) Training courses utilizing airplane simulators and other training devices may be included in the certificate...

  5. 14 CFR 135.397 - Small transport category airplane performance operating limitations.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Small transport category airplane... PERSONS ON BOARD SUCH AIRCRAFT Airplane Performance Operating Limitations § 135.397 Small transport category airplane performance operating limitations. (a) No person may operate a reciprocating...

  6. 14 CFR Appendix D to Part 125 - Airplane Flight Recorder Specification

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane Flight Recorder Specification D... AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD... Appendix D to Part 125—Airplane Flight Recorder Specification Parameters Range Accuracy sensor input...

  7. 14 CFR 121.407 - Training program: Approval of airplane simulators and other training devices.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Training program: Approval of airplane... Program § 121.407 Training program: Approval of airplane simulators and other training devices. (a) Each airplane simulator and other training device that is used in a training course permitted under §...

  8. 14 CFR 135.399 - Small nontransport category airplane performance operating limitations.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Small nontransport category airplane... PERSONS ON BOARD SUCH AIRCRAFT Airplane Performance Operating Limitations § 135.399 Small nontransport category airplane performance operating limitations. (a) No person may operate a reciprocating engine...

  9. 14 CFR 121.277 - Protection of other airplane components against fire.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Protection of other airplane components....277 Protection of other airplane components against fire. (a) Except as provided in paragraph (b) of this section, all airplane surfaces aft of the nacelles in the area of one nacelle diameter on...

  10. 14 CFR 121.1105 - Aging airplane inspections and records reviews.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Aging airplane inspections and records... Improvements § 121.1105 Aging airplane inspections and records reviews. (a) Applicability. This section applies to all airplanes operated by a certificate holder under this part, except for those...

  11. 14 CFR 121.411 - Qualifications: Check airmen (airplane) and check airmen (simulator).

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Qualifications: Check airmen (airplane) and... § 121.411 Qualifications: Check airmen (airplane) and check airmen (simulator). (a) For the purposes of this section and § 121.413: (1) A check airman (airplane) is a person who is qualified, and...

  12. 14 CFR Appendix D to Part 135 - Airplane Flight Recorder Specification

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane Flight Recorder Specification D.... D Appendix D to Part 135—Airplane Flight Recorder Specification Parameters Range Accuracy sensor.... 3 For airplanes that can demonstrate the capability of deriving either the control input on...

  13. 76 FR 63167 - Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes With Supplemental Type...

    Science.gov (United States)

    2011-10-12

    ... Industries GmbH Airplanes With Supplemental Type Certificate (STC) SA03674AT AGENCY: Federal Aviation...): 2011-21-10 Diamond Aircraft Industries GmbH Airplanes Equipped With Supplemental Type Certificate (STC... airworthiness directive (AD) for Diamond Aircraft Industries GmbH Model (Diamond) DA 40 airplanes equipped...

  14. 14 CFR 91.605 - Transport category civil airplane weight limitations.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Transport category civil airplane weight... Equipment and Operating Requirements for Large and Transport Category Aircraft § 91.605 Transport category civil airplane weight limitations. (a) No person may take off any transport category airplane...

  15. 14 CFR 121.195 - Airplanes: Turbine engine powered: Landing limitations: Destination airports.

    Science.gov (United States)

    2010-01-01

    ... limitations: Destination airports. 121.195 Section 121.195 Aeronautics and Space FEDERAL AVIATION...: Destination airports. (a) No person operating a turbine engine powered airplane may take off that airplane at... alternate airport) the weight of the airplane on arrival would exceed the landing weight set forth in...

  16. 14 CFR 135.395 - Large nontransport category airplanes: Landing limitations: Alternate airports.

    Science.gov (United States)

    2010-01-01

    ...: Landing limitations: Alternate airports. 135.395 Section 135.395 Aeronautics and Space FEDERAL AVIATION... category airplanes: Landing limitations: Alternate airports. No person may select an airport as an alternate airport for a large nontransport category airplane unless that airplane (at the weight...

  17. 14 CFR 135.385 - Large transport category airplanes: Turbine engine powered: Landing limitations: Destination...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Large transport category airplanes: Turbine....385 Large transport category airplanes: Turbine engine powered: Landing limitations: Destination airports. (a) No person operating a turbine engine powered large transport category airplane may take...

  18. 14 CFR 135.387 - Large transport category airplanes: Turbine engine powered: Landing limitations: Alternate airports.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Large transport category airplanes: Turbine....387 Large transport category airplanes: Turbine engine powered: Landing limitations: Alternate... alternate airport for a turbine engine powered large transport category airplane unless (based on...

  19. 14 CFR 121.191 - Airplanes: Turbine engine powered: En route limitations: One engine inoperative.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplanes: Turbine engine powered: En route... Performance Operating Limitations § 121.191 Airplanes: Turbine engine powered: En route limitations: One engine inoperative. (a) No person operating a turbine engine powered airplane may take off that...

  20. 14 CFR 121.193 - Airplanes: Turbine engine powered: En route limitations: Two engines inoperative.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplanes: Turbine engine powered: En route... Performance Operating Limitations § 121.193 Airplanes: Turbine engine powered: En route limitations: Two...). No person may operate a turbine engine powered airplane along an intended route unless he...

  1. Solar Airplanes and Regenerative Fuel Cells

    Science.gov (United States)

    Bents, David J.

    2007-01-01

    A solar electric aircraft with the potential to "fly forever" has captured NASA's interest, and the concept for such an aircraft was pursued under Aeronautics Environmental Research Aircraft and Sensor Technology (ERAST) project. Feasibility of this aircraft happens to depend on the successful development of solar power technologies critical to NASA's Exploration Initiatives; hence, there was widespread interest throughout NASA to bring these technologies to a flight demonstration. The most critical is an energy storage system to sustain mission power during night periods. For the solar airplane, whose flight capability is already limited by the diffuse nature of solar flux and subject to latitude and time of year constraints, the feasibility of long endurance flight depends on a storage density figure of merit better than 400-600 watt-hr per kilogram. This figure of merit is beyond the capability of present day storage technologies (other than nuclear) but may be achievable in the hydrogen-oxygen regenerative fuel cell (RFC). This potential has led NASA to undertake the practical development of a hydrogen-oxygen regenerative fuel cell, initially as solar energy storage for a high altitude UAV science platform but eventually to serve as the primary power source for NASAs lunar base and other planet surface installations. Potentially the highest storage capacity and lowest weight of any non-nuclear device, a flight-weight RFC aboard a solar-electric aircraft that is flown continuously through several successive day-night cycles will provide the most convincing demonstration that this technology's widespread potential has been realized. In 1998 NASA began development of a closed cycle hydrogen oxygen PEM RFC under the Aeronautics Environmental Research Aircraft and Sensor Technology (ERAST) project and continued its development, originally for a solar electric airplane flight, through FY2005 under the Low Emissions Alternative Power (LEAP) project. Construction of

  2. Planetary Airplane Extraction System Development and Subscale Testing

    Science.gov (United States)

    Teter, John E., Jr.

    2006-01-01

    The Aerial Regional-scale Environmental Survey (ARES) project will employ an airplane as the science platform from which to collect science data in the previously inaccessible, thin atmosphere of Mars. In order for the airplane to arrive safely in the Martian atmosphere, a number of sequences must occur. A critical element in the entry sequence at Mars is an extraction maneuver to separate the airplane quickly (in less than a second) from its protective backshell to reduce the possibility of re-contact, potentially leading to mission failure. This paper describes the development, testing, and lessons learned from building a 1/3 scale model of this airplane extraction system. This design, based on the successful Mars Exploration Rover (MER) extraction mechanism, employs a series of trucks rolling along tracks located on the surface of the central parachute can. Numerous tests using high speed video were conducted at the Langley Research Center to validate this concept. One area of concern was that that although the airplane released cleanly, a pitching moment could be introduced. While targeted for a Mars mission, this concept will enable environmental surveys by aircraft in other planetary bodies with a sensible atmosphere such as Venus or Saturn's moon, Titan.

  3. Solar Airplane Concept Developed for Venus Exploration

    Science.gov (United States)

    Landis, Geoffrey A.

    2004-01-01

    An airplane is the ideal vehicle for gathering atmospheric data over a wide range of locations and altitudes, while having the freedom to maneuver to regions of scientific interest. Solar energy is available in abundance on Venus. Venus has an exoatmospheric solar flux of 2600 W/m2, compared with Earth's 1370 W/m2. The solar intensity is 20 to 50 percent of the exoatmospheric intensity at the bottom of the cloud layer, and it increases to nearly 95 percent of the exoatmospheric intensity at 65 km. At these altitudes, the temperature of the atmosphere is moderate, in the range of 0 to 100 degrees Celsius, depending on the altitude. A Venus exploration aircraft, sized to fit in a small aeroshell for a "Discovery" class scientific mission, has been designed and analyzed at the NASA Glenn Research Center. For an exploratory aircraft to remain continually illuminated by sunlight, it would have to be capable of sustained flight at or above the wind speed, about 95 m/sec at the cloud-top level. The analysis concluded that, at typical flight altitudes above the cloud layer (65 to 75 km above the surface), a small aircraft powered by solar energy could fly continuously in the atmosphere of Venus. At this altitude, the atmospheric pressure is similar to pressure at terrestrial flight altitudes.

  4. Advances in Thrust-Based Emergency Control of an Airplane

    Science.gov (United States)

    Creech, Gray; Burken, John J.; Burcham, Bill

    2003-01-01

    Engineers at NASA's Dryden Flight Research Center have received a patent on an emergency flight-control method implemented by a propulsion-controlled aircraft (PCA) system. Utilizing the preexisting auto-throttle and engine-pressure-ratio trim controls of the airplane, the PCA system provides pitch and roll control for landing an airplane safely without using aerodynamic control surfaces that have ceased to function because of a primary-flight-control-system failure. The installation of the PCA does not entail any changes in pre-existing engine hardware or software. [Aspects of the method and system at previous stages of development were reported in Thrust-Control System for Emergency Control of an Airplane (DRC-96-07), NASA Tech Briefs, Vol. 25, No. 3 (March 2001), page 68 and Emergency Landing Using Thrust Control and Shift of Weight (DRC-96-55), NASA Tech Briefs, Vol. 26, No. 5 (May 2002), page 58.]. Aircraft flight-control systems are designed with extensive redundancy to ensure low probabilities of failure. During recent years, however, several airplanes have exhibited major flight-control-system failures, leaving engine thrust as the last mode of flight control. In some of these emergency situations, engine thrusts were successfully modulated by the pilots to maintain flight paths or pitch angles, but in other situations, lateral control was also needed. In the majority of such control-system failures, crashes resulted and over 1,200 people died. The challenge lay in creating a means of sufficient degree of thrust-modulation control to safely fly and land a stricken airplane. A thrust-modulation control system designed for this purpose was flight-tested in a PCA an MD-11 airplane. The results of the flight test showed that without any operational control surfaces, a pilot can land a crippled airplane (U.S. Patent 5,330,131). The installation of the original PCA system entailed modifications not only of the flight-control computer (FCC) of the airplane but

  5. Estimation of fatigue damage of airplane landing gear

    Institute of Scientific and Technical Information of China (English)

    LIU Ke-ge; YAN Chu-liang; ZHANG Shu-ming

    2006-01-01

    Taking the main landing gears of fighter and transport airplanes as examples,the fatigue life was estimated by means of the Miner's rule and from the spectrum of the real measurements.The computed results show that the landing damage to the fighter and transport airplanes is 75% and 60% of the total damage,and the damage caused by the landing stroke is 40% of the landing-gear damage.The fatigue damage properties can provide important information for reliable designing and the structural optimization.

  6. Phase 2 program on ground test of refanned JT8D turbofan engines and nacelles for the 727 airplane. Volume 4: Airplane evaluation and analysis

    Science.gov (United States)

    1975-01-01

    The retrofit of JT8D-109 (refan) engines are evaluated on a 727-200 airplane in terms of airworthiness, performance, and noise. Design of certifiable hardware, manufacture, and ground testing of the essential nacelle components is included along with analysis of the certifiable airplane design to ensure airworthiness compliance and to predict the in-flight performance and noise characteristics of the modified airplane. The analyses confirm that the 727 refan airplane is certifiable. The refan airplane range would be 15% less that of the baseline airplane and block fuel would be increased by 1.5% to 3%. However, with this particular 727-200 model, with a brake release gross weight of 172,500 lb (78,245 kg), it is possible to operate the airplane (with minor structural modifications) at higher gross weights and increase the range up to 15% over the 727-200 (baseline) airplane. The refan airplane FAR Part 36 noise levels would be 6 to 8 EPNdB (effective perceived noise in decibels) below the baseline. Noise footprint studies showed that approach noise contour areas are small compared to takeoff areas. The 727 refan realizes a 68% to 83% reduction in annoyance-weighted area when compared to the 727-200 over a range of gross weights and operational procedures.

  7. 77 FR 65501 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-29

    ...-17-20, Amendment 39-12411 (66 FR 44954, August 27, 2001), for certain Model 707 airplanes, and Model... AD, Amendment 39-12411 (66 FR 44954, August 27, 2001) Was Issued Since we issued AD 2001-17-20, Amendment 39-12411 (66 FR 44954, August 27, 2001), we have determined through service experience that...

  8. 78 FR 4047 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-01-18

    ... FR 18137). That NPRM proposed to require various repetitive inspections of the MDSCD latch pin... presents the comments received on the proposal (77 FR 18137, March 27, 2012) and the FAA's response to each... limit the applicability of the NPRM (77 FR 18137, March 27, 2012) to airplanes with a...

  9. 78 FR 32349 - Airworthiness Directives; Cessna Aircraft Company Airplanes

    Science.gov (United States)

    2013-05-30

    ..., S550, 560, 560XL, and 650 airplanes. This AD was prompted by multiple reports of smoke and/or fire in...) motor. This AD requires inspecting to determine if certain A/C compressor motors are installed and to determine the accumulated hours on certain A/C drive motor assemblies; repetitive replacement of the...

  10. 78 FR 9346 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-02-08

    ... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will... airplanes, modifications to the escape slide/rafts and escape slides. We are proposing this AD to prevent a latch hook moving from closed to open in an escape slide/raft or escape slide, which could result in...

  11. 77 FR 65617 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Science.gov (United States)

    2012-10-30

    ... cap of hydraulic accumulators on other airplane models, resulting in high-energy impact damage to... the associated hydraulic system and high-energy impact damage to adjacent systems and structure. To... by cases of on-ground hydraulic accumulator/screw cap/end cap failure, resulting in...

  12. 78 FR 33010 - Airworthiness Directives; Saab AB, Saab Aerosystems Airplanes

    Science.gov (United States)

    2013-06-03

    ... in an aircraft maintenance manual is incorrect for Saab 340B airplane. This proposed AD would require... information identified in this proposed AD, contact Saab AB, Saab Aeronautics, SE-581 88, Link ping, Sweden... Aircraft Maintenance Manual (AMM), which quotes an elevator position of 4 degrees trailing edge down...

  13. The Paper Airplane Challenge: A Market Economy Simulation. Lesson Plan.

    Science.gov (United States)

    Owens, Kimberly

    This lesson plan features a classroom simulation that helps students understand the characteristics of a market economic system. The lesson plan states a purpose; cites student objectives; suggests a time duration; lists materials needed; and details a step-by-step teaching procedure. The "Paper Airplane Challenge" handout is attached. (BT)

  14. 77 FR 25647 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-05-01

    ... of the main landing gear (MLG) inner cylinder/truck beam. This proposed AD would require repetitive... proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC... in other products of the same type designs. Proposed AD Requirements This proposed AD would...

  15. 78 FR 42895 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-07-18

    ... Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207... of cracks in the pressure floor of the main landing gear (MLG) wheel wells. Three operators reported... previously is likely to exist or develop in other products of the same type design. Proposed AD...

  16. 78 FR 26720 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-05-08

    ... certain airplanes. Since we issued that AD, an operator reported a crack found in a 6061 machined aluminum...-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), for certain The Boeing Company Model 747... during an emergency evacuation. Actions Since Existing AD (73 FR 56960, October 1, 2008) Was Issued...

  17. 77 FR 36206 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-06-18

    ... Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will... proposing this AD to prevent contactor failures, which could result in uncontained hot debris flow due to ELMS contactor breakdown, consequent smoke and heat damage to airplane structure and equipment...

  18. A Study of Transport Airplane Crash-Resistant Fuel Systems

    Science.gov (United States)

    Jones, Lisa (Technical Monitor); Robertson, S. H.; Johnson, N. B.; Hall, D. S.; Rimson, I. J.

    2002-01-01

    This report presents the results of a study, funded by the Federal Aviation Administration (FAA), of transport airplane crash-resistant fuel system (CRFS). The report covers the historical studies related to aircraft crash fires and fuel containment concepts undertaken by the FAA, NASA, and the U.S. Army, which ultimately led to the current state of the art in CRFS technology. It describes the basic research, testing, field investigations and production efforts which have led to the highly successful military CRFS, which has saved many lives and reduced costs of accidents. Current CRFS technology used in transport category airplanes is defined and compared to the available state-of-the-art technology. The report provides information to the FAA and other government organizations which can help them plan their efforts to improve the state of crash fire protection in the transport airplane fleet. The report provides guidance to designers looking for information about CRFS design problems, analysis tools to use for product improvement, and a summary of current and proposed regulations for transport category airplane fuel systems.

  19. 78 FR 47233 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-08-05

    ... inspections of the radome assembly of various Model 737 series airplanes that had in-flight entertainment...). This proposed AD was prompted by reports of cracks found during inspections of the in-flight... charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing...

  20. Boeing Satellite Television Airplane Receiving System (STARS) performance

    Science.gov (United States)

    Vertatschitsch, Edward J.; Fitzsimmons, George W.

    1995-01-01

    Boeing Defense and Space Group is developing a Satellite Television Airplane Receiving System (STARS) capable of delivering Direct Broadcast Satellite (DBS) television to an aircraft in-flight. This enables a new service for commercial airplanes that will make use of existing and future DBS systems. The home entertainment satellites, along with STARS, provide a new mobile satellite communication application. This paper will provide a brief background of the antenna issues associated with STARS for commercial airplanes and then describe the innovative Boeing phased-array solution to these problems. The paper then provides a link budget of the STARS using the Hughes DBS as an example, but the system will work with all of the proposed DBS satellites in the 12.2-12.7 GHz band. It concludes with operational performance calculations of the STARS system, supported by measured test data of an operational 16-element subarray. Although this system is being developed for commercial airplanes, it is well suited for a wide variety of mobile military and other commercial communications systems in air, on land and at sea. The applications include sending high quality video for the digital battlefield and large volumes of data on the information superhighway at rates in excess of 350 Mbps.

  1. The airplane: A simulated commercial air transportation study

    Science.gov (United States)

    Dauteuil, Mark; Geniesse, Pete; Hunniford, Michael; Lawler, Kathleen; Quirk, Elena; Tognarelli, Michael

    1993-01-01

    The 'Airplane' is a moderate-range, 70 passenger aircraft. It is designed to serve demands for flights up to 10,000 feet and it cruises at 32 ft/s. The major drivers for the design of the Airplane are economic competitiveness, takeoff performance, and weight minimization. The Airplane is propelled by a single Astro 15 electric motor and a Zinger 12-8 propeller. The wing section is a Spica airfoil which, because of its flat bottom, provides simplicity in manufacturing and thus helps to cut costs. The wing is constructed of a single load bearing mainspar and shape-holding ribs coated with Monokote skin, lending to a light weight structural makeup. The fuselage houses the motor, flight deck and passenger compartments as well as the fuel and control actuating systems. The wing will be attached to the top of the fuselage as will the fuel and control actuator systems for easy disassembly and maintenance. The aircraft is maneuvered about its pitch axis by means of an aft elevator on the flat plate horizontal tail. The twin vertical tail surfaces are also flat plates and each features a rudder for both directional and roll control. Along with wing dihedral, the rudders will be used to roll the aircraft. The Airplane is less costly to operate at its own maximum range and capacity as well as at its maximum range and the HB-40's maximum capacity than the HB-40.

  2. 77 FR 71357 - Airworthiness Directives; Pacific Aerospace Limited Airplanes

    Science.gov (United States)

    2012-11-30

    ... On September 21, 2010, we issued AD 2010-20-18, Amendment 39-16453 (75 FR 59606, September 28, 2010... issued AD 2010-20-18, Amendment 39-16453 (75 FR 59606, September 28, 2010), information has been received... airplanes. This proposed AD also retains all actions in AD 2010-20-18, Amendment 39-16453 (75 FR...

  3. 76 FR 55614 - Airworthiness Directives; Pacific Aerospace Limited Airplanes

    Science.gov (United States)

    2011-09-08

    ... Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Pacific Aerospace... (AD) for Pacific Aerospace Limited Models FU24-954 and FU24A-954 airplanes modified with an...

  4. 78 FR 9781 - Airworthiness Directives; Pacific Aerospace Limited Airplanes

    Science.gov (United States)

    2013-02-12

    ... November 30, 2012 (77 FR 71357), and proposed to supersede AD 2010-20-18, Amendment 39- 16453 (75 FR 59606, September 28, 2010). Since we issued AD 2010-20-18, Amendment 39-16453 (75 FR 59606, September 28, 2010... airplanes. This AD also retains all actions in AD 2010-20-18, Amendment 39-16453 (75 FR 59606, September...

  5. 77 FR 54787 - Airworthiness Directives; M7 Aerospace LLC Airplanes

    Science.gov (United States)

    2012-09-06

    ... not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26...-17177; AD 2012-18-01] RIN 2120-AA64 Airworthiness Directives; M7 Aerospace LLC Airplanes AGENCY: Federal... new airworthiness directive (AD) for all M7 Aerospace LLC Models SA226-AT, SA226-T, SA226-T(B),...

  6. 78 FR 71989 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-12-02

    ... report that during the replacement of the No. 2 engine, an operator conducted a non-destructive test (NDT... result in separation of an engine under power from the airplane, and consequent loss of control of the... CFR 11.43 and 11.45, by any of the following methods: Federal eRulemaking Portal: Go to...

  7. 77 FR 26945 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-05-08

    ... Southwest Airlines) and Southwest Airlines (SWA) requested that the NPRM (76 FR 22828, April 25, 2011) be... NPRM published in the Federal Register on April 25, 2011 (76 FR 22828). That NPRM proposed to require... (76 FR 22828, April 25, 2011) applies to all airplanes identified in paragraph (h) of this AD and...

  8. 78 FR 25377 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-05-01

    ... changed the AD in this regard. Request for Change to Airplane Groups Southwest Airlines requested a change... the Federal Register on March 16, 2012 (77 FR 15638). The original NPRM (74 FR 15683, April 7, 2009... in developing this AD. The following presents the comments received on the supplemental NPRM (77...

  9. 77 FR 5996 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-02-07

    ... new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, and -300...-101-AD; Amendment 39-16932; AD 2012-02-09] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... start a small fire and lead to a larger fire that may spread throughout the airplane through the...

  10. 78 FR 31389 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-05-24

    ..., positive or negative, on a substantial number of small entities under the criteria of the Regulatory... corners of the door frame and reinforcement of the cross beam of the forward cargo door, which terminates... airplanes previously modified or repaired, and a one-time inspection of the reinforcement angle...

  11. 78 FR 25374 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-05-01

    ... economic impact, positive or negative, on a substantial number of small entities under the criteria of the... AD was prompted by a report that certain airplanes might not have reinforcement straps installed on the center overhead stowage bins in the passenger compartment, and some installed reinforcement...

  12. 77 FR 63266 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-16

    ... not have a significant economic impact, positive or negative, on a substantial number of small..., reinforcement straps were not bonded to the center overhead stowage bins in the passenger compartment. For certain airplanes, this proposed AD would require performing an inspection of reinforcement straps...

  13. Physical and situational inequality on airplanes predicts air rage.

    Science.gov (United States)

    DeCelles, Katherine A; Norton, Michael I

    2016-05-17

    We posit that the modern airplane is a social microcosm of class-based society, and that the increasing incidence of "air rage" can be understood through the lens of inequality. Research on inequality typically examines the effects of relatively fixed, macrostructural forms of inequality, such as socioeconomic status; we examine how temporary exposure to both physical and situational inequality, induced by the design of environments, can foster antisocial behavior. We use a complete set of all onboard air rage incidents over several years from a large, international airline to test our predictions. Physical inequality on airplanes-that is, the presence of a first class cabin-is associated with more frequent air rage incidents in economy class. Situational inequality-boarding from the front (requiring walking through the first class cabin) versus the middle of the plane-also significantly increases the odds of air rage in both economy and first class. We show that physical design that highlights inequality can trigger antisocial behavior on airplanes. More broadly, these results point to the importance of considering the design of environments-from airplanes to office layouts to stadium seating-in understanding both the form and emergence of antisocial behavior. PMID:27140642

  14. 78 FR 26233 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-05-06

    ... Retainer Support on the Left (Right) Thrust Reverser Half,'' have View B showing the top fastener in the... Support on the Left (Right) Thrust Reverser Half,'' have View B showing the top rivet hole. That rivet... this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707,...

  15. 78 FR 60679 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-10-02

    ...-273-AD; Amendment 39-17604; AD 2013-19-22] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes. This AD was... result in damage to the adjacent structure and consequent loss of structural integrity of the...

  16. 77 FR 54848 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-09-06

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company...). SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737... not electrically bonded to primary structure of the airplane. This proposed AD would...

  17. 77 FR 65506 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-29

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company... Boeing Company Model 757-200 and - 200PF series airplanes. The existing AD currently requires modification of the nacelle strut and wing structure, and repair of any damage found during the...

  18. 78 FR 72836 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-12-04

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company...). SUMMARY: We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 717-200... adjacent structure and consequent loss of structural integrity of the airplane. DATES: We must...

  19. 78 FR 17290 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-03-21

    ...-056-AD; Amendment 39-17375; AD 2013-05-03] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and... measuring the electrical resistance of the bond from the adapter plate to the airplane structure, and...

  20. 78 FR 28729 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-05-16

    ...-172-AD; Amendment 39-17455; AD 2013-10-02] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 757-200 and -200PF series airplanes. That AD currently requires modifying the nacelle strut and wing structure,...

  1. 77 FR 50414 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-08-21

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company...). SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737... structure, which could result in uncontrolled decompression of the airplane. DATES: We must receive...

  2. 77 FR 15640 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-03-16

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company... directive (AD) for certain The Boeing Company Model 737-200, -200C, -300, -400, and -500 series airplanes... cracks in the skin and surrounding structure under the number 3 VHF antenna on the lower external...

  3. 78 FR 14469 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-03-06

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company... Boeing Company Model 747-100, 747- 100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400... the adjacent body structure and could result in depressurization of the airplane in flight. DATES:...

  4. 77 FR 71485 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-12-03

    ... Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300... and internal support structure, which could result in uncontrolled decompression of the...

  5. 77 FR 37793 - Airworthiness Directives; the Boeing Company Airplanes

    Science.gov (United States)

    2012-06-25

    ...-124-AD; Amendment 39-17099; AD 2012-12-19] RIN 2120-AA64 Airworthiness Directives; the Boeing Company... new airworthiness directive (AD) for certain the Boeing Company Model 777-200, -200LR, and -300ER... ceiling support structure of Section 41, in airplanes incorporating the overhead space utilization...

  6. 78 FR 9796 - Airworthiness Directives; Cessna Aircraft Company Airplanes

    Science.gov (United States)

    2013-02-12

    ... Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Models 172R and 172S... structure; and, if any damage is found, replace the fuel return line assembly. We are issuing this AD...

  7. 77 FR 40828 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-07-11

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company...). SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model DC-10... structure, which could adversely affect the airplane's continued safe flight and landing. DATES: We...

  8. 77 FR 65803 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-31

    ...-050-AD; Amendment 39-17234; AD 2012-21-18] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for certain The Boeing Company Model MD-90-30 airplanes. This AD was... AD to detect and correct such cracking, which could result in the wing structure not supporting...

  9. 77 FR 65611 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-30

    ...-17229; AD 2012-21-13] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY... airworthiness directive (AD) for certain The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD... result in the wing structure not supporting the limit load condition, which could lead to loss...

  10. 78 FR 17294 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-03-21

    ...-054-AD; Amendment 39-17377; AD 2013-05-05] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and... smoke and heat damage to airplane structure and equipment during ground operations, and...

  11. 78 FR 35110 - Airworthiness Directives; Piper Aircraft, Inc. Airplanes

    Science.gov (United States)

    2013-06-12

    ... airplane exhaust system. This AD was prompted by reports of exhaust system failures upstream of aircraft... comment. Discuss Exhaust System Misalignment, Its Effect on Exhaust System Failures, and Pertinent Company... Condition This AD was prompted by the forced landings of aircraft due to exhaust system failures...

  12. 77 FR 13187 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-03-06

    ... external repair and cutout reinforcement areas; and related investigative and corrective actions if... Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207... http://www.regulations.gov ; or in person at the Docket Management Facility between 9 a.m. and 5...

  13. 78 FR 79289 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-12-30

    ... necessary. This AD also requires installing a fiberglass reinforcement overcoat to the underside of the..., contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H-65... Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD...

  14. 78 FR 21571 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-04-11

    ... AD would also require installing a fiberglass reinforcement overcoat to the top surface of the aft... identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P... Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD...

  15. 77 FR 54854 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-09-06

    ... following a false FWD CARGO FIRE message, with no change in frequency, which resulted in an air turn back..., extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com . You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,...

  16. 77 FR 24353 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Science.gov (United States)

    2012-04-24

    ... requires replacing or relocating of certain circuit breaker panel (CBP) bus bars on certain airplanes, inspecting for any loose or improperly crimped lugs in certain electrical panel locations and replacement if... to the specified products. That NPRM was published in the Federal Register on October 26, 2011 (76...

  17. 75 FR 12667 - Airworthiness Directives; Learjet Inc. Model 45 Airplanes

    Science.gov (United States)

    2010-03-17

    ... on both actuators on one flap, resulting in flap asymmetry and loss of control of the airplane. DATES... information identified in this AD, contact Learjet, Inc., One Learjet Way, Wichita, Kansas 67209-2942... received, and other information. The street address for the Docket Office (telephone 800-647-5527) is...

  18. 78 FR 32579 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Science.gov (United States)

    2013-05-31

    ... Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will... 1000) airplanes. This proposed AD was prompted by reports of erratic pitch movement and oscillatory behaviors of the elevator control system. This proposed AD would require repetitive replacement of...

  19. 78 FR 12991 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-02-26

    .... 12128 (66 FR 13227, March 5, 2001)). Inspection of elevator PCA 23 work-hours x $85 per 0 390 $1,955... elevator surface, resulting in a significant pitch upset and possible loss of control of the airplane...-17-05, Amendment 39-11879 (65 FR 51754, August 25, 2000), for certain The Boeing Company Model...

  20. 78 FR 12256 - Airworthiness Directives; Embraer S.A. Airplanes

    Science.gov (United States)

    2013-02-22

    ... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not... unit (APU) electronic starter controller (ESC) power cables and the airplane tail cone firewall. This... APU ESC power cables, installing ] new grommet support in the tail cone firewall, and...

  1. 78 FR 8999 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-02-07

    ... 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034...-400 series airplanes. This proposed AD was prompted by reports of auxiliary power unit (APU) faults... the APU power feeder cables; replacing the clamps and installing grommets; and related...

  2. Blended Buffet-Load-Alleviation System for Fighter Airplane

    Science.gov (United States)

    Moses, Robert W.

    2005-01-01

    The capability of modern fighter airplanes to sustain flight at high angles of attack and/or moderate angles of sideslip often results in immersion of part of such an airplane in unsteady, separated, vortical flow emanating from its forebody or wings. The flows from these surfaces become turbulent and separated during flight under these conditions. These flows contain significant levels of energy over a frequency band coincident with that of low-order structural vibration modes of wings, fins, and control surfaces. The unsteady pressures applied to these lifting surfaces as a result of the turbulent flows are commonly denoted buffet loads, and the resulting vibrations of the affected structures are known as buffeting. Prolonged exposure to buffet loads has resulted in fatigue of structures on several airplanes. Damage to airplanes caused by buffeting has led to redesigns of airplane structures and increased support costs for the United States Air Force and Navy as well as the armed forces of other countries. Time spent inspecting, repairing, and replacing structures adversely affects availability of aircraft for missions. A blend of rudder-control and piezoelectric- actuator engineering concepts was selected as a basis for the design of a vertical-tail buffet-load-alleviation system for the F/A-18 airplane. In this system, the rudder actuator is used to control the response of the first tail vibrational mode (bending at a frequency near 15 Hz), while directional patch piezoelectric actuators are used to control the second tail vibrational mode (tip torsion at a frequency near 45 Hz). This blend of two types of actuator utilizes the most effective features of each. An analytical model of the aeroservoelastic behavior of the airplane equipped with this system was validated by good agreement with measured results from a full-scale ground test, flight-test measurement of buffet response, and an in-flight commanded rudder frequency sweep. The overall performance of the

  3. Airplane numerical simulation for the rapid prototyping process

    Science.gov (United States)

    Roysdon, Paul F.

    Airplane Numerical Simulation for the Rapid Prototyping Process is a comprehensive research investigation into the most up-to-date methods for airplane development and design. Uses of modern engineering software tools, like MatLab and Excel, are presented with examples of batch and optimization algorithms which combine the computing power of MatLab with robust aerodynamic tools like XFOIL and AVL. The resulting data is demonstrated in the development and use of a full non-linear six-degrees-of-freedom simulator. The applications for this numerical tool-box vary from un-manned aerial vehicles to first-order analysis of manned aircraft. A Blended-Wing-Body airplane is used for the analysis to demonstrate the flexibility of the code from classic wing-and-tail configurations to less common configurations like the blended-wing-body. This configuration has been shown to have superior aerodynamic performance -- in contrast to their classic wing-and-tube fuselage counterparts -- and have reduced sensitivity to aerodynamic flutter as well as potential for increased engine noise abatement. Of course without a classic tail elevator to damp the nose up pitching moment, and the vertical tail rudder to damp the yaw and possible rolling aerodynamics, the challenges in lateral roll and yaw stability, as well as pitching moment are not insignificant. This thesis work applies the tools necessary to perform the airplane development and optimization on a rapid basis, demonstrating the strength of this tool through examples and comparison of the results to similar airplane performance characteristics published in literature.

  4. 14 CFR 135.422 - Aging airplane inspections and records reviews for multiengine airplanes certificated with nine...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Aging airplane inspections and records... Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIR CARRIERS... AND ON DEMAND OPERATIONS AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Maintenance,...

  5. Investigation of control law reconfigurations to accommodate a control element failure on a commercial airplane

    Science.gov (United States)

    Ostroff, A. J.; Hueschen, R. M.

    1984-01-01

    The ability of a pilot to reconfigure the control surfaces on an airplane after a failure, allowing the airplane to recover to a safe condition, becomes more difficult with increasing airplane complexity. Techniques are needed to stabilize and control the airplane immediately after a failure, allowing the pilot more time to make longer range decisions. This paper presents a baseline design of a discrete multivariable control law using four controls for the longitudinal channel of a B-737. Non-reconfigured and reconfigured control laws are then evaluated, both analytically and by means of a digital airplane simulation, for three individual control element failures (stabilizer, elevator, spoilers). The simulation results are used to evaluate the effectiveness of the control reconfiguration on tracking ability during the approach and landing phase of flight with severe windshear and turbulence disturbing the airplane dynamics.

  6. 78 FR 57672 - Aviation Rulemaking Advisory Committee Meeting on Transport Airplane and Engine Issues

    Science.gov (United States)

    2013-09-19

    ... Engine Issues AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of public meeting...) Transport Airplane and Engine (TAE) Subcommittee to discuss TAE issues. DATES: The meeting is scheduled...

  7. 76 FR 60115 - Aviation Rulemaking Advisory Committee Meeting on Transport Airplane and Engine Issues

    Science.gov (United States)

    2011-09-28

    ... Engine Issues AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of public meeting...) to discuss transport airplane and engine (TAE) issues. DATES: The meeting is scheduled for...

  8. 76 FR 14115 - Aviation Rulemaking Advisory Committee Meeting on Transport Airplane and Engine Issues

    Science.gov (United States)

    2011-03-15

    ... Engine Issues AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of public meeting... ] (ARAC) to discuss transport airplane and engine (TAE) issues. DATES: The meeting is scheduled...

  9. 77 FR 24759 - Aviation Rulemaking Advisory Committee Meeting on Transport Airplane and Engine Issues

    Science.gov (United States)

    2012-04-25

    ... Engine Issues AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of public meeting...) to discuss transport airplane and engine (TAE) issues. DATES: The meeting is scheduled for...

  10. Physical interpretation of gray cloud observed from airplanes.

    Science.gov (United States)

    Okamura, Rintaro; Iwabuchi, Hironobu

    2016-07-20

    When obliquely observed from an airplane, gray clouds near the horizon are sometimes observed to overlap with white clouds. Photographic observation from an airplane and simulations using a three-dimensional radiative transfer model are conducted to understand why such clouds appear gray. From observations, the brightness depression rate of gray clouds relative to surrounding whitish clouds is about 25%, whereas in simulations, it is as high as about 30%. Conditions necessary for the observation of gray clouds are as follows: (1) two clouds at different altitudes do not overlap, but the higher cloud overlaps with the lower cloud along the line of sight when these clouds are observed in near-horizontal direction, and (2) the higher cloud is optically thin in the vertical direction, but optically thick along the line of sight. PMID:27463934

  11. Development of Outboard Nacelle for the XB-36 Airplane

    Science.gov (United States)

    Nuber, Robert J.

    1947-01-01

    An investigation of two 1/14 scale model configurations of an outboard nacelle for the XB-36 airplane was made in the Langley two-dimensional low-turbulence tunnels over a range of airplane lift coefficients (C (sub L) = 0.409 to C(sub L) = 0.943) for three representative flow conditions. The purpose of the investigation was to develop a low-drag wing-nacelle pusher combination which incorporated an internal air-flow system. The present investigation has led to the development of a nacelle which had external drag coefficients of similar order of magnitude to those obtained previously from tests of an inboard nacelle configuration at the corresponding operating lift coefficients and from approximately one-third to one-half of those of conventional tractor designs having the same ratio of wing thickness to nacelle diameter.

  12. 75 FR 71346 - Special Conditions: Boeing Model 787-8 Airplane; Lightning Protection of Fuel Tank Structure To...

    Science.gov (United States)

    2010-11-23

    ... Boeing Model 787-8 airplane will be a new design, two-engine turbo-jet transport category airplane with a..., 2009 (74 FR 52698). Several comments were received from two commenters (Cessna and NATCA). Cessna...

  13. Numerical simulation of RCS for carrier electronic warfare airplanes

    Directory of Open Access Journals (Sweden)

    Yue Kuizhi

    2015-04-01

    Full Text Available This paper studies the radar cross section (RCS of carrier electronic warfare airplanes. Under the typical naval operations section, the mathematical model of the radar wave’s pitch angle incidence range analysis is established. Based on the CATIA software, considering dynamic deflections of duck wing leading edge flaps, flaperons, horizontal tail, and rudder, as well as aircraft with air-to-air missile, anti-radiation missile, electronic jamming pod, and other weapons, the 3D models of carrier electronic warfare airplanes Model A and Model B with weapons were established. Based on the physical optics method and the equivalent electromagnetic flow method, by the use of the RCSAnsys software, the characteristics of carrier electronic warfare airplanes’ RCS under steady and dynamic flights were simulated under the UHF, X, and S radar bands. This paper researches the detection probability of aircraft by radars under the condition of electronic warfare, and completes the mathematical statistical analysis of the simulation results. The results show that: The Model A of carrier electronic warfare airplane is better than Model B on stealth performance and on discover probability by radar detection effectively.

  14. Headache associated with airplane travel: A rare entity

    Directory of Open Access Journals (Sweden)

    Ajith Cherian

    2013-01-01

    Full Text Available Airplane travel headache is rare and has recently been described as a new form of headache associated with a specific situation. Of the 1,208 patients with primary headaches attending a tertiary care neurology hospital, two (0.16% patients satisfied the criteria for headache related to airplane travel. Both the patients fulfilled the proposed diagnostic criteria for airplane travel headache. This unique headache had a mean duration of 24 minutes, localized to the medial supraorbital region described as having an intense jabbing or stabbing character that occurred exclusively and maximally during aircraft landing or take-off, following which pain intensity subsided . This rare headache felt on aircraft descent is probably due to the squeeze effect on the frontal sinus wall, when air trapped inside it contracts producing a negative pressure leading to mucosal edema, transudation and intense pain. Use of nasal decongestants either alone or in combination with naproxen sodium prior to ascent and descent abated the headache episodes. Awareness about this unique entity is essential to provide proper treatment and avoid patient suffering.

  15. 76 FR 63823 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G280 Airplane Pilot-Compartment View...

    Science.gov (United States)

    2011-10-14

    ...-SC for the GALP Model G280 airplane was published in the Federal Register on May 25, 2011 (76 FR... following novel or unusual design features: The GALP Model G280 airplane flight-deck design incorporates a... as the approach to land, where the airplane is at a higher-than-normal pitch attitude. In these...

  16. 77 FR 5990 - Special Conditions: Learjet Inc., Model LJ-200-1A10 Airplane, Pilot-Compartment View Through...

    Science.gov (United States)

    2012-02-07

    ... Learjet Model LJ-200-1A10 airplane was published in the Federal Register on October 14, 2011 (76 FR 63851... novel or unusual design features: The Model LJ-200-1A10 airplane flight deck design incorporates a... approach to land, where the airplane is at a higher-than-normal pitch attitude. In these cases, areas...

  17. 78 FR 8961 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Hydrophobic Coatings in Lieu of...

    Science.gov (United States)

    2013-02-07

    ...-550 airplanes was published in the Federal Register on November 9, 2012, (77 FR 67308). No comments...; Hydrophobic Coatings in Lieu of Windshield Wipers AGENCY: Federal Aviation Administration (FAA), DOT. ACTION...-550 airplane. This airplane will have a novel or unusual design feature(s) associated with...

  18. 75 FR 76647 - Special Conditions: Boeing Model 747-8 Airplanes, Systems and Data Networks Security-Isolation or...

    Science.gov (United States)

    2010-12-09

    ... 747-8 Airplanes, Systems and Data Networks Security--Isolation or Protection From Unauthorized... information services, than previous 747-8 airplane models. This may allow the exploitation of network security... passenger domain computer systems to the airplane critical systems and data networks. The...

  19. 14 CFR 121.333 - Supplemental oxygen for emergency descent and for first aid; turbine engine powered airplanes...

    Science.gov (United States)

    2010-01-01

    ... and for first aid; turbine engine powered airplanes with pressurized cabins. 121.333 Section 121.333... for emergency descent and for first aid; turbine engine powered airplanes with pressurized cabins. (a) General. When operating a turbine engine powered airplane with a pressurized cabin, the certificate...

  20. 14 CFR 135.383 - Large transport category airplanes: Turbine engine powered: En route limitations: Two engines...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Large transport category airplanes: Turbine... Limitations § 135.383 Large transport category airplanes: Turbine engine powered: En route limitations: Two...). No person may operate a turbine engine powered large transport category airplane along an...

  1. 76 FR 472 - Harmonization of Airworthiness Standards for Transport Category Airplanes-Landing Gear Retracting...

    Science.gov (United States)

    2011-01-05

    ... Airworthiness Standards for Transport Category Airplanes--Landing Gear Retracting Mechanisms and Pilot... transport category airplanes on landing gear retracting mechanisms and the pilot compartment view. This... in a stalling maneuver, and would add an additional requirement to keep the landing gear and doors...

  2. 77 FR 1614 - Harmonization of Airworthiness Standards for Transport Category Airplanes-Landing Gear Retracting...

    Science.gov (United States)

    2012-01-11

    ... Register on January 5, 2011 (76 FR 472). The NPRM proposed to amend the standards for landing gear... Transport Category Airplanes--Landing Gear Retracting Mechanisms and Pilot Compartment View AGENCY: Federal... the airworthiness standards for transport category airplanes on landing gear retracting mechanisms...

  3. 76 FR 39763 - Special Conditions: Boeing Model 787-8 Airplane; Interaction of Systems and Structures...

    Science.gov (United States)

    2011-07-07

    ... airplane system immunity is demonstrated when exposed to the HIRF environments in either paragraph (a) OR... Administration 14 CFR Part 25 Special Conditions: Boeing Model 787-8 Airplane; Interaction of Systems and...: Federal Aviation Administration (FAA), DOT. ACTION: Amended special conditions SUMMARY: These...

  4. 76 FR 38062 - Airworthiness Directives; Gulfstream Aerospace LP Model Galaxy and Gulfstream 200 Airplanes

    Science.gov (United States)

    2011-06-29

    ... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... Aerospace LP Model Galaxy and Gulfstream 200 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... LP Model Galaxy and Gulfstream 200 airplanes, certificated in any category, serial numbers...

  5. 77 FR 60005 - Aviation Rulemaking Advisory Committee Meeting on Transport Airplane and Engine Issues

    Science.gov (United States)

    2012-10-01

    ... Airplane and Engine Issues'' (77 FR 59243), in FR Doc. 2012-23709, that published on September 26, 2012... Engine Issues AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of public meeting...) to discuss transport airplane and engine (TAE) issues. It also withdraws the notice...

  6. 14 CFR Appendix B to Part 135 - Airplane Flight Recorder Specifications

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane Flight Recorder Specifications B Appendix B to Part 135 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION.... B Appendix B to Part 135—Airplane Flight Recorder Specifications Parameters Range Installed system...

  7. 14 CFR Appendix E to Part 91 - Airplane Flight Recorder Specifications

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Airplane Flight Recorder Specifications E Appendix E to Part 91 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION... Appendix E to Part 91—Airplane Flight Recorder Specifications Parameters Range Installed system 1...

  8. 77 FR 16155 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Airplanes

    Science.gov (United States)

    2012-03-20

    ... and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and... de Aeronautica S.A. (EMBRAER) Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... directive (AD) for all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 airplanes. This...

  9. 76 FR 72855 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Airplanes

    Science.gov (United States)

    2011-11-28

    ... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... de Aeronautica S.A. (EMBRAER) Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ] ACTION... all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 190 airplanes. This proposed AD...

  10. 77 FR 36224 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Airplanes

    Science.gov (United States)

    2012-06-18

    ... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... de Aeronautica S.A. (EMBRAER) Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 airplanes, and Model...

  11. 14 CFR 121.412 - Qualifications: Flight instructors (airplane) and flight instructors (simulator).

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Qualifications: Flight instructors (airplane) and flight instructors (simulator). 121.412 Section 121.412 Aeronautics and Space FEDERAL... OPERATIONS Training Program § 121.412 Qualifications: Flight instructors (airplane) and flight...

  12. 76 FR 8278 - Special Conditions: Gulfstream Model GVI Airplane; Enhanced Flight Vision System

    Science.gov (United States)

    2011-02-14

    ... Flight Vision System AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions..., Airplane and Flight Crew Interface Branch, ANM-111, Transport Standards Staff, Transport Airplane... Design Features The enhanced flight vision system (EFVS) is a novel or unusual design feature because...

  13. 76 FR 12556 - Airworthiness Directives; Various Transport Category Airplanes Equipped With Chemical Oxygen...

    Science.gov (United States)

    2011-03-08

    ... 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034... Category Airplanes Equipped With Chemical Oxygen Generators Installed in a Lavatory AGENCY: Federal... affected airplanes identified above. This AD requires modifying the chemical oxygen generators in...

  14. 76 FR 36870 - Special Conditions: Gulfstream Model GVI Airplane; Design Roll Maneuver Requirement for...

    Science.gov (United States)

    2011-06-23

    ... electronic flight control system that provides roll control of the airplane through pilot inputs to the... equipped with an electronic flight control system that provides roll control of the airplane through pilot... system. Discussion The GVI is equipped with an electronic flight control system that provides...

  15. 76 FR 8319 - Special Conditions: Gulfstream Model GVI Airplane; Design Roll Maneuver Requirement for...

    Science.gov (United States)

    2011-02-14

    ... with an electronic flight control system that provides roll control of the airplane through pilot... airplanes. These design features include an electronic flight control system that provides roll control of... Design Features The GVI is equipped with an electronic flight control system that provides roll...

  16. 76 FR 17183 - Aviation Rulemaking Advisory Committee; Transport Airplane and Engine Issues-New Task

    Science.gov (United States)

    2011-03-28

    .../AM-10/14, The Rudder Survey Technical Report. For a copy, call Sarah Peterson at (405) 954-6840. 2... airplanes to meet their needs while ensuring airplane safety. ARAC would also need to recommend methods of... needed to ensure safe rudder usage, what is the recommended method to mandate retrofit? (Ad...

  17. 78 FR 63848 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Sidestick Controllers

    Science.gov (United States)

    2013-10-25

    ... be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http...: Loran Haworth, FAA, Airplane and Flight Crew Interface Branch, ANM-111, Transport Airplane Directorate... sidestick controllers. Certain ergonomic considerations such as armrest support, freedom of arm...

  18. 76 FR 9265 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Flight Control System: Control...

    Science.gov (United States)

    2011-02-17

    ... Model GVI Airplane; Electronic Flight Control System: Control Surface Position Awareness AGENCY: Federal... transport category airplanes. These design features include an electronic flight control system. The... The GVI has an electronic flight control system and no direct coupling from the cockpit controller...

  19. 14 CFR 121.641 - Fuel supply: Nonturbine and turbo-propeller-powered airplanes: Flag operations.

    Science.gov (United States)

    2010-01-01

    ...-powered airplanes: Flag operations. 121.641 Section 121.641 Aeronautics and Space FEDERAL AVIATION...: CERTIFICATION AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Dispatching and Flight Release Rules § 121.641 Fuel supply: Nonturbine and turbo-propeller-powered airplanes:...

  20. 14 CFR 135.398 - Commuter category airplanes performance operating limitations.

    Science.gov (United States)

    2010-01-01

    ... all commuter category airplanes notwithstanding their stated applicability to turbine-engine-powered... used, the elevation of the airport, the effective runway gradient, and ambient temperature, and wind... person may take off an airplane type certificated in the commuter category at a weight greater than...

  1. 14 CFR 135.379 - Large transport category airplanes: Turbine engine powered: Takeoff limitations.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Large transport category airplanes: Turbine... category airplanes: Turbine engine powered: Takeoff limitations. (a) No person operating a turbine engine... existing at take- off. (b) No person operating a turbine engine powered large transport category...

  2. 14 CFR 91.1037 - Large transport category airplanes: Turbine engine powered; Limitations; Destination and...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Large transport category airplanes: Turbine....1037 Large transport category airplanes: Turbine engine powered; Limitations; Destination and alternate airports. (a) No program manager or any other person may permit a turbine engine powered large...

  3. 14 CFR 23.1045 - Cooling test procedures for turbine engine powered airplanes.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Cooling test procedures for turbine engine powered airplanes. 23.1045 Section 23.1045 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... CATEGORY AIRPLANES Powerplant Cooling § 23.1045 Cooling test procedures for turbine engine...

  4. 14 CFR 121.329 - Supplemental oxygen for sustenance: Turbine engine powered airplanes.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Supplemental oxygen for sustenance: Turbine... Equipment Requirements § 121.329 Supplemental oxygen for sustenance: Turbine engine powered airplanes. (a) General. When operating a turbine engine powered airplane, each certificate holder shall equip...

  5. 76 FR 37684 - Airworthiness Directives; Diamond Aircraft Industries GmbH Model (Diamond) DA 40 Airplanes...

    Science.gov (United States)

    2011-06-28

    ... Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will... Industries GmbH Model (Diamond) DA 40 Airplanes Equipped With Certain Cabin Air Conditioning Systems AGENCY... inspections of the Diamond Model DA 40 airplanes equipped with a VCS installed per Premier Aircraft...

  6. 77 FR 2439 - Airworthiness Directives; Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D Airplanes

    Science.gov (United States)

    2012-01-18

    ... nose up. The airplane pitch was controlled with the elevator trim and the airplane returned to base... Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR... elevator bob-weight and attaching linkage for correct installation and for damage or deformation to...

  7. Reconfigurable multivariable control law for commercial airplane using a direct digital output feedback design

    Science.gov (United States)

    Ostroff, A. J.; Hueschen, R. M.

    1984-01-01

    The ability of a pilot to reconfigure the control surfaces on an airplane after a failure, allowing the airplane to recover to a safe condition for landing, becomes more difficult with increasing airplane complexity. Techniques are needed to stabilize and control the airplane immediately after a failure, allowing the pilot time to make longer range decisions. This paper shows a design of a discrete multivariable control law using four controls for the longitudinal channel of a B-737. Single control element failures are allowed in three of the four controls. The four controls design and failure cases are analyzed by means of a digital airplane simulation, with regard to tracking capability and ability to overcome severe windshear and turbulence during the aproach and landing phase of flight.

  8. Radiated Emissions from a Remote-Controlled Airplane-Measured in a Reverberation Chamber

    Science.gov (United States)

    Ely, Jay J.; Koppen, Sandra V.; Nguyen, Truong X.; Dudley, Kenneth L.; Szatkowski, George N.; Quach, Cuong C.; Vazquez, Sixto L.; Mielnik, John J.; Hogge, Edward F.; Hill, Boyd L.; Strom, Thomas H.

    2011-01-01

    A full-vehicle, subscale all-electric model airplane was tested for radiated emissions, using a reverberation chamber. The mission of the NASA model airplane is to test in-flight airframe damage diagnosis and battery prognosis algorithms, and provide experimental data for other aviation safety research. Subscale model airplanes are economical experimental tools, but assembling their systems from hobbyist and low-cost components may lead to unforseen electromagnetic compatibility problems. This report provides a guide for accommodating the on-board radio systems, so that all model airplane systems may be operated during radiated emission testing. Radiated emission data are provided for on-board systems being operated separately and together, so that potential interferors can be isolated and mitigated. The report concludes with recommendations for EMI/EMC best practices for subscale model airplanes and airships used for research.

  9. Proton Exchange Membrane Fuel Cells for Electrical Power Generation On-Board Commercial Airplanes

    Energy Technology Data Exchange (ETDEWEB)

    Pratt, Joesph W. [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States); Klebanoff, Leonard E. [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States); Munoz-Ramos, Karina [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States); Akhil, Abbas A. [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States); Curgus, Dita B. [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States); Schenkman, Benjamin L. [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States)

    2011-05-01

    Deployed on a commercial airplane, proton exchange membrane fuel cells may offer emissions reductions, thermal efficiency gains, and enable locating the power near the point of use. This work seeks to understand whether on-board fuel cell systems are technically feasible, and, if so, if they offer a performance advantage for the airplane as a whole. Through hardware analysis and thermodynamic and electrical simulation, we found that while adding a fuel cell system using today’s technology for the PEM fuel cell and hydrogen storage is technically feasible, it will not likely give the airplane a performance benefit. However, when we re-did the analysis using DOE-target technology for the PEM fuel cell and hydrogen storage, we found that the fuel cell system would provide a performance benefit to the airplane (i.e., it can save the airplane some fuel), depending on the way it is configured.

  10. Proton exchange membrane fuel cells for electrical power generation on-board commercial airplanes.

    Energy Technology Data Exchange (ETDEWEB)

    Curgus, Dita Brigitte; Munoz-Ramos, Karina (Sandia National Laboratories, Albuquerque, NM); Pratt, Joseph William; Akhil, Abbas Ali (Sandia National Laboratories, Albuquerque, NM); Klebanoff, Leonard E.; Schenkman, Benjamin L. (Sandia National Laboratories, Albuquerque, NM)

    2011-05-01

    Deployed on a commercial airplane, proton exchange membrane fuel cells may offer emissions reductions, thermal efficiency gains, and enable locating the power near the point of use. This work seeks to understand whether on-board fuel cell systems are technically feasible, and, if so, if they offer a performance advantage for the airplane as a whole. Through hardware analysis and thermodynamic and electrical simulation, we found that while adding a fuel cell system using today's technology for the PEM fuel cell and hydrogen storage is technically feasible, it will not likely give the airplane a performance benefit. However, when we re-did the analysis using DOE-target technology for the PEM fuel cell and hydrogen storage, we found that the fuel cell system would provide a performance benefit to the airplane (i.e., it can save the airplane some fuel), depending on the way it is configured.

  11. STATIC TESTS OF UNCONVENTIONAL PROPULSION UNITS FOR ULTRALIGHT AIRPLANES

    Directory of Open Access Journals (Sweden)

    Martin Helmich

    2014-06-01

    Full Text Available This paper presents static tests of a new unconventional propulsion unit for small aviation airplanes. Our laboratory stand – a fan drive demonstrator – enables us to compare various design options. We performed experiments to verify the propulsion functionality and a measurement procedure to determine the available thrust of the propulsion unit and its dependence on engine speed. The results used for subsequent optimization include the operating parameters of the propulsion unit, and the temperature and velocity fields in parts of the air duct.

  12. An Accurate Method for Measuring Airplane-Borne Conformal Antenna's Radar Cross Section

    Science.gov (United States)

    Guo, Shuxia; Zhang, Lei; Wang, Yafeng; Hu, Chufeng

    2016-09-01

    The airplane-borne conformal antenna attaches itself tightly with the airplane skin, so the conventional measurement method cannot determine the contribution of the airplane-borne conformal antenna to its radar cross section (RCS). This paper uses the 2D microwave imaging to isolate and extract the distribution of the reflectivity of the airplane-borne conformal antenna. It obtains the 2D spatial spectra of the conformal antenna through the wave spectral transform between the 2D spatial image and the 2D spatial spectrum. After the interpolation from the rectangular coordinate domain to the polar coordinate domain, the spectral domain data for the variation of the scatter of the conformal antenna with frequency and angle is obtained. The experimental results show that the measurement method proposed in this paper greatly enhances the airplane-borne conformal antenna's RCS measurement accuracy, essentially eliminates the influences caused by the airplane skin and more accurately reveals the airplane-borne conformal antenna's RCS scatter properties.

  13. Comparative Analysis of Interference Pathloss Coupling Patterns on B-737 VS. B757 Airplanes

    Science.gov (United States)

    Jafri, Madiha; Ely, Jay; Vahala, Linda

    2005-01-01

    Portable wireless technology provides many benefits to modern day travelers. Over the years however, numerous reports have cited portable electronic devices (PEDs) as a possible cause of electromagnetic interference (EMI) to aircraft navigation and communication radio systems. PEDs may act as transmitters, both intentional and unintentional, and their signals may be detected by the various radio receiver antennas installed on the aircraft. Measurement of the radiated field coupling between passenger cabin locations and aircraft communication and navigation receivers, via their antennas is defined herein as interference path loss (IPL). IPL data is required for assessing the threat of PEDs to aircraft radios, and is very dependent upon airplane size, the interfering transmitter position within the airplane, and the location of the particular antenna for the aircraft system of concern. NASA Langley Research Center, Eagles Wings Inc., and United Airlines personnel performed extensive IPL measurements on several Boeing 737 airplanes. In the Spring of 2004, extensive IPL measurements were also taken on several Boeing 757 airplanes under a cooperative agreement between NASA Langley Research Center and Delta Airlines. The objective of this paper is to analyze IPL measurement data, to better understand the impact on coupling levels based on the different locations of the aircraft radio antennas on B-757 and B-737 airplanes, and to provide a basis for future fuzzy logic modeling of airplane IPL. This effort will build upon previous fuzzy modeling of IPL data for B-737 airplane data.

  14. Predicting Tail Buffet Loads of a Fighter Airplane

    Science.gov (United States)

    Moses, Robert W.; Pototzky, Anthony S.

    2006-01-01

    Buffet loads on aft aerodynamic surfaces pose a recurring problem on most twin-tailed fighter airplanes: During maneuvers at high angles of attack, vortices emanating from various surfaces on the forward parts of such an airplane (engine inlets, wings, or other fuselage appendages) often burst, immersing the tails in their wakes. Although these vortices increase lift, the frequency contents of the burst vortices become so low as to cause the aft surfaces to vibrate destructively. Now, there exists a new analysis capability for predicting buffet loads during the earliest design phase of a fighter-aircraft program. In effect, buffet pressures are applied to mathematical models in the framework of a finite-element code, complete with aeroelastic properties and working knowledge of the spatiality of the buffet pressures for all flight conditions. The results of analysis performed by use of this capability illustrate those vibratory modes of a tail fin that are most likely to be affected by buffet loads. Hence, the results help in identifying the flight conditions during which to expect problems. Using this capability, an aircraft designer can make adjustments to the airframe and possibly the aerodynamics, leading to a more robust design.

  15. Bird flight and airplane flight. [instruments to measure air currents and flight characteristics

    Science.gov (United States)

    Magnan, A.

    1980-01-01

    Research was based on a series of mechanical, electrical, and cinematographic instruments developed to measure various features of air current behavior as well as bird and airplane flight. Investigation of rising obstruction and thermal currents led to a theory of bird flight, especially of the gliding and soaring types. It was shown how a knowledge of bird flight can be applied to glider and ultimately motorized aircraft construction. The instruments and methods used in studying stress in airplanes and in comparing the lift to drag ratios of airplanes and birds are described.

  16. Evaluation of a total energy-rate sensor on a transport airplane

    Science.gov (United States)

    Ostroff, A. J.; Hueschen, R. M.; Hellbaum, R. F.; Belcastro, C. M.; Creedon, J. F.

    1983-01-01

    A sensor that measures the rate of change of total energy of an airplane with respect to the airstream has been evaluated. The sensor consists of two cylindrical probes located on the fuselage of a transport airplane, an in line acoustic filter, and a pressure sensing altitude rate transducer. Sections of this report include the sensor description and experimental configuration, frequency response tests, analytical model development, and flight test results for several airplane maneuvers. The results section includes time history comparisons between data generated by the total energy rate sensor and calculated data derived from independent sources.

  17. Flight Tests of a Ministick Controller in an F/A-18 Airplane

    Science.gov (United States)

    Stoliker, Patrick C.; Carter, John

    2003-01-01

    In March of 1999, five pilots performed flight tests to evaluate the handling qualities of an F/A-18 research airplane equipped with a small-displacement center stick (ministick) controller that had been developed for the JAS 39 Gripen airplane (a fighter/attack/ reconnaissance airplane used by the Swedish air force). For these tests, the ministick was installed in the aft cockpit (see figure) and production support flight control computers (PSFCCs) were used as interfaces between the controller hardware and the standard F/A-18 flight-control laws. The primary objective of the flight tests was to assess any changes in handling qualities of the F/A-18 airplane attributable to the mechanical characteristics of the ministick. The secondary objective was to demonstrate the capability of the PSFCCs to support flight-test experiments.

  18. System design overview of JAXA small supersonic experimental airplane (NEXST-1)

    OpenAIRE

    Takami, Hikaru; 高見 光

    2007-01-01

    The system of JAXA small supersonic experimental airplane (NEXST-1: National EXperimental Supersonic Transport-1) has been briefly explained. Some design problems that the designers have encountered have also been briefly explained.

  19. Evaluation of an aeroelastic model technique for predicting airplane buffet loads

    Science.gov (United States)

    Hanson, P. W.

    1973-01-01

    A wind-tunnel technique which makes use of a dynamically scaled aeroelastic model to predict full-scale airplane buffet loads during buffet boundary penetration is evaluated. A 1/8-scale flutter model of a fighter airplane with remotely controllable variable-sweep wings and trimming surfaces was used for the evaluation. The model was flown on a cable-mount system which permitted high lift forces comparable to those in maneuvering flight. Bending moments and accelerations due to buffet were measured on the flutter model and compared with those measured on the full-scale airplane in an independent flight buffet research study. It is concluded that the technique can provide valuable information on airplane buffet load characteristics not available from any other source except flight test.

  20. Effects of road traffic background noise on judgments of individual airplane noises. Ph.D. Thesis

    Science.gov (United States)

    Powell, C. A.

    1979-01-01

    Two laboratory experiments were conducted to investigate the effects of road-traffic background noise on judgments of individual airplane flyover noises. In the first experiment, 27 subjects judged a set of 16 airplane flyover noises in the presence of traffic-noise sessions of 30-min duration consisting of the combinations of 3 traffic-noise types and 3 noise levels. In the second experiment, 24 subjects judged the same airplane flyover noises in the presence of traffic-noise sessions of 10-min duration consisting of the combinations of 2 traffic-noise types and 4 noise levels. In both experiments the airplane noises were judged less annoying in the presence of high traffic-noise levels than in the presence of low traffic-noise levels.

  1. The Research and Application About "Dry Peeling Off" Technology for Airplane Surface Paint Layer

    Institute of Scientific and Technical Information of China (English)

    WANG Ding-jiang; TANG Zheng-jie; CHEN Ming-hua; GUO Bi-xin; Chen Yi-can; TANG Ying

    2004-01-01

    In this paper, the principle of spurting take off lacquer were introduced; and with orthogonal method the unsaturate polyester was prepared ;it was easy to peel airplane paint layer off with this material and equipment.

  2. “COANDA-1910” - the first jet propulsor for airplane

    Directory of Open Access Journals (Sweden)

    Romulus PETCU

    2010-12-01

    Full Text Available This paper contains the authors’ research regarding the first airplane equippedwith a jet propulsion system made by Henri Coanda in 1910, also being homage pays toHenri Coanda, his inventor.

  3. Proton exchange membrane fuel cells for electrical power generation on-board commercial airplanes

    International Nuclear Information System (INIS)

    Highlights: ► We examine proton exchange membrane fuel cells on-board commercial airplanes. ► We model the added fuel cell system’s effect on overall airplane performance. ► It is feasible to implement an on-board fuel cell system with current technology. ► Systems that maximize waste heat recovery are the best performing. ► Current PEM and H2 storage technology results in an airplane performance penalty. -- Abstract: Deployed on a commercial airplane, proton exchange membrane (PEM) fuel cells may offer emissions reductions, thermal efficiency gains, and enable locating the power near the point of use. This work seeks to understand whether on-board fuel cell systems are technically feasible, and, if so, if they could offer a performance advantage for the airplane when using today’s off-the-shelf technology. We also examine the effects of the fuel cell system on airplane performance with (1) different electrical loads, (2) different locations on the airplane, and (3) expected advances in fuel cell and hydrogen storage technologies. Through hardware analysis and thermodynamic simulation, we found that an additional fuel cell system on a commercial airplane is technically feasible using current technology. Although applied to a Boeing 787-type airplane, the method presented is applicable to other airframes as well. Recovery and on-board use of the heat and water that is generated by the fuel cell is an important method to increase the benefit of such a system. The best performance is achieved when the fuel cell is coupled to a load that utilizes the full output of the fuel cell for the entire flight. The effects of location are small and location may be better determined by other considerations such as safety and modularity. Although the PEM fuel cell generates power more efficiently than the gas turbine generators currently used, when considering the effect of the fuel cell system on the airplane’s overall performance we found that an overall

  4. Flutter clearance of the horizontal tail of the Bellanca Skyrocket II airplane

    Science.gov (United States)

    Ricketts, R. H.; Cazier, F. W., Jr.; Farmer, M. G.

    1982-01-01

    The Skyrocket II is an all composite constructed experimental prototype airplane. A flutter clearance program was conducted on the horizontal tail so that the airplane could be safely flown to acquire natural laminar flow aerodynamic data. Ground vibration test data were used in a lifting surface flutter analysis to predict symmetric and antisymmetric flutter boundaries. Subcritical response data which were acquired during flight tests are compared with the analytical results. The final flutter clearance placard speed was based on flight test data.

  5. Traian Vuia – the Romanian inventor who first flew a powered airplane in 1906

    Directory of Open Access Journals (Sweden)

    Liviu FILIMON

    2011-09-01

    Full Text Available As observed the beginning of heavier than air devices started with Wright Brothers who flew in 1903 the first catapulted airplane equipped with an engine, similar to present motor gliders. In March 1906 took place the first flight of Vuia’s monoplane using on board installations. Since then a real competition between manufacturers has started to improve their airplanes as they become more efficient. Traian Vuia’s first flights and his beginnings are explained below.

  6. F-16XL Airplane Research Paint Scheme Aerials

    Science.gov (United States)

    1993-01-01

    The NASA F-16XL research airplane is shown in flight over Eastern Shore of Virginia During the Cranked-Arrow Wing Aerodynamics Project (CAWAP). The aircraft is shown in the research paint scheme utilized for on-surface flow visualization. During CAWAP, tufts, oil, and liquid crystals were used to document the flow patterns on the upper surfaces of the wings. The images were recorded by onboard video cameras and hand-held video and still cameras in a chase aircraft. The visual images are being correlated with on board measurements of surface pressures, boundary-layer velocity profiles, and skin friction. Ultimately, the in-flight data will be combined with wind-tunnel results and computational-fluid-dynamics solutions to document the aerodynamics of cranked-arrow wings. CAWAP is a cooperative venture of the Langley Research Center and the Dryden Flight Research Center.

  7. 78 FR 70848 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Science.gov (United States)

    2013-11-27

    ... unintentional corruption of data and systems critical to the safety and maintenance of the airplane. The... navigation systems, 2. Operator business and administrative support (operator information services),...

  8. 78 FR 70849 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Science.gov (United States)

    2013-11-27

    ... unintentional corruption of data and systems critical to the safety and maintenance of the airplane. The... and administrative support (operator information services), 3. Passenger information systems, and,...

  9. Aerodynamic Effects of a 24-foot Multisegmented Telescoping Nose Boom on an F-15B Airplane

    Science.gov (United States)

    Cumming, Stephen B.; Smith, Mark S.; Frederick, Michael A.

    2008-01-01

    An experimental multisegmented telescoping nose boom has been installed on an F-15B airplane to be tested in a flight environment. The experimental nose boom is representative of one that could be used to tailor the sonic boom signature of an airplane such as a supersonic business jet. The nose boom consists of multiple sections and could be extended during flight to a length of 24 ft. The preliminary analyses indicate that the addition of the experimental nose boom could adversely affect vehicle flight characteristics and air data systems. Before the boom was added, a series of flights was conducted to update the aerodynamic model and characterize the air data systems of the baseline airplane. The baseline results have been used in conjunction with estimates of the nose boom's influence to prepare for a series of research flights conducted with the nose boom installed. Data from these flights indicate that the presence of the experimental boom reduced the static pitch and yaw stability of the airplane. The boom also adversely affected the static-position error of the airplane but did not significantly affect angle-of-attack or angle-of-sideslip measurements. The research flight series has been successfully completed.

  10. Modelling and Simulation of Fuel Cell Dynamics for Electrical Energy Usage of Hercules Airplanes

    Directory of Open Access Journals (Sweden)

    Hamid Radmanesh

    2014-01-01

    Full Text Available Dynamics of proton exchange membrane fuel cells (PEMFC with hydrogen storage system for generating part of Hercules airplanes electrical energy is presented. Feasibility of using fuel cell (FC for this airplane is evaluated by means of simulations. Temperature change and dual layer capacity effect are considered in all simulations. Using a three-level 3-phase inverter, FC’s output voltage is connected to the essential bus of the airplane. Moreover, it is possible to connect FC’s output voltage to airplane DC bus alternatively. PID controller is presented to control flow of hydrogen and oxygen to FC and improve transient and steady state responses of the output voltage to load disturbances. FC’s output voltage is regulated via an ultracapacitor. Simulations are carried out via MATLAB/SIMULINK and results show that the load tracking and output voltage regulation are acceptable. The proposed system utilizes an electrolyser to generate hydrogen and a tank for storage. Therefore, there is no need for batteries. Moreover, the generated oxygen could be used in other applications in airplane.

  11. Modelling and simulation of fuel cell dynamics for electrical energy usage of Hercules airplanes.

    Science.gov (United States)

    Radmanesh, Hamid; Heidari Yazdi, Seyed Saeid; Gharehpetian, G B; Fathi, S H

    2014-01-01

    Dynamics of proton exchange membrane fuel cells (PEMFC) with hydrogen storage system for generating part of Hercules airplanes electrical energy is presented. Feasibility of using fuel cell (FC) for this airplane is evaluated by means of simulations. Temperature change and dual layer capacity effect are considered in all simulations. Using a three-level 3-phase inverter, FC's output voltage is connected to the essential bus of the airplane. Moreover, it is possible to connect FC's output voltage to airplane DC bus alternatively. PID controller is presented to control flow of hydrogen and oxygen to FC and improve transient and steady state responses of the output voltage to load disturbances. FC's output voltage is regulated via an ultracapacitor. Simulations are carried out via MATLAB/SIMULINK and results show that the load tracking and output voltage regulation are acceptable. The proposed system utilizes an electrolyser to generate hydrogen and a tank for storage. Therefore, there is no need for batteries. Moreover, the generated oxygen could be used in other applications in airplane.

  12. Modeling the Aerodynamics and Performances of a Historic Airplane: the Spanish

    Directory of Open Access Journals (Sweden)

    A. González-Betes

    2003-01-01

    Full Text Available The process of modeling the aerodynamics and performances of a historic airplane is very similar to the conceptual and preliminary design phases of a new plane, with the advantage of knowing the configuration and that the airplane was airworthy; thus it is unnecessary to outline and assess many different alternatives. However, the drag polar, the real performances, stability features, etc, are still unknown. For various reasons (in particular because of two World Wars, or the Civil War in the Spanish case most details of many historical airplanes have been lost.In the present research work, the situation is as follows. In June 1933 the "Cuatro Vientos", a Spanish-built Bréguet XIX Super TR, flew non-stop from Seville to Cuba; a distance of 7500 km (about 4100 nautical miles in around 40 hours. A few days later, in a far less complicated stage between Havana and Mexico, the airplane was lost with its occupants to a storm in the Yucatan peninsula.The modeling considered in this paper starts by addressing the aerodynamic modifications introduced in the airplane for the extremely long flight. Then, with the help of old and present day aerodynamic data and methods the drag polar is estimated. The available engine data is completed and extrapolated to obtain information on power and fuel consumption. Finally, all this data is integrated to provide a reliable and technically sound reproduction of the Seville-Cuba flight.

  13. 78 FR 5146 - Special Conditions: Embraer S.A., Model EMB-550 Airplane, Dive Speed Definition With Speed...

    Science.gov (United States)

    2013-01-24

    ... Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477 19478), as well as...., Model EMB-550 Airplane, Dive Speed Definition With Speed Protection System AGENCY: Federal Aviation... category airplanes. These design features include a high-speed protection system. The...

  14. 77 FR 70384 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Design Roll Maneuver for Electronic...

    Science.gov (United States)

    2012-11-26

    ... control system that provides control of the aircraft through pilot inputs to the flight computer. The... control system for the Model EMB-550 airplane does not have a direct mechanical link or a linear gain between the airplane flight control surface and the pilot's cockpit control device, which is not...

  15. 75 FR 2434 - Special Conditions: Boeing Model 747-8/-8F Series Airplanes; Design Roll Maneuver Requirement

    Science.gov (United States)

    2010-01-15

    ... electronic flight control system that provides roll control of the airplane through pilot inputs to the... electronic flight control system that provides roll control of the airplane through pilot inputs to the... novel or unusual design features: An electronic flight control system that provides roll control of......

  16. 78 FR 68986 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Science.gov (United States)

    2013-11-18

    ... and connectivity capabilities of the airplane's onboard network computer systems, which may allow access to or by external computer systems and networks. This onboard network system will be composed of a... airplane's onboard network system. The applicable airworthiness regulations do not contain adequate...

  17. 78 FR 49655 - Special Conditions: Embraer, S.A., Model EMB-550 Airplane; Side-Facing Seats; Installation of...

    Science.gov (United States)

    2013-08-15

    ..., Airframe and Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service... considered a novel design for transport category airplanes that include Amendment 25-64 in their... requirement to provide support for the pelvis, upper arm, chest, and head contained in the previous...

  18. 75 FR 2433 - Special Conditions: Boeing Model 747-8/-8F Airplanes, Systems and Data Networks Security...

    Science.gov (United States)

    2010-01-15

    ... Security--Protection of Airplane Systems and Data Networks From Unauthorized External Access AGENCY... external systems and networks may result in security vulnerabilities to the airplane's systems. The... network sources. The architecture and network configuration may allow the exploitation of network...

  19. 14 CFR 36.9 - Acoustical change: Propeller-driven small airplanes and propeller-driven commuter category...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Acoustical change: Propeller-driven small airplanes and propeller-driven commuter category airplanes. 36.9 Section 36.9 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT NOISE STANDARDS: AIRCRAFT TYPE AND AIRWORTHINESS CERTIFICATION General §...

  20. 14 CFR 135.381 - Large transport category airplanes: Turbine engine powered: En route limitations: One engine...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Large transport category airplanes: Turbine... Limitations § 135.381 Large transport category airplanes: Turbine engine powered: En route limitations: One engine inoperative. (a) No person operating a turbine engine powered large transport category...

  1. 75 FR 70090 - Special Conditions: Bombardier Inc. Model CL-600-2E25 Airplane, Operation Without Normal...

    Science.gov (United States)

    2010-11-17

    ... (APU)-generated electrical power. Service experience on other airplane models with similar electrical... engine generators or APU, is not extremely improbable. Thus, it must be demonstrated that the airplane... landing with inoperative normal engine- and APU-generated electrical power (for example,...

  2. [The airplane accident in Torghatten on May 6, 1988].

    Science.gov (United States)

    Solheim, T; Stene-Johansen, W; Lorentsen, M; Sakshaug, O

    1989-01-01

    On May 6th, 1988, a Dash 7 airplane crashed into the mountain of Torghatten, near Brønnøy-sund in northern Norway. All 33 passengers and the three crew members were killed. The National Identification Commission, including a forensic dentist, was at the disaster site twelve hours later. A dentist and a forensic pathologist worked with the police at the site until all the victims had been found. Three other dentists were responsible for collecting antemortem material and for the postmortem examination of all victims. 32 of the victims, or 89%, could be identified by dental means alone; a higher percentage than ever before reported. The final meeting of the Identification Commission took place five days after the disaster. All the victims were identified on the basis of technical, medical, and dental evidence, and the report signed by each of the three specialist groups. The quality of the dental records was evaluated with respect to requirements set up by the Ministry of Social Affairs in 1983. Dental records had improved since the "Alexander Kielland" disaster in 1980. However, only five of the missing persons had full mouth intraoral radiography, only nine records met the requirements for general information about the patient (birth date and identification number, home and business address, etc), only three had information about earlier diseases, and none had recorded previous dental restorations. Diagnoses were given only for nine persons. The records showed that 21 of the victims had not received any prophylactic treatment.

  3. Development of Inboard Nacelle for the XB-36 Airplane

    Science.gov (United States)

    Nuber, Robert J.

    1947-01-01

    A series of investigations of several 1/14-scale models of an inboard nacelle for the XB-36 airplane was made in the Langley two-dimensional low-turbulence tunnels. The purpose of these investigations was to develop a low-drag wing-nacelle pusher combination which incorporated an internal air-flow system. As a result of these investigations, a nacelle was developed which had external drag coefficients considerably lower than the original basic form with the external nacelle drag approximately one-half to two-thirds of those of conventional tractor designs. The largest reductions in drag resulted from sealing the gaps between the wing flaps and nacelle, reducing the thickness of the nacelle training-edge lip, and bringing the under-wing air inlet to the wing leading edge. It was found that without the engine cooling fan adequate cooling air would be available for all conditions of flight except for cruise and climb at 40,000 feet. Sufficient oil cooling at an altitude of 40,000 feet may be obtained by the use of flap-type exit doors.

  4. Approximations for column effect in airplane wing spars

    Science.gov (United States)

    Warner, Edward P; Short, Mac

    1927-01-01

    The significance attaching to "column effect" in airplane wing spars has been increasingly realized with the passage of time, but exact computations of the corrections to bending moment curves resulting from the existence of end loads are frequently omitted because of the additional labor involved in an analysis by rigorously correct methods. The present report represents an attempt to provide for approximate column effect corrections that can be graphically or otherwise expressed so as to be applied with a minimum of labor. Curves are plotted giving approximate values of the correction factors for single and two bay trusses of varying proportions and with various relationships between axial and lateral loads. It is further shown from an analysis of those curves that rough but useful approximations can be obtained from Perry's formula for corrected bending moment, with the assumed distance between points of inflection arbitrarily modified in accordance with rules given in the report. The discussion of general rules of variation of bending stress with axial load is accompanied by a study of the best distribution of the points of support along a spar for various conditions of loading.

  5. A New Intelligent Airplane Landing Planning Method in Congested Airports

    Directory of Open Access Journals (Sweden)

    Kazem Dastgerdi

    2015-06-01

    Full Text Available Nowadays considering many advantages of air traveling, we notice that traffic congestion has significantly increased in airspace of countries, and it is expected that this growth rate, increases even more in the forthcoming years.This growth rate and different limitations posed on developing some airports led to the problem of landing airplanes to become one of the most important issues formed in the field of aviation. In this paper, in the form of a new approach based on CPSO algorithm for intelligent landing planning, determining optimal landing times, optimal allocation of runways, and at last the order of successive landings of planes has been done in a way that appropriately fulfills the main goal of the problem (minimizing the total flights delays; thus helping significantly to controlling air traffic congestion in airports approaches. The simulation results show that compared to the last presented methods, including methods based on genetic algorithms, GLS and Bionomic, has decreased the total amounts of flight delays considerably. Getting zero for total amount of flight delays for the two problems with real data of DFW airport in Texas, United States, confirms the more capability of CPSO algorithm compared to the other intelligent methods for obtaining optimal solutions to the problem.

  6. Trade Study of Multiple Thruster Options for the Mars Airplane Concept

    Science.gov (United States)

    Kuhl, Christopher A.; Gayle, Steven W.; Hunter, Craig A.; Kenney, Patrick S.; Scola, Salvatore; Paddock, David A.; Wright, Henry S.; Gasbarre, Joseph F.

    2009-01-01

    A trade study was performed at NASA Langley Research Center under the Planetary Airplane Risk Reduction (PARR) project (2004-2005) to examine the option of using multiple, smaller thrusters in place of a single large thruster on the Mars airplane concept with the goal to reduce overall cost, schedule, and technical risk. The 5-lbf (22N) thruster is a common reaction control thruster on many satellites. Thousands of these types of thrusters have been built and flown on numerous programs, including MILSTAR and Intelsat VI. This study has examined the use of three 22N thrusters for the Mars airplane propulsion system and compared the results to those of the baseline single thruster system.

  7. Research and application of ORACLE performance optimizing technologies for building airplane environment resource database

    Science.gov (United States)

    Zhang, Jianjun; Sun, Jianyong; Cheng, Conggao

    2013-03-01

    Many problems exist in processing experimental aircraft vibration (temperature, humidity) data and generating the intermediate calculations during the construction of airplane environment resource database, such as the need to deal with both structural and non-structural data, weak capacity of the client browser for data processing and massive network data transferring etc. To solve the above problems, some strategies on tuning and optimization performance of database are employed base on Oracle11g, which include data storage structure tuning, the memory configuration of the server, the disk I/O tuning and SQL statement tuning. The experimental results show that the performance of airplane environment resource database is enhanced about 80% compared with the database developed in the initial demonstration and validation phase. The application of new optimization strategies to the database construction can lay a sound foundation for finishing building airplane environment resource database.

  8. Self-Propelled Pedestrian Dynamics Model: Application to Passenger Movement and Infection Propagation in Airplanes

    CERN Document Server

    Namilae, S; Mubayi, A; Scotch, M; Pahle, R

    2016-01-01

    Reducing the number of contacts between passengers on an airplane can potentially curb the spread of infectious diseases. In this paper, a social force based pedestrian movement model is formulated and applied to evaluate the movement and contacts among passengers during boarding and deplaning of an airplane. Within the social force modeling framework, we introduce location dependence on the self-propelling momentum of pedestrian particles. The model parameters are varied over a large design space and the results are compared with experimental observations to validate the model. This model is then used to assess the different approaches to minimize passenger contacts during boarding and deplaning of airplanes. We find that smaller aircrafts are effective in reducing the contacts between passengers. Column wise deplaning and random boarding are found to be two strategies that reduced the number of contacts during passenger movement, and can potentially lower the likelihood of infection spread.

  9. A controls engineering approach for analyzing airplane input-output characteristics

    Science.gov (United States)

    Arbuckle, P. Douglas

    1991-01-01

    An engineering approach for analyzing airplane control and output characteristics is presented. State-space matrix equations describing the linear perturbation dynamics are transformed from physical coordinates into scaled coordinates. The scaling is accomplished by applying various transformations to the system to employ prior engineering knowledge of the airplane physics. Two different analysis techniques are then explained. Modal analysis techniques calculate the influence of each system input on each fundamental mode of motion and the distribution of each mode among the system outputs. The optimal steady state response technique computes the blending of steady state control inputs that optimize the steady state response of selected system outputs. Analysis of an example airplane model is presented to demonstrate the described engineering approach.

  10. Design study of technology requirements for high performance single-propeller-driven business airplanes

    Science.gov (United States)

    Kohlman, D. L.; Hammer, J.

    1985-01-01

    Developments in aerodyamic, structural and propulsion technologies which influence the potential for significant improvements in performance and fuel efficiency of general aviation business airplanes are discussed. The advancements include such technolgies as natural laminar flow, composite materials, and advanced intermittent combustion engines. The design goal for this parameter design study is a range of 1300 nm at 300 knots true airspeed with a payload of 1200lbs at 35,000 ft cruise altitude. The individual and synergistic effects of various advanced technologies on the optimization of this class of high performance, single engine, propeller driven business airplanes are identified.

  11. A Hardware-in-the-Loop Simulator for Software Development for a Mars Airplane

    Science.gov (United States)

    Slagowski, Stefan E.; Vican, Justin E.; Kenney, P. Sean

    2007-01-01

    Draper Laboratory recently developed a Hardware-In-The-Loop Simulator (HILSIM) to provide a simulation of the Aerial Regional-scale Environmental Survey (ARES) airplane executing a mission in the Martian environment. The HILSIM was used to support risk mitigation activities under the Planetary Airplane Risk Reduction (PARR) program. PARR supported NASA Langley Research Center's (LaRC) ARES proposal efforts for the Mars Scout 2011 opportunity. The HILSIM software was a successful integration of two simulation frameworks, Draper's CSIM and NASA LaRC's Langley Standard Real-Time Simulation in C++ (LaSRS++).

  12. Organization for breakthrough. How skunkworks developed airplanes; Breakthrough no tameno kaihatsu soshiki. Rokkidosha skunkworks ni tsuite

    Energy Technology Data Exchange (ETDEWEB)

    Masuda, K. [Civil Aircraft Engineering Service Co., Bellevue (United States)

    1998-07-05

    `Skunkworks` is stated to be a secret research institute or equipments for developing reformative products in the fields of aviation and aerospace. Skunkworks was established in 1943 by Lockheed Company to develop the first jet engine fighter. This team continued after that and successfully developed advanced airplanes. Skunkworks is now used as a pronoun of the development form of this kind. This paper introduces its organization, development form and results. Fourteen rules of Skunkworks are dealt with first. Then the developments of SR-71 supersonic reconnaissance planes and F-117 stealth fighters are described. Skunkworks has successfully developed advanced airplanes in a short time in secret. 3 refs., 2 figs.

  13. Airplane Ice Detector Based on a Microwave Transmission Line

    Science.gov (United States)

    Ngo, Phong; Arndt, G. Dickey; Carl, James R.

    2004-01-01

    An electronic instrument that could detect the potentially dangerous buildup of ice on an airplane wing is undergoing development. The instrument is based on a microwave transmission line configured as a capacitance probe: at selected spots, the transmission-line conductors are partly exposed to allow any ice and/or liquid water present at those spots to act as predominantly capacitive electrical loads on the transmission line. These loads change the input impedance of the transmission line, as measured at a suitable excitation frequency. Thus, it should be possible to infer the presence of ice and/or liquid water from measurements of the input impedance and/or electrical parameters related to the input impedance. The sensory transmission line is of the microstrip type and thus thin enough to be placed on an airplane wing without unduly disturbing airflow in flight. The sensory spots are small areas from which the upper layer of the microstrip has been removed to allow any liquid water or ice on the surface to reach the transmission line. The sensory spots are spaced at nominal open-circuit points, which are at intervals of a half wavelength (in the transmission line, not in air) at the excitation frequency. The excitation frequency used in the experiments has been 1 GHz, for which a half wavelength in the transmission line is .4 in. (.10 cm). The figure depicts a laboratory prototype of the instrument. The impedance-related quantities chosen for use in this version of the instrument are the magnitude and phase of the scattering parameter S11 as manifested in the in-phase (I ) and quadrature (Q) outputs of the phase detector. By careful layout of the transmission line (including the half-wavelength sensor spacing), one can ensure that the amplitude and phase of the input to the phase detector keep shifting in the same direction as ice forms on one or more of the sensor areas. Although only one transmission-line sensor strip is used in the laboratory version, in a

  14. Scaling behavior of an airplane-boarding model.

    Science.gov (United States)

    Brics, Martins; Kaupužs, Jevgenijs; Mahnke, Reinhard

    2013-04-01

    An airplane-boarding model, introduced earlier by Frette and Hemmer [Phys. Rev. E 85, 011130 (2012)], is studied with the aim of determining precisely its asymptotic power-law scaling behavior for a large number of passengers N. Based on Monte Carlo simulation data for very large system sizes up to N=2(16)=65536, we have analyzed numerically the scaling behavior of the mean boarding time and other related quantities. In analogy with critical phenomena, we have used appropriate scaling Ansätze, which include the leading term as some power of N (e.g., [proportionality]N(α) for ), as well as power-law corrections to scaling. Our results clearly show that α=1/2 holds with a very high numerical accuracy (α=0.5001±0.0001). This value deviates essentially from α=/~0.69, obtained earlier by Frette and Hemmer from data within the range 2≤N≤16. Our results confirm the convergence of the effective exponent α(eff)(N) to 1/2 at large N as observed by Bernstein. Our analysis explains this effect. Namely, the effective exponent α(eff)(N) varies from values about 0.7 for small system sizes to the true asymptotic value 1/2 at N→∞ almost linearly in N(-1/3) for large N. This means that the variation is caused by corrections to scaling, the leading correction-to-scaling exponent being θ≈1/3. We have estimated also other exponents: ν=1/2 for the mean number of passengers taking seats simultaneously in one time step, β=1 for the second moment of t(b), and γ≈1/3 for its variance. PMID:23679383

  15. Electromagnetic compatibility and the all-electric airplane

    Science.gov (United States)

    Christman, Al

    1995-01-01

    NASA is studying the feasibility of installing 'all-electric' controls in future commercial aircraft, replacing the current hydraulic and pneumatic systems. Planes utilizing such equipment should weigh less and be cheaper to maintain, but might also be susceptible to interference from undesired external electromagnetic fields. Possible sources of these extraneous signals include radio and television broadcasters, two-way communications stations, and radar installations of all kinds. One way to reduce the hazard would be to use fiber-optic cables to carry signals from the cockpit to the various points of use, a concept known as 'fly-by-light' or FBL. However, electrical circuits (PBW, or 'power-by-wire') would still be required at both ends of the cables to perform control functions, so the possibility of harmful interference would remain. Computer models for two different antennas were created in order to find the magnitude of the electric fields which would be generated in the airspace around them while in the transmit mode. The first antenna was a horizontal 'rhombic' used by the Voice of America (VOA) for long-distance short-wave broadcasting. The second antenna was a multi-element 'log-periodic dipole array' (LPDA) of a type often used for two-way radio communications. For each case, a specified amount of power was applied in the computer model, and the resulting electric field intensity was predicted at a variety of locations surrounding the antenna. This information will then be used to calculate the levels of interference which could occur inside an airplane flying in the vicinity of these radiation emitters.

  16. Scaling behavior of an airplane-boarding model.

    Science.gov (United States)

    Brics, Martins; Kaupužs, Jevgenijs; Mahnke, Reinhard

    2013-04-01

    An airplane-boarding model, introduced earlier by Frette and Hemmer [Phys. Rev. E 85, 011130 (2012)], is studied with the aim of determining precisely its asymptotic power-law scaling behavior for a large number of passengers N. Based on Monte Carlo simulation data for very large system sizes up to N=2(16)=65536, we have analyzed numerically the scaling behavior of the mean boarding time and other related quantities. In analogy with critical phenomena, we have used appropriate scaling Ansätze, which include the leading term as some power of N (e.g., [proportionality]N(α) for ), as well as power-law corrections to scaling. Our results clearly show that α=1/2 holds with a very high numerical accuracy (α=0.5001±0.0001). This value deviates essentially from α=/~0.69, obtained earlier by Frette and Hemmer from data within the range 2≤N≤16. Our results confirm the convergence of the effective exponent α(eff)(N) to 1/2 at large N as observed by Bernstein. Our analysis explains this effect. Namely, the effective exponent α(eff)(N) varies from values about 0.7 for small system sizes to the true asymptotic value 1/2 at N→∞ almost linearly in N(-1/3) for large N. This means that the variation is caused by corrections to scaling, the leading correction-to-scaling exponent being θ≈1/3. We have estimated also other exponents: ν=1/2 for the mean number of passengers taking seats simultaneously in one time step, β=1 for the second moment of t(b), and γ≈1/3 for its variance.

  17. A Brief Study of the Speed Reduction of Overtaking Airplanes by Means of Air Brakes, Special Report

    Science.gov (United States)

    Pearson, H. A.; Amderspm. R. F.

    1942-01-01

    As an aid to airplane designers interested in providing pursuit airplanes with decelerating devices intended to increase the firing time when overtaking another airplane, formulas are given relating the pertinent distances and speeds in horizontal flight to the drag increase required. Charts are given for a representative parasite-drag coefficient from which the drag increase, the time gained, and the closing distance may be found. The charts are made up for three values of the ratio of the final speed of the pursuing airplane to the speed of the pursued airplane and for several values of the ratio of the speed of the pursued airplane to the initial speed of the pursuing airplane. Charts are also given indicating the drag increases obtainable with double split flaps and with conventional propellers. The use of the charts is illustrated by an example in which it is indicated that either double split flaps or, under certain ideal conditions, reversible propellers should provide the speed reductions required.

  18. 75 FR 20518 - Special Conditions: Cirrus Design Corporation Model SF50 Airplane; Full Authority Digital Engine...

    Science.gov (United States)

    2010-04-20

    ... design feature(s) associated with the use of an electronic engine control system instead of a traditional... design features: Electronic engine control system. Applicability As discussed above, these special... certification basis for Cirrus Design Corporation model SF50 airplanes. 1. Electronic Engine Control...

  19. Pressure Distribution Over the Fuselage of a PW-9 Pursuit Airplane in Flight

    Science.gov (United States)

    Rhode, Richard V; Lundquist, Eugene E

    1932-01-01

    This report presents the results obtained from pressure distribution tests on the fuselage of a PW-9 pursuit airplane in a number of conditions of flight. The investigation was made to determine the contribution of the fuselage to the total lift in conditions considered critical for the wing structure, and also to determine whether the fuselage loads acting simultaneously with the maximum tail loads were of such a character as to be of concern with respect to the structural design of other parts of the airplane. The results show that the contribution of the fuselage toward the total lift is small on this airplane. Aerodynamic loads on the fuselage are, in general, unimportant from the structural viewpoint, and in most cases they are of such character that, if neglected, a conservative design results. In spins, aerodynamic forces on the fuselage produce diving moments of appreciable magnitude and yawing moments of small magnitude, but opposing the rotation of the airplane. A table of cowling pressures for various maneuvers is included in the report.

  20. 75 FR 21528 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes

    Science.gov (United States)

    2010-04-26

    ... Policies and Procedures (44 FR 11034, February 26, 1979), and 3. Will not have a significant economic... have the same design as those installed on Model MD-90-30 airplanes. Therefore, Model MD-90-30..., hangar lighting, flashlight, or ] droplight and may require removal or opening of access panels or...

  1. 76 FR 31454 - Special Conditions: Gulfstream Model GVI Airplane; Automatic Speed Protection for Design Dive Speed

    Science.gov (United States)

    2011-06-01

    ... for Gulfstream GVI airplanes was published in the Federal Register on February 16, 2011 (76 FR 8917...; Automatic Speed Protection for Design Dive Speed AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... high speed protection system. These special conditions contain the additional safety standards that...

  2. 78 FR 60995 - Aviation Rulemaking Advisory Committee Meeting on Transport Airplane and Engine Issues

    Science.gov (United States)

    2013-10-02

    ... Engine Issues AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of rescheduled public... Rulemaking Advisory Committee (ARAC) Transport Airplane and Engine (TAE) Subcommittee to discuss TAE issues. A number of issues have arisen that may affect the Committee's ability to have an effective...

  3. 76 FR 18964 - Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Model P2006T Airplanes

    Science.gov (United States)

    2011-04-06

    ... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... Aeronautiche Tecnam srl Model P2006T Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing...

  4. 76 FR 48045 - Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Model P2006T Airplanes

    Science.gov (United States)

    2011-08-08

    ... Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic... Directives; Costruzioni Aeronautiche Tecnam srl Model P2006T Airplanes AGENCY: Federal Aviation... authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the...

  5. Brace for impact! A thesis on medical care following an airplane crash

    NARCIS (Netherlands)

    I.L.E. Postma

    2014-01-01

    In this thesis the events and management of a mass casualty incident (MCI) of an airplane crash are studied from a medical point of view. The incident is broken down into areas that are applicable to other MCIs. it is believed that the detailed study of an exceptional event can provide vital informa

  6. 14 CFR 121.414 - Initial and transition training and checking requirements: flight instructors (airplane), flight...

    Science.gov (United States)

    2010-01-01

    ... teaching-learning process; (ii) Teaching methods and procedures; and (iii) The instructor-student... in the required normal, abnormal, and emergency procedures to ensure competence as an instructor; and... instructors (airplane), in-flight training to ensure competence to perform assigned duties. (f)...

  7. 78 FR 66258 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Airplanes

    Science.gov (United States)

    2013-11-05

    ... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation... de Aeronautica S.A. (EMBRAER) Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... directive (AD) for certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135ER, - 135KE,...

  8. Teaching Lean Six Sigma within a Supply Chain Context: The Airplane Supply Chain Simulation

    Science.gov (United States)

    Ellis, Scott C.; Goldsby, Thomas J.; Bailey, Ana M.; Oh, Jae-Young

    2014-01-01

    Lean six sigma is a management methodology that firms can employ to achieve substantial improvement in supply chain performance. However, few pedagogical exercises facilitate students' use of a comprehensive set of lean six sigma principles within a supply chain context. We describe the Airplane Supply Chain Simulation that helps students…

  9. 14 CFR 26.39 - Newly produced airplanes: Fuel tank flammability.

    Science.gov (United States)

    2010-01-01

    ... TRANSPORTATION AIRCRAFT CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES Fuel...) that meet the requirements of 14 CFR 25.981 in effect on December 26, 2008. (1) The fuel tank is... tank exceeds a Fleet Average Flammability Exposure of 7 percent. (c) All other fuel tanks that...

  10. 76 FR 25229 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane, Dynamic Test Requirements...

    Science.gov (United States)

    2011-05-04

    ... most seating is forward/aft facing on transport-category airplanes, the pass/fail criteria developed in... arm, chest, and head of an occupant seated next to the structure. A conservative representation of the... supports (armrests/walls). Pass/fail injury assessments: TTI and pelvic acceleration. (b) One...

  11. SIMULATION OF FLUID-SOLID INTERACTION ON WATER DITCHING OF AN AIRPLANE BY ALE METHOD

    Institute of Scientific and Technical Information of China (English)

    HUA Cheng; FANG Chao; CHENG Jin

    2011-01-01

    Ditching is considered as one of the important aspects of safety performances of airplanes.It is related primarily with the fluid-solid interaction,whose studies mainly depend on experiments at the present time.Numerical and analytical methods for fluid-solid interaction by using 3-D full scale airplane's model will reduce the dependence on the expensive model tests.Numerical studies can be used to estimate the safety of ditching and provide a reference for the crashworthiness design.This article proposes a 3-D dynamical structural model after the real shape of an airplane and an Arbitrary Lagrange-Euler (ALE) fluid-field model,to simulate the fluid-solid interactions caused by low speed ditching.The simulation is based on interaction computational methods,within LS-DYNA nonlinear finite-element code.The results of pressure distributions and accelerating time histories of the airplane's subfloor are discussed in the context of the safety of ditching,and the simulation results and the analytical methods are verified.

  12. 78 FR 75451 - Special Conditions: Cessna Model 750 Series Airplanes; Aircraft Electronic System Security...

    Science.gov (United States)

    2013-12-12

    ... the search function of the docket Web site, anyone can find and read the electronic form of all... be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http... Model 750 is a twin-engine pressurized executive jet airplane with standard seating provisions for...

  13. 76 FR 65103 - Special Conditions: Gulfstream Aerospace Corporation, Model GIV-X Airplane; Aircraft Electronic...

    Science.gov (United States)

    2011-10-20

    ... the commenter provides. Using the search function of the docket Web site, anyone can find and read the... Privacy Act Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478... configuration in the Gulfstream Model GIV-X passenger airplane. The Gulfstream Model GIV-X is a two-engine...

  14. 78 FR 73993 - Special Conditions: Cessna Model 680 Series Airplanes; Aircraft Electronic System Security...

    Science.gov (United States)

    2013-12-10

    .... Using the search function of the docket Web site, anyone can find and read the electronic form of all... 680 ``New Sovereign'' is a twin-engine pressurized executive jet airplane with standard seating..., and will have two aft-mounted Pratt & Whitney 306D engines. The proposed Cessna Model 680...

  15. 75 FR 70854 - Harmonization of Various Airworthiness Standards for Transport Category Airplanes-Flight Rules

    Science.gov (United States)

    2010-11-19

    ... complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78) or you... Conditions. In the preamble to that rulemaking (72 FR 44665), the FAA stated that we needed more time and... preamble to Amendment 25- 72, Special Review: Transport Category Airplane Airworthiness Standards (55...

  16. 76 FR 74649 - Harmonization of Various Airworthiness Standards for Transport Category Airplanes-Flight Rules

    Science.gov (United States)

    2011-12-01

    ... November 19, 2010 (75 FR 70854). The proposal discussed changes to part 25 in four areas: 1. Selection of... (55 FR 29756), July 20, 1990. The FAA considered them unnecessary since directional and lateral... Standards for Transport Category Airplanes--Flight Rules AGENCY: Federal Aviation Administration (FAA),...

  17. 76 FR 5503 - Airworthiness Directives; The Boeing Company Model 777-200 Series Airplanes

    Science.gov (United States)

    2011-02-01

    ..., and wiring to allow the flightcrew to turn off electrical power to the in-flight entertainment (IFE... category airplanes, we conducted a comprehensive in-flight entertainment (IFE) systems review. Earlier.... Unsafe Condition (e) This AD results from an in-flight entertainment (IFE) systems review. We...

  18. 76 FR 5505 - Airworthiness Directives; The Boeing Company Model 777-200 Series Airplanes

    Science.gov (United States)

    2011-02-01

    ..., and wiring to allow the flightcrew to turn off electrical power to the in-flight entertainment (IFE... various models of transport category airplanes, we conducted a comprehensive in-flight entertainment (IFE... in-flight entertainment (IFE) systems review. We are issuing this AD to ensure that the flightcrew...

  19. 75 FR 38945 - Airworthiness Directives; The Boeing Company Model 777-200 and -300 Series Airplanes

    Science.gov (United States)

    2010-07-07

    ... AD results from an in-flight entertainment (IFE) systems review. We are proposing this AD to ensure... category airplanes, we conducted a comprehensive in-flight entertainment (IFE) systems review. Earlier...: Communications. Unsafe Condition (e) This AD results from an in-flight entertainment (IFE) systems review. We...

  20. 76 FR 12617 - Airworthiness Directives; The Boeing Company Model 777-200 and -300 Series Airplanes

    Science.gov (United States)

    2011-03-08

    .... This proposed AD results from an in-flight entertainment (IFE) systems review. We are proposing this AD... various models of transport category airplanes, we conducted a comprehensive in-flight entertainment (IFE... AD results from an in-flight entertainment (IFE) systems review. We are issuing this AD to...

  1. 14 CFR 121.327 - Supplemental oxygen: Reciprocating engine powered airplanes.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Supplemental oxygen: Reciprocating engine... Equipment Requirements § 121.327 Supplemental oxygen: Reciprocating engine powered airplanes. (a) General. Except where supplemental oxygen is provided in accordance with § 121.331, no person may operate...

  2. 77 FR 16486 - Airworthiness Directives; Fokker Services B.V. Airplanes

    Science.gov (United States)

    2012-03-21

    ..., Amendment 39-10310 (63 FR 6066, February 6, 1998); and FAA AD 2009-18-05, Amendment 39-16001 (74 FR 43625... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not... arcing and potentially an onboard fire, possibly resulting in damage to the airplane and injury...

  3. 75 FR 80735 - Special Conditions: Gulfstream Model GVI Airplane; High Incidence Protection

    Science.gov (United States)

    2010-12-23

    ... conditions: (a) Electronic Flight Control System (EFCS)--The electronic and software command and control elements of the flight control system. (b) High Incidence Protection Function--An airplane level function... decelerated at an entry rate not exceeding 1 knot per second until the longitudinal pilot control is on...

  4. 76 FR 35324 - Special Conditions: Boeing Model 787 Series Airplanes; Seats With Inflatable Lapbelts

    Science.gov (United States)

    2011-06-17

    ... galley loading, passenger baggage, etc.); airplanes also operate where exposure to high intensity.... The inflatable material may not have an average burn rate of greater than 2.5 inches/minute when... materials are needed. The standard normally applied to fabrics is a 12-second vertical ignition...

  5. 14 CFR 121.511 - Flight time limitations: Flight engineers: airplanes.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Flight time limitations: Flight engineers... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Time Limitations: Supplemental Operations § 121.511 Flight time limitations: Flight engineers: airplanes. (a) In any operation in which...

  6. 75 FR 50869 - Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-12/47E Airplanes

    Science.gov (United States)

    2010-08-18

    ... Register on June 10, 2010 (75 FR 32863). That NPRM proposed to correct an unsafe condition for the... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant... Ltd. Model PC-12/47E Airplanes AGENCY: Federal Aviation Administration (FAA), Department...

  7. 75 FR 12150 - Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7 Airplanes

    Science.gov (United States)

    2010-03-15

    ... Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic... Ltd. Model PC-7 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation.... Relevant Service Information PILATUS Aircraft Ltd. has issued PILATUS PC-7 Service Bulletin No....

  8. 75 FR 32863 - Airworthiness Directives; PILATUS AIRCRAFT LTD. Model PC-12/47E Airplanes

    Science.gov (United States)

    2010-06-10

    ... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... Directives; PILATUS AIRCRAFT LTD. Model PC-12/47E Airplanes AGENCY: Federal Aviation Administration (FAA... receive comments by July 26, 2010. Affected ADs (b) None. Applicability (c) This AD applies to...

  9. 75 FR 66655 - Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7 Airplanes

    Science.gov (United States)

    2010-10-29

    ... Register on August 26, 2010 (75 FR 52482). That NPRM proposed to correct an unsafe condition for the...'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a... Ltd. Model PC-7 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...

  10. 75 FR 52482 - Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7 Airplanes

    Science.gov (United States)

    2010-08-26

    ... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... Ltd. Model PC-7 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation... Pilatus Aircraft Ltd. has issued PC-7 Service Bulletin No. 57-015, Rev. No. 1, date July 23, 2010....

  11. 14 CFR 125.377 - Fuel supply: Turbine-engine-powered airplanes other than turbopropeller.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Fuel supply: Turbine-engine-powered... AIRCRAFT Flight Release Rules § 125.377 Fuel supply: Turbine-engine-powered airplanes other than... wind and other weather conditions expected, it has enough fuel— (1) To fly to and land at the...

  12. Fracture and strain rate behavior of airplane fuselage materials under blast loading

    NARCIS (Netherlands)

    Mediavilla Varas, J.; Soetens, F.; Kroon, E.; Aanhold, J.E. van; Meulen, O.R. van der; Sagimon, M.

    2010-01-01

    The dynamic behavior of three commonly used airplane fuselage materials is investigated, namely of Al2024-T3, Glare-3 and CFRP. Dynamic tensile tests using a servo-hydraulic and a light weight shock testing machine (LSM) have been performed. The results showed no strain rate effect on Al2024-T3 and a

  13. 78 FR 70209 - Airworthiness Directives; XtremeAir GmbH Airplanes

    Science.gov (United States)

    2013-11-25

    ..., Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4123; fax: (816) 329-4090; email: karl.schletzbaum@faa.gov . SUPPLEMENTARY INFORMATION... mounts from a specific supplier may be affected. This condition, if not detected and corrected,...

  14. 78 FR 64894 - Airworthiness Directives; B-N Group Ltd. Airplanes

    Science.gov (United States)

    2013-10-30

    ... INFORMATION CONTACT: Taylor Martin, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301... . SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments... control of the aeroplane. To address this potential unsafe condition, Britten-Norman Aircraft have...

  15. 78 FR 1765 - Requirements for Chemical Oxygen Generators Installed on Transport Category Airplanes

    Science.gov (United States)

    2013-01-09

    ..., Security Considerations for Lavatory Oxygen Systems (76 FR 12550, March 8, 2011), Docket No. FAA-2011-0186... Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as... Airplanes (77 FR 38000, June 26, 2012). Several years ago in an unrelated initiative, the FAA tasked...

  16. 75 FR 52255 - Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes

    Science.gov (United States)

    2010-08-25

    ... (75 FR 35616, June 23, 2010), and by adding a new AD to read as follows: 2010-17-18 Air Tractor, Inc... FR 19994, April 19, 2006), the Director of the Federal Register approved the incorporation by..., AT-600, and AT- 800 series airplanes. In 2001, we issued AD 2001-10-04, Amendment 39-12230 (66...

  17. 75 FR 35616 - Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes

    Science.gov (United States)

    2010-06-23

    ... airplane. DATES: This AD becomes effective on July 28, 2010. As of April 21, 2006 (71 FR 19994, April 19... (74 FR 39243). The NPRM proposed to supersede AD 2006-08-09 to clarify the SNs of the Models AT-802... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a...

  18. 78 FR 76248 - Special Conditions: Airbus, Model A350-900 Series Airplane; Side Stick Controller

    Science.gov (United States)

    2013-12-17

    ..., 2000 (65 FR 19477-19478), as well as at http:// DocketsInfo.dot.gov/ . Docket: Background documents or... Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW... by wrist and not by arms. Discussion Special conditions for Airbus side stick controllers have...

  19. 78 FR 67077 - Special Conditions: Airbus, Model A350-900 Series Airplane; Side Stick Controllers

    Science.gov (United States)

    2013-11-08

    ... Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as... FURTHER INFORMATION CONTACT: Loran Haworth, FAA, Airplane and Flight Interface Branch, ANM-111, Transport... maneuverability, including the effects of turbulence. (2) General ergonomics: Arm rest comfort and support,...

  20. 76 FR 54141 - Airworthiness Directives; Cessna Aircraft Company Model 680 Airplanes

    Science.gov (United States)

    2011-08-31

    ... the left main electrical bus and selected the left generator to OFF. The co-pilot (flying the airplane... pounds. Loss of power on the left main electrical bus results in a false cross-feed command to the right... after receipt. FOR FURTHER INFORMATION CONTACT: Nhien Hoang, Aerospace Engineer, Electrical Systems...

  1. 78 FR 75453 - Special Conditions: Cessna Model 750 Series Airplanes; Aircraft Electronic System Security...

    Science.gov (United States)

    2013-12-12

    ... Privacy Act Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478... control and navigation systems, 2. Operator business and administrative support, and 3. Passenger... unintentional corruption of data and systems critical to the safety and maintenance of the airplane....

  2. 77 FR 21395 - Airworthiness Directives; Fokker Services B.V. Airplanes

    Science.gov (United States)

    2012-04-10

    ... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034...-085-AD; Amendment 39-17011; AD 2012-07-05] RIN 2120-AA64 Airworthiness Directives; Fokker Services B.V... Fokker Services B.V. Model F.27 Mark 050 airplanes. This proposed AD would require performing a...

  3. An example of applied colour vision research: the conspicuity of airplane colour

    NARCIS (Netherlands)

    Lucassen, M.P.

    2002-01-01

    This paper describes the application of the combined knowledge on colorimetry, colour imaging (visualization) and colour perception in an aviation related research project. It involves the optimisation of the conspicuity of the colour scheme of an airplane, with the purpose of minimizing the changes

  4. A Conceptual Design and Analysis Method for Conventional and Unconventional Airplanes

    NARCIS (Netherlands)

    Elmendorp, R.J.M.; Vos, R.; La Rocca, G.

    2014-01-01

    A design method is presented that has been implemented in a software program to investigate the merits of conventional and unconventional transport airplanes. Design and analysis methods are implemented in a design tool capable of creating a conceptual design based on a set of toplevel requirements.

  5. 78 FR 275 - Airworthiness Directives; REIMS Aviation S.A. Airplanes

    Science.gov (United States)

    2013-01-03

    ... 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... Directives; REIMS Aviation S.A. Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a...

  6. 14 CFR 135.393 - Large nontransport category airplanes: Landing limitations: Destination airports.

    Science.gov (United States)

    2010-01-01

    ...: Landing limitations: Destination airports. 135.393 Section 135.393 Aeronautics and Space FEDERAL AVIATION... category airplanes: Landing limitations: Destination airports. (a) No person operating a large nontransport... effective length of the most suitable runway at the destination airport; and (2) Is greater than the...

  7. 76 FR 67633 - Airworthiness Directives; Dassault Aviation Model Mystere-Falcon 50 Airplanes

    Science.gov (United States)

    2011-11-02

    ... products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI... the flap tracks could lead to flap asymmetry and loss of control of the airplane. The proposed AD... Friday, except Federal holidays. For service information identified in this proposed AD, contact...

  8. 76 FR 14346 - Airworthiness Directives; Diamond Aircraft Industries GmbH Model DA 42 Airplanes

    Science.gov (United States)

    2011-03-16

    ... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... Industries GmbH Model DA 42 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... been reportedly found on DA 42 Main Landing Gear (MLG) Damper-to-Trailing Arm joints during...

  9. 76 FR 31457 - Airworthiness Directives; Diamond Aircraft Industries GmbH Model DA 42 Airplanes

    Science.gov (United States)

    2011-06-01

    ... (76 FR 14346). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant... Industries GmbH Model DA 42 Airplanes AGENCY: Federal Aviation Administration (FAA), Department...

  10. 76 FR 81360 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G280 Airplane, Operation Without Normal...

    Science.gov (United States)

    2011-12-28

    ... 27, 2011 (76 FR 66660). No comments were received, and the special conditions are adopted as proposed... generation and distribution architecture is equipped with an auxiliary power unit (APU) and is not equipped... power, which is generated by the airplane's engine generators or APU is not extremely improbable....

  11. 76 FR 36864 - Special Conditions: Gulfstream Model GVI Airplane; Operation Without Normal Electric Power

    Science.gov (United States)

    2011-06-23

    ... published in the Federal Register on February 14, 2011 (76 FR 8314). Only one comment was received, which... normal sources of engine and auxiliary power unit (APU) generated electrical power inoperative. Service experience has shown that loss of all electrical power from the airplane's engine and APU driven...

  12. 76 FR 8314 - Special Conditions: Gulfstream Model GVI Airplane; Operation Without Normal Electric Power

    Science.gov (United States)

    2011-02-14

    ... power unit (APU) generated electrical power inoperative. Service experience has shown that loss of all electrical power from the airplane's engine and APU driven generators is not extremely improbable. Thus... failure must be made. 4. Availability of APU operation should not be considered in establishing...

  13. 78 FR 41684 - Special Conditions: Embraer S.A. Model EMB-550 Airplanes, Sudden Engine Stoppage

    Science.gov (United States)

    2013-07-11

    ... airplane, was published in the Federal Register on September 25, 2012 (77 FR 58970). No comments were... auxiliary power unit (APU) installations, the APU mounts and adjacent supporting airframe structure must be... imposed by each of the following: (a) Sudden APU deceleration due to malfunction or structural...

  14. 76 FR 63851 - Special Conditions: Learjet Inc., Model LJ-200-1A10 Airplane, Pilot-Compartment View Through...

    Science.gov (United States)

    2011-10-14

    ... the following novel or unusual design features: The Model LJ-200-1A10 airplane flight deck design... pitch attitude. In these cases, areas of airflow disturbance or separation on the windshield could...

  15. Parametric study of variation in cargo-airplane performance related to progression from current to spanloader designs

    Science.gov (United States)

    Toll, T. A.

    1980-01-01

    A parametric analysis was made to investigate the relationship between current cargo airplanes and possible future designs that may differ greatly in both size and configuration. The method makes use of empirical scaling laws developed from statistical studies of data from current and advanced airplanes and, in addition, accounts for payload density, effects of span distributed load, and variations in tail area ratio. The method is believed to be particularly useful for exploratory studies of design and technology options for large airplanes. The analysis predicts somewhat more favorable variations of the ratios of payload to gross weight and block fuel to payload as the airplane size is increased than has been generally understood from interpretations of the cube-square law. In terms of these same ratios, large all wing (spanloader) designs show an advantage over wing-fuselage designs.

  16. Comparison of theoretical predicted longitudinal aerodynamic characteristics with full-scale wind tunnel data on the ATLIT airplane

    Science.gov (United States)

    Vandam, C. P. G.; Griswold, M.; Roskam, J.

    1979-01-01

    An analytical method is presented for predicting the lift coefficient, the pitching moment coefficient, and the drag coefficient of light, twin-engine, propeller-driven airplanes. The method was applied to the Advanced Technology Light Twin-Engine airplane. The calculated characteristics were then correlated against full scale wind tunnel data. The analytical method was found to predict the drag and pitching moment fairly well. However, the lift prediction was extremely poor.

  17. Rotation-and-scale-invariant airplane detection in high-resolution satellite images based on deep-Hough-forests

    Science.gov (United States)

    Yu, Yongtao; Guan, Haiyan; Zai, Dawei; Ji, Zheng

    2016-02-01

    This paper proposes a rotation-and-scale-invariant method for detecting airplanes from high-resolution satellite images. To improve feature representation capability, a multi-layer feature generation model is created to produce high-order feature representations for local image patches through deep learning techniques. To effectively estimate airplane centroids, a Hough forest model is trained to learn mappings from high-order patch features to the probabilities of an airplane being present at specific locations. To handle airplanes with varying orientations, patch orientation is defined and integrated into the Hough forest to augment Hough voting. The scale invariance is achieved by using a set of scale factors embedded in the Hough forest. Quantitative evaluations on the images collected from Google Earth service show that the proposed method achieves a completeness, correctness, quality, and F1-measure of 0.968, 0.972, 0.942, and 0.970, respectively, in detecting airplanes with arbitrary orientations and sizes. Comparative studies also demonstrate that the proposed method outperforms the other three existing methods in accurately and completely detecting airplanes in high-resolution remotely sensed images.

  18. Predicted performance benefits of an adaptive digital engine control system of an F-15 airplane

    Science.gov (United States)

    Burcham, F. W., Jr.; Myers, L. P.; Ray, R. J.

    1985-01-01

    The highly integrated digital electronic control (HIDEC) program will demonstrate and evaluate the improvements in performance and mission effectiveness that result from integrating engine-airframe control systems. Currently this is accomplished on the NASA Ames Research Center's F-15 airplane. The two control modes used to implement the systems are an integrated flightpath management mode and in integrated adaptive engine control system (ADECS) mode. The ADECS mode is a highly integrated mode in which the airplane flight conditions, the resulting inlet distortion, and the available engine stall margin are continually computed. The excess stall margin is traded for thrust. The predicted increase in engine performance due to the ADECS mode is presented in this report.

  19. Interactive Multi-objective Optimization Design for the Pylon Structure of an Airplane

    Institute of Scientific and Technical Information of China (English)

    An Weigang; Li Weiji

    2007-01-01

    The pylon structure of an airplane is very complex, and its high-fidelity analysis is quite time-consuming. If posterior preference optimization algorithm is used to solve this problem, the huge time consumption will be unacceptable in engineering practice due to the large amount of evaluation needed for the algorithm. So, a new interactive optimization algorithm-interactive multi-objective particle swarm optimization (IMOPSO) is presented. IMOPSO is efficient, simple and operable. The decision-maker can expediently determine the accurate preference in IMOPSO. IMOPSO is used to perform the pylon structure optimization design of an airplane, and a satisfactory design is achieved after only 12 generations of IMOPSO evolutions. Compared with original design, the maximum displacement of the satisfactory design is reduced, and the mass of the satisfactory design is decreased for 22%.

  20. Application of selected advanced technologies to high performance, single-engine, business airplanes

    Science.gov (United States)

    Domack, C. S.; Martin, G. L.

    1984-01-01

    Improvements in performance and fuel efficiency are evaluated for five new configurations of a six place, single turboprop, business airplane derived from a conventional, aluminum construction baseline aircraft. Results show the greatest performance gains for enhancements in natural laminar flow. A conceptual diesel engine provides greater fuel efficiency but reduced performance. Less significant effects are produced by the utilization of composite materials construction or by reconfiguration from tractor to pusher propeller installation.

  1. 76 FR 9495 - Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes

    Science.gov (United States)

    2011-02-18

    ..., amendment 39-16412 (75 FR 52255, August 25, 2010), for all Air Tractor Models AT-802 and AT- 802A airplanes.... On December 16, 2010, we issued AD 2010-17-18 R1, amendment 39- 16552 (75 FR 82219, December 30, 2010...-029-AD; Amendment 39-16552; AD 2010-17-18 R1] RIN 2120-AA64 Airworthiness Directives; Air Tractor,...

  2. Analysis of airplane boarding via space-time geometry and random matrix theory

    CERN Document Server

    Bachmat, E; Skiena, S S; Stolyarov, N; Berend, D; Bachmat, Eitan; Sapir, Luba; Skiena, Steven; Stolyarov, Natan; berend, Daniel

    2005-01-01

    We show that airplane boarding can be asymptotically modeled by 2-dimensional Lorentzian geometry. Boarding time is given by the maximal proper time among curves in the model. Discrepancies between the model and simulation results are closely related to random matrix theory. We then show how such models can be used to explain why some commonly practiced airline boarding policies are ineffective and even detrimental.

  3. Role of Meteorology in Flights of a Solar-Powered Airplane

    Science.gov (United States)

    Donohue, Casey

    2004-01-01

    In the summer of 2001, the Helios prototype solar-powered uninhabited aerial vehicle (UAV) [a lightweight, remotely piloted airplane] was deployed to the Pacific Missile Range Facility (PMRF), at Kauai, Hawaii, in an attempt to fly to altitudes above 100,000 ft (30.48 km). The goal of flying a UAV to such high altitudes has been designated a level-I milestone of the NASA Environmental Research Aircraft and Sensor Technology (ERAST) program. In support of this goal, meteorologists from NASA Dryden Flight Research Center were sent to PMRF, as part of the flight crew, to provide current and forecast weather information to the pilots, mission directors, and planners. Information of this kind is needed to optimize flight conditions for peak aircraft performance and to enable avoidance of weather conditions that could adversely affect safety. In general, the primary weather data of concern for ground and flight operations are wind speeds (see Figure 1). Because of its long wing span [247 ft (.75 m)] and low weight [1,500 to 1,600 lb (about 680 to 726 kg)], the Helios airplane is sensitive to wind speeds exceeding 7 kn (3.6 m/s) at the surface. Also, clouds are of concern because they can block sunlight needed to energize an array of solar photovoltaic cells that provide power to the airplane. Vertical wind shear is very closely monitored in order to prevent damage or loss of control due to turbulence.

  4. Analysis of an NPP Structure subjected to Vibrations Induced from Airplane Crashes

    International Nuclear Information System (INIS)

    After the terrorists' attacks with civilian airplanes on September 11, 2001, special attention has been paid to the potential for an airplane crash into a Nuclear Power Plant (NPP) as a man-made hazard. An airplane crash (APC) into an NPP has the potential to damage the roofs and walls of these structures, as well as other systems and components such as pipelines, electric motors, power supplies, power cables of electricity transmission that are important for safety. Therefore, an evaluation of the structural response to an APC is important for the safety of NPPs to be confirmed. A structural integrity analysis was carried out focusing on the vibration effects of an APC on an NPP structure. The NPP structure under consideration has been conceptually redesigned based on APR1400 to have double containments for the purpose of a feasibility study to meet European requirements. The finite element method was used for the structural analysis of the NPP, and the computer code ABAQUS was employed for this analysis

  5. Exposure to tri-o-cresyl phosphate detected in jet airplane passengers

    International Nuclear Information System (INIS)

    The aircraft cabin and flight deck ventilation are supplied from partially compressed unfiltered bleed air directly from the engine. Worn or defective engine seals can result in the release of engine oil into the cabin air supply. Aircrew and passengers have complained of illness following such “fume events”. Adverse health effects are hypothesized to result from exposure to tricresyl phosphate mixed esters, a chemical added to jet engine oil and hydraulic fluid for its anti-wear properties. Our goal was to develop a laboratory test for exposure to tricresyl phosphate. The assay was based on the fact that the active-site serine of butyrylcholinesterase reacts with the active metabolite of tri-o-cresyl phosphate, cresyl saligenin phosphate, to make a stable phosphorylated adduct with an added mass of 80 Da. No other organophosphorus agent makes this adduct in vivo on butyrylcholinesterase. Blood samples from jet airplane passengers were obtained 24–48 h after completing a flight. Butyrylcholinesterase was partially purified from 25 ml serum or plasma, digested with pepsin, enriched for phosphorylated peptides by binding to titanium oxide, and analyzed by mass spectrometry. Of 12 jet airplane passengers tested, 6 were positive for exposure to tri-o-cresyl phosphate that is, they had detectable amounts of the phosphorylated peptide FGEpSAGAAS. The level of exposure was very low. No more than 0.05 to 3% of plasma butyrylcholinesterase was modified. None of the subjects had toxic symptoms. Four of the positive subjects were retested 3 to 7 months following their last airplane trip and were found to be negative for phosphorylated butyrylcholinesterase. In conclusion, this is the first report of an assay that detects exposure to tri-o-cresyl phosphate in jet airplane travelers. -- Highlights: ► Travel on jet airplanes is associated with an illness, aerotoxic syndrome. ► A possible cause is exposure to tricresyl phosphate in engine lubricating oil. ► A blood

  6. A knowledge-based design framework for airplane conceptual and preliminary design

    Science.gov (United States)

    Anemaat, Wilhelmus A. J.

    The goal of work described herein is to develop the second generation of Advanced Aircraft Analysis (AAA) into an object-oriented structure which can be used in different environments. One such environment is the third generation of AAA with its own user interface, the other environment with the same AAA methods (i.e. the knowledge) is the AAA-AML program. AAA-AML automates the initial airplane design process using current AAA methods in combination with AMRaven methodologies for dependency tracking and knowledge management, using the TechnoSoft Adaptive Modeling Language (AML). This will lead to the following benefits: (1) Reduced design time: computer aided design methods can reduce design and development time and replace tedious hand calculations. (2) Better product through improved design: more alternative designs can be evaluated in the same time span, which can lead to improved quality. (3) Reduced design cost: due to less training and less calculation errors substantial savings in design time and related cost can be obtained. (4) Improved Efficiency: the design engineer can avoid technically correct but irrelevant calculations on incomplete or out of sync information, particularly if the process enables robust geometry earlier. Although numerous advancements in knowledge based design have been developed for detailed design, currently no such integrated knowledge based conceptual and preliminary airplane design system exists. The third generation AAA methods are tested over a ten year period on many different airplane designs. Using AAA methods will demonstrate significant time savings. The AAA-AML system will be exercised and tested using 27 existing airplanes ranging from single engine propeller, business jets, airliners, UAV's to fighters. Data for the varied sizing methods will be compared with AAA results, to validate these methods. One new design, a Light Sport Aircraft (LSA), will be developed as an exercise to use the tool for designing a new airplane

  7. Exposure to tri-o-cresyl phosphate detected in jet airplane passengers

    Energy Technology Data Exchange (ETDEWEB)

    Liyasova, Mariya, E-mail: mliyasov@unmc.edu [Eppley Institute, University of Nebraska Medical Center, Omaha, NE 68198-5950 (United States); Department of Environmental, Agricultural, and Occupational Health, University of Nebraska Medical Center, Omaha, NE (United States); Li, Bin, E-mail: binli@unmc.edu [Eppley Institute, University of Nebraska Medical Center, Omaha, NE 68198-5950 (United States); Schopfer, Lawrence M., E-mail: lmschopf@unmc.edu [Eppley Institute, University of Nebraska Medical Center, Omaha, NE 68198-5950 (United States); Nachon, Florian, E-mail: fnachon@nachon.net [Departement de Toxicologie, Institut de Recherche Biomedicale des Armees, 24 avenue des Marquis du Gresivaudan, 38702 La Tronche (France); Masson, Patrick, E-mail: pmasson@unmc.edu [Departement de Toxicologie, Institut de Recherche Biomedicale des Armees, 24 avenue des Marquis du Gresivaudan, 38702 La Tronche (France); Eppley Institute, University of Nebraska Medical Center, Omaha, NE 68198-5950 (United States); Furlong, Clement E., E-mail: clem@uw.edu [Department of Medicine (Div. Medical Genetics) and Genome Sciences, University of Washington, Seattle, WA 98195 (United States); Lockridge, Oksana, E-mail: olockrid@unmc.edu [Eppley Institute, University of Nebraska Medical Center, Omaha, NE 68198-5950 (United States); Department of Environmental, Agricultural, and Occupational Health, University of Nebraska Medical Center, Omaha, NE (United States)

    2011-11-15

    The aircraft cabin and flight deck ventilation are supplied from partially compressed unfiltered bleed air directly from the engine. Worn or defective engine seals can result in the release of engine oil into the cabin air supply. Aircrew and passengers have complained of illness following such 'fume events'. Adverse health effects are hypothesized to result from exposure to tricresyl phosphate mixed esters, a chemical added to jet engine oil and hydraulic fluid for its anti-wear properties. Our goal was to develop a laboratory test for exposure to tricresyl phosphate. The assay was based on the fact that the active-site serine of butyrylcholinesterase reacts with the active metabolite of tri-o-cresyl phosphate, cresyl saligenin phosphate, to make a stable phosphorylated adduct with an added mass of 80 Da. No other organophosphorus agent makes this adduct in vivo on butyrylcholinesterase. Blood samples from jet airplane passengers were obtained 24-48 h after completing a flight. Butyrylcholinesterase was partially purified from 25 ml serum or plasma, digested with pepsin, enriched for phosphorylated peptides by binding to titanium oxide, and analyzed by mass spectrometry. Of 12 jet airplane passengers tested, 6 were positive for exposure to tri-o-cresyl phosphate that is, they had detectable amounts of the phosphorylated peptide FGEpSAGAAS. The level of exposure was very low. No more than 0.05 to 3% of plasma butyrylcholinesterase was modified. None of the subjects had toxic symptoms. Four of the positive subjects were retested 3 to 7 months following their last airplane trip and were found to be negative for phosphorylated butyrylcholinesterase. In conclusion, this is the first report of an assay that detects exposure to tri-o-cresyl phosphate in jet airplane travelers. -- Highlights: Black-Right-Pointing-Pointer Travel on jet airplanes is associated with an illness, aerotoxic syndrome. Black-Right-Pointing-Pointer A possible cause is exposure to

  8. Effects from airplane crashes and gas explosions to Leningrad nuclear plant

    Energy Technology Data Exchange (ETDEWEB)

    Junttila, K.; Varpasuo, P. [IVO Power Engineering Oy, Vantaa (Finland)

    1998-12-31

    In this study the effects of aircraft crash and gas explosion to Leningrad Nuclear Power Plant has been researched. One of the two reactor buildings is modeled with finite element method using the pre-processor program MSC/PATRAN and analyzed with MSC/NASTRAN analysis program. In MSC/PATRAN or FEMAP, which is a pre-processor program of MSC/NASTRAN for Windows, the reactor building of the plant has been modeled with shell and beam elements and the load sets describing the aircraft crash and gas explosion have been developed. The crash loads are from Cessna 210 civil airplane crash with impact velocity 360 km/h and maximum impact force of 7 MN and Phantom RF-43 military airplane crash with impact velocity 215 m/s and with maximum impact force of 110 MN. The gas explosion pressure wave simulates the deflagration wave with maximum pressure of 0,045 MPa. Seven Cessna 210 airplane crash locations, two Phantom RF-43 airplane crash locations and one gas explosion load case is modeled. Airplane crash loads were from different directions and to different points of impact in the reactor building. The gas explosion load was assumed to affect the reactor building from one side parallel to one of the global coordinate axes of the model. With MSC/NASTRAN reactions from loads are analyzed. All loads were timedependent; their magnitude varied with time and consequently the analysis was carried out with the aid of transient response analysis. Time step in Cessna 210 analysis was 0,003 s and in Phantom RF-43 and gas explosion analyses 0,01 s. The greatest displacement from Cessna 210 loads was 12 mm and from Phantom RF-43 load 344 mm. The last value shows that construction would fail with that load. The greatest displacement from gas explosion load was 68 mm. Stresses are not so interesting in this preliminary analysis of the effects, but they are shown in pictures embedded in the report text. Displacements were greatest in upper part of the reactor building, where no intersections

  9. Definition of 1992 Technology Aircraft Noise Levels and the Methodology for Assessing Airplane Noise Impact of Component Noise Reduction Concepts

    Science.gov (United States)

    Kumasaka, Henry A.; Martinez, Michael M.; Weir, Donald S.

    1996-01-01

    This report describes the methodology for assessing the impact of component noise reduction on total airplane system noise. The methodology is intended to be applied to the results of individual study elements of the NASA-Advanced Subsonic Technology (AST) Noise Reduction Program, which will address the development of noise reduction concepts for specific components. Program progress will be assessed in terms of noise reduction achieved, relative to baseline levels representative of 1992 technology airplane/engine design and performance. In this report, the 1992 technology reference levels are defined for assessment models based on four airplane sizes - an average business jet and three commercial transports: a small twin, a medium sized twin, and a large quad. Study results indicate that component changes defined as program final goals for nacelle treatment and engine/airframe source noise reduction would achieve from 6-7 EPNdB reduction of total airplane noise at FAR 36 Stage 3 noise certification conditions for all of the airplane noise assessment models.

  10. 77 FR 64029 - Special Conditions: Airbus Model A318, A319, A320, and A321 Series Airplanes; Design Dive Speed

    Science.gov (United States)

    2012-10-18

    ... April 11, 2000 (65 FR 19477-19478), as well as at http: DocketsInfo.dot.gov/. Docket: Background... Series Airplanes; Design Dive Speed AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final... airplanes. These design features include a high-speed protection system. The applicable...

  11. 78 FR 76736 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Side...

    Science.gov (United States)

    2013-12-19

    ... be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http...: Joe Jacobsen, FAA, Airplane and Flightcrew Interface Branch, ANM-111, Transport Airplane Directorate... turbulence. 2. General ergonomics: Arm rest comfort and support, local freedom of movement,...

  12. 14 CFR Appendix F to Part 36 - Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller-Driven, Commuter...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller-Driven, Commuter Category Airplane Certification Tests Prior to December 22, 1988 F Appendix F to Part 36 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT NOISE...

  13. Design of a Mars Airplane Propulsion System for the Aerial Regional-Scale Environmental Survey (ARES) Mission Concept

    Science.gov (United States)

    Kuhl. Christopher A.

    2009-01-01

    The Aerial Regional-Scale Environmental Survey (ARES) is a Mars exploration mission concept with the goal of taking scientific measurements of the atmosphere, surface, and subsurface of Mars by using an airplane as the payload platform. ARES team first conducted a Phase-A study for a 2007 launch opportunity, which was completed in May 2003. Following this study, significant efforts were undertaken to reduce the risk of the atmospheric flight system, under the NASA Langley Planetary Airplane Risk Reduction Project. The concept was then proposed to the Mars Scout program in 2006 for a 2011 launch opportunity. This paper summarizes the design and development of the ARES airplane propulsion subsystem beginning with the inception of the ARES project in 2002 through the submittal of the Mars Scout proposal in July 2006.

  14. Full-Scale Wind-Tunnel Investigation of the VZ-5 Four-Propeller Deflected-Slipstream VTOL Airplane

    Science.gov (United States)

    Fink, Marvin P.

    1963-01-01

    The investigation was conducted to determine the static stability and control characteristics of the VZ-5 VTOL air-plane over the speed range from hovering to forward flight. Force and moment data were taken over a range of angles of attack of 0 to 15 deg and a range of sideslip of +/-10 deg for flap deflections from 0 to 77 deg. The longitudinal stability and trim characteristics were found to be quite unacceptable and it did not seem that they could be corrected with any reasonable modifications to the airplane.

  15. A revolutionary approach to composite construction and flight management systems for small, general aviation airplanes

    Science.gov (United States)

    Roskam, Jan; Wenninger, ED

    1992-01-01

    The design studies for two composite general aviation airplanes are presented. The main consideration for both of the designs was to avoid the typical 'metal replacement' philosophy that has hindered the widespread use of composites in general aviation aircraft. The first design is for a low wing aircraft based on the Smith Aircraft Corporation GT-3 Global Trainer. The second aircraft is a composite version of the Cessna 152. The project was conducted as a graduate level design class under the auspices of the KU/NASA/USRA Advanced Design Program in aeronautics. The results obtained from the Fall semester of 1991 and the Spring semester of 1992 are presented.

  16. Effect of two types of helium circulators on the performance of a subsonic nuclear powered airplane

    Science.gov (United States)

    Strack, W. C.

    1971-01-01

    Two types of helium circulators are analytically compared on the bases of their influence on airplane payload and on propulsion system variables. One type of circulator is driven by the turbofan engines with power takeoff shafting while the other, a turbocirculator, is powered by a turbine placed in the helium loop between the nuclear reactor and the helium-to-air heat exchangers inside the engines. Typical results show that the turbocirculator yields more payload for circulator efficiencies greater than 0.82. Optimum engine and heat exchanger temperatures and pressures are significantly lower in the turbocirculator case compared to the engine-driven circulator scheme.

  17. Impact of sequential disorder on the scaling behavior of airplane boarding time

    CERN Document Server

    Baek, Yongjoo; Jeong, Hawoong

    2013-01-01

    Airplane boarding process is an example where disorder properties of the system are relevant to the emergence of universality classes. Based on a simple model, we present a systematic analysis of finite-size effects in boarding time, and propose a comprehensive view of the role of sequential disorder in the scaling behavior of boarding time against the plane size. Using numerical simulations and mathematical arguments, we find how the scaling behavior depends on the number of seat columns and the range of sequential disorder. Our results show that new scaling exponents can arise as disorder is localized to varying extents.

  18. AVIATR - Aerial Vehicle for In-situ and Airborne Titan Reconnaissance A Titan Airplane Mission Concept

    Science.gov (United States)

    Barnes, Jason W.; Lemke, Lawrence; Foch, Rick; McKay, Christopher P.; Beyer, Ross A.; Radebaugh, Jani; Atkinson, David H.; Lorenz, Ralph D.; LeMouelic, Stephane; Rodriguez, Sebastien; Gundlach, Jay; Giannini, Francesco; Bain, Sean; Flasar, F. Michael; Hurford, Terry; Anderson, Carrie M.; Merrison, Jon; Adamkovics, Mate; Kattenhorn, Simon A.; Mitchell, Jonathan; Burr, Devon M.; Colaprete, Anthony; Schaller, Emily; Friedson, A. James; Edgett, Kenneth S.; Coradini, Angioletta; Adriani, Alberto; Sayanagi, Kunio M.; Malaska, Michael J.; Morabito, David; Reh, Kim

    2011-01-01

    We describe a mission concept for a stand-alone Titan airplane mission: Aerial Vehicle for In-situ and Airborne Titan Reconnaissance (AVIATR). With independent delivery and direct-to-Earth communications, AVIATR could contribute to Titan science either alone or as part of a sustained Titan Exploration Program. As a focused mission, AVIATR as we have envisioned it would concentrate on the science that an airplane can do best: exploration of Titan's global diversity. We focus on surface geology/hydrology and lower-atmospheric structure and dynamics. With a carefully chosen set of seven instruments-2 near-IR cameras, 1 near-IR spectrometer, a RADAR altimeter, an atmospheric structure suite, a haze sensor, and a raindrop detector-AVIATR could accomplish a significant subset of the scientific objectives of the aerial element of flagship studies. The AVIATR spacecraft stack is composed of a Space Vehicle (SV) for cruise, an Entry Vehicle (EV) for entry and descent, and the Air Vehicle (AV) to fly in Titan's atmosphere. Using an Earth-Jupiter gravity assist trajectory delivers the spacecraft to Titan in 7.5 years, after which the AVIATR AV would operate for a 1-Earth-year nominal mission. We propose a novel 'gravity battery' climb-then-glide strategy to store energy for optimal use during telecommunications sessions. We would optimize our science by using the flexibility of the airplane platform, generating context data and stereo pairs by flying and banking the AV instead of using gimbaled cameras. AVIATR would climb up to 14 km altitude and descend down to 3.5 km altitude once per Earth day, allowing for repeated atmospheric structure and wind measurements all over the globe. An initial Team-X run at JPL priced the AVIATR mission at FY10 $715M based on the rules stipulated in the recent Discovery announcement of opportunity. Hence we find that a standalone Titan airplane mission can achieve important science building on Cassini's discoveries and can likely do so within

  19. Assessment of JVX Proprotor Performance Data in Hover and Airplane-Mode Flight Conditions

    Science.gov (United States)

    Acree, C. W., Jr.

    2016-01-01

    A 0.656-scale V-22 proprotor, the Joint Vertical Experimental (JVX) rotor, was tested at the NASA Ames Research Center in both hover and airplane-mode (high-speed axial flow) flight conditions, up to an advance ratio of 0.562 (231 knots). This paper examines the two principal data sets generated by those tests, and includes investigations of hub spinner tares, torque/thrust measurement interactions, tunnel blockage effects, and other phenomena suspected of causing erroneous measurements or predictions. Uncertainties in hover and high-speed data are characterized. The results are reported here to provide guidance for future wind tunnel tests, data processing, and data analysis.

  20. Real-Time Simulation of Aeroheating of the Hyper-X Airplane

    Science.gov (United States)

    Gong, Les

    2005-01-01

    A capability for real-time computational simulation of aeroheating has been developed in support of the Hyper-X program, which is directed toward demonstrating the feasibility of operating an air-breathing ramjet/scramjet engine at mach 5, mach 7, and mach 10. The simulation software will serve as a valuable design tool for initial trajectory studies in which aerodynamic heating is expected to exert a major influence in the design of the Hyper-X airplane; this tool will aid in the selection of materials, sizing of structural skin thicknesses, and selection of components of a thermal-protection system (TPS) for structures that must be insulated against aeroheating.

  1. THREE DIMENSIONAL MOVEMENT MEASUREMENT FOR THE WING OF A FLYING AIRPLANE

    Institute of Scientific and Technical Information of China (English)

    于起峰; 邱志强; 孙祥一; 陆宏伟

    2003-01-01

    The movement parameters of a wing of a flying airplane are important for its design,analysis and life-estimation, while the three dimensional (3D) measurement of these parameters is a difficult task. A measurement setup is proposed as well as its corresponding calibration methods for the camera system on both ground condition and air condition, image processing algorithms and a new method of locating 3D straight lines through plane-plane intersection are developed. The test results show that the 3D measurement accuracy in the condition of flying in the air can be better than 1 mm.

  2. Fatigue of titanium alloys in a supersonic-cruise airplane environment

    Science.gov (United States)

    Imig, L. A.

    1976-01-01

    The test programs conducted by several aerospace companies and NASA, summarized in this paper, studied several titanium materials previously identified as having high potential for application to supersonic cruise airplane structures. These studies demonstrate that the temperature (560 K) by itself produced no significant degradation of the materials. However, the fatigue resistance of titanium-alloy structures, in which thermal and loading effects are combined, has been studied insufficiently. The predominant topic for future study of fatigue problems in Mach 3 structures should be the influences of thermal stress particularly, the effects of thermal stress on failure location.

  3. Investigation of a fatal airplane crash: autopsy, computed tomography, and injury pattern analysis used to determine who was steering the plane at time of accident. A case report

    DEFF Research Database (Denmark)

    Høyer, Christian Bjerre; Nielsen, Trine Skov; Nagel, Lise Loft;

    2012-01-01

    A fatal accident is reported in which a small single-engine light airplane crashed. The airplane carried two persons in the front seats, both of whom possessed valid pilot certificates. Both victims were subject to autopsy, including post-mortem computed tomography scanning (PMCT) prior to the au......A fatal accident is reported in which a small single-engine light airplane crashed. The airplane carried two persons in the front seats, both of whom possessed valid pilot certificates. Both victims were subject to autopsy, including post-mortem computed tomography scanning (PMCT) prior...... to the autopsy. The autopsies showed massive destruction to the bodies of the two victims but did not identify any signs of acute or chronic medical conditions that could explain loss of control of the airplane. PMCT, histological examination, and forensic chemical analysis also failed to identify an explanation...... for the crash. A detailed review of an airplane identical to the crashed airplane was performed in collaboration with the Danish Accident Investigation Board and the Danish National Police, National Centre of Forensic Services. The injuries were described using the abbreviated injury scale, the injury severity...

  4. Fuel-Cell-Powered Electric Motor Drive Analyzed for a Large Airplane

    Science.gov (United States)

    Brown, Gerald V.; Choi, Benjamin B.

    2005-01-01

    Because of its high efficiency, fuel cell technology may be used to launch a new generation of more-electric aeropropulsion and power systems for future aircraft. Electric-motor-driven airplanes using fuel-cell powerplants would be beneficial to the environment because of fuel savings, low noise, and zero carbon-dioxide emissions. In spite of the fuel cell s efficiency benefit, to produce the same shaft drive power, a fuel cell- powered electric-drive system must be definitely heavier than a turbine-drive system. However, the fuel-cell system s overall efficiency from fuel-to-shaft power is higher than for a turbine-drive system. This means that the fuel consumption rate could be lower than for a conventional system. For heavier, fuel-laden planes for longer flights, we might achieve substantial fuel savings. In the airplane industry, in fact, an efficiency gain of even a few percentage points can make a major economic difference in operating costs.

  5. Flight Test Results from the Rake Airflow Gage Experiment on the F-15B Airplane

    Science.gov (United States)

    Frederick, Michael A.; Ratnayake, Nalin A.

    2011-01-01

    The Rake Airflow Gage Experiment involves a flow-field survey rake that was flown on the Propulsion Flight Test Fixture at the NASA Dryden Flight Research Center using the Dryden F-15B research test bed airplane. The objective of this flight test was to ascertain the flow-field angularity, local Mach number profile, total pressure distortion, and dynamic pressure at the aerodynamic interface plane of the Channeled Centerbody Inlet Experiment. This new mixed-compression, supersonic inlet is planned for flight test in the near term. Knowledge of the flow-field characteristics at this location underneath the airplane is essential to flight test planning and computational modeling of the new inlet, anairplane, flying at a free-stream Mach number of 1.65 and a pressure altitude of 40,000 ft, would achieve the desired local Mach number for the future inlet flight test. Interface plane distortion levels of 2 percent and a local angle of attack of -2 deg were observed at this condition. Alternative flight conditions for future testing and an exploration of certain anomalous data also are provided.

  6. Flight Test of the F/A-18 Active Aeroelastic Wing Airplane

    Science.gov (United States)

    Voracek, David

    2007-01-01

    A viewgraph presentation of flight tests performed on the F/A active aeroelastic wing airplane is shown. The topics include: 1) F/A-18 AAW Airplane; 2) F/A-18 AAW Control Surfaces; 3) Flight Test Background; 4) Roll Control Effectiveness Regions; 5) AAW Design Test Points; 6) AAW Phase I Test Maneuvers; 7) OBES Pitch Doublets; 8) OBES Roll Doublets; 9) AAW Aileron Flexibility; 10) Phase I - Lessons Learned; 11) Control Law Development and Verification & Validation Testing; 12) AAW Phase II RFCS Envelopes; 13) AAW 1-g Phase II Flight Test; 14) Region I - Subsonic 1-g Rolls; 15) Region I - Subsonic 1-g 360 Roll; 16) Region II - Supersonic 1-g Rolls; 17) Region II - Supersonic 1-g 360 Roll; 18) Region III - Subsonic 1-g Rolls; 19) Roll Axis HOS/LOS Comparison Region II - Supersonic (open-loop); 20) Roll Axis HOS/LOS Comparison Region II - Supersonic (closed-loop); 21) AAW Phase II Elevated-g Flight Test; 22) Region I - Subsonic 4-g RPO; and 23) Phase II - Lessons Learned

  7. Engine Installation Effects of Four Civil Transport Airplanes: Wallops Flight Facility Study

    Science.gov (United States)

    Fleming, Gregg G.; Senzig, David A.; McCurdy, David A.; Roof, Christopher J.; Rapoza, Amanda S.

    2003-01-01

    The National Aeronautics and Space Administration (NASA), Langley Research Center (LaRC), the Environmental Measurement and Modeling Division of the United States Department of Transportation s John A. Volpe National Transportation Systems Center (Volpe), and several other organizations (see Appendix A for a complete list of participating organizations and individuals) conducted a noise measurement study at NASA s Wallops Flight Facility (Wallops) near Chincoteague, Virginia during September 2000. This test was intended to determine engine installation effects on four civil transport airplanes: a Boeing 767-400, a McDonnell-Douglas DC9, a Dassault Falcon 2000, and a Beechcraft King Air. Wallops was chosen for this study because of the relatively low ambient noise of the site and the degree of control over airplane operating procedures enabled by operating over a runway closed to other uses during the test period. Measurements were conducted using a twenty microphone U-shaped array oriented perpendicular to the flight path; microphones were mounted such that ground effects were minimized and low elevation angles were observed.

  8. Flight measurements of buffet characteristics of the F-104 airplane for selected wing-flap deflections

    Science.gov (United States)

    Friend, E. L.; Sefic, W. J.

    1972-01-01

    A flight program was conducted on the F-104 airplane to investigate the effects of moderate deflections of wing leading- and trailing-edge flaps on the buffet characteristics at subsonic and transonic Mach numbers. Selected deflections of the wing leading and trailing-edge flaps, individually and in combination, were used to assess buffet onset, intensity, and frequency; lift curves; and wing-rock characteristics for each configuration. Increased deflection of the trailing-edge flap delayed the buffet onset and buffet intensity rise to a significantly higher airplane normal-force coefficient. Deflection of the leading-edge flap produced some delay in buffet onset and the resulting intensity rise at low subsonic speeds. Increased deflection of the trailing-edge flap provided appreciable lift increments in the angle-of-attack range covered, whereas the leading-edge flap provided lift increments only at high angles-of-attack. The pilots appreciated the increased maneuvering envelope provided by the flaps because of the improved turn capability.

  9. PALS-Based Analysis of an Airplane Multirate Control System in Real-Time Maude

    Directory of Open Access Journals (Sweden)

    Kyungmin Bae

    2012-12-01

    Full Text Available Distributed cyber-physical systems (DCPS are pervasive in areas such as aeronautics and ground transportation systems, including the case of distributed hybrid systems. DCPS design and verification is quite challenging because of asynchronous communication, network delays, and clock skews. Furthermore, their model checking verification typically becomes unfeasible due to the huge state space explosion caused by the system's concurrency. The PALS ("physically asynchronous, logically synchronous" methodology has been proposed to reduce the design and verification of a DCPS to the much simpler task of designing and verifying its underlying synchronous version. The original PALS methodology assumes a single logical period, but Multirate PALS extends it to deal with multirate DCPS in which components may operate with different logical periods. This paper shows how Multirate PALS can be applied to formally verify a nontrivial multirate DCPS. We use Real-Time Maude to formally specify a multirate distributed hybrid system consisting of an airplane maneuvered by a pilot who turns the airplane according to a specified angle through a distributed control system. Our formal analysis revealed that the original design was ineffective in achieving a smooth turning maneuver, and led to a redesign of the system that satisfies the desired correctness properties. This shows that the Multirate PALS methodology is not only effective for formal DCPS verification, but can also be used effectively in the DCPS design process, even before properties are verified.

  10. Security Considerations of Transport Category Airplane%运输类飞机安保事项

    Institute of Scientific and Technical Information of China (English)

    张柱国

    2012-01-01

    On 2002 and 2008, the Federal Aviation Administration (FAA) promulgated Amendment No. 25-106 and 25-127 respectively, which specified overall security considerations for transport category airplanes. This paper introduces the background and history related to security considerations and explains the security considerations. Finally, this paper is concluded with the trend of security and the implementation of security considerations for existing fleet, type design under certification and some kind airplane.%2002年和2008年美国联邦航空局(FAA)分别发布的联邦航空条例FAR25部第25—106和25—127修正案,对运输类飞机提出了全面的安保要求。介绍了运输类飞机安保要求的背景和演变历史,对安保要求进行了解析。最后针对安保发展趋势、在役飞机和在审型号设计及C919飞机对安保要求的贯彻情况进行了总结。

  11. 78 FR 11562 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection: High Speed...

    Science.gov (United States)

    2013-02-19

    ... Embraer S.A. Model EMB-550 airplanes was published in the Federal Register on November 20, 2012 (77 FR...; Flight Envelope Protection: High Speed Limiting AGENCY: Federal Aviation Administration (FAA), DOT... inadvertently or intentionally exceeding a speed approximately equivalent to V FC or attaining V DF ....

  12. 14 CFR Appendix G to Part 141 - Flight Instructor Instrument (For an Airplane, Helicopter, or Powered-Lift Instrument Instructor...

    Science.gov (United States)

    2010-01-01

    ... Airplane, Helicopter, or Powered-Lift Instrument Instructor Rating, as Appropriate) Certification Course G Appendix G to Part 141 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) SCHOOLS AND OTHER CERTIFICATED AGENCIES PILOT SCHOOLS Pt. 141, App. G Appendix G to Part...

  13. 75 FR 53609 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes

    Science.gov (United States)

    2010-09-01

    ... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes AGENCY: Federal Aviation... de Aeronautica S.A. (EMBRAER): Docket No. FAA- 2010-0870; Directorate Identifier...

  14. 75 FR 30284 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes

    Science.gov (United States)

    2010-06-01

    ... March 4, 2010 (75 FR 9811). That NPRM proposed to correct an unsafe condition for the specified products... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant... de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes AGENCY: Federal Aviation Administration...

  15. 75 FR 63422 - Airworthiness Directives; Embraer-Empresa Brasileira de Aeronautica S.A. Model EMB-500 Airplanes

    Science.gov (United States)

    2010-10-15

    ... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will... Brasileira de Aeronautica S.A. Model EMB-500 Airplanes AGENCY: Federal Aviation Administration (FAA.... 39.13 by adding the following new AD: Empresa Brasileira de Aeronautica S.A. (EMBRAER): Docket...

  16. 76 FR 5298 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes

    Science.gov (United States)

    2011-01-31

    ... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes AGENCY: Federal Aviation Administration (FAA.... 39.13 2. The FAA amends Sec. 39.13 by adding the following new AD: Empresa Brasileira de...

  17. 75 FR 68684 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes

    Science.gov (United States)

    2010-11-09

    ..., 2010 (75 FR ] 53609). That NPRM proposed to correct an unsafe condition for the specified products. The... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant... de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes AGENCY: Federal Aviation Administration...

  18. 75 FR 9811 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes

    Science.gov (United States)

    2010-03-04

    ... Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic... de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes AGENCY: Federal Aviation Administration (FAA... information identified in this proposed AD, contact Empresa Brasileira de Aeronautica S.A....

  19. 75 FR 63048 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes

    Science.gov (United States)

    2010-10-14

    ... (75 FR 45558). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI... Order 12866; (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034... de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes AGENCY: Federal Aviation Administration...

  20. 76 FR 444 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes

    Science.gov (United States)

    2011-01-05

    ..., 2010 (75 FR 63422). That NPRM proposed to correct an unsafe condition for the specified products. The... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant... de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes AGENCY: Federal Aviation Administration...

  1. 76 FR 55783 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 190 Airplanes

    Science.gov (United States)

    2011-09-09

    ... (76 FR 13539). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant... de Aeronautica S.A. (EMBRAER) Model ERJ 190 Airplanes AGENCY: Federal Aviation Administration...

  2. 75 FR 45558 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes

    Science.gov (United States)

    2010-08-03

    ... Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic... de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes AGENCY: Federal Aviation Administration (FAA...: Empresa Brasileira de Aeronautica S.A. (EMBRAER): Docket No. FAA- 2010-0754; Directorate Identifier...

  3. 76 FR 13539 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 190 Airplanes

    Science.gov (United States)

    2011-03-14

    ... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... de Aeronautica S.A. (EMBRAER) Model ERJ 190 Airplanes AGENCY: Federal Aviation Administration (FAA... information identified in this proposed AD, contact Empresa Brasileira de Aeronautica S.A....

  4. 75 FR 2060 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes

    Science.gov (United States)

    2010-01-14

    ... Register on July 15, 2009 (74 FR 34276). That NPRM proposed to correct an unsafe condition for the... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes AGENCY: Federal Aviation Administration...

  5. 77 FR 67251 - Special Conditions: Boeing Model 757 Series Airplanes; Seats with Non-Traditional, Large, Non...

    Science.gov (United States)

    2012-11-09

    ...-engine, turbo-fan-powered, single aisle, medium-sized transport category airplanes. The applicable... April 11, 2000 (65 FR 19477-19478), as well as at http://DocketsInfo.dot.gov/ . Docket: Background... the Notice of Proposed Rule Making, Notice No. 85-10 (50 FR 15038, April 16, 1985) and the Final...

  6. 78 FR 63902 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection: Normal...

    Science.gov (United States)

    2013-10-25

    ... associated with an electronic flight control system that prevents the pilot from inadvertently or... of the electronic flight control system for the Model EMB-550 airplane incorporates normal load... features: The design of the electronic flight control system incorporates normal load factor limiting on...

  7. 78 FR 11555 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Design Roll Maneuver for Electronic...

    Science.gov (United States)

    2013-02-19

    ... by the pilot or copilot sidestick. The flight control system for the Model EMB-550 airplane does not... electronic flight control system that provides control of the aircraft through pilot inputs to the flight... design roll maneuver for electronic flight controls, specifically an electronic flight control...

  8. 76 FR 41045 - Special Conditions; Gulfstream Aerospace LP (GALP) Model G250 Airplane, Design Roll-Maneuver...

    Science.gov (United States)

    2011-07-13

    ... flight control system that provides control through the pilot inputs to the flight computer. This novel... airplane is equipped with an electronic spoiler-control system and a mechanical aileron-control system that provide roll control of the aircraft through pilot inputs. An electronic control unit operates the......

  9. 77 FR 70941 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Interaction of Systems and Structures

    Science.gov (United States)

    2012-11-28

    ... the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http://DocketsInfo...., Model EMB-550 Airplane; Interaction of Systems and Structures AGENCY: Federal Aviation Administration... feature(s) associated with the interaction of systems and structures. The applicable...

  10. 78 FR 68985 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Science.gov (United States)

    2013-11-18

    ... and data networks. This onboard network system will be composed of a network file server, a network... installation of an onboard network system, associated line replaceable units (LRUs) and additional software..., -300ER series airplanes will incorporate the following novel or unusual design features: An...

  11. 78 FR 65235 - Special Conditions: Learjet Inc., Model LJ-200-1A10 Airplane; Crashworthiness, Emergency Landing...

    Science.gov (United States)

    2013-10-31

    ... the ``Model LJ-200''). The Model LJ-200 is a business class airplane powered by two high-bypass... From the Federal Register Online via the Government Publishing Office ] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 Special Conditions: Learjet Inc., Model...

  12. 14 CFR 125.333 - Stowage of food, beverage, and passenger service equipment during airplane movement on the...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Stowage of food, beverage, and passenger service equipment during airplane movement on the surface, takeoff, and landing. 125.333 Section 125.333 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIR CARRIERS AND OPERATORS FOR COMPENSATION OR...

  13. 14 CFR 121.577 - Stowage of food, beverage, and passenger service equipment during airplane movement on the...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Stowage of food, beverage, and passenger service equipment during airplane movement on the surface, takeoff, and landing. 121.577 Section 121.577 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIR CARRIERS AND OPERATORS FOR COMPENSATION OR...

  14. 14 CFR 121.645 - Fuel supply: Turbine-engine powered airplanes, other than turbo propeller: Flag and supplemental...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Fuel supply: Turbine-engine powered... SUPPLEMENTAL OPERATIONS Dispatching and Flight Release Rules § 121.645 Fuel supply: Turbine-engine powered... Columbia with a turbine engine powered airplane the fuel requirements of § 121.643 apply....

  15. 14 CFR Appendix B to Part 36 - Noise Levels for Transport Category and Jet Airplanes Under § 36.103

    Science.gov (United States)

    2010-01-01

    ... for the calculation of atmospheric absorption coefficients. (i) Sea level atmospheric pressure of 2116... height in the determination of the landing distance for manual landings. For Concorde airplanes, a steady... variation of EPNL with weight for both takeoff and approach test conditions. The necessary EPNL...

  16. 76 FR 41142 - Special Conditions; Cessna Aircraft Company Model M680 Airplane; Lithium-ion Battery Installations

    Science.gov (United States)

    2011-07-13

    ... Aircraft Company Model M680 Airplane; Lithium-ion Battery Installations AGENCY: Federal Aviation... design feature associated with Lithium-ion batteries. The applicable airworthiness regulations do not...) T00012WI for installation of Lithium-ion batteries in the Model 680. The Model 680 is a twin-engine,...

  17. 78 FR 62495 - Special Conditions: Learjet Model 35, 35A, 36, and 36A Airplanes; Rechargeable Lithium-Ion...

    Science.gov (United States)

    2013-10-22

    ..., 2000 (65 FR 19477-19478), as well as at http://DocketsInfo.dot.gov/ . Docket: Background documents or... Airplanes; Rechargeable Lithium-Ion Batteries and Battery Systems AGENCY: Federal Aviation Administration... associated with rechargeable lithium-ion batteries and battery systems. These batteries have certain...

  18. 76 FR 57627 - Special Conditions: Cessna Aircraft Company Model M680 Airplane; Rechargeable Lithium-Ion Battery...

    Science.gov (United States)

    2011-09-16

    ... published in the Federal Register on July 1, 2011 (76 FR 41142). No comments were received, and the special... Airplane; Rechargeable Lithium-Ion Battery Installations AGENCY: Federal Aviation Administration (FAA), DOT... lithium-ion batteries. The applicable airworthiness regulations do not contain adequate or...

  19. 78 FR 52107 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Rechargeable Lithium...

    Science.gov (United States)

    2013-08-22

    ... installation of batteries in large transport category airplanes were derived from Civil Air Regulations (CAR... 1965. The new battery requirements, Sec. 25.1353(c)(1) through (c)(4), basically reworded the CAR... requirements, are established to ensure the availability of electrical power from the batteries when needed....

  20. 75 FR 1536 - Airworthiness Directives; The Boeing Company Model 737-600, -700, and -800 Series Airplanes

    Science.gov (United States)

    2010-01-12

    ... valves, fueling manifold, fuel temperature sensor, and motor operated fuel shutoff valve adapter plate..., -700, and -800 series airplanes. This AD requires an inspection of the free flange, vertical web, and... assurance inspection at the final assembly plant. We are issuing this AD to prevent cracks from...

  1. 77 FR 67308 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Hydrophobic Coatings in Lieu of...

    Science.gov (United States)

    2012-11-09

    ... April 11, 2000 (65 FR 19477-19478), as well as at http://DocketsInfo.dot.gov/ . Docket: Background...., Model EMB-550 Airplane; Hydrophobic Coatings in Lieu of Windshield Wipers AGENCY: Federal Aviation... feature(s) associated with hydrophobic coatings. The applicable airworthiness regulations do not...

  2. 76 FR 28373 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 Airplanes

    Science.gov (United States)

    2011-05-17

    ... and Maintenance and Inspection Requirements'' (66 FR 23086, May 7, 2001). In addition to new... Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR.... Model F.28 Mark 1000, 2000, 3000, and 4000 Airplanes AGENCY: Federal Aviation Administration (FAA),...

  3. 76 FR 18029 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 Airplanes

    Science.gov (United States)

    2011-04-01

    ... was published in the Federal Register on January 5, 2011 (76 FR 482). That NPRM proposed to correct an... Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR.... Model F.28 Mark 1000, 2000, 3000, and 4000 Airplanes AGENCY: Federal Aviation Administration...

  4. 76 FR 50111 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 Airplanes

    Science.gov (United States)

    2011-08-12

    ... published in the Federal Register on May 17, 2011 (76 FR 28376). That NPRM proposed to correct an unsafe... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or..., 2000, 3000, and 4000 Airplanes AGENCY: Federal Aviation Administration (FAA), Department...

  5. 76 FR 50115 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 Airplanes

    Science.gov (United States)

    2011-08-12

    ... products. That NPRM was published in the Federal Register on May 17, 2011 (76 FR 28373). That NPRM proposed... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or.... Model F.28 Mark 1000, 2000, 3000, and 4000 Airplanes AGENCY: Federal Aviation Administration...

  6. 76 FR 28376 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 Airplanes

    Science.gov (United States)

    2011-05-17

    ... and Maintenance and Inspection Requirements'' (66 FR 23086, May 7, 2001). In addition to new... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will.... Model F.28 Mark 1000, 2000, 3000, and 4000 Airplanes AGENCY: Federal Aviation Administration (FAA),...

  7. 14 CFR 135.373 - Part 25 transport category airplanes with four or more engines: Reciprocating engine powered: En...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Part 25 transport category airplanes with four or more engines: Reciprocating engine powered: En route limitations: Two engines inoperative. 135... engines: Reciprocating engine powered: En route limitations: Two engines inoperative. (a) No person...

  8. 14 CFR 121.183 - Part 25 airplanes with four or more engines: Reciprocating engine powered: En route limitations...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Part 25 airplanes with four or more engines: Reciprocating engine powered: En route limitations: Two engines inoperative. 121.183 Section 121.183 Aeronautics... more engines: Reciprocating engine powered: En route limitations: Two engines inoperative. (a)...

  9. 75 FR 38011 - Airworthiness Directives; Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) Airplanes

    Science.gov (United States)

    2010-07-01

    ... products. That NPRM was published in the Federal Register on January 4, 2010 (75 FR 91). That NPRM proposed... Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR.... Model CL-600-2B16 (CL- 604 Variant) Airplanes AGENCY: Federal Aviation Administration (FAA),...

  10. 77 FR 69573 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Electronic Flight Control System...

    Science.gov (United States)

    2012-11-20

    ...; Electronic Flight Control System: Lateral-Directional and Longitudinal Stability and Low Energy Awareness... airplane will have a novel or unusual design feature(s) associated with an electronic flight control system... features: (1) Lateral-Directional Static Stability: The electronic flight control system on the Model...

  11. 78 FR 11553 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Electronic Flight Control System...

    Science.gov (United States)

    2013-02-19

    ... Airplane; Electronic Flight Control System: Control Surface Awareness and Mode Annunciation AGENCY: Federal... feature(s) associated with the control surface awareness and mode annunciation of the electronic flight... a fly-by-wire electronic flight control system and no direct coupling from the flightdeck...

  12. 75 FR 67639 - Airworthiness Directives; Piaggio Aero Industries S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-11-03

    ... Airplane Flight Manual, stating that the towing bar P/N 01-1227-0000 or similar ferromagnetic masses are... City, Missouri 64106. For information on the availability of this material at the FAA, call 816-329... similar ferromagnetic masses are prohibited to be carried in the baggage compartment. Temporary Change...

  13. 76 FR 67343 - Airworthiness Directives; The Boeing Company Model 737-300, -400, and -500 Series Airplanes

    Science.gov (United States)

    2011-11-01

    ... prompted by reports of cracking in the frame, or in the frame and frame reinforcement, common to the 1.04..., contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65... Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays....

  14. 78 FR 76252 - Special Conditions: Airbus, Model A350-900 Series Airplane; Isolation or Protection of the...

    Science.gov (United States)

    2013-12-17

    ... From the Federal Register Online via the Government Publishing Office DEPARTMENT OF TRANSPORTATION... the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http://DocketsInfo... corruption of data and systems critical to the safety and maintenance of the airplane. The...

  15. 78 FR 26280 - Special Conditions: Embraer, S.A., Model EMB-550 Airplane; Side-Facing Seats; Installation of...

    Science.gov (United States)

    2013-05-06

    ... the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http://DocketsInfo... primary structure is metal with composite empennage and control surfaces. The Model EMB-550 airplane is..., during a side-facing-seat dynamic test, the flailing of the occupant causes his or her head to...

  16. 76 FR 64229 - Function and Reliability Flight Testing for Turbine-Powered Airplanes Weighing 6,000 Pounds or Less

    Science.gov (United States)

    2011-10-18

    ... Certificated Weight.'' (See 69 FR 5239, February 3, 2004.) In that notice, we announced our intention to.... (See 75 FR 50853, August 18, 2010.) This final rule will eliminate the need for issuing special...-Powered Airplanes Weighing 6,000 Pounds or Less.'' (See 75 FR 18134, April 9, 2010.) In that NPRM,...

  17. 75 FR 52292 - Airworthiness Directives; Diamond Aircraft Industries GmbH Models DA 40 and DA 40F Airplanes

    Science.gov (United States)

    2010-08-25

    ... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3... Industries GmbH Models DA 40 and DA 40F Airplanes AGENCY: Federal Aviation Administration (FAA), Department... new airworthiness directive (AD) for all Diamond Aircraft Industries GmbH Models DA 40 and DA...

  18. 75 FR 75868 - Airworthiness Directives; Diamond Aircraft Industries GmbH Models DA 40 and DA 40F Airplanes

    Science.gov (United States)

    2010-12-07

    ... Register on August 25, 2010 (75 FR 52292). That NPRM proposed to require a retrofit of the rear passenger... 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034... Aircraft Industries GmbH Models DA 40 and DA 40F Airplanes AGENCY: Federal Aviation Administration,...

  19. Capabilities and applications of a computer program system for dynamic loads analyses of flexible airplanes with active controls /DYLOFLEX/

    Science.gov (United States)

    Perry, B., III; Goetz, R. C.; Kroll, R. I.; Miller, R. D.

    1979-01-01

    This paper describes and illustrates the capabilities of the DYLOFLEX Computer Program System. DYLOFLEX is an integrated system of computer programs for calculating dynamic loads of flexible airplanes with active control systems. A brief discussion of the engineering formulation for each of the nine DYLOFLEX programs is described. The capabilities of the system are illustrated by the analyses of two example configurations.

  20. Free-to-Roll Testing of Airplane Models in Wind Tunnels

    Science.gov (United States)

    Capone, Francis J.; Owens, D. Bruce; Hall, Robert M.

    2007-01-01

    A free-to-roll (FTR) test technique and test rig make it possible to evaluate both the transonic performance and the wingdrop/ rock behavior of a high-strength airplane model in a single wind-tunnel entry. The free-to-roll test technique is a single degree-of-motion method in which the model is free to roll about the longitudinal axis. The rolling motion is observed, recorded, and analyzed to gain insight into wing-drop/rock behavior. Wing-drop/rock is one of several phenomena symptomatic of abrupt wing stall. FTR testing was developed as part of the NASA/Navy Abrupt Wing Stall Program, which was established for the purposes of understanding and preventing significant unexpected and uncommanded (thus, highly undesirable) lateral-directional motions associated with wing-drop/rock, which have been observed mostly in fighter airplanes under high-subsonic and transonic maneuvering conditions. Before FTR testing became available, wingrock/ drop behavior of high-performance airplanes undergoing development was not recognized until flight testing. FTR testing is a reliable means of detecting, and evaluating design modifications for reducing or preventing, very complex abrupt wing stall phenomena in a ground facility prior to flight testing. The FTR test rig was designed to replace an older sting attachment butt, such that a model with its force balance and support sting could freely rotate about the longitudinal axis. The rig (see figure) includes a rotary head supported in a stationary head with a forward spherical roller bearing and an aft needle bearing. Rotation is amplified by a set of gears and measured by a shaft-angle resolver; the roll angle can be resolved to within 0.067 degrees at a rotational speed up to 1,000 degrees/s. An assembly of electrically actuated brakes between the rotary and stationary heads can be used to hold the model against a rolling torque at a commanded roll angle. When static testing is required, a locking bar is used to fix the rotating

  1. Free-Spinning Wind-Tunnel Tests of a Low-Wing Monoplane with Systematic Changes in Wings and Tails V : Effect of Airplane Relative Density

    Science.gov (United States)

    Seidman, Oscar; Neihouse, A I

    1940-01-01

    The reported tests are a continuation of an NACA investigation being made in the free-spinning wind tunnel to determine the effects of independent variations in load distribution, wing and tail arrangement, and control disposition on the spin characteristics of airplanes. The standard series of tests was repeated to determine the effect of airplane relative density. Tests were made at values of the relative-density parameter of 6.8, 8.4 (basic), and 12.0; and the results were analyzed. The tested variations in the relative-density parameter may be considered either as variations in the wing loading of an airplane spun at a given altitude, with the radii of gyration kept constant, or as a variation of the altitude at which the spin takes place for a given airplane. The lower values of the relative-density parameter correspond to the lower wing loadings or to the lower altitudes of the spin.

  2. On the analytic and numeric optimisation of airplane trajectories under real atmospheric conditions

    Science.gov (United States)

    Gonzalo, J.; Domínguez, D.; López, D.

    2014-12-01

    From the beginning of aviation era, economic constraints have forced operators to continuously improve the planning of the flights. The revenue is proportional to the cost per flight and the airspace occupancy. Many methods, the first started in the middle of last century, have explore analytical, numerical and artificial intelligence resources to reach the optimal flight planning. In parallel, advances in meteorology and communications allow an almost real-time knowledge of the atmospheric conditions and a reliable, error-bounded forecast for the near future. Thus, apart from weather risks to be avoided, airplanes can dynamically adapt their trajectories to minimise their costs. International regulators are aware about these capabilities, so it is reasonable to envisage some changes to allow this dynamic planning negotiation to soon become operational. Moreover, current unmanned airplanes, very popular and often small, suffer the impact of winds and other weather conditions in form of dramatic changes in their performance. The present paper reviews analytic and numeric solutions for typical trajectory planning problems. Analytic methods are those trying to solve the problem using the Pontryagin principle, where influence parameters are added to state variables to form a split condition differential equation problem. The system can be solved numerically -indirect optimisation- or using parameterised functions -direct optimisation-. On the other hand, numerical methods are based on Bellman's dynamic programming (or Dijkstra algorithms), where the fact that two optimal trajectories can be concatenated to form a new optimal one if the joint point is demonstrated to belong to the final optimal solution. There is no a-priori conditions for the best method. Traditionally, analytic has been more employed for continuous problems whereas numeric for discrete ones. In the current problem, airplane behaviour is defined by continuous equations, while wind fields are given in a

  3. Experiments to Determine Neighborhood Reactions to Light Airplanes With and Without External Noise Reduction

    Science.gov (United States)

    Elwell, Fred S

    1953-01-01

    The work reported was part of a program of experimentation with external noise reduction on light airplanes. This particular study was in effect a byproduct survey conceived to utilize already available equipment and personnel to further the findings of the original research and to determine reactions in populated neighborhoods to light aircraft with and without noise-reduction equipment. The findings indicate that at the 10 sites within and about metropolitan Boston the degree of noise reduction previously found to be aerodynamically and structurally feasible did eliminate substantially all neighborhood objections to noise per se. The evidence clearly suggests that, when the noise nuisance is minimized to the extent found feasible, the number and severity of other objections also diminish -- evidently because the flight operations are noticed less when heard less.

  4. Subjective response to combined noise and vibration during flight of a large twin-jet airplane

    Science.gov (United States)

    Clevenson, S. A.

    1976-01-01

    A NASA twin-jet airplane was used to obtain controlled noise and vibration environments during flight while obtaining subjective responses from 13 passenger-subjects (6 females and 7 males). Subjective ratings of overall comfort, comfort when considering only vibration, and comfort when considering only noise were obtained during times of different vibration and noise environments. Passenger-subjects were able to distinguish and rate noise better than vibration. In addition, there was a statistically significant difference in ratings of ride comfort due to both sex type and flight experience. Males rated flying discomfort much more severely than females when rating the overall ride and the ride when considering only the noise environment. Experienced passengers also rated the overall ride to be more uncomfortable than inexperienced passengers.

  5. The 727 airplane target thrust reverser static performance model test for refanned JT8D engines

    Science.gov (United States)

    Chow, C. T. P.; Atkey, E. N.

    1974-01-01

    The results of a scale model static performance test of target thrust reverser configurations for the Pratt and Whitney Aircraft JT8D-100 series engine are presented. The objective of the test was to select a series of suitable candidate reverser configurations for the subsequent airplane model wind tunnel ingestion and flight controls tests. Test results indicate that adequate reverse thrust performance with compatible engine airflow match is achievable for the selected configurations. Tapering of the lips results in loss of performance and only minimal flow directivity. Door pressure surveys were conducted on a selected number of lip and fence configurations to obtain data to support the design of the thrust reverser system.

  6. Fracture and strain rate behavior of airplane fuselage materials under blast loading

    Directory of Open Access Journals (Sweden)

    van der Meulen O.R.

    2010-06-01

    Full Text Available The dynamic behavior of three commonly used airplane fuselage materials is investigated, namely of Al2024-T3, Glare-3 and CFRP. Dynamic tensile tests using a servo-hydraulic and a light weight shock testing machine (LSM have been performed. The results showed no strain rate effect on Al2024-T3 and an increase in the failure strain and failure strength of Glare-3, but no stiffening. The LSM results on CFRP were inconclusive. Two types of fracture tests were carried out to determine the dynamic crack propagation behavior of these materials, using prestressed plates and pressurized barrels, both with the help of explosives. The prestressed plates proved to be not suitable, whereas the barrel tests were quite reliable, allowing to measure the crack speeds. The tougher, more ductile materials, Al2024-T3 and Glare-3, showed lower crack speeds than CFRP, which failed in a brittle manner.

  7. Mathematical adventures in performance analysis from storage systems, through airplane boarding, to express line queues

    CERN Document Server

    Bachmat, Eitan

    2014-01-01

    This monograph describes problems in the field of performance analysis, primarily the study of storage systems and the diverse mathematical techniques that are required for solving such problems. Topics covered include best practices for scheduling I/O requests to a disk drive, how this problem is related to airplane boarding, and how both problems can be modeled using space-time geometry. The author also explains how Riemann's proof of the analytic continuation and functional equation of the Riemann zeta function can be used to analyze express-line queues in a minimarket. Overall, the book reveals the surprising applicability of abstract mathematical ideas that are not usually associated with applied topics. Advanced undergraduate students or graduate students with an interest in the applications of mathematics will find this book a useful resource. It will also be of interest to professional mathematicians who want exposure to the surprising ways that theoretical mathematics may be applied to engineering pr...

  8. Wing Torsional Stiffness Tests of the Active Aeroelastic Wing F/A-18 Airplane

    Science.gov (United States)

    Lokos, William A.; Olney, Candida D.; Crawford, Natalie D.; Stauf, Rick; Reichenbach, Eric Y.

    2002-01-01

    The left wing of the Active Aeroelastic Wing (AAW) F/A-18 airplane has been ground-load-tested to quantify its torsional stiffness. The test has been performed at the NASA Dryden Flight Research Center in November 1996, and again in April 2001 after a wing skin modification was performed. The primary objectives of these tests were to characterize the wing behavior before the first flight, and provide a before-and-after measurement of the torsional stiffness. Two streamwise load couples have been applied. The wing skin modification is shown to have more torsional flexibility than the original configuration has. Additionally, structural hysteresis is shown to be reduced by the skin modification. Data comparisons show good repeatability between the tests.

  9. Effects of Medium Characteristics on Laser RCS of Airplane with E-Wave Polarization

    Directory of Open Access Journals (Sweden)

    Hosam El-Ocla

    2015-01-01

    Full Text Available Plane wave incidence should be postulated to have an authentic target detection. Practically, the plane wave is incapable usually of keeping its power in the far field especially when propagating through an inhomogeneous medium. Consequently, we assume an incident beam wave with a finite width around the target. In this work, we calculate numerically a laser radar cross section (LRCS of conducting targets having smooth cross sections with inflection points such as airplane in random media. Effects of fluctuations intensity of random media on the LRCS performance are studied in this paper. E-wave polarization (E-wave incidence is considered while the mean target size is approximately twice the wavelength.

  10. Nanosecond-level time synchronization of AERA using a beacon reference transmitter and commercial airplanes

    CERN Document Server

    Huege, Tim

    2016-01-01

    Radio detection of cosmic-ray air showers requires time synchronization of detectors on a nanosecond level, especially for advanced reconstruction algorithms based on the wavefront curvature and for interferometric analysis approaches. At the Auger Engineering Radio Array, the distributed, autonomous detector stations are time-synchronized via the Global Positioning System which, however, does not provide sufficient timing accuracy. We thus employ a dedicated beacon reference transmitter to correct for event-by-event clock drifts in our offline data analysis. In an independent cross-check of this "beacon correction" using radio pulses emitted by commercial airplanes, we have shown that the combined timing accuracy of the two methods is better than 2 nanoseconds.

  11. UWB EMI To Aircraft Radios: Field Evaluation on Operational Commercial Transport Airplanes. Volume 1

    Science.gov (United States)

    Oria, A. J. (Editor); Ely, Jay J.; Martin, Warren L.; Shaver, Timothy W.; Fuller, Gerald L.; Zimmerman, John; Fuschino, Robert L.; Larsen, William E.

    2005-01-01

    Ultrawideband (UWB) transmitters may soon be integrated into a wide variety of portable electronic devices (PEDs) that passengers routinely carry on board commercial airplanes. Airlines and the FAA will have difficulty controlling passenger use of UWB transmitters during flights with current airline policies and existing wireless product standards. The aeronautical community is concerned as to whether evolving FCC UWB rules are adequate to protect legacy and emerging aeronautical radio systems from electromagnetic interference (EMI) from emerging UWB products. To address these concerns, the NASA Office of Space Communications and Chief Spectrum Managers assembled a multidisciplinary team from NASA LaRC, NASA JPL, NASA ARC, FAA, United Airlines, Sky West Airlines, and Eagles Wings Inc. to carry out a comprehensive series of tests aimed at determining the nature and extent of any EMI to aeronautical communication and navigation systems from UWB devices meeting FCCapproved and proposed levels for unlicensed handheld transmitters.

  12. ANALYSIS FOR AERODYNAMICS OF THE SIMPLIFIED MODEL OF A COMMERCIAL AIRPLANE CRUISING AT TRANSONIC SPEED

    Directory of Open Access Journals (Sweden)

    KIM YANGKYUN

    2010-12-01

    Full Text Available This paper describes the computational analysis and visualization of flow around the model of a commercial airplane, Boeing 747-400. The geometry was realized through reverse engineering technique based on the photo scanning measurement. The steady three-dimensional viscous compressible governing equations were solved in the unstructured grid system. The basic conditions for computation were chosen as the same to those of Boeing 747-400’s cruising state. The high Reynolds turbulence models are tried. The angle of attack is varied to investigate the effect of the flight conditions to the aerodynamic performance. And flow and aerodynamic characteristics due to the existence of winglet were compared.

  13. Pitch Controllability Based on Airplane Model without Short-Period Approximation—Flight Simulator Experiment—

    Science.gov (United States)

    Sato, Osamu; Kobayashi, Osamu

    Pitch controllability of an airplane is very important for longitudinal flying qualities, therefore, much research has been conducted. However, it has not been clarified why pitch handling qualities degrades in the low speed, e.g. take-off and landing flight phases. On this topic, this paper investigates the effect of several parameters of the short-period mode and phugoid mode using a flight simulator. The results show the following conclusions: The difference between the initial phase angles in two modal components in the pitch attitude response to elevator step input plays the most important role in the pitch handling qualities among modal parameters; and the difference of the two modal natural frequencies has small effect on the pitch controllability even when flight speed decreases.

  14. Annoyance from Road Traffic, Trains, Airplanes and from Total Environmental Noise Levels

    Directory of Open Access Journals (Sweden)

    Martina S. Ragettli

    2015-12-01

    Full Text Available There is a lack of studies assessing the exposure-response relationship between transportation noise and annoyance in North America. Our aims were to investigate the prevalence of noise annoyance induced by road traffic, trains and airplanes in relation to distance to transportation noise sources, and to total environmental noise levels in Montreal, Canada; annoyance was assessed as noise-induced disturbance. A telephone-based survey among 4336 persons aged >18 years was conducted. Exposure to total environmental noise (A-weighted outdoor noise levels—LAeq24h and day-evening-night equivalent noise levels—Lden for each study participant was determined using a statistical noise model (land use regression—LUR that is based on actual outdoor noise measurements. The proportion of the population annoyed by road traffic, airplane and train noise was 20.1%, 13.0% and 6.1%, respectively. As the distance to major roads, railways and the Montreal International Airport increased, the percentage of people disturbed and highly disturbed due to the corresponding traffic noise significantly decreased. When applying the statistical noise model we found a relationship between noise levels and disturbance from road traffic and total environmental noise, with Prevalence Proportion Ratios (PPR for highly disturbed people of 1.10 (95% CI: 1.07–1.13 and 1.04 (1.02–1.06 per 1 dB(A Lden, respectively. Our study provides the first comprehensive information on the relationship between transportation noise levels and disturbance in a Canadian city. LUR models are still in development and further studies on transportation noise induced annoyance are consequently needed, especially for sources other than road traffic.

  15. Sleep Disturbance from Road Traffic, Railways, Airplanes and from Total Environmental Noise Levels in Montreal

    Directory of Open Access Journals (Sweden)

    Stéphane Perron

    2016-08-01

    Full Text Available The objective of our study was to measure the impact of transportation-related noise and total environmental noise on sleep disturbance for the residents of Montreal, Canada. A telephone-based survey on noise-related sleep disturbance among 4336 persons aged 18 years and over was conducted. LNight for each study participant was estimated using a land use regression (LUR model. Distance of the respondent’s residence to the nearest transportation noise source was also used as an indicator of noise exposure. The proportion of the population whose sleep was disturbed by outdoor environmental noise in the past 4 weeks was 12.4%. The proportion of those affected by road traffic, airplane and railway noise was 4.2%, 1.5% and 1.1%, respectively. We observed an increased prevalence in sleep disturbance for those exposed to both rail and road noise when compared for those exposed to road only. We did not observe an increased prevalence in sleep disturbance for those that were both exposed to road and planes when compared to those exposed to road or planes only. We developed regression models to assess the marginal proportion of sleep disturbance as a function of estimated LNight and distance to transportation noise sources. In our models, sleep disturbance increased with proximity to transportation noise sources (railway, airplane and road traffic and with increasing LNight values. Our study provides a quantitative estimate of the association between total environmental noise levels estimated using an LUR model and sleep disturbance from transportation noise.

  16. Sleep Disturbance from Road Traffic, Railways, Airplanes and from Total Environmental Noise Levels in Montreal.

    Science.gov (United States)

    Perron, Stéphane; Plante, Céline; Ragettli, Martina S; Kaiser, David J; Goudreau, Sophie; Smargiassi, Audrey

    2016-01-01

    The objective of our study was to measure the impact of transportation-related noise and total environmental noise on sleep disturbance for the residents of Montreal, Canada. A telephone-based survey on noise-related sleep disturbance among 4336 persons aged 18 years and over was conducted. LNight for each study participant was estimated using a land use regression (LUR) model. Distance of the respondent's residence to the nearest transportation noise source was also used as an indicator of noise exposure. The proportion of the population whose sleep was disturbed by outdoor environmental noise in the past 4 weeks was 12.4%. The proportion of those affected by road traffic, airplane and railway noise was 4.2%, 1.5% and 1.1%, respectively. We observed an increased prevalence in sleep disturbance for those exposed to both rail and road noise when compared for those exposed to road only. We did not observe an increased prevalence in sleep disturbance for those that were both exposed to road and planes when compared to those exposed to road or planes only. We developed regression models to assess the marginal proportion of sleep disturbance as a function of estimated LNight and distance to transportation noise sources. In our models, sleep disturbance increased with proximity to transportation noise sources (railway, airplane and road traffic) and with increasing LNight values. Our study provides a quantitative estimate of the association between total environmental noise levels estimated using an LUR model and sleep disturbance from transportation noise. PMID:27529260

  17. Drop test and crash simulation of a civil airplane fuselage section

    Directory of Open Access Journals (Sweden)

    Liu Xiaochuan

    2015-04-01

    Full Text Available Crashworthiness of a civil airplane fuselage section was studied in this paper. Firstly, the failure criterion of a rivet was studied by test, showing that the ultimate tension and shear failure loads were obviously affected by the loading speed. The relations between the loading speed and the average ultimate shear, tension loads were expressed by two logarithmic functions. Then, a vertical drop test of a civil airplane fuselage section was conducted with an actual impact velocity of 6.85 m/s, meanwhile the deformation of cabin frame and the accelerations at typical locations were measured. The finite element model of a main fuselage structure was developed and validated by modal test, and the error between the calculated frequencies and the test ones of the first four modes were less than 5%. Numerical simulation of the drop test was performed by using the LS-DYNA code and the simulation results show a good agreement with that of drop test. Deforming mode of the analysis was the same as the drop test; the maximum average rigid acceleration in test was 8.81g while the calculated one was 9.17g, with an error of 4.1%; average maximum test deformation at four points on the front cabin floor was 420 mm, while the calculated one was 406 mm, with an error of 3.2%; the peak value of the calculated acceleration at a typical location was 14.72g, which is lower than the test result by 5.46%; the calculated rebound velocity result was greater than the test result 17.8% and energy absorption duration was longer than the test result by 5.73%.

  18. AIRPLANE INFORMATION

    Institute of Scientific and Technical Information of China (English)

    2009-01-01

    Air France Over the past few years. Air France has been committed to bringing its brand image up-to-date. Today, Air France unveils an important new stage, its revamped logo. To avoid additional costs, the change will be made gradually. Aircraft will be painted with the new

  19. Applications of power beaming from space-based nuclear power stations. [Laser beaming to airplanes; microwave beaming to ground

    Energy Technology Data Exchange (ETDEWEB)

    Powell, J.R.; Botts, T.E.; Hertzberg, A.

    1981-01-01

    Power beaming from space-based reactor systems is examined using an advanced compact, lightweight Rotating Bed Reactor (RBR). Closed Brayton power conversion efficiencies in the range of 30 to 40% can be achieved with turbines, with reactor exit temperatures on the order of 2000/sup 0/K and a liquid drop radiator to reject heat at temperatures of approx. 500/sup 0/K. Higher RBR coolant temperatures (up to approx. 3000/sup 0/K) are possible, but gains in power conversion efficiency are minimal, due to lower expander efficiency (e.g., a MHD generator). Two power beaming applications are examined - laser beaming to airplanes and microwave beaming to fixed ground receivers. Use of the RBR greatly reduces system weight and cost, as compared to solar power sources. Payback times are a few years at present prices for power and airplane fuel.

  20. A class 2 weight assessment for the implementation of commonality and preliminary structural designs for the family of commuter airplanes

    Science.gov (United States)

    Creighton, Tom; Dragush, George; Hendrich, Louis; Hensley, Doug; Morgan, Louise; Oxendine, Charles; Remen, John; Robinson, Terry; Russell, Mark; Swift, Jerry

    1987-01-01

    The feasibility of commonality objectives are determined. Commonality is discussed in terms of weight penalties that increase the take-off weight of several members of the family of airplanes. Preliminary designs of fuselage structural members and a discussion of weight penalties due to implementation of common fuselage structure throughout the family is examined. Wing torque box designs are discussed along with structural weight penalties incurred. A landing gear design study is contained along with the weight penalties that a common gear system will impose. Implementation of common power plants throughout the family and the weight penalties that occur are discussed. The weight penalties imposed by commonality on all the airplanes in the family are summarized. Class 2 breakdowns are also presented. The feasibility of commonality based on a percentage of take-off weight increase over the Class 2 baseline weights is then assessed.

  1. Calculated performance of a mercury-compressor-jet powered airplane using a nuclear reactor as an energy source

    Science.gov (United States)

    Doyle, R B

    1951-01-01

    An analysis was made at a flight Mach number of 1.5, an altitude of 45,000 feet, a turbine-inlet temperature of 1460 degrees R, of a mercury compressor-jet powered airplane using a nuclear reactor as an energy source. The calculations covered a range of turbine-exhaust and turbine-inlet pressures and condenser-inlet Mach numbers. For a turbine--inlet pressure of 40 pounds per square inch absolute, a turbine-exhaust pressure of 14 pounds per square inch absolute, and a condenser-inlet Mach number of 0.23 the calculated airplane gross weight required to carry a 20,000 pound payload was 322000 pounds and the reactor heat release per unit volume was 8.9 kilowatts per cubic inch. These do not represent optimum operating conditions.

  2. Phase 2 program on ground test of refanned JT8D turbofan engines and nacelles for the 727 airplane. Volume 1: Summary

    Science.gov (United States)

    1975-01-01

    The propulsion performance, acoustic, structural, and systems changes to a 727-200 airplane retrofitted with a refan modification of the JT8D turbofan engine are evaluated. Model tests, design of certifiable airplane retrofit kit hardware, manufacture of test hardware, ground test of a current production JT8D engine, followed by test of the same engine modified to the refan configuration, detailed analyses of the retrofit impact on airplane airworthiness, performance, and noise, and a preliminary analysis of retrofit costs are included. Results indicate that the refan retrofit of the 727-200 would be certifiable and would result in a 6-to 8 EPNdb reduction in effective perceived noise level (EPNL) at the FAR 36 measuring points and an annoyance-weighted footprint area reduction of 68% to 83%. The installed refan engine is estimated to provide 14% greater takeoff thrust at zero velocity and 10% greater thrust at 100 kn (51.4 m/s). There would be an approximate 0.6% increase in cruise specific fuel consumption (SFC). The refan engine performance in conjunction with the increase in stalled weight results in a range reduction of approximately 15% over the unmodified airplane at the same brake release gross weight (BRGW), with a block fuel increase of 1.5% to 3%. With the particular model 727 that was studied, however, it is possible to operate the airplane (with minor structural modifications) at a higher BRGW and increase the range up to approximately 15% relative to the nonrefanned airplane (with equal or slightly increased noise levels). The JT8D refan engine also improves the limited-field range of the airplane.

  3. The Unmanned Research Airplane Facility at the Cyprus Institute: Advanced Atmospheric Observations

    Science.gov (United States)

    Lange, Manfred A.; Argyrides, Marios; Ioannou, Stelios; Keleshis, Christos

    2014-05-01

    Unmanned Aerial Systems (UASs) have been established as versatile tools for different applications, providing data and observations for atmospheric and Earth-Systems research. They provide an urgently needed link between in-situ ground based measurements and satellite remote sensing observations and are distinguished by significant versatility, flexibility and moderate operational costs. Building on an earlier project (Autonomous Flying Platforms for Atmospheric and Earth Surface Observations project; APAESO) of the Energy, Environment and Water Research Center (EEWRC) at the Cyprus Institute (APAESO is co-financed by the European Development Fund and the Republic of Cyprus through the Cyprus Research Promotion Foundation), we have built up an Unmanned Research Aircraft Facility at The Cyprus Institute (CyI-URAF). The basic components of this facility comprise four CRUISERS airplanes (ET-Air, Slovakia) as UAS platforms, a substantial range of scientific instruments to be flown on these platforms, a mobile Ground Control Station and a well-equipped workshop and calibration laboratory. The APAESO platforms are suitable to carrying out atmospheric and earth-surface observations in the (Eastern) Mediterranean (and elsewhere). They enable 3D measurements for determining physical, chemical and radiative atmospheric properties, aerosol and dust concentrations and atmospheric dynamics as well as 2D investigations into land management practices, vegetation and agricultural mapping, contaminant detection and the monitoring and assessment of hydrological parameters and processes of a given region at high spatial resolution. We will report on some of the essential modifications of the platforms and some of the instrumentation that were instrumental in preparing the research airplanes for a variety of collaborative research projects with. The first scientific mission involved the employment of a DOAS-system (Differential Optical Absorption Spectroscopy) in cooperation with

  4. Pareto-optimal multi-objective design of airplane control systems

    Science.gov (United States)

    Schy, A. A.; Johnson, K. G.; Giesy, D. P.

    1980-01-01

    A constrained minimization algorithm for the computer aided design of airplane control systems to meet many requirements over a set of flight conditions is generalized using the concept of Pareto-optimization. The new algorithm yields solutions on the boundary of the achievable domain in objective space in a single run, whereas the older method required a sequence of runs to approximate such a limiting solution. However, Pareto-optimality does not guarantee a satisfactory design, since such solutions may emphasize some objectives at the expense of others. The designer must still interact with the program to obtain a well-balanced set of objectives. Using the example of a fighter lateral stability augmentation system (SAS) design over five flight conditions, several effective techniques are developed for obtaining well-balanced Pareto-optimal solutions. For comparison, one of these techniques is also used in a recently developed algorithm of Kreisselmeier and Steinhauser, which replaces the hard constraints with soft constraints, using a special penalty function. It is shown that comparable results can be obtained.

  5. Proposed Flight Research of a Dual-Bell Rocket Nozzle Using the NASA F-15 Airplane

    Science.gov (United States)

    Jones, Daniel S.; Bui, Trong T.; Ruf, Joseph H.

    2013-01-01

    For more than a half-century, several types of altitude-compensating rocket nozzles have been proposed and analyzed, but very few have been adequately tested in a relevant flight environment. One type of altitude-compensating nozzle is the dual-bell rocket nozzle, which was first introduced into literature in 1949. Despite the performance advantages that have been predicted, both analytically and through static test data, the dual-bell nozzle has still not been adequately tested in a relevant flight environment. This paper proposes a method for conducting testing and research with a dual-bell rocket nozzle in a flight environment. We propose to leverage the existing NASA F-15 airplane and Propulsion Flight Test Fixture as the flight testbed, with the dual-bell nozzle operating during captive-carried flights, and with the nozzle subjected to a local flow field similar to that of a launch vehicle. The primary objective of this effort is not only to advance the technology readiness level of the dual-bell nozzle, but also to gain a greater understanding of the nozzle mode transitional sensitivity to local flow-field effects, and to quantify the performance benefits with this technology. The predicted performance benefits are significant, and may result in reducing the cost of delivering payloads to low-Earth orbit.

  6. Whirling Arm Tests on the Effect of Ground Proximity to an Airplane Wing

    Science.gov (United States)

    Long, M. E.

    1944-01-01

    This report gives the results of tests on a rectangular wing model with a 20% full spun split flap, conducted on the whirling arm at the Daniel Guggenheim Airship Institute in Akron, Ohio. The effect of a ground board on the lift and pitching moment was measured. The ground board consisted of an inclined ramp rising up in the test channel to a level floor extending for some distance parallel to the model path. The path of the wing model with respect to the ground board accordingly represented with comparative exactness an airplane coming in for a landing. The ground clearances over the level portion of the board varied from 0 6 to 1,6 chord lengths. Results are given in the standard dimensionless coefficients plotted versus angle of attack for a particular ground clearance. The effect of the ground board is to increase the lift coefficient for a given angle of attack all the way up the stall. The magnitude of the increase varies both with the ground clearance and the angle of attack. The effect on the pitching moment coefficient is not so readily apparent due to experimental difficulties but, in general, the diving moment increases over the ground board. This effect is apparent principally at the high angles of attack. An exception to this effect occurs with flaps deflected at the lowest ground clearance (0.6 chords). Here the diving moment decreases over the ground board.

  7. Auto-immune concept for dealing with the problem of airplane hijacking

    Science.gov (United States)

    Tibi, Dov Y.

    2003-08-01

    This paper analyzes the inherent contradictions that exist in most of the conventional approaches dealing with airplane hijacking, and presents a completely different approach, employing innovative technological and operational solution. The suggested techno-operational concept is derived from the Systematic Inventive Thinking (SIT) methodology which enforces the problem solver to search for a solution under a few constraining rules -- causing the solution (if found) to be very cost effective. The basic problem that arises from most existing conventional concepts is their very poor cost effectiveness. Passengers, airport operators and aviation companies are all forced to invest on a continual basis, huge amounts of resources and time in order to prevent a hijacking event. The "Auto Immune" concept, discussed here, is based upon enlisting the passengers (in a case of "Hijacking Event" only) to foil the event successfully by releasing, in real-time, a very effective "One-time Non-Lethal Apparatus" (ONLA). This new paradigm changes dramatically the balance of power in favor of the "good guys", and the few hijackers will be neutralized at low risk to the passengers and the aircraft. The detailed technological and operational concept is described, including: operation modes of ONLA, location, release method, safety issues, psychological and legal issues, etc.

  8. 国内飞机数字化装配技术现状研究%Reflection on Improving Airplane Assembly Technology

    Institute of Scientific and Technical Information of China (English)

    初桂兰

    2016-01-01

    On the basis of comparison ,the paper analyzes and concludes the current situation and develop‐ment trend of domestic and overseas airplane assembly technologies ,introduces the key to the development of airplane assembly technology ,and illustrates how aviation manufacturing enterprises can command key airplane assembly technology and make breakthroughs .%通过对国内外飞机数字化装配技术发展的现状和发展的趋势进行分析与总结,对比了国内外飞机数字化装配技术发展的差距,介绍了飞机数字化装配技术发展的关键技术,提出了国内航空制造企业掌握和突破飞机数字化装配关键技术的思路。

  9. A Preliminary Flight Test on a Basic Performance of the Flight Research Airplane Do 228:Velocity v.s. Glide Path Angle

    OpenAIRE

    Yoshikazu, Miyazawa; Takatsugu, Ono; Yasuhito, Kawagoe

    1989-01-01

    A preliminary flight test was conducted of the research airplane Dornier Do228-200 that is being modified for use as an in-flight simulator by the National Aerospace Laboratory. The basic performance of the airplane was evaluated by the flight test. Glide path angles were examined with various parameters, such as velocity, altitude, and power. The flight test results were compared with those of a mathematical model based on the Dornier GmbH wind-tunnel test data. Since an onboard data acquisi...

  10. An algorithm for target airplane segmentation & extraction%一种目标飞机分割提取方法

    Institute of Scientific and Technical Information of China (English)

    谷东格

    2016-01-01

    In this paper, an algorithm for target airplane segmentation & extraction was proposed. In order to segment &extract the target airplane quickly and accurately, the algorithm adopted GrabCut algorithm which was improved by using pyramid segment tactics and based on color Gaussian Mixture Model and iterative energy minimum. The test results show that in the majority situation, this algorithm can accurately segment&extract the target airplane without using any other interaction while its processing speed is almost five times in comparison to the primary algorithm.%提出了一种目标飞机分割提取方法,该方法采用改进的使用金字塔式分割策略的以彩色高斯混合模型GMM (Gaussian Mixture Model)和迭代能量最小化为基础的GrabCut算法,达到将目标飞机快速精确分割提取的目的。实验结果表明在多数情况下,只需围绕目标飞机画一个框无需额外交互,就可以快速的将目标飞机精确分割提取出来,即便是在某些情况下不能够将目标飞机精确提取分割也只需额外的少数交互就可以达到将目标飞机精确分割提取的目的。

  11. Interference Path Loss Prediction in A319/320 Airplanes Using Modulated Fuzzy Logic and Neural Networks

    Science.gov (United States)

    Jafri, Madiha J.; Ely, Jay J.; Vahala, Linda L.

    2007-01-01

    In this paper, neural network (NN) modeling is combined with fuzzy logic to estimate Interference Path Loss measurements on Airbus 319 and 320 airplanes. Interference patterns inside the aircraft are classified and predicted based on the locations of the doors, windows, aircraft structures and the communication/navigation system-of-concern. Modeled results are compared with measured data. Combining fuzzy logic and NN modeling is shown to improve estimates of measured data over estimates obtained with NN alone. A plan is proposed to enhance the modeling for better prediction of electromagnetic coupling problems inside aircraft.

  12. AVIATR—Aerial Vehicle for In-situ and Airborne Titan Reconnaissance. A Titan airplane mission concept

    Science.gov (United States)

    Barnes, Jason W.; Lemke, Lawrence; Foch, Rick; McKay, Christopher P.; Beyer, Ross A.; Radebaugh, Jani; Atkinson, David H.; Lorenz, Ralph D.; Le Mouélic, Stéphane; Rodriguez, Sebastien; Gundlach, Jay; Giannini, Francesco; Bain, Sean; Flasar, F. Michael; Hurford, Terry; Anderson, Carrie M.; Merrison, Jon; Ádámkovics, Máté; Kattenhorn, Simon A.; Mitchell, Jonathan; Burr, Devon M.; Colaprete, Anthony; Schaller, Emily; Friedson, A. James; Edgett, Kenneth S.; Coradini, Angioletta; Adriani, Alberto; Sayanagi, Kunio M.; Malaska, Michael J.; Morabito, David; Reh, Kim

    2012-03-01

    We describe a mission concept for a stand-alone Titan airplane mission: Aerial Vehicle for In-situ and Airborne Titan Reconnaissance (AVIATR). With independent delivery and direct-to-Earth communications, AVIATR could contribute to Titan science either alone or as part of a sustained Titan Exploration Program. As a focused mission, AVIATR as we have envisioned it would concentrate on the science that an airplane can do best: exploration of Titan's global diversity. We focus on surface geology/hydrology and lower-atmospheric structure and dynamics. With a carefully chosen set of seven instruments—2 near-IR cameras, 1 near-IR spectrometer, a RADAR altimeter, an atmospheric structure suite, a haze sensor, and a raindrop detector—AVIATR could accomplish a significant subset of the scientific objectives of the aerial element of flagship studies. The AVIATR spacecraft stack is composed of a Space Vehicle (SV) for cruise, an Entry Vehicle (EV) for entry and descent, and the Air Vehicle (AV) to fly in Titan's atmosphere. Using an Earth-Jupiter gravity assist trajectory delivers the spacecraft to Titan in 7.5 years, after which the AVIATR AV would operate for a 1-Earth-year nominal mission. We propose a novel `gravity battery' climb-then-glide strategy to store energy for optimal use during telecommunications sessions. We would optimize our science by using the flexibility of the airplane platform, generating context data and stereo pairs by flying and banking the AV instead of using gimbaled cameras. AVIATR would climb up to 14 km altitude and descend down to 3.5 km altitude once per Earth day, allowing for repeated atmospheric structure and wind measurements all over the globe. An initial Team-X run at JPL priced the AVIATR mission at FY10 715M based on the rules stipulated in the recent Discovery announcement of opportunity. Hence we find that a standalone Titan airplane mission can achieve important science building on Cassini's discoveries and can likely do so

  13. A 727 airplane center duct inlet low speed performance confirmation model test for refanned JT8D engines, phase 2

    Science.gov (United States)

    Kaldschmidt, G.; Syltebo, B. E.; Ting, C. T.

    1973-01-01

    The results from testing of a 0.3 scale model center duct inlet (S duct) for the Pratt and Whitney Aircraft JT8D-100 engines are presented. The objective of this test was to demonstrate that the required airflow of the JT8D-100 engine (480 lb/sec as compared to 334 lb/sec for JT8D-15) can be achieved with minimum modifications to the existing 727 airplane structure at acceptable levels of total pressure recovery and distortion. Steady-state pressure recovery, steady-state pressure distortion, and dynamic pressure measurements were taken at the engine face station. Surface static pressure measurements were taken along the duct. Test results indicated that the required airflow was achieved with acceptable pressure recovery (comparable to the current 727-200 S duct). Inlet inflow angle variation within the 727 airplane operating regime (minus 5 to 5 degrees) had no effect on the inlet performance. Pressure distortion at static and forward speed at takeoff airflow conditions are within P and WA limits for the Phase II duct when equipped with vortex generators. Static crosswind operation between 10 knots and 25 knots appears feasible at full takeoff power.

  14. Conceptual Design for a Dual-Bell Rocket Nozzle System Using a NASA F-15 Airplane as the Flight Testbed

    Science.gov (United States)

    Jones, Daniel S.; Ruf, Joseph H.; Bui, Trong T.; Martinez, Martel; St. John, Clinton W.

    2014-01-01

    The dual-bell rocket nozzle was first proposed in 1949, offering a potential improvement in rocket nozzle performance over the conventional-bell nozzle. Despite the performance advantages that have been predicted, both analytically and through static test data, the dual-bell nozzle has still not been adequately tested in a relevant flight environment. In 2013 a proposal was constructed that offered a National Aeronautics and Space Administration (NASA) F-15 airplane as the flight testbed, with the plan to operate a dual-bell rocket nozzle during captive-carried flight. If implemented, this capability will permit nozzle operation into an external flow field similar to that of a launch vehicle, and facilitate an improved understanding of dual-bell nozzle plume sensitivity to external flow-field effects. More importantly, this flight testbed can be utilized to help quantify the performance benefit with the dual-bell nozzle, as well as to advance its technology readiness level. Toward this ultimate goal, this report provides plans for future flights to quantify the external flow field of the airplane near the nozzle experiment, as well as details on the conceptual design for the dual-bell nozzle cold-flow propellant feed system integration within the NASA F-15 Propulsion Flight Test Fixture. The current study shows that this concept of flight research is feasible, and could result in valuable flight data for the dual-bell nozzle.

  15. Minimum time and fuel flight profiles for an F-15 airplane with a Highly Integrated Digital Electronic Control (HIDEC) system

    Science.gov (United States)

    Haering, E. A., Jr.; Burcham, F. W., Jr.

    1984-01-01

    A simulation study was conducted to optimize minimum time and fuel consumption paths for an F-15 airplane powered by two F100 Engine Model Derivative (EMD) engines. The benefits of using variable stall margin (uptrim) to increase performance were also determined. This study supports the NASA Highly Integrated Digital Electronic Control (HIDEC) program. The basis for this comparison was minimum time and fuel used to reach Mach 2 at 13,716 m (45,000 ft) from the initial conditions of Mach 0.15 at 1524 m (5000 ft). Results were also compared to a pilot's estimated minimum time and fuel trajectory determined from the F-15 flight manual and previous experience. The minimum time trajectory took 15 percent less time than the pilot's estimate for the standard EMD engines, while the minimum fuel trajectory used 1 percent less fuel than the pilot's estimate for the minimum fuel trajectory. The F-15 airplane with EMD engines and uptrim, was 23 percent faster than the pilot's estimate. The minimum fuel used was 5 percent less than the estimate.

  16. Aerodynamic Modeling and Parameter Estimation from QAR Data of an Airplane Approaching a High-altitude Airport

    Institute of Scientific and Technical Information of China (English)

    WANG Qing; WU Kaiyuan; ZHANG Tianjiao; KONG Yi'nan; QIAN Weiqi

    2012-01-01

    Aerodynamic modeling and parameter estimation from quick accesses recorder (QAR) data is an important technical way to analyze the effects of highland weather conditions upon aerodynamic characteristics of airplane.It is also an essential content of flight accident analysis.The related techniques are developed in the present paper,including the geometric method for angle of attack and sideslip angle estimation,the extended Kalman filter associated with modified Bryson-Frazier smoother (EKF-MBF) method for aerodynamic coefficient identification,the radial basis function (RBF) neural network method for aerodynamic modeling,and the Delta method for stability/control derivative estimation.As an application example,the QAR data of a civil airplane approaching a high-altitude airport are processed and the aerodynamic coefficient and derivative estimates are obtained.The estimation results are reasonable,which shows that the developed techniques are feasible.The causes for the distribution of aerodynamic derivative estimates are analyzed.Accordingly,several measures to improve estimation accuracy are put forward.

  17. Assessing V and V Processes for Automation with Respect to Vulnerabilities to Loss of Airplane State Awareness

    Science.gov (United States)

    Whitlow, Stephen; Wilkinson, Chris; Hamblin, Chris

    2014-01-01

    Automation has contributed substantially to the sustained improvement of aviation safety by minimizing the physical workload of the pilot and increasing operational efficiency. Nevertheless, in complex and highly automated aircraft, automation also has unintended consequences. As systems become more complex and the authority and autonomy (A&A) of the automation increases, human operators become relegated to the role of a system supervisor or administrator, a passive role not conducive to maintaining engagement and airplane state awareness (ASA). The consequence is that flight crews can often come to over rely on the automation, become less engaged in the human-machine interaction, and lose awareness of the automation mode under which the aircraft is operating. Likewise, the complexity of the system and automation modes may lead to poor understanding of the interaction between a mode of automation and a particular system configuration or phase of flight. These and other examples of mode confusion often lead to mismanaging the aircraftâ€"TM"s energy state or the aircraft deviating from the intended flight path. This report examines methods for assessing whether, and how, operational constructs properly assign authority and autonomy in a safe and coordinated manner, with particular emphasis on assuring adequate airplane state awareness by the flight crew and air traffic controllers in off-nominal and/or complex situations.

  18. Aerodynamic Characteristics and Flying Qualities of a Tailless Triangular-wing Airplane Configuration as Obtained from Flights of Rocket-propelled Models at Transonic and Supersonic Speeds

    Science.gov (United States)

    Mitcham, Grady L; Stevens, Joseph E; Norris, Harry P

    1956-01-01

    A flight investigation of rocket-powered models of a tailless triangular-wing airplane configuration was made through the transonic and low supersonic speed range at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. An analysis of the aerodynamic coefficients, stability derivatives, and flying qualities based on the results obtained from the successful flight tests of three models is presented.

  19. Wind tunnel test of model target thrust reversers for the Pratt and Whitney aircraft JT8D-100 series engines installed on a 727-200 airplane

    Science.gov (United States)

    Hambly, D.

    1974-01-01

    The results of a low speed wind tunnel test of 0.046 scale model target thrust reversers installed on a 727-200 model airplane are presented. The full airplane model was mounted on a force balance, except for the nacelles and thrust reversers, which were independently mounted and isolated from it. The installation had the capability of simulating the inlet airflows and of supplying the correct proportions of primary and secondary air to the nozzles. The objectives of the test were to assess the compatibility of the thrust reversers target door design with the engine and airplane. The following measurements were made: hot gas ingestion at the nacelle inlets; model lift, drag, and pitching moment; hot gas impingement on the airplane structure; and qualitative assessment of the rudder effectiveness. The major parameters controlling hot gas ingestion were found to be thrust reverser orientation, engine power setting, and the lip height of the bottom thrust reverser doors on the side nacelles. The thrust reversers tended to increase the model lift, decrease the drag, and decrease the pitching moment.

  20. 78 FR 75285 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Flight...

    Science.gov (United States)

    2013-12-11

    ... control system that prevents the pilot from inadvertently or intentionally exceeding the positive or... design for an electronic flight control system with load factor limiting. It is possible that pilots... design of the electronic flight control system for the C-series airplanes incorporates normal load...

  1. 78 FR 76734 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Seats...

    Science.gov (United States)

    2013-12-19

    ... be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http...- bubble fuselage, sized for nominal 5-abreast seating. Each airplane's powerplant consists of two under...\\ installed per seat place. The panel may consist of either a single component or multiple components in...

  2. 78 FR 75287 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Flight...

    Science.gov (United States)

    2013-12-11

    ... Privacy Act Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478..., blended double- bubble fuselage, sized for nominal 5-abreast seating. Each airplane's powerplant consists... significant change (or multiple changes) occurs in the EFCS control laws as the limit is approached...

  3. Pollution Type and Control Ways of Hydraulic System of Civil Airplane%民机液压系统污染种类以及控制方法

    Institute of Scientific and Technical Information of China (English)

    翁康静

    2015-01-01

    介绍了液压系统的集中污染源,分析了污染源造成的原因并采取了相应的控制措施。%This paper mainly analyzed the pollution sources in the hydraulic system of civil airplane ,found out the reasons ,and put forword the relevant measures .

  4. 大修飞机故障分析与设计改进%Breakdown Analysis during Airplane Major Repair and Design Improvement

    Institute of Scientific and Technical Information of China (English)

    刘小明

    2014-01-01

    There are various breakdowns during airplane major repair ,some of which are very common . Furthermore ,these breakdowns occur during normal use ,often caused by unreasonable designs .Discove-ring unreasonable designs and manufacturing via rigorously analyzing reasons for these failures is an impor-tant means to improve airplane performance and quality .Through some cases ,the paper introduces how to improve airplane design according to common breakdow ns discovered in major repair of airplane .%大修飞机出现的故障多种多样,有些故障是普遍存在的问题,而且这些故障是在正常使用过程中出现的,这类故障通常是由于设计不合理造成的。通过对大修飞机出现的故障的原因进行严密的分析,从而发现设计、制造环节中的不合理之处,并进行改进,是不断提高飞机性能及质量的重要手段之一。通过案例,介绍了如何从大修飞机出现的故障对飞机设计进行改进。

  5. Problems and Countermeasures of the Protection of New Airplane Aviation Materials%新机航材保障问题与对策

    Institute of Scientific and Technical Information of China (English)

    李卫灵; 郭星香; 张明传; 吴昊

    2014-01-01

    随着新型飞机逐步装备部队,新机航材保障的地位和作用愈加突出。做好新机航材保障,将为航空兵作战效能的提升起到积极作用。文章主要分析了当前新机航材保障面临的主要问题,并对问题提出了针对性的对策。%With the arming of troops by the new type airplanes, the position and role of new type airplane aviation materials are more and more prominent. It plays a positive role in promoting the effectiveness of aviation combat to protect the new type airplane aviation materials. This paper mainly analyzes the main problems of the new type airplane aviation materials at present and puts forward the corresponding countermeasures.

  6. 飞机红外辐射特性建模与仿真%Modeling and simulation of airplane infrared characteristic

    Institute of Scientific and Technical Information of China (English)

    刘娟; 龚光红; 韩亮; 高栋栋

    2011-01-01

    Airplane's infrared radiation simulation and modeling is an important branch for synthetic nature environment. It's needed to establish the infrared radiation model accurately according to airplane's status in present. In this paper, firstly, based on synthetic nature environment as well as aerodynamics, heat transfer theory, work principle of engine, airplane's infrared radiation characteristic models including airplane-skin and engine nozzle components, exhaust plume were established under current status. Then, moving airplane's infrared radiation characteristics with working status as the input was calculated and analyzed. Finally, airplane' s infrared radiation results were obtained through the simulating model mentioned above under condition of different status. This modeling method will have an important effect on infrared platform detecting and real time scene generating in defense and military simulation system.%飞机红外辐射建模与仿真研究是综合自然环境仿真的重要分支,根据目标飞行状态建立红外辐射模型是当前仿真的需求.文中基于综合自然环境、空气动力学、传热学和发动机工作原理,建立了飞机在当前飞行状态下蒙皮及发动机尾喷管、羽流的红外辐射强度特性模型.在当前飞行状态为输入情况下,分析并计算了运动飞机的红外辐射特性,并通过仿真获到了飞机在不同状态下的红外辐射结果.此建模方法对国防军事仿真系统中的平台红外探测与实时红外场景生成具有重要意义.

  7. 柔性飞机起落架改进设计%IMPROVED LANDING-GEAR DESIGN FOR FLEXIBLE AIRPLANE

    Institute of Scientific and Technical Information of China (English)

    史友进

    2005-01-01

    综合运用着陆响应模拟和优化设计方法以改进大柔性飞机起落架的设计.以弹性飞机的三质量块等效模型、油气缓冲器多方指数气体弹力模型、油气缓冲器速率平方油孔阻力模型和幂函数轮胎力模型模拟弹性飞机着陆动力学.考虑了大柔性飞机着陆撞击中的缓冲器最大行程、最大缓冲器力及机翼最大位移,对起落架参数进行优化设计.结果表明,大柔性飞机机体结构弹性对起落架参数设计有较大的影响,采用优化设计的油针式缓冲器可以改进起落架的着陆性能.%Landing dynamic simulation and landing-gear optimization design are used to improve the landing-gear design for a flexible airplane. Landing response is simulated by using velocity-squared damping, polytropic exponential air-compression spring, tire force power function characteristics, and an equivalent three-mass system.Optimization of landing-gear parameters is performed considering the maximum displacement of the landing-gear shock stroke, the maximum landing-gear force and the maximum deformation of the wingtip in the landing impact. Resutls show that landing-gear design parameters have an important influence on the structural flexibility of the airplane. And the landing performance of the landing-gear can be improved by the optimized metering pin type landing-gear.

  8. The risk of PTSD and depression after an airplane crash and its potential association with physical injury: A longitudinal study.

    Science.gov (United States)

    Gouweloos, Juul; Postma, Ingri L E; te Brake, Hans; Sijbrandij, Marit; Kleber, Rolf J; Goslings, J Carel

    2016-01-01

    In 2009, a commercial airplane crashed near Amsterdam. This longitudinal study aims to investigate (1) the proportion of survivors of the airplane crash showing a probable posttraumatic stress disorders (PTSD) or depressive disorder, and (2) whether symptoms of PTSD and depression were predicted by trauma characteristics. Identifying these trauma characteristics is crucial for early detection and treatment. Of the 121 adult survivors, 82 participated in this study 2 months after the crash and 76 participated 9 months after the crash. Risk for PTSD and depression was measured with the self-report instruments Trauma Screening Questionnaire and Patient Health Questionnaire-2. Trauma characteristics assessed were Injury Severity Score (ISS), hospitalisation, length of hospital stay, and seating position in the plane. Two months after the crash, 32 participants (of N=70, 46%) were at risk for PTSD and 28 (of N=80, 32%) were at risk for depression. Nine months after the crash, 35 participants (of N=75, 47%) were at risk for PTSD and 24 (of N=76, 35%) were at risk for depression. There was a moderate correlation between length of hospital stay and symptoms of PTSD and depression 9 months after the crash (r=.33 and r=.45, respectively). There were no differences in seating position between participants at high risk vs. participants at low risk for PTSD or depression. Mixed design ANOVAs showed also no association between the course of symptoms of PTSD and depression 2 and 9 months after the crash and ISS or hospitalisation. This suggests that health care providers need to be aware that survivors may be at risk for PTSD or depression, regardless of the objective severity of their physical injuries. PMID:26210753

  9. Stability and Controls Analysis and Flight Test Results of a 24-Foot Telescoping Nose Boom on an F-15B Airplane

    Science.gov (United States)

    Moua, Cheng M.; Cox, Timothy H.; McWherter, Shaun C.

    2008-01-01

    The Quiet Spike(TradeMark) F-15B flight research program investigated supersonic shock reduction using a 24-ft telescoping nose boom on an F-15B airplane. The program goal was to collect flight data for model validation up to 1.8 Mach. In the area of stability and controls, the primary concerns were to assess the potential destabilizing effect of the oversized nose boom on the stability, controllability, and handling qualities of the airplane and to ensure adequate stability margins across the entire research flight envelope. This paper reports on the stability and control analytical methods, flight envelope clearance approach, and flight test results of the F-15B telescoping nose boom configuration. Also discussed are brief pilot commentary on typical piloting tasks and refueling tasks.

  10. Wind-tunnel tests of a 1/4 scale model of the Bell XS-1 transonic airplane. 1: Longitudinal stability and control characteristics

    Science.gov (United States)

    Donlan, C. J.; Kemp, W. B., Jr.; Polhamus, E. C.

    1976-01-01

    A 1/4 scale model of the Bell XS-1 transonic aircraft was tested in the Langley 300 mile-per-hour 7 by 10 foot tunnel to determine its low speed longitudinal stability and control characteristics. Pertinent longitudinal flying qualities expected of the XS-1 research airplane were estimated from the results of these tests including the effects of compressibility likely to be encountered at speeds below the force break. It appears that the static longitudinal stability and elevator control power will be adequate, but that the elevator control force gradient in steady flight will be undesirably low for all configurations. It is suggested that a centering spring be incorporated in the elevator control system of the airplane in order to increase the control force gradient in steady flight and in maneuvers.

  11. 运输类飞机飞行手册设计与开发%Flight Manual Design and Development for Transport Category Airplanes

    Institute of Scientific and Technical Information of China (English)

    谢辉松; 周琳

    2012-01-01

    An AFM is an important document developed by the manufacture and approved by the Airworthiness Authorities. An AFM, which is needed for safe operation, contains the essential information that is peculiar to the particular airplane type or model, including operating limitations, operating procedures and performance information. The main contents and guides of the flight manual design and development for transport category airplane are presented in this paper%飞机飞行手册是经制造商开发并由适航当局批准的重要文件,它提供对某一特定机型飞机安全操作所必须的重要信息,包括使用限制、操作程序和性能信息。介绍了运输类飞机飞行手册设计与开发的主要内容。

  12. An analysis of airspeed, altitude, and acceleration data obtained from a twin-engine transport airplane operated over a feeder-line route in the Rocky Mountains

    Science.gov (United States)

    Copp, Martin R; Fetner, Mary W

    1956-01-01

    Time-history data of airspeed, altitude, and acceleration obtained with the NACA VGH recorder from a twin-engine airplane operated by a regional feeder airline in the Rocky Mountains are evaluated to determine the magnitude and frequency of occurrence of gusts and gust accelerations and the operating airspeeds and altitudes. The results obtained are compared with the results previously obtained from a representative short-haul and long-haul operation.

  13. Guidance for contact tracing of cases of Lassa fever, Ebola or Marburg haemorrhagic fever on an airplane: results of a European expert consultation

    OpenAIRE

    Gilsdorf Andreas; Morgan Dilys; Leitmeyer Katrin

    2012-01-01

    Abstract Background Travel from countries where viral haemorrhagic fevers (VHF) are endemic has increased significantly over the past decades. In several reported VHF events on airplanes, passenger trace back was initiated but the scale of the trace back differed considerably. The absence of guidance documents to help the decision on necessity and scale of the trace back contributed to this variation. This article outlines the recommendations of an expert panel on Lassa fever, Ebola and Marbu...

  14. Research On Combat Airplane Maneuvering Flight Path Simulation%作战飞机机动飞行航迹仿真建模研究

    Institute of Scientific and Technical Information of China (English)

    杨莉; 安红

    2011-01-01

    在各类与作战飞机相关的动态仿真系统中,通常会涉及到对飞机飞行姿态和飞行航迹的仿真要求。针对作战飞机通常采用的飞行方式,在大地坐标系下建立了这些常见飞行方式的仿真模型。当飞机机动飞行时会形成比较复杂的航迹,可以将复杂的飞行航迹分解为多个简单的航迹段,每个航迹段为直线飞行或转弯机动。根据这种方式对飞机机动飞行航迹进行了仿真,通过仿真运行给出了一些机动飞行时的航迹仿真结果,验证了机动飞行航迹仿真模型的正确性。%Many dynamic simulation system that relate to combat airplane refer to airplane attitude and flight path. In this paper, the models of combat airplane maneuvering flight path in geographic coordinate system are built. And we made some simulation experiments in several kinds of typical maneuvering fly modes, the simulation results proves simulation model of airplane maneuvering is valid.

  15. Research on Service Life Monitoring of Airplane%某型飞机单机寿命监控技术研究

    Institute of Scientific and Technical Information of China (English)

    夏念国; 王钊

    2011-01-01

    This paper made a quantitative analysis of life for an airplane based on the method which is using the fatigue life of a class of dangerous parts instead of the whole machine, meanwhile fatigue life of dangerous parts for an airplane has been analyzed quantitatively based on local stress-strain approach which considered the memory characteristic of the material and the calculated results is matching the experimental results. Finally, with the local stress-strain approach and the modified Manson-Coffin formula, the actual fatigue life of dangerous parts for an airplane has been received based on the actual flight data spectrum and life monitoring of individual an airplane has been found according to the results.%用一类疲劳危险部位的寿命代替全机疲劳寿命的方法,对某型飞机的寿命做了定量分析,并基于考虑材料记忆特性的局部应力应变法,对某型飞机的疲劳危险部位进行了标准谱下的寿命计算,计算结果与试验结果较吻合.最后采用局部应力应变法及修正的Manson-Coffin公式,得到了基于飞参数据载荷谱的某型飞机危险部位的实际寿命,并与基于标准谱的疲劳寿命做了对比,为某型飞机的单机寿命监控奠定了基础.

  16. The Wind and Beyond: A Documentary Journey into the History of Aerodynamics in America. Volume 1; The Ascent of the Airplane

    Science.gov (United States)

    Hansen, James R. (Editor); Taylor, D. Bryan; Kinney, Jeremy; Lee, J. Lawrence

    2003-01-01

    This first volume, plus the succeeding five now in preparation, covers the impact of aerodynamic development on the evolution of the airplane in America. As the six-volume series will ultimately demonstrate, just as the airplane is a defining technology of the twentieth century, aerodynamics has been the defining element of the airplane. Volumes two through six will proceed in roughly chronological order, covering such developments as the biplane, the advent of commercial airliners, flying boats, rotary aircraft, supersonic flight, and hypersonic flight. This series is designed as an aeronautics companion to the Exploring the Unknown: Selected Documents in the History of the U.S. Civil Space Program (NASA SP-4407) series of books. As with Exploring the Unknown, the documents collected during this research project were assembled from a diverse number of public and private sources. A major repository of primary source materials relative to the history of the civil space program is the NASA Historical Reference Collection in the NASA Headquarters History Office. Historical materials housed at NASA field centers, academic institutions, and Presidential libraries were other sources of documents considered for inclusion, as were papers in the archives of private individuals and corporations.

  17. Effects of flaps on buffet characteristics and wind-rock onset of an F-8C airplane at subsonic and transonic speeds

    Science.gov (United States)

    Monaghan, R. C.; Friend, E. L.

    1973-01-01

    Wind-up-turn maneuvers were performed to establish the values of airplane normal force coefficient for buffet onset, wing-rock onset, and buffet loads with various combinations of leading- and trailing-edge flap deflections. Data were gathered at both subsonic and transonic speeds covering a range from Mach 0.64 to Mach 0.92. Buffet onset and buffet loads were obtained from wingtip acceleration and wing-root bending-moment data, and wing-rock onset was obtained from airplane roll rate data. Buffet onset, wing-rock onset, and buffet loads were similarly affected by the various combinations of leading- and training-edge flaps. Subsonically, the 12 deg leading-edge-flap and trailing-edge-flap combination was most effective in delaying buffet onset, wing-rock onset, and equivalent values of buffet loads to a higher value of airplane normal force coefficient. This was the maximum flap deflection investigated. Transonically, however, the optimum leading-edge flap position was generally less than 12 deg.

  18. 一种计算机支持的飞机协同设计中的感知模型%An Awareness Model for Airplane Cooperative Design

    Institute of Scientific and Technical Information of China (English)

    周安宁; 刘毅; 李文正

    2011-01-01

    为了实现飞机设计中的协同感知,针对其学科多、设计流程复杂的特点,通过研究飞机协同设计中涉及的感知信息及其关联、层次,以协同对象附加设计资源分配、产品结构、工作流、设计意图等工程背景信息的方式建立了一种感知模型.该模型使用设计资源空间呈现不同学科在同一物理量上的冲突;针对不同深度的感知需求设计呈现模式,并据此给出实现协同感知所需传输的数据和格式;基于CATIA实现感知模型原型,为设计人员提供自主、一致的工作视图,呈现不同深度的感知信息.最后通过实例显示,文中模型满足飞机协同设计的感知要求,有助于高效、流畅地完成设计任务.%Because of varied disciplines and complex processes in airplane design, this paper presents an awareness model to achieve cooperative awareness in airplane cooperative design. To conform to the awareness information involved in airplane cooperative design and its hierarchy, the model is attached with engineering contexts, such as design resource allocation, product structure, design mission in work flow and design intention. The concept of design resource space is introduced, in which the conflict of some physical quantity among varied disciplines is demonstrated. Then the representation modes and data format for transmitting are designed for various depth of awareness requirements. And then, a prototype based on the CATIA software is developed to provide intuitive displaying of design objects with consistency and locally controlled viewpoint. At last, an example is used to show that the model satisfies cooperative awareness in airplane design and can boost airplane design with more smoothness and efficiency.

  19. The effect of chine tires on nose gear water-spray characteristics of a twin engine airplane

    Science.gov (United States)

    Yager, T. J.; Stubbs, S. M.; Mccarty, J. L.

    1975-01-01

    An experimental investigation was performed to evaluate the effectiveness of nose gear chine tires in eliminating or minimizing the engine spray ingestion problem encountered on several occasions by the Merlin 4, a twin-engine propjet airplane. A study of the photographic and television coverage indicated that under similar test conditions the spray from the chine tires presented less of a potential engine spray ingestion problem than the conventional tires. Neither tire configuration appeared to pose any ingestion problem at aircraft speeds in excess of the hydroplaning speed for each tire, however, significant differences were noted in the spray patterns of the two sets of tires at sub-hydroplaning speeds. At sub-hydroplaning speeds, the conventional tires produced substantial spray above the wing which approached the general area of the engine air inlet at lower test speeds. The chine tires produced two distinct spray plumes at sub-hydroplaning speeds: one low-level plume which presented no apparent threat of ingestion, and one which at most test speeds was observed to be below the wing leading edge and thus displaced from the intakes on the engine nacelle.

  20. The 727 airplane side inlet low-speed performance confirmation model test for refanned JT8D engines

    Science.gov (United States)

    Schuehle, A. L.

    1974-01-01

    The results of a low-speed wind tunnel test of a 0.3 scale model 727 airplane side inlet for JT8D-100 engines are presented. The objectives of the test were to develop lines for a full-scale flightworthy inlet, to evaluate inlet total pressure recovery and steady-state total pressure distortion, and to obtain model-scale distortion data which can be used in the assessment of the compatibility of the inlet with the JT8D-100 series engines. A secondary objective was to obtain internal/external cowl static pressures for the determination of nacelle loads. Two basic inlet models were tested at static, forward speed, angle-of-attack (inflow angle), and cross-wind conditions. One model was with and one without an acoustic ring. Two modifications to the models were also tested, one with the ring closer to the inlet throat and one with a larger lip. Test measurements consisted of inlet surface static pressure, engine face total pressure, inlet airflow, tunnel total pressure, tunnel total temperature and tunnel velocity. Total pressure traverses were taken directly behind the ring and strut. No dynamic measurements were taken.

  1. Some subsonic and transonic buffet characteristics of the twin-vertical-tails of a fighter airplane configuration

    Science.gov (United States)

    Moss, Steven W.; Cole, Stanley R.; Doggett, Robert V., Jr.

    1991-01-01

    Vertical-tail buffet response data were obtained from tests in the Langley Transonic Dynamics Tunnel using a rigid, 1/6-size, full-span model of an F-18 airplane that was fitted with flexible vertical tails of two different levels of structural stiffness. Response data are presented at Mach numbers from 0.30 to 0.95 over a range of angles of attack from -10 to +40 degrees. These data indicate the following: (1) the buffet response occurs in the first bending mode; (2) the buffet response is a maximum in the angle of attack range from 30 to 40 degrees; (3) the buffet response increases with increasing dynamic pressure, but changes in response are not linearly proportional to the changes in dynamic pressure; (4) the buffet response is larger at M = 0.30 than it is at the higher Mach numbers; and (5) the maximum intensity of the buffeting is described as heavy to severe using an assessment criteria proposed by another investigator.

  2. Development of a measurement platformon a light airplane and analysis of airborne measurementsin the atmospheric boundary layer

    Directory of Open Access Journals (Sweden)

    D. Zardi

    2003-06-01

    Full Text Available In the present paper we provide an overview of a long term research project aimed at setting up a suitable platform for measurements in the atmospheric boundary layer on a light airplane along with some preliminary results obtained from fi eld campaigns at selected sites. Measurements of air pressure, temperature and relative humidity have been performed in various Alpine valleys up to a height of about 2500 m a.m.s.l. By means of GPS resources and specifi c post-processing procedures careful positioning of measurement points within the explored domain has been achieved. The analysis of collected data allowed detailed investigation of atmospheric vertical structures and dynamics typical of valley environment, such as morning transition from ground based inversion to fully developed well mixed convective boundary layer. Based on data collected along fl ights, 3D fi elds of the explored variables have been detected and identifi ed through application of geostatistical techniques (Kriging. The adopted procedures allowed evaluation of the intrinsic statistical structure of the spatial distribution of measured quantities and the estimate of the values of the same variable at unexplored locations by suitable weighted average of data recorded at close locations. Results thus obtained are presented and discussed.

  3. Study of civil airplane wingtip design%民用飞机翼尖设计研究

    Institute of Scientific and Technical Information of China (English)

    翁晨涛; 夏露

    2011-01-01

    利用机翼翼尖装置减少机翼诱导阻力是飞机减阻研究的重要组成部分.综合介绍了机翼翼尖装置的减阻技术研究的新发展,着重讨论了几种典型的翼尖装置减阻原理、特性以及应用情况.研究结果表明,使用翼尖装置在减少诱导阻力方面会起到很大的作用.最后,基于翼尖装置的研究和发展现状,对其发展前景进行了评述和展望.%Reducing the induced drag by using a wingtip device is very important in airplane drag reduction study. In this paper, some new developments in the drag reduction are investigated. Developments of the wingtip device are expatiated, including its typical theories, characteristics, and application status. Research results prove that the wingtip device is very effective to reduce the induced drag. In the end, some comments and prospects for the wingtip device are concluded.

  4. 客机交易议价模型研究%The Bargaining Model for Commercial Airplane Trade

    Institute of Scientific and Technical Information of China (English)

    赵星晨

    2016-01-01

    由于交易的特殊性,客机的成交价格和目录价格之间往往存在较大差异,而且具体差异程度由于商业保密的原因难以被外界获知。本文从不完全信息动态博弈的角度,利用Zeuthen模型,对客机交易的过程和结果进行了研究,分析了交易双方在不同报价策略情况下合同成交价格的变化,并讨论了交易双方的议价能力,得到的结果具有合理性和参考价值。%Due to the highly business sensitivity and confidentiality, the list price and contract price of airplane often have huge difference, the extent of which is unknown to the public. Based on Zeuthen model, took an example of the dynamic game of incomplete information, this paper analyzed the process of negotiation, studied the relationships between ending contract prices and initial bids, as well as discussed the implications of bidding strategy on bargaining powers. The results are reasonable and helpful for decision-making.

  5. The results of a low-speed wind tunnel test to investigate the effects of the Refan JT8D engine target thrust reverser on the stability and control characteristics of the Boeing 727-200 airplane

    Science.gov (United States)

    Kupcis, E. A.

    1974-01-01

    The effects of the Refan JT8D side engine target thrust reverser on the stability and control characteristics of the Boeing 727-200 airplane were investigated using the Boeing-Vertol 20 x 20 ft Low-Speed Wind Tunnel. A powered model of the 727-200 was tested in groud effect in the landing configuration. The Refan target reverser configuration was evaluated relative to the basic production 727 airplane with its clamshell-deflector door thrust reverser design. The Refan configuration had slightly improved directional control characteristics relative to the basic airplane. Clocking the Refan thrust reversers 20 degrees outboard to direct the reverser flow away from the vertical tail, had little effect on directional control. However, clocking them 20 degrees inboard resulted in a complete loss of rudder effectiveness for speeds greater than 90 knots. Variations in Refan reverser lip/fence geometry had a minor effect on directional control.

  6. The results of a high-speed wind tunnel test to investigate the effects of the NASA refan JT8D engine nacelles on the stability and control characteristics of the Boeing 727 airplane

    Science.gov (United States)

    Kupcis, E. A.

    1973-01-01

    A high speed wind tunnel test was conducted to investigate the effects of the NASA Refan JT8D engine nacelles on the stability and control characteristics of the Boeing 727 airplane. The test was performed at the Calspan Corporation 8x8 ft. (2.44x2.44 m.) transonic wind tunnel. Both the 727-200 and -100 models were tested. A small nose-down pitching moment increment and a slight increase in longitudinal stability were noted due to the Refan nacelles. The directional stability of the 727-200 airplane increased up to 10 percent. A smaller improvement was observed on the 727-100 model. In general, the high speed stability and control characteristics of the basic airplane are not significantly altered by the Refan nacelle installation.

  7. High Altitude Long Endurance UAV Analysis Model Development and Application Study Comparing Solar Powered Airplane and Airship Station-Keeping Capabilities

    Science.gov (United States)

    Ozoroski, Thomas A.; Nickol, Craig L.; Guynn, Mark D.

    2015-01-01

    There have been ongoing efforts in the Aeronautics Systems Analysis Branch at NASA Langley Research Center to develop a suite of integrated physics-based computational utilities suitable for modeling and analyzing extended-duration missions carried out using solar powered aircraft. From these efforts, SolFlyte has emerged as a state-of-the-art vehicle analysis and mission simulation tool capable of modeling both heavier-than-air (HTA) and lighter-than-air (LTA) vehicle concepts. This study compares solar powered airplane and airship station-keeping capability during a variety of high altitude missions, using SolFlyte as the primary analysis component. Three Unmanned Aerial Vehicle (UAV) concepts were designed for this study: an airplane (Operating Empty Weight (OEW) = 3285 kilograms, span = 127 meters, array area = 450 square meters), a small airship (OEW = 3790 kilograms, length = 115 meters, array area = 570 square meters), and a large airship (OEW = 6250 kilograms, length = 135 meters, array area = 1080 square meters). All the vehicles were sized for payload weight and power requirements of 454 kilograms and 5 kilowatts, respectively. Seven mission sites distributed throughout the United States were selected to provide a basis for assessing the vehicle energy budgets and site-persistent operational availability. Seasonal, 30-day duration missions were simulated at each of the sites during March, June, September, and December; one-year duration missions were simulated at three of the sites. Atmospheric conditions during the simulated missions were correlated to National Climatic Data Center (NCDC) historical data measurements at each mission site, at four flight levels. Unique features of the SolFlyte model are described, including methods for calculating recoverable and energy-optimal flight trajectories and the effects of shadows on solar energy collection. Results of this study indicate that: 1) the airplane concept attained longer periods of on

  8. Exploratory study of the effects of wing-leading-edge modifications on the stall/spin behavior of a light general aviation airplane

    Science.gov (United States)

    1979-01-01

    Configurations with full-span and segmented leading-edge flaps and full-span and segmented leading-edge droop were tested. Studies were conducted with wind-tunnel models, with an outdoor radio-controlled model, and with a full-scale airplane. Results show that wing-leading-edge modifications can produce large effects on stall/spin characteristics, particularly on spin resistance. One outboard wing-leading-edge modification tested significantly improved lateral stability at stall, spin resistance, and developed spin characteristics.

  9. Results obtained during accelerated transonic tests of the Bell XS-1 airplane in flights to a Mach number of 0.92

    Science.gov (United States)

    Drake, Hubert M; Mclaughlin, Milton D; Goodman, Harold R

    1948-01-01

    Results are presented of tests up to a Mach number of 0.92 at altitudes around 30,000 feet. The data obtained show that the airplane can be flown to this Mach number above 30,000 feet. Longitudinal trim changes have been experienced but the forces involved have been small. The elevator effectiveness decreased about one-half with increase of Mach number from 0.70 to 0.87. Buffeting has been experienced in level flight but it has been mild and the associated tail loads have been small. No aileron buzz or other flutter phenomena have been noted.

  10. Wind Tunnel Testing of a 120th Scale Large Civil Tilt-Rotor Model in Airplane and Helicopter Modes

    Science.gov (United States)

    Theodore, Colin R.; Willink, Gina C.; Russell, Carl R.; Amy, Alexander R.; Pete, Ashley E.

    2014-01-01

    In April 2012 and October 2013, NASA and the U.S. Army jointly conducted a wind tunnel test program examining two notional large tilt rotor designs: NASA's Large Civil Tilt Rotor and the Army's High Efficiency Tilt Rotor. The approximately 6%-scale airframe models (unpowered) were tested without rotors in the U.S. Army 7- by 10-foot wind tunnel at NASA Ames Research Center. Measurements of all six forces and moments acting on the airframe were taken using the wind tunnel scale system. In addition to force and moment measurements, flow visualization using tufts, infrared thermography and oil flow were used to identify flow trajectories, boundary layer transition and areas of flow separation. The purpose of this test was to collect data for the validation of computational fluid dynamics tools, for the development of flight dynamics simulation models, and to validate performance predictions made during conceptual design. This paper focuses on the results for the Large Civil Tilt Rotor model in an airplane mode configuration up to 200 knots of wind tunnel speed. Results are presented with the full airframe model with various wing tip and nacelle configurations, and for a wing-only case also with various wing tip and nacelle configurations. Key results show that the addition of a wing extension outboard of the nacelles produces a significant increase in the lift-to-drag ratio, and interestingly decreases the drag compared to the case where the wing extension is not present. The drag decrease is likely due to complex aerodynamic interactions between the nacelle and wing extension that results in a significant drag benefit.

  11. Mass and performance optimization of an airplane wing leading edge structure against bird strike using Taguchi-based grey relational analysis

    Directory of Open Access Journals (Sweden)

    Hassan Pahange

    2016-08-01

    Full Text Available Collisions between birds and aircraft are one of the most dangerous threats to flight safety. In this study, smoothed particles hydrodynamics (SPH method is used for simulating the bird strike to an airplane wing leading edge structure. In order to verify the model, first, experiment of bird strike to a flat aluminum plate is simulated, and then bird impact on an airplane wing leading edge structure is investigated. After that, considering dimensions of wing internal structural components like ribs, skin and spar as design variables, we try to minimize structural mass and wing skin deformation simultaneously. To do this, bird strike simulations to 18 different wing structures are made based on Taguchi’s L18 factorial design of experiment. Then grey relational analysis is used to minimize structural mass and wing skin deformation due to the bird strike. The analysis of variance (ANOVA is also applied and it is concluded that the most significant parameter for the performance of wing structure against impact is the skin thickness. Finally, a validation simulation is conducted under the optimal condition to show the improvement of performance of the wing structure.

  12. A methodology for airplane parameter estimation and confidence interval determination in nonlinear estimation problems. Ph.D. Thesis - George Washington Univ., Apr. 1985

    Science.gov (United States)

    Murphy, P. C.

    1986-01-01

    An algorithm for maximum likelihood (ML) estimation is developed with an efficient method for approximating the sensitivities. The ML algorithm relies on a new optimization method referred to as a modified Newton-Raphson with estimated sensitivities (MNRES). MNRES determines sensitivities by using slope information from local surface approximations of each output variable in parameter space. With the fitted surface, sensitivity information can be updated at each iteration with less computational effort than that required by either a finite-difference method or integration of the analytically determined sensitivity equations. MNRES eliminates the need to derive sensitivity equations for each new model, and thus provides flexibility to use model equations in any convenient format. A random search technique for determining the confidence limits of ML parameter estimates is applied to nonlinear estimation problems for airplanes. The confidence intervals obtained by the search are compared with Cramer-Rao (CR) bounds at the same confidence level. The degree of nonlinearity in the estimation problem is an important factor in the relationship between CR bounds and the error bounds determined by the search technique. Beale's measure of nonlinearity is developed in this study for airplane identification problems; it is used to empirically correct confidence levels and to predict the degree of agreement between CR bounds and search estimates.

  13. Mass and performance optimization of an airplane wing leading edge structure against bird strike using Taguchi-based grey relational analysis

    Institute of Scientific and Technical Information of China (English)

    Hassan Pahange; Mohammad Hossein Abolbashari

    2016-01-01

    Collisions between birds and aircraft are one of the most dangerous threats to flight safety. In this study, smoothed particles hydrodynamics (SPH) method is used for simulating the bird strike to an airplane wing leading edge structure. In order to verify the model, first, experiment of bird strike to a flat aluminum plate is simulated, and then bird impact on an airplane wing lead-ing edge structure is investigated. After that, considering dimensions of wing internal structural components like ribs, skin and spar as design variables, we try to minimize structural mass and wing skin deformation simultaneously. To do this, bird strike simulations to 18 different wing structures are made based on Taguchi’s L18 factorial design of experiment. Then grey relational analysis is used to minimize structural mass and wing skin deformation due to the bird strike. The analysis of variance (ANOVA) is also applied and it is concluded that the most significant parameter for the performance of wing structure against impact is the skin thickness. Finally, a validation simu-lation is conducted under the optimal condition to show the improvement of performance of the wing structure.

  14. The energy spectrum of cosmic-ray induced neutrons measured on an airplane over a wide range of altitude and latitude.

    Science.gov (United States)

    Goldhagen, P; Clem, J M; Wilson, J W

    2004-01-01

    Crews of high-altitude aircraft are exposed to radiation from galactic cosmic rays (GCRs). To help determine such exposures, the Atmospheric Ionizing Radiation Project, an international collaboration of 15 laboratories, made simultaneous radiation measurements with 14 instruments on a NASA ER-2 high-altitude airplane. The primary instrument was a sensitive extended-energy multisphere neutron spectrometer. Its detector responses were calculated for energies up to 100 GeV using the radiation transport code MCNPX 2.5.d with improved nuclear models and including the effects of the airplane structure. New calculations of GCR-induced particle spectra in the atmosphere were used to correct for spectrometer counts produced by protons, pions and light nuclear ions. Neutron spectra were unfolded from the corrected measured count rates using the deconvolution code MAXED 3.1. The results for the measured cosmic-ray neutron spectrum (thermal to >10 GeV), total neutron fluence rate, and neutron dose equivalent and effective dose rates, and their dependence on altitude and geomagnetic cut-off agree well with results from recent calculations of GCR-induced neutron spectra.

  15. Wind-Tunnel Investigation of Effects of Unsymmetrical Horizontal-Tail Arrangements on Power-on Static Longitudinal Stability of a Single-Engine Airplane Model

    Science.gov (United States)

    Purser, Paul E.; Spear, Margaret F.

    1947-01-01

    A wind-tunnel investigation has been made to determine the effects of unsymmetrical horizontal-tail arrangements on the power-on static longitudinal stability of a single-engine single-rotation airplane model. Although the tests and analyses showed that extreme asymmetry in the horizontal tail indicated a reduction in power effects on longitudinal stability for single-engine single-rotation airplanes, the particular "practical" arrangement tested did not show marked improvement. Differences in average downwash between the normal tail arrangement and various other tail arrangements estimated from computed values of propeller-slipstream rotation agreed with values estimated from pitching-moment test data for the flaps-up condition (low thrust and torque) and disagreed for the flaps-down condition (high thrust and torque). This disagreement indicated the necessity for continued research to determine the characteristics of the slip-stream behind various propeller-fuselage-wing combinations. Out-of-trim lateral forces and moments of the unsymmetrical tail arrangements that were best from consideration of longitudinal stability were no greater than those of the normal tail arrangement.

  16. 民用飞机结构的全尺寸疲劳试验%Full-Scale Fatigue Test of Commercial Airplane Structure

    Institute of Scientific and Technical Information of China (English)

    斯而健

    2012-01-01

    Full-Scale fatigue test must be conducted for new type certificate of commercial airplane. It would also provide the verification of fatigue and damage tolerance design criteria and evaluation technology. Based on the new airworthiness regulation, this paper gives an overview on the full-scale fatigue test of commercial airplane structure. The 777 full-scale fatigue test is used in this paper as an example to describe various technical issues on the test methods, especially the test loading spectrum.%进行全尺寸疲劳试验是新型民用飞机取得型号合格证的必要前提,也是对疲劳和损伤容限设计准则和评定技术的考核验证。从适航条例的最新要求出发,对民机结构的全尺寸疲劳试验作综述,并以波音777飞机的全尺寸疲劳试验为例,对试验相关的各项技术要点,特别是试验载荷谱予以阐述。

  17. 军用运输机集装运输托盘需求分析%Analysis of General Requirement of Military Transport Airplane Container Transport Pallets

    Institute of Scientific and Technical Information of China (English)

    张家应; 刘子明

    2015-01-01

    对军用运输机集装运输托盘研制的业务功能、保障环境、适用机型和技术规范标准等方面的需求进行初步分析,提出了军用运输机集装运输托盘研制需求的详细内容。随着托盘设计研究的不断深入,有关需求的内容与标准要求还应随之不断补充调整。%In order to provide some theoretical references for the development of military transport airplane container transport pallet, the requirements on every aspect of the development military transport airplane container transport pallet, including its operational functions,support environment,suitable model,tactical and technical capabilities performance indexes, specifications,were analyzed and discussed in this paper.

  18. Softver za proračun uzdužne statičke stabilnosti i upravljivosti aviona za osnovnu obuku pilota / Software for calculation of an axial static stability and management of airplanes for basic pilot training

    Directory of Open Access Journals (Sweden)

    Dalibor Petrović

    2006-07-01

    Full Text Available U ovom radu opisan je softver za proračun uzdužne statičke stabilnosti i upravljivosti aviona za osnovnu obuku pilota. Softver je urađen sa numerom da konstruktorima omogući brzo i lako dobijanje potrebnih rezultata vezanih za stabilnost i upravljivost kod preliminarnih proračuna vezanih za ovu vrstu aviona. Program je urađen na osnovu analize velikog broja aviona iz ove klase, a njegova tačnost je testirana na avionu "Lasta". Rezultati koji su dobijeni ovim softverom bili su više od zadovoljavajućih, s obzirom na to da se radi o programu koji bi se koristio za preliminarni proračun. / This document introduced software for calculation of an axial static stability and management of airplanes for basic pilot training. The purpose of this software is to provide a quicker and an easier way of getting results regarding preliminary calculation of stability and management for these types of airplanes. The program is based upon analysis of data gathered from a large number of tested airplanes of this class. The accuracy of the program has been tested on the airplane type 'Lasta' and results were more than satisfying, especially regarding the fact that the program is meant to be used for preliminary calculation.

  19. 无人机低空遥感的航路设计%The Designo f Flight Course for the Rem ote Sensing of Unmanned Airplane on Low-Lying Air

    Institute of Scientific and Technical Information of China (English)

    高云飞; 苏玉瑞; 王晓南; 姬洪亮

    2014-01-01

    The design of flight course is very strict because the photogrammetry for unmanned airplane is unstable and can miss meas -urement and repeat measurement .This paper analyze the pivotal technique for the design of flight course of unmanned airplane , pro-vide the formula of calculating , establish the base of design of flight course of unmanned airplane and improve the quality of photo -grammetry for unmanned airplane .%由于无人机航摄稳定性较差,为了防止漏测、叠测等现象,对航路设计要求相当严格。本文针对航路设计中的关键技术问题进行认真分析,并给出相应的计算公式,为今后无人机航摄飞机航路设计奠定基础,从而提高航摄质量。

  20. Experimental research on surface temperature field of airplane under solar radiation%太阳辐射作用下的飞机表面温场分布实验研究

    Institute of Scientific and Technical Information of China (English)

    张春华; 赵元; 喻煌超; 陈循

    2012-01-01

    This paper presents an experimental method to measure surface temperature field distribution of airplane under solar radiation by airplane downsizing model, and suggests a method to realize analogue display of 3 dimensions for temperature field distribution by finite element method. This method may avoid the influence of the uncontrollable intensity of natural solar radiation and the variable ambient temperature under field measuring condition, and provide an efficient method to validate the theoretical model of surface temperature field distribution of airplane under solar radiation and to measure it by experiment. It will be beneficial to the research of infrared characteristics and calendar life for airplane.%提出一种通过缩比模型测试飞机在太阳辐射作用下的表面温度场分布,进而通过有限元方法实现太阳辐射温场的三维模拟显示的实验方法.该方法避免了外场测试条件中自然日光辐射强度不可控和环境温度变化的影响,为飞机在太阳辐射作用下的表面温场理论模型验证和实测提供一种有效的方法,对飞机红外特性、日历寿命等研究具有借鉴意义.

  1. Study of Airplane's Paint Removal Test by Ultrahigh Pressure Rotated Jets%超高压旋转射流飞机除漆试验研究

    Institute of Scientific and Technical Information of China (English)

    鲁飞; 薛胜雄; 任启乐; 陈正文; 苏吉鑫; 韩彩红; 庞雷

    2013-01-01

    The paint removal and recoating are the very important process in airplane maintenance .The traditional technology is to use the chemical way corroding the paint with paint remover .For changing the defects , corrosion&pollution&manual working , of the traditional technology , the physical process which removes the paint of airplane with 200MPa/250kW high pressure rotary water jet though the plane cleaner installed on the six axis robot is studied .The paint layer of airplane is very thin and close .The contradiction of water jet paint removal is to remove the paint layer evenly and not damage the surface of airplane .In order to solve the contradiction ,the best working condition must be reached through tests .The paint removal efficiency with ultra-high pressure and move speed of not damaged to the surface .The move speed of this test is about 2m/min,and the paint removal efficiency is 30~40 m2/h,and the paint removal active area is 85%~90%.No-repeat and no-omit are the based requests of the robot program . The physical pant removal technology will be applied in airplane maintenance , and will face the safety detection of application permission.%飞机的除漆、再涂装,是其大修的重要环节。传统工艺都是采用化学工艺:即用脱漆剂腐蚀除漆。为了改变传统化学工艺的腐蚀、污染和人工作业的缺点,笔者研究了物理工艺,即采用200MPa、250kW的超高压旋转水射流,借助六轴机器人配置平面清洗器对飞机大表面和小曲面除漆作业。飞机的涂装层极其薄而致密,采用水射流除漆面对的矛盾是:均匀除去漆层而不损伤飞机铝合金表面。要做到这一点就必须试验得出最优化工况,即超高压参数下的除漆效率和不损伤表面的横移速度。本项试验横移速度约2m/min,除漆效率30~40m2/h,除漆有效面积达到85%~90%。执行机构的不重复、不遗漏是机器人示教编程的基本要求。物理除漆

  2. Calculational Method of Sandstones Rolled up by Airplane Tyres%飞机轮胎所造成的砂石飞溅数目的计算方法

    Institute of Scientific and Technical Information of China (English)

    张岳青; 徐绯; 闫蕊; 吕军

    2013-01-01

    飞机在起飞和降落时,由于轮胎的影响所造成的跑道上外来物(FOD)飞溅是个复杂的过程.以砂石为例,介绍了几种典型的砂石飞溅的类型,提供了飞机所能遭遇到的砂石数目和造成飞机结构损伤的概率计算公式.以某型客机为例,根据民用机场的FOD调研报告和国内民用机场跑道的类型,分析了在临界能量下飞机所能遭遇到并能对飞机造成冲击破坏的可能性,为飞机结构抗冲击设计提供一定的依据.%When an airplane takes off and lands, the foreign objectd damage (FOD) splash made by its tyres on the airport runway is a very complex process. Taking sandstone as an example, a number of classical types of sandstone splash are introduced, and a few formulas are given which calculate the number of the sandstones that the airplane meet and the probability of the airplane structure damage. Then a passenger plane made in China is taken for example. The paper analyzes the damage probability of the airplane structure impacted by sandstones with critical energy according to the FOD report of the civil airport and the type of the airport runway. This study can provide useful reference for airplane structure anti-impact design.

  3. Modeling and simulation of solar-powered airplane for the conceptual design%太阳能飞机方案设计阶段建模与仿真

    Institute of Scientific and Technical Information of China (English)

    赵凯; 祝小平; 周洲

    2011-01-01

    This paper presents a simulation model of solar-powered airplane for the conceptual design. Components of the model include energy flow, solar energy collection, secondary battery, and airplane motion and energy management. In the mean time, two concepts of solar-powered airplane were compared respectively with fixed solar planes and rotational solar planes on their efficiency of solar energy capture and airplane endurance. It was seen that the second concept showed obvious advantage on the efficiency of solar energy capture and its endurance was longer during the days with scarce solar radiation. Those discussed in the paper present that the model could be used for verifying and analyzing the concepts of solar-powered airplane.%建立了太阳能飞机方案设计阶段的仿真模型,包括能量流动、太阳能采集、蓄电池、飞机运动及能量管理等部分.通过仿真比较了太阳能电池固定安装和可转动安装两种飞机方案的太阳能采集效率和续航性能.仿真结果表明,方案2的设计采集效率优势明显,在光照匮乏时飞机飞行时间较长.该模型可用于太阳能飞机方案设计阶段的验证分析,为方案的选择和改进提供依据.

  4. Flight Test Technology Research on Crosswind Takeoff and Landing of Civil Airplane%民用飞机大侧风起降试飞关键技术研究

    Institute of Scientific and Technical Information of China (English)

    张海妮; 程伟豪; 张强

    2015-01-01

    In China, the critical lfight test technology of crosswind takeoff and landing was ifrst applied to civil airplane according to CCAR-25 when the interrelated lfight test of a civil airplane was carried out. Based on the test, this paper researched and validated a method of evaluating an airplane’s capability of resistance to crosswind, brought out a method of converting an airplane’s capability of resistance to crosswind within the whole weight range of the airplane, and expatiated the critical lfight test technology of the crosswind takeoff and landing lfight test of civil airplane. Those can provide an important reference for other transport category airplane.%某型民用飞机的大侧风起降试飞是我国首次严格按照CCAR25部的要求将相关试飞技术完整运用于民用飞机。结合该飞机的大侧风起降试飞,对飞机理论抗侧风量的预测方法进行了研究和验证,提出了将飞机的理论抗侧风量换算至全重量范围内的方法,并详细阐述了民用飞机大侧风起降试飞过程中的关键试飞技术,可为其他运输类飞机的大侧风起降试飞提供重要的参考。

  5. Research on Transport Category Airplane Flight Manual and Effectivity Management%运输类飞机飞行手册及其有效性管理研究

    Institute of Scientific and Technical Information of China (English)

    王媛媛

    2015-01-01

    Airplane Flight Manual contains information considered necessary for safely operating the airplane, and is the document essential for the type certificate application.Firstly,This paper introduces the contents and history of airplane flight manual(AFM), and airworthiness regulations which is the development of AFM based on;Secondly,This paper provides definition and presentation about airplane flight manual effectivity according to related specification;Then, analyzing the method for mature type AFM effectivity management. Finally,this paper give three advice about airplane flight manual effectivity management, which is the minimum data unit of effectivity statement,the form of performance data and effectivity management method of appendix and supplement.%飞机飞行手册包含飞机安全运行所必需的资料,是申请型号合格证必须的资料。该文首先介绍了飞机飞行手册内容以及变化历程,并对飞机飞行手册编制依据的适航规章进行概述;其次,依据相关标准给出飞机飞行手册有效性概念和表达方式;然后,分析成熟机型飞机飞行手册有效性管理的方法;最后,在综合上述分析的基础上,从有效性声明的最小数据单元、性能数据的编写形式以及附录与补充有效性管理方式三个方面,对飞机飞行手册有效性管理提出建议。

  6. 一种获取飞机RAT带载能力的试飞方法%A Flight Test Method of Determining Airplane RAT's Load Capacity

    Institute of Scientific and Technical Information of China (English)

    刘超强; 马明

    2014-01-01

    The load capacity of airplane's ram air turbine ( RAT) depends not only on airplane airspeed, but al-so on the flight attitude. It is difficult to calculate by using theoretical equations. A flight test method is designed to determine the RAT's real-time load capacity by just analyzing some flight test data obtained. This method plans two test subjects:RAT load capacity test at level flight and RAT load capacity test at sideslip. The former test can obtain the variation of RAT airspeed with airplane airspeed for different weights, and the latter can bring us the re-lationship for different sideslip angles. The results of the two tests show that the RAT airspeed at any weight and flight attitude can be determined and further know its load capacity.%飞机RAT的实际带载能力不仅取决于飞机空度,而且受到飞行姿态的制约,很难用理论公式准确推算。提出了一种飞行试验方法,分析特定的试飞测试数据,可获得飞机RAT的实际带载能力。试验包括RAT平飞带载和RAT侧滑带载两部分试飞。通过RAT平飞带载试验,得到不同重量下的RAT空速与飞机空速的关系曲线;通过RAT侧滑带载试验,可得到不同侧滑角飞行下RAT空速与飞机空速的关系曲线。结合试验结果,可以确定飞机在任意重量和飞行姿态下的RAT空速,进而获知RAT实际带载能力。

  7. Wind-tunnel investigation of the effect of power and flaps on the static lateral characteristics of a single-engine low-wing airplane model

    Science.gov (United States)

    Tamburello, Vito; Weil, Joseph

    1947-01-01

    Tests were made in the Langley 7- by 10-foot tunnel to determine the lateral-stability characteristics with and without power of a model of a typical low-wing single-engine airplane with flaps neutral, with a full-span single slotted flap, and with a full-span double slotted flap. Power decreased the dihedral effect regardless of flap condition, and the double-slotted flap configuration showed the most marked decrease. The usual effect of power in increasing the directional stability was also shown. Deflection of the single slotted flap produced negative dihedral effect, but increased the directional stability. The effects of deflecting the double slotted flap were erratic and marked changes in both effective dihedral and directional stability occurred. The addition of the tail surfaces always contributed directional stability and generally produced positive dihedral effect.

  8. Design and testing of new center inlet and S-duct for B-727 airplane with refanned JT8D engines

    Science.gov (United States)

    Ting, C. T.; Kaldschmidt, G.; Syltebo, B. E.

    1975-01-01

    The work described in this paper was part of the NASA refan program. The airflow requirement of the refanned JT8D (-100 series) engine increased about 50% above that of the basic JT8D. This required a redesign of the center inlet and S-duct of the Boeing 727 airplane. The paper describes the design constraints for the S-duct and the analytic method used to define the lines of the new duct. Model tests that were conducted at static, angle-of-attack, and crosswind conditions are described with a variety of flow control devices. Test results showed that the new inlet and S-duct have a pressure recovery comparable to that of the existing inlet. By employing corotating vortex generators, less flow distortion was obtained for the core region than the existing duct has with its counter rotating vortex generators.

  9. Analysis on ATC Problems of Boeing 737NG Airplane%波音737NG飞机ATC FAIL故障浅析

    Institute of Scientific and Technical Information of China (English)

    罗康

    2015-01-01

    The occurrence frequency of ATC problems of Boeing 737NG Airplane is high in the running, as it cooperated with TCAS, it has great obstacles of the airplane’s normal operation and flight delay. This paper will analyze the fail of ACT.%波音737NG飞机在运行中经常会出现ATC FAIL故障,由于该系统牵涉到飞机的防撞系统,对飞机的正常运行产生很大的影响,引起航班延误,本文对该故障现象进行浅析。

  10. A Method for Parameter Estimation of Civil Airplane in Interference Localization Background%地面干扰源定位问题中飞机参数估计新方法

    Institute of Scientific and Technical Information of China (English)

    李丽

    2014-01-01

    民航地空通信受到无线电干扰会严重危机民航飞机的正常飞行。发射信号经过飞机反射后的回波信号中包含了与目标有关的多普勒频率信息,通过对多普勒频率信息检测便可以实现对目标的定位。但是怎样获得飞机的实时状态信息成为另一个研究的重点。本文在地面干扰源定位的研究背景下,提出了一种估计飞机运动状态信息的新方法。首先提出一个新的回波信号模型。并采用二维MUSIC算法实现了目标的二维角的联合估计。进一步,根据阵列模型中的几何关系,实现了对目标的运动状态及空间位置估计,从而实现了对飞机状态信息的准确的实时估计,为后续地面干扰源定位打下良好的基础。仿真实验验证了算法的有效性。%The ground-air communication of civil aviation is interfered by radios, which has seriously endangered the normal flight of civil airplanes. Echo signal, reflected from the plane, in comparison with the transmitted waveform, contains the Doppler frequency information associated with the target. Target localization is realized by utilizing Doppler frequency. How to obtain information of civil airplane has become research focus. This paper proposes an airplane information estimation algorithm based on the study of the problem of interference localization. Firstly, a novel signal model to accurately estimate parameters of the airplane is proposed. A method of Doppler estimation based on peak searching is proposed, and the 2D-MUSIC algorithm is applied to estimate the azimuth angle and elevation angle. Furthermore, the velocity and location of the airplane are estimated by employing array geometry. As a result, the airplane localization is achieved in bistatic radar, laying the foundations for interference localization. The correctness and effectiveness of the proposed method are verified with the computer simulation.

  11. 飞机液压铁鸟试验台测试系统研究%Research of Measurement System for Airplane Iron Bird Hydraulic Test-bed

    Institute of Scientific and Technical Information of China (English)

    刘永智; 安思危; 王纪森

    2015-01-01

    Airplane iron bird hydraulic test⁃bed is an important device of aircraft ground test, the accuracy of the testing system directly affects the safety of the whole flight process and landing process of aircraft. But it has many test loops, the equipments are scat⁃tered, test process is difficult to control. According to these, the literature about iron bird test aircraft hydraulic system solutions at home and abroad were reviewed, their advantages and disadvantages were analyzed. Combining with a certain type of measurement sys⁃tem for unmanned airplane iron bird hydraulic test⁃bed requirements, the suitable scheme were chosen, and the future trend of the test system was discussed.%飞机液压铁鸟试验台是飞机地面试验的重要装置,其测试系统的精度直接影响到飞机的整个飞行过程和降落过程的安全性。然而其试验回路多、设备分散、试验过程难以控制管理。针对此,综述国内外文献飞机液压铁鸟试验测试系统解决方案,分析其优缺点,结合某型无人机液压铁鸟试验台测试系统测试要求选择适合的方案,并对未来测试系统的发展趋势作出展望。

  12. 民用飞机鸟撞研究现状%Investigation of the Present Status of Research on Bird Impacting on Commercial Airplanes

    Institute of Scientific and Technical Information of China (English)

    李玉龙; 石霄鹏

    2012-01-01

    Bird impact accidents pose one of the biggest risks to civil aviation, which consequently become one of the focuses of research. An investigation of the status of bird impacting on commercial airplanes is presented in this paper. The losses caused by bird impact accidents in recent years are enumerated and the regulations about bird impacting on commercial airplanes in different countries are reviewed. The three aspects of theoretical investigation,numerical simulation and experimental study for bird impact are introduced in detail and a number of designs of aeronautical structures against bird impact accidents in recent years are presented. Finally, prospects in future bird impact research are proposed.%鸟撞事故是近年来对民用航空威胁较大的事故之一,民用飞机鸟撞研究已经渐渐成为各国学者研究的新热点.本文详细介绍了民用飞机鸟撞研究的现状.总结了近年来鸟撞事故所造成的损失,列举了一些航空大国的航空管理部门针对鸟撞作出的适航管理规定.对于鸟撞问题的研究,从鸟撞过程的理论分析研究、数值模拟研究和试验研究3个方面进行了综述.对于近些年国内外的飞机抗鸟撞设计,主要包括新材料的运用以及新的结构形式的运用,进行了详细介绍.最后,对未来民用飞机抗鸟撞研究的发展作了展望.

  13. 客机镜面翼尖零件拉深成形工艺%Deep drawing process for airplane wingtip with mirror surface

    Institute of Scientific and Technical Information of China (English)

    宋波; 于忠奇; 桑阳

    2012-01-01

    The deep drawing process for the airplane wingtip of aluminum alloy 2219-O sheet with mirror surface was studied, based on numerical simulation technology and experimental method in this paper. The numerical simulation indicated that the ap-propriate process parameters could lead to the relatively small strain distribution, which was helpful to prevent the surface defects, such as coarse grains. Test results showed that the surface defects such as scratch, ridge can be restrained by means of rubber membrane and normal compressive stress method. It proved that deep drawing method could manufacture the aluminum alloy 2219-0 airplane wingtip part with good mirror surface.%利用数值模拟技术和试验方法,对铝合金板2219-O镜面翼尖零件的拉深工艺进行研究.翼尖零件拉深性能的数值仿真研究表明,通过合理设定工艺参数,可以获得较小的均匀应变分布,有利于抑制粗晶等表面缺陷的产生.表面质量试验显示,通过在铝合金板2219-O表面覆上一层橡皮膜,并借助模具的厚向压应力,可以消除翼尖零件表面擦伤、端部凸起等表面质量缺陷.

  14. Review about Bird Strike and Substantiation for Transport Category Airplane%运输类飞机鸟撞及符合性验证综述

    Institute of Scientific and Technical Information of China (English)

    张柱国; 郝一鸣

    2013-01-01

    Regarding to the bird strike which is an important threat to the safety of civil aviation transportation, this paper summaried the bird strike related airworthiness requirements for transport category airplane, introduced the history of these requirements, and explained the origin and development of the significant regulatory difference about the bird weight between the FAA and EASA. Based on the bird strike certiifcation guidance by foreign airworthiness authorities, the determination of bird strike areas/zones and the means of compliance were summarized and a roadmap of bird strike substantiation was proposed. In the last, the development of bird strike related requirements and the means of compliance were expected, and suggestion about the substantiation of domestic C919 airplane was given.%针对民航运输安全的重要威胁--鸟撞,简析了运输类飞机型号合格审定中鸟撞相关的适航要求,概述了这些要求的演变历史,对国外适航当局(FAA和EASA)关于鸟重量方面重大规章差异的缘由进行了解释。在综合考虑国外适航当局进行鸟撞审定指导的基础上,重点归纳了鸟撞符合性验证中鸟撞部位的确定及符合性验证思路,制定了鸟撞验证路线图。最后,对鸟撞适航要求和符合性验证方法的发展趋势进行了展望,为C919大型客机鸟撞的符合性验证提出了建议。

  15. Experiments with airplane brakes

    Science.gov (United States)

    Michael, Franz

    1931-01-01

    This report begins by examining the forces on the brake shoes. For the determination of the load distribution over the shoes it was assumed that the brake linings follow Hooke's law, are neatly fitted and bedded in by wear. The assumption of Hooke's law, that is, the proportionality between compression of the lining and the absorption of force, is fulfilled to a certain extent for the loading, as becomes apparent from the load tests described further on. But there is a material discrepancy at unloading. From the load distribution we merely defined the position of the normal force resultant, while for the rest, the effect of the distribution was disregarded in the comparison of the different shoe dispositions.

  16. Stability and Control Characteristics of a Complete Airplane Model Having a Wing with Quarter-chord Line Swept Back 40 Degrees, Aspect Ratio 2.50, and Taper Ratio 0.42

    Science.gov (United States)

    Schulderfrei, Marvin; Comisarow, Paul; Goodson, Kenneth W

    1951-01-01

    An investigation has been made of a complete airplane model having a wing with the quarter-chord line swept back 40 degrees, aspect ratio 2.50, and taper ratio 0.42 to determine its low-speed stability and control characteristics. The longitudinal stability investigation included stabilizer and tail-off tests with different wing dihedral angles (Gamma = 0 degrees and Gamma = -10 degrees) over an angle-of-attack range for the cruising and landing configurations and tests. with a high horizontal-tail location (Gamma = -10 degrees) for the cruising configuration. Tests were made of the wing alone and to determine the effect of wing end plates in pitch. Lateral stability characteristics were determined for the airplane with different geometric wing dihedrals, with end plates, and with several dorsal modifications. Tests were made with ailerons and spoilers to determine control characteristics.

  17. Wind-tunnel/flight correlation study of aerodynamic characteristics of a large flexible supersonic cruise airplane (XB-701) 2: Extrapolation of wind-tunnel data to full-scale conditions

    Science.gov (United States)

    Peterson, J. B., Jr.; Mann, M. J.; Sorrells, R. B., III; Sawyer, W. C.; Fuller, D. E.

    1980-01-01

    The results of calculations necessary to extrapolate performance data on an XB-70-1 wind tunnel model to full scale at Mach numbers from 0.76 to 2.53 are presented. The extrapolation was part of a joint program to evaluate performance prediction techniques for large flexible supersonic airplanes similar to a supersonic transport. The extrapolation procedure included: interpolation of the wind tunnel data at the specific conditions of the flight test points; determination of the drag increments to be applied to the wind tunnel data, such as spillage drag, boundary layer trip drag, and skin friction increments; and estimates of the drag items not represented on the wind tunnel model, such as bypass doors, roughness, protuberances, and leakage drag. In addition, estimates of the effects of flexibility of the airplane were determined.

  18. Aerodynamic analysis on fly-at-zero of big airplane in field environment%野战环境下大型飞机超低空气动特性分析

    Institute of Scientific and Technical Information of China (English)

    陈杰; 马存宝; 许和勇

    2013-01-01

    According to the fly-at-zero of big airplane on unconventional condition such as field environment,the influences of ground effect on airplane' s aerodynamic parameters with forward or asymmetrical lateral obstacles on the ground were presented by CFD approach,including the longitudinal stability and lateral wing rock.The research results show that the uncertain obstacles on the ground will deteriorate the stability of big plane,and then cause the nodding or wing rock,this flight process will induce the airplane to touch the ground.In the end,the article presents the research idea for closed loop control approach for large airplane with conventional configuration in terms of modem flight control theory.%针对野战环境下的大型飞机超低空飞行,采用CFD方法对地面存在前向或横向不对称障碍物时地面效应对气动参数的影响进行了数值分析,包括纵向稳定性和侧向摇晃等问题.研究结果表明,野战等非常规飞行条件下,地面不确定障碍物会造成大型飞机稳定性变差,严重时可能出现纵向点头和横侧向摇晃现象,容易导致触地危险.最后,从现代飞行控制理论角度提出了对常规布局大型飞机进行闭环控制的研究思路.

  19. 基于多指标综合评判法的空中加油机作战效能评估%Operational Effectiveness Assessment of Tanker Airplane Based on Multi-index Comprehensive Evaluation Method

    Institute of Scientific and Technical Information of China (English)

    潘科; 潘宣宏; 董文洪; 李刚强; 何杨

    2015-01-01

    According to the problem of tanker airplane operational effectiveness evaluation,in this paper, the evaluation in⁃dex system of the operational effectiveness of the tanker airplane was constructed,and the operational effectiveness index of tanker airplane was digging. The importance of index attributes was obtained by using information entropy concept first⁃ly. Then,the index messages were normalized, and the multi-index comprehensive evaluation model of refueling aircraft operational effectiveness was established by TOPSIS. Finally, through case study, this method was proved to be feasible for analyzing the operational effectiveness of several current typical tanker airplane, and the result was satisfactory.%针对空中加油机作战效能评估问题,构建了空中加油机作战效能评估指标体系,并对空中加油机的作战效能指标数据进行挖掘,利用信息熵概念求得各指标属性的重要度,并归一化处理为各效能指标的权重系数,克服了传统权重系数确定方法的主观性;然后,建立了基于理性解法的空中加油机作战效能多指标综合评价模型;最后,通过实例,对几种现役典型的空中加油机作战效能进行了评估,并得到了计算结果,同时验证了该模型的有效性。

  20. 运输类飞机燃油系统点火源防护相关适航限制研究%Airworthiness Limitation Study of Fuel System ’ s Ignition Source Prevention for Transport Category Airplane

    Institute of Scientific and Technical Information of China (English)

    毛文懿; 李涛; 贾洪

    2016-01-01

    燃油箱爆炸对航空安全构成持续不断的严重威胁。通过对运输类飞机燃油系统点火源防护的适航限制相关条款要求、咨询通告的分析、研究,梳理了燃油系统点火源防护相关适航限制的制定流程、考虑;并对典型机型的燃油系统点火源防护相关适航限制进行了分析。可为运输类飞机燃油系统点火源防护相关适航限制的制定提供参考。%Fuel tank explosions have been a constant serious threat with aviation safety. Based on the analysis and study of the requirements of regulation and advisory circular which are about the airworthiness limitation for trans-port category airplane fuel system’ s ignition source prevention, this paper has given the flow chart on how to estab-lish the airworthiness limitation. The paper also analyzes the airworthiness limitation for an typical transport airplane fuel system’ s ignition source prevention. The research can provide guidance for establishing the airworthiness limi-tation for transport category airplane fuel system’ s ignition source prevention.