Dryden Technical Report Server
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- SIMULATOR INVESTIGATION OF THE CONTROL REQUIREMENTS OF A TYPICAL HYPERSONIC GLIDER , Technical Memorandum
Authors: L. W. Taylor, Jr., J. L. Samuels and J. W. Smith
Report Number: NASA-TM-X-635
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The handling qualities of a typical hypersonic glider were investigated with a flight simulator at Mach numbers of 0.26, 1.0, 3.5, 8, and 20 over an angle-of-attack range of 0• to 50•. Inasmuch as flight conditions influencing the control of the glider can be expected to change relatively slowly, a five-degree-of-freedom mechanization was used. Pilots assessed the controllability of the glider without augmentation with fixed gain dampers, and with on adaptive control system. The investigation was limited to aerodynamic control.
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Report Date: March 1962
No. Pages: 66
Keywords: Angle of attack; Damping; Flight control; Flight simulators; Hypersonic gliders.
- AERODYNAMIC-DERIVATIVE CHARACTERISTICS OF THE X-15 RESEARCH AIRPLANE AS DETERMINED FROM FLIGHT TESTS FOR MACH NUMBERS FROM 0.6 TO 3.4 , Technical Note
Authors: R. B. Yancey, H. A. Rediess and G. H. Robinson
Report Number: NASA-TN-D-1060
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Lateral, directional, and longitudinal stability and control derivatives are determined from flight tests of the X-15 airplane with the low-power LR11 rocket engine. Approximate relationships are developed for determining the derivatives C sub n sub Beta, C sub 1 sub Beta, and (C sub n sub r - C sub n sub derivative of Beta) and for isolating the effects of stability augmentation. Wind-tunnel predictions are compared with the flight-determined derivatives.
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Subject Category: 15
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Report Date: January 1962
No. Pages: 68
Keywords: Aircraft control; Approximation; Flight tests; Stability; Subsonic speed; X-15 aircraft.
- PRELIMINARY PERFORMANCE ANALYSIS OF AIR LAUNCHING MANNED ORBITAL VEHICLES , Technical Memorandum
Authors: D. R. Bellman and H. P. Washington
Report Number: NASA-TM-X-636
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A preliminary performance analysis was made to determine the capability of large subsonic and supersonic bombers for air launching manned hypersonic and satellite vehicles. The bombers considered now exist or are being developed in the United States. Four booster configurations were used in the calculations, with a winged vehicle of the Dyna-Soar type as the payload. Comparisons were made on the basis of vacuum specific impulse, burnout velocity, ratio of payload weight to launch-package gross weight, and structural weight.
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Report Date: February 1962
No. Pages: 38
Keywords: Air launching; Bomber aircraft; Hypersonic vehicles; Manned spacecraft.
- STRUCTURAL HEATING EXPERIENCES ON THE X-15 AIRPLANES , Technical Memorandum
Authors: Eldon E. Kordes, Robert D. Reed and Alpha L. Dawdy
Report Number: NASA-TM-X-711
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A survey of maximum structural temperatures measured on the X-15 airplane during speed flights up to a Mach number of 6 is presented. Structural problems caused by local hot spots and discontinuities are described. Structural modifications in the affected areas to eliminate the problems are discussed.
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Report Date: March 1962
No. Pages: 18
Keywords: Heating; Hypersonic speed; Supersonic speed; X-15 aircraft.
- STABILITY AND CONTROL DERIVATIVE CHARACTERISTICS OF THE X-15 AIRPLANE , Technical Memorandum
Authors: Harold J. Walker and Chester H. Wolowicz
Report Number: NASA-TM-X-714
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The flight-determined derivative characteristics are compared with the predictions from wind-tunnel tests and theory for Mach numbers extending to 5.5 and angles of attack up to 17 degrees. With few exceptions, the predictions were found generally to be in good agreement with the flight data. Areas of deficient stability and control are briefly discussed.
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Report Date: March 1962
No. Pages: 31
Keywords: Derivation; In-flight monitoring; Measuring instruments; Stability; X-15 aircraft.
- X-15 AIRPLANE STABILITY AUGMENTATION SYSTEM , Technical Note
Authors: Lawrence W. Taylor, Jr. and G. B. Merrick
Report Number: NASA-TN-D-1157
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The basic damper system currently installed in the airplane is described. Some of the problems encountered during the development and flight testing of the system are discussed, and the reliability of the system is reviewed briefly.
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Report Date: March 1962
No. Pages: 14
Keywords: Dampers; Stability; Stability augmentation; X-15 aircraft.
- AERODYNAMIC FORCES ON COMPONENTS OF THE X-15 AIRPLANE , Technical Memorandum
Authors: Earl R. Keener and Chris Pembo
Report Number: NASA-TM-X-712
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Aerodynamic force data on the components of the X-15 airplane have been obtained by both pressure and strain-gage measurements in flights covering a Mach number range up to 6.04, altitudes up to about 217,000 feet, and angles of attack up to 15 degrees. Comparison of the flight data with wind-tunnel data shows generally good agreement for the flight conditions covered.
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Report Date: March 1962
No. Pages: 12
Keywords: Aerodynamic forces; Strain gages; X-15 aircraft.
- LANDING LOADS AND DYNAMICS OF THE X-15 AIRPLANE , Technical Memorandum
Authors: James M. McKay and Eldon E. Kordes
Report Number: NASA-TM-X-639
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The loads, accelerations, and displacement of the X-15 airplane and landing-gear system measured during landing impact are discussed. The measured qualities are related to the initial touchdown conditions and are compared with data from a theoretical analysis to determine the effects of variations in such parameters as elevator position, skid coefficient of friction, main-gear location, and initial touchdown conditions beyond the range of the experimental data.
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Subject Category: 05
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Report Date: March 1962
No. Pages: 17
Keywords: Acceleration; Displacement; Impact; Landing; Landing gear.
- MISSION PLANNING AND OPERATIONAL PROCEDURES FOR THE X-15 AIRPLANE , Technical Note
Authors: Robert G. Hoey and Richard E. Day
Report Number: NASA-TN-D-1159
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Mission-planning methods and techniques used for the X-15 airplane envelope-expansion flight-test program are discussed. Use of the six-degree-of-freedom, ground-based simulator is indicated for prediction of performance, stability and controllability; development of piloting techniques and pilot training; evaluation of, and practice for, all possible emergency conditions; and energy management development. Other pilot-training devices and the role of the ground-monitoring station are also described. Predicted trajectory data and actual flight results are compared. The initial reasons and the final justifications for conducting the X-15 envelope expansion by performance increment are presented.
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Report Date: March 1962
No. Pages: 18
Keywords: Flight tests; Mission planning; Operational problems; Reliability; Trajectories; X-15 aircraft.
- COMPARISON OF FULL-SCALE LIFT AND DRAG CHARACTERISTICS OF THE X-15 AIRPLANE WITH WIND-TUNNEL RESULTS AND THEORY , Technical Memorandum
Authors: Edward J. Hopkins, David E. Fetterman, Jr. and Edwin J. Saltzman
Report Number: NASA-TM-X-713
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Comparisons are made between the minimum drag characteristics of the full-scale X-15 airplane and wind-tunnel model data and theory extrapolated to flight Reynolds numbers for Mach numbers of 2.5 and 3.0. Similar comparisons are made for drag due to lift and maximum lift-drag ratio for Mach numbers up to about 5. Speed-brake drag and base-drag results are presented up to Mach numbers of 5.5 and 6, respectively.
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Report Date: March 1962
No. Pages: 18
Keywords: Aerodynamic drag; Drag; Lift; Scale models; Wind tunnel models.
- THE X-15 PROGRAM
Authors: J. A. Walker
Report Number: H-264
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The high-temperature structural design approach utilized for the X-15 configuration has been successful; no major design deficiencies were encountered nor major modifications required. With but few exceptions, the local thermal problems encountered have not affected primary structural areas. In general, the aerodynamic derivatives extracted from flight-test data have confirmed the estimated derivatives obtained from wind-tunnel evaluations at hypersonic speeds. The aerodynamic flight control system and the simple stability augmentation system of the X-15 airplane have proved to be good technical designs. The airplane can be flown with satisfactory handling qualities through the range of dynamic pressures from about 1,500 lb/sq ft to below 100 lb/sq ft through the range of Mach numbers from 6.0 to subsonic landing conditions. Although only limited flight experience has been gained with the reaction control system, its basic design appears to be
completely adequate. This type of system apparently provides an adequate means of attitude control for future space vehicles. Pilot transition from aerodynamic controls to reaction controls has been accomplished without problems.
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Report Date: January 1962
No. Pages: 17
Keywords: Aerodynamics; High temperature; Mach number; Mosaics; Spacecraft.
Notes: FOR PRESENTATION AT THE INST. OF AEROSPACE SCIENCES MEETING, ST. LOUIS, MO., APR. 30-MAY 2, 1962.
- THEORETICAL FLUTTER ANALYSIS OF FLAT RECTANGULAR PANELS IN UNIFORM COPLANAR FLOW WITH ARBITRARY DIRECTION. , Technical Note
Authors: Eldon E. Kordes and Richard B. Noll
Report Number: NASA-TN-D-1156
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Numerical calculations show that small variations in flow direction have a marked effect on the flutter of simply supported rectangular panels. The results of the calculations also show that the critical flutter mode changes at small flow angles when the length-width ratio is less than 1. Flutter conditions for a given panel at different flow angles can be compared on a comon basis by use of a dynamic-pressure-parameter ratio referenced to flow conditions of an aligned panel.
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Subject Category: 39
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Report Date: January 1962
No. Pages: 18
Keywords: Computation; Flutter analysis; Panel flutter; Planar structures; Rectangular panels.
- LATERAL-DIRECTIONAL CONTROL OF THE X-15 AIRPLANE , Technical Memorandum
Authors: F. S. Petersen, H. A. Rediess and J. Weil
Report Number: NASA-TM-X-726
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The deterioration of lateral-directional controllability with roll damper off and the pilot performing a lateral-control task is discussed. The problem area was defined by fixed-base and airborne simulators and verified by closed-loop analysis in which a human transfer function represents the pilot. A parameter which predicts the problem area for the X-15 airplane is developed. The means considered to alleviate the control problem in the X-15 airplane are also discussed.
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Report Date: March 1962
No. Pages: 26
Keywords: Directional control; Directional stability; Lateral control; Lateral stability; X-15 aircraft.
- RESUME OF HANDLING QUALITIES OF THE X-15 AIRPLANE , Technical Memorandum
Authors: Robert M. White, Glenn H. Robinson and Gene J. Matranga
Report Number: NASA-TM-X-715
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A summary of handling qualities is presented as assessed from pilot opinion and flight data. Segments of the flight profile which were evaluated include the launch, climbout, semiballistic flight, atmosphere entry, and landing. Longitudinal controllability is compared with results from current studies of reentry-type vehicles.
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Report Date: March 1962
No. Pages: 19
Keywords: Aircraft control; Atmospheric entry; Controllability; Flight characteristics; Launching.
- FLIGHT SIMULATED OFF-THE-PAD ESCAPE AND LANDING MANEUVERS FOR A VERTICALLY LAUNCHED HYPERSONIC GLIDER , Technical Memorandum
Authors: Gene J. Matranga, William H. Dana and Neil A. Armstrong
Report Number: NASA-TM-X-637
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A series of subsonic maneuvers was flown with an airplane having a maximum lift-drag ratio of 4.7. No particularly difficult piloting or maneuvering problems were encountered. A reduction of the pilot's visibility from the cockpit did not appreciably impair his navigation capabilities, but did adversely affect his performance of the escape and landing maneuvers.
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Report Date: March 1962
No. Pages: 27
Keywords: Flight simulation; Hypersonic gliders; Landing simulation; Launching pads; Pilot performance.
- STRUCTURAL DYNAMICS EXPERIENCES OF THE X-15 AIRPLANE , Technical Note
Authors: Gareth H. Jordan, Norman J. McLeod and Lawrence D. Guy
Report Number: NASA-TN-D-1158
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The structural dynamic problems anticipated during the design of the X-15 airplane are reviewed briefly, and the actual flight experiences with the airplane are described. The noise environment, acoustic fatigue problems, and panel-flutter experiences are discussed. Where these problems led to structural modifications, the modifications are described.
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Subject Category: 39
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Report Date: March 1962
No. Pages: 14
Keywords: Buffeting; Dynamic response; Dynamic structural analysis; X-15 aircraft.
- THE RECORD-SETTING RESEARCH AIRPLANES
Authors: J. A. Martin
Report Number: H-285
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The first compilation of all available data on the unofficial records of the rocket airplanes is presented. The maximum Mach number, true velocity, and the altitude obtained by the X-1-1, D-558-II, X-1A, X-2, and X-15 airplanes are given in tabular form. Also, the physical characteristics of these airplanes are given and include wing spans, wing sweep, launch weight, and landing weight.
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Report Date: January 1962
No. Pages: 6
Keywords: Airspeed; D-558 aircraft; High altitude; High speed; Research aircraft.
Notes: INST. OF THE AEROSPACE SCI., 1962 REPR. FROM AEROSPV. 21, NO. 12, DEC. 1962 P 49-54.
- CREW SAFETY AND SURVIVAL ASPECTS OF THE LUNAR-LANDING MISSION , Conference Paper
Authors: H. M. Drake
Report Number: H-286
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Some of the safety and survival aspects of the manned lunar-landing mission are examined. The conditions requiring abort to the earth, lunar orbit, and lunar surface are determined. Some of the possible design requirements to permit abort to lunar orbit or surface are indicated. Lunar orbital and surface survival kits are described, and the stationing of such kits in lunar orbit and at the intended landing site is proposed.
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Subject Category: 36
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Report Date: January 1962
No. Pages: 10
Keywords: Lunar landing; Manned spacecraft; Safety factors; Space flight; Spacecrews.
Notes: PRESENTATION AT IAS MEETING ON ''MAN'S PROGRESS IN THE CONQUEST OF SPACE'', ST. LOUIS, MO., APR. 30 - MAY 2, 1962.
- REVIEW OF THE X-15 PROGRAM , Technical Note
Authors: J. Weil
Report Number: NASA-TN-D-1278
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The X-15 project is reviewed from its inception in 1954 through 1961. Some of the more important historical aspects of the program are noted, but major emphasis is placed on the significant research results.
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Report Date: June 1962
No. Pages: 54
Keywords: Aerodynamics; Aeronautics; Experience; Simplification; Stability.
- OPERATIONAL EXPERIENCES AND CHARACTERISTICS OF THE X-15 FLIGHT CONTROL SYSTEM , Technical Note
Authors: R. A. Tremant
Report Number: NASA-TN-D-1402
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: X-15 flight and simulator experiences with the manual flight control and stability augmentation system for the period from December 1958 to January 1962 are presented. The flight data extend to a Mach number of 6.04 and an altitude of 217,000 feet, and the simulator data cover the design flight envelope. The characteristics of the manual flight control system and the stability augmentation system are discussed, in conjunction with pilot evaluation, operational problems, modifications, and reliability. Pertinent X-15 flight history is included.
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Report Date: December 1962
No. Pages: 50
Keywords: Flight control; High altitude; Hypersonic aircraft; Mach number; Stability.
- MANNED PARAGLIDER FLIGHT TESTS
Authors: V. W. Horton
Report Number: H-300
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: No abstract available.
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Report Date: July 1962
No. Pages: 10
Keywords: Control; Flight recorder; Free flight test apparatus; Paragliders; Towed bodies.
Notes: In its Compilation of Papers Presented to Meeting on Space Vehicle Landing and Recovery Res. and Technol.
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