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Author : Albion H. Bowers
Publisher : Unknown
Page : 44 pages
File Size : 46,5 Mb
Release : 1996
Category : Fighter planes
ISBN : NASA:31769000524481
Author : David F. Fisher
Publisher : Unknown
Page : 44 pages
File Size : 40,7 Mb
Release : 1991
Category : Electronic
ISBN : NASA:31769000586571
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 28 pages
File Size : 41,9 Mb
Release : 2018-06-30
Category : Electronic
ISBN : 1722079312
The NASA F/A-18 High Alpha Research Vehicle (HARV) has been the flight test bed of a focused technology effort to significantly increase maneuvering capability at high angles of attack. Development and flight test of control law design methodologies, handling qualities metrics, performance guidelines, and flight evaluation maneuvers are described. The HARV has been modified to include two research control effectors, thrust vectoring, and actuated forebody strakes in order to provide increased control power at high angles of attack. A research flight control system has been used to provide a flexible, easily modified capability for high-angle-of-attack research controls. Different control law design techniques have been implemented and flight-tested, including eigenstructure assignment, variable gain output feedback, pseudo controls, and model-following. Extensive piloted simulation has been used to develop nonlinear performance guide-lines and handling qualities criteria for high angles of attack. This paper reviews the development and evaluation of technologies useful for high-angle-of-attack control. Design, development, and flight test of the research flight control system, control laws, flying qualities specifications, and flight test maneuvers are described. Flight test results are used to illustrate some of the lessons learned during flight test and handling qualities evaluations. Pahle, Joseph W. and Wichman, Keith D. and Foster, John V. and Bundick, W. Thomas Armstrong Flight Research Center; Langley Research Center ...
Author : Albion H. Bowers
Publisher : Unknown
Page : 36 pages
File Size : 47,7 Mb
Release : 1996
Category : Airplanes
ISBN : NASA:31769000524473
Author : National Aeronautics and Space Adm Nasa
Publisher : Unknown
Page : 72 pages
File Size : 52,6 Mb
Release : 2018-11-03
Category : Electronic
ISBN : 1730773206
This report contains a description of a lateral-directional control law designed for the NASA High-Alpha Research Vehicle (HARV). The HARV is a F/A-18 aircraft modified to include a research flight computer, spin chute, and thrust-vectoring in the pitch and yaw axes. Two separate design tools, CRAFT and Pseudo Controls, were integrated to synthesize the lateral-directional control law. This report contains a description of the lateral-directional control law, analyses, and nonlinear simulation (batch and piloted) results. Linear analysis results include closed-loop eigenvalues, stability margins, robustness to changes in various plant parameters, and servo-elastic frequency responses. Step time responses from nonlinear batch simulation are presented and compared to design guidelines. Piloted simulation task scenarios, task guidelines, and pilot subjective ratings for the various maneuvers are discussed. Linear analysis shows that the control law meets the stability margin guidelines and is robust to stability and control parameter changes. Nonlinear batch simulation analysis shows the control law exhibits good performance and meets most of the design guidelines over the entire range of angle-of-attack. This control law (designated NASA-1A) was flight tested during the Summer of 1994 at NASA Dryden Flight Research Center. Davidson, John B. and Murphy, Patrick C. and Lallman, Frederick J. and Hoffler, Keith D. and Bacon, Barton J. Langley Research Center...
Author : Keith D. Wichman
Publisher : Unknown
Page : 42 pages
File Size : 55,8 Mb
Release : 1996
Category : Airplanes
ISBN : NASA:31769000524499
Author : David F. Fisher
Publisher : Unknown
Page : 40 pages
File Size : 41,7 Mb
Release : 1990
Category : Aerodynamics
ISBN : UIUC:30112106565705
Author : Kenneth W. Iliff
Publisher : Unknown
Page : 74 pages
File Size : 43,6 Mb
Release : 1997
Category : Aerodynamics
ISBN : NASA:31769000449879
Author : David F. Fisher
Publisher : Unknown
Page : 18 pages
File Size : 46,5 Mb
Release : 1998
Category : Eddies
ISBN : NASA:31769000627847
Off-surface smoke flow visualization and extensive pressure measurements were obtained on the forebody of the NASA F-18 High Alpha Research Vehicle equipped with actuated forebody strakes. Test points at [alpha]=50 deg. were examined in which only one strake was deflected or in which both strakes were deflected differentially. The forebody pressures were integrated to obtain forebody yawing moments. Results showed that small single strake deflections can cause an undesirable yawing moment reversal. At [alpha]=50 deg., this reversal was corrected by deploying both strakes at 20 deg. initially, then differentially from 20 deg. to create a yawing moment. The off-surface flow visualization showed that in the case of the small single strake deflection, the resulting forebody/strake vortex remained close to the surface and caused accelerated flow and increased suction pressures on the deflected side. When both strakes were deflected differentially, two forebody/strake vortices were present. The forebody/strake vortex from the larger deflection would lift from the surface while the other would remain close to the surface. The nearer forebody/strake vortex would cause greater flow acceleration, higher suction pressures and a yawing moment on that side ot the forebody. Flow visualization provided clear description of the strake vortices fluid mechanics.
Author : John B. Davidson
Publisher : Unknown
Page : 74 pages
File Size : 46,7 Mb
Release : 1998
Category : Airplanes
ISBN : NASA:31769000450307
Author : Robert G. Ferguson
Publisher : Unknown
Page : 312 pages
File Size : 50,9 Mb
Release : 2013
Category : Electronic
ISBN : UCSD:31822041095381
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 34 pages
File Size : 42,6 Mb
Release : 2018-07-05
Category : Electronic
ISBN : 1722303409
Surface and off-surface flow visualization techniques were used to visualize the 3-D separated flows on the NASA F-18 high alpha research vehicle at high angles of attack. Results near the alpha = 25 to 26 deg and alpha = 45 to 49 deg are presented. Both the forebody and leading edge extension (LEX) vortex cores and breakdown locations were visualized using smoke. Forebody and LEX vortex separation lines on the surface were defined using an emitted fluid technique. A laminar separation bubble was also detected on the nose cone using the emitted fluid technique and was similar to that observed in the wind tunnel test, but not as extensive. Regions of attached, separated, and vortical flow were noted on the wing and the leading edge flap using tufts and flow cones, and compared well with limited wind tunnel results. Fisher, David F. and Delfrate, John H. and Richwine, David M. Ames Research Center; Armstrong Flight Research Center RTOP 505-68-71...
Author : Jeremy R. Kinney
Publisher : Government Printing Office
Page : 318 pages
File Size : 44,8 Mb
Release : 2018-02-15
Category : Airplanes
ISBN : 1626830371
The NACA and aircraft propulsion, 1915-1958 -- NASA gets to work, 1958-1975 -- The shift toward commercial aviation, 1966-1975 -- The quest for propulsive efficiency, 1976-1989 -- Propulsion control enters the computer era, 1976-1998 -- Transiting to a new century, 1990-2008 -- Toward the future
Author : National Aeronautics and Space Adm Nasa
Publisher : Independently Published
Page : 68 pages
File Size : 46,7 Mb
Release : 2018-09-20
Category : Science
ISBN : 1723851639
Pressure distributions on the wings of the F/A-18A High Alpha Research Vehicle (HARV) were obtained using both flush-mounted pressure orifices and surface-mounted pressure tubing. During quasi-stabilized 1-g flight, data were gathered at ranges for angle of attack from 5 deg to 70 deg, for angle of sideslip from -12 deg to +12 deg, and for Mach from 0.23 to 0.64, at various engine settings, and with and without the leading edge extension fence installed. Angle of attack strongly influenced the wing pressure distribution, as demonstrated by a distinct flow separation pattern that occurred between the range from 15 deg to 30 deg. Influence by the leading edge extension fence was evident on the inboard wing pressure distribution, but little influence was seen on the outboard portion of the wing. Angle-of-sideslip influence on wing pressure distribution was strongest at low angle of attack. Influence of Mach number was observed in the regions of local supersonic flow, diminishing as angle of attack was increased. Engine throttle setting had little influence on the wing pressure distribution.Davis, Mark C. and Saltzman, John A.Armstrong Flight Research CenterWINGS; PRESSURE DISTRIBUTION; WIND TUNNEL TESTS; F-18 AIRCRAFT; RESEARCH VEHICLES; LIFT; ORIFICES; SUPERSONIC FLOW; BOUNDARY LAYER SEPARATION; DATA REDUCTION; COMPUTATIONAL FLUID DYNAMICS; PIPES (TUBES); FLOW VISUALIZATION; FLIGHT TESTS; ANGLE OF ATTACK
Author : Anonim
Publisher : Unknown
Page : 1064 pages
File Size : 53,9 Mb
Release : 2010
Category : Aeronautics
ISBN : UCSD:31822036341212
Two-volume collection of case studies on aspects of NACA-NASA research by noted engineers, airmen, historians, museum curators, journalists, and independent scholars. Explores various aspects of how NACA-NASA research took aeronautics from the subsonic to the hypersonic era.-publisher description.