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Author : Albion H. Bowers
Publisher : Unknown
Page : 36 pages
File Size : 52,5 Mb
Release : 1996
Category : Airplanes
ISBN : NASA:31769000524473
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 170 pages
File Size : 55,6 Mb
Release : 2018-07-17
Category : Electronic
ISBN : 1722909714
A static (wind-off) test was conducted in the static test facility of the Langley 16-foot Transonic Tunnel to evaluate the vectoring capability and isolated nozzle performance of the proposed thrust vectoring system of the F/A-18 high alpha research vehicle (HARV). The thrust vectoring system consisted of three asymmetrically spaced vanes installed externally on a single test nozzle. Two nozzle configurations were tested: A maximum afterburner-power nozzle and a military-power nozzle. Vane size and vane actuation geometry were investigated, and an extensive matrix of vane deflection angles was tested. The nozzle pressure ratios ranged from two to six. The results indicate that the three vane system can successfully generate multiaxis (pitch and yaw) thrust vectoring. However, large resultant vector angles incurred large thrust losses. Resultant vector angles were always lower than the vane deflection angles. The maximum thrust vectoring angles achieved for the military-power nozzle were larger than the angles achieved for the maximum afterburner-power nozzle. Mason, Mary L. and Capone, Francis J. and Asbury, Scott C. Langley Research Center F-18 AIRCRAFT; NOZZLE EFFICIENCY; NOZZLE GEOMETRY; RESEARCH VEHICLES; STATIC TESTS; THRUST VECTOR CONTROL; WIND TUNNEL TESTS; AFTERBURNING; EFFECTS; JET VANES; NOZZLES; PRESSURE RATIO; STATIC THRUST; TRANSONIC WIND TUNNELS...
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 180 pages
File Size : 52,8 Mb
Release : 2018-07-18
Category : Electronic
ISBN : 1723218766
An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine the multiaxis thrust-vectoring characteristics of the F-18 High-Alpha Research Vehicle (HARV). A wingtip supported, partially metric, 0.10-scale jet-effects model of an F-18 prototype aircraft was modified with hardware to simulate the thrust-vectoring control system of the HARV. Testing was conducted at free-stream Mach numbers ranging from 0.30 to 0.70, at angles of attack from O' to 70', and at nozzle pressure ratios from 1.0 to approximately 5.0. Results indicate that the thrust-vectoring control system of the HARV can successfully generate multiaxis thrust-vectoring forces and moments. During vectoring, resultant thrust vector angles were always less than the corresponding geometric vane deflection angle and were accompanied by large thrust losses. Significant external flow effects that were dependent on Mach number and angle of attack were noted during vectoring operation. Comparisons of the aerodynamic and propulsive control capabilities of the HARV configuration indicate that substantial gains in controllability are provided by the multiaxis thrust-vectoring control system. Asbury, Scott C. and Capone, Francis J. Langley Research Center F-18 AIRCRAFT; THRUST VECTOR CONTROL; RESEARCH VEHICLES; NOZZLES; ANGLE OF ATTACK; CONTROLLABILITY; FREE FLOW; MACH NUMBER; PRESSURE RATIO; TRANSONIC WIND TUNNELS; WING TIPS...
Author : Kenneth W. Iliff
Publisher : Unknown
Page : 74 pages
File Size : 47,5 Mb
Release : 1997
Category : Aerodynamics
ISBN : NASA:31769000449879
Author : Kenneth W. Iliff
Publisher : Unknown
Page : 92 pages
File Size : 45,7 Mb
Release : 1999
Category : Aerodynamics
ISBN : NASA:31769000449960
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 70 pages
File Size : 44,8 Mb
Release : 2018-07-08
Category : Electronic
ISBN : 1722434880
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 : John B. Davidson
Publisher : Unknown
Page : 74 pages
File Size : 51,8 Mb
Release : 1998
Category : Airplanes
ISBN : NASA:31769000450307
Author : Steven A. Johnson
Publisher : Unknown
Page : 36 pages
File Size : 43,8 Mb
Release : 1992
Category : Airplanes
ISBN : UIUC:30112105147315
Author : National Aeronautics and Space Adm Nasa
Publisher : Independently Published
Page : 78 pages
File Size : 47,8 Mb
Release : 2018-11-12
Category : Science
ISBN : 1731186797
The advantages and disadvantages of using thrust vectoring for lateral-directional control and the effects of reducing the tail size of a single-engine aircraft were investigated. The aerodynamic characteristics of the F-16 aircraft were generated by using the Aerodynamic Preliminary Analysis System II panel code. The resulting lateral-directional linear perturbation analysis of a modified F-16 aircraft with various tail sizes and yaw vectoring was performed at several speeds and altitudes to determine the stability and control trends for the aircraft compared to these trends for a baseline aircraft. A study of the paddle-type turning vane thrust vectoring control system as used on the National Aeronautics and Space Administration F/A-18 High Alpha Research Vehicle is also presented. Peron, Lee R. and Carpenter, Thomas Armstrong Flight Research Center...
Author : Frederick J. Lallman
Publisher : Unknown
Page : 48 pages
File Size : 43,7 Mb
Release : 1998
Category : Airplanes
ISBN : NASA:31769000450299
Author : Keith D. Wichman
Publisher : Unknown
Page : 42 pages
File Size : 44,9 Mb
Release : 1996
Category : Airplanes
ISBN : NASA:31769000524499
Author : Anonim
Publisher : Unknown
Page : 40 pages
File Size : 42,7 Mb
Release : 1992
Category : Aeronautics
ISBN : MINN:31951P007525874
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 28 pages
File Size : 52,9 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 : Robert G. Ferguson
Publisher : Unknown
Page : 312 pages
File Size : 43,8 Mb
Release : 2013
Category : Electronic
ISBN : UCSD:31822041095381
Author : Albion H. Bowers
Publisher : Unknown
Page : 44 pages
File Size : 51,6 Mb
Release : 1996
Category : Fighter planes
ISBN : NASA:31769000524481
