Results 251 to 260 of about 5,057 (307)

LIQUID INJECTION THRUST VECTOR CONTROL

AIAA Journal, 1963
Abstract : The technique of obtaining thrust vector control by the injection of a liquid into the supersonic region of a rocket nozzle was studied. Liquids studied were water, Freon-12, Perchloroethylene, nitrogen tetroxide and bromine. In addition, unsymmetrical dimethylhydrazine and inhibited red fuming nitric acid were injected simultaneously to ...
C. J. GREEN, FOY McCULLOUGH
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Advanced Technology Thrust Vectoring Exhaust Systems

Journal of Aircraft, 1973
Figures 18-21 are plots of some data recorded during the flight tests. These data are typical of the flight test data and are included to show the similarity with the laboratory data. These plots cannot be compared directly with any of the other data presented here for the same reasons given in the paragraph on drop tests.
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Thrust vectoring of ion engines.

Journal of Spacecraft and Rockets, 1969
The causes of thrust vector misalignments in ion engines were studied both analytically and experimentally. It was found that the major cause of such misalignments is translation, or displacement of one of the electrodes in a direction perpendicular to the exhaust beam axis.
GORDON SOHL, VERRYL V. FOSNIGHT
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Thrust-vectored energy turns

Automatica, 1982
Turning performance is studied in 'energy approximation' for aircraft incorporating thrust vectoring. Over much of the energy range, this capability provides a small efficiency improvement in energy rate and in sustainable turn rate. For aircraft with static thrust in excess of weight, a spectacular improvement in maneuverability is realized at ...
Cliff, Eugene M., Kelley, Henry J., Lefton, Leon   +2 more
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Liquid-Injection Thrust Vector Control.

Journal of Spacecraft and Rockets, 1977
Theme A PROCEDURE is presented for preliminary design of a liquid-injection thrust-vector-control (LITVC) system for solid-propellant rockets. In LITVC, a rocket jet is deflected for steering purposes by injecting liquid into the side of the nozzle exit flow (see Fig. 1). The liquid is preferably both dense and exothermally reactive.
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Thrust Vectoring F-18 Design

1994
This section presents the design of a full envelope flight control system for a modified F-18 aircraft. The purpose of the design is to take advantage of advanced linear control design techniques while addressing practical implementation issues. A description of the aircraft model is presented, followed by detailed descriptions of the flight control ...
Richard J. Adams, James M. Buffington, Andrew G. Sparks, Siva S. Banda   +3 more
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A compact installation for testing vectored-thrust engines

17th Joint Propulsion Conference, 1981
An installation has been built to test the Pegasus engine in its vectored-thrust mode, in a conventional enclosed sea-level test cell, in response to the Navy's requirement for test facilities for V/STOL propulsion systems. The main features of the installation are the hardware for measuring vectored thrust and for redirecting engine exhaust gases out ...
W. H. Cunningham, J. F. Boytos
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Ion beam deflection for thrust vector control

5th Electric Propulsion Conference, 1966
Ion propulsion systems can be used for the combined functions of attitude control and station keeping of a synchronous satellite because they control thrust direction. The principal advantages of such a control system are power supply and thruster sharing, system weight reduction, and easy inclusion of redundant equipment.
J. ROBERT ANDERSON, GEORGE A. WORK
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Evaluation of fluidic thrust vectoring nozzle via thrust pitching angle and thrust pitching moment

Shock Waves, 2016
Shock vector control (SVC) in a converging–diverging nozzle with a rectangular cross-section is discussed as a fluidic thrust vectoring (FTV) method. The interaction between the primary nozzle flow and the secondary jet is examined using experiments and numerical simulations.
L. Li, M. Hirota, K. Ouchi, T. Saito
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Thrust Vector Control using movable probes

28th Aerospace Sciences Meeting, 1990
A study was undertaken to determine if movable probes or struts positioned in the nozzle can be used to provide Thrust Vector Control of the Space Shuttle Solid Rocket Booster. The study employed CFD to determine estimates of the shock standoff distance from the probe.
ROBERT CAVALLERI, WEIHNURNG TIARN, HARVEY READEY   +2 more
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