Aeronautics and astronautics – Aircraft – steering propulsion – Fluid
Patent
1992-11-02
1993-12-28
Huppert, Michael S.
Aeronautics and astronautics
Aircraft, steering propulsion
Fluid
244 322, 244 23D, 244 76J, F41G 700, F42B 1060
Patent
active
052732371
ABSTRACT:
A system for augmenting yaw control in an aircraft is described which comprises first and second thrust nozzles disposed on the upper surface of the aircraft forebody aft of the forebody nose apex a distance of about 0.5 times the forebody diameter at about 45.degree. to either side of the symmetry plane of the forebody, each thrust nozzle oriented to direct a fluid jet at an angle of about 10.degree. from the surface of the forebody and generally rearwardly toward the symmetry plane at about 60.degree. .+-.10.degree. to the symmetry plane, and a source of pressurized fluid operatively connected to the thrust nozzles for generating the jets.
REFERENCES:
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patent: 3113520 (1963-12-01), Geissler et al.
patent: 3142153 (1964-07-01), Hensley
patent: 3276376 (1966-10-01), Cubbison et al.
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patent: 5004184 (1991-04-01), Bernard
patent: 5080301 (1992-01-01), Knoche
"X-29 Forebody Jet Blowing", Guyton et al., AIAA 92-0017 (1992).
"An Experimental Study of Pneumatic Vortex Flow Control on High Angle of Attack Forebody Model", Cornelius et al., AIAA 92-0018 (1992).
Cornelius Kenneth C.
Guyton Robert W.
Tinapple Jon A.
Ansley Virna Lissi
Huppert Michael S.
Kundert Thomas L.
Scearce Bobby D.
The United States of America as represented by the Secretary of
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