Aeronautics and astronautics – Aircraft – heavier-than-air – Fluid sustained
Patent
1989-02-08
1991-11-05
Peters, Jr., Joseph F.
Aeronautics and astronautics
Aircraft, heavier-than-air
Fluid sustained
244 23B, 244 124, 244 125, B64C 2900
Patent
active
050625888
ABSTRACT:
A thrust deflector for use in VSTOL aircraft which has a pressurized gas generator. The thrust deflector consists of a number of adjacent nozzles. Each of the nozzles has a body with a first face and a second face. The nozzles further have an inlet for receiving pressurized gas from the pressurized gas generator and at least one outlet connected to the inlet for discharging pressurized gas from the nozzle. Each of the nozzles is rotatable from a first position in which the outlet directs pressurized gas downwardly, to a second position in which the outlet directs pressurized gas rearwardly. In the first position the first and second faces of the bodies of adjacent nozzles are spaced apart to permit air to flow between the nozzles. In the second position the first and second faces of adjacent nozzles are in contact preventing air passage between adjacent nozzles. The thrust deflector may be mounted in stub wings along either side of the fuselage or in a chordwise arrangement in the main wing of the aircraft. Lower ejector doors may be rotatably mounted adjacent the nozzles distal the fuselage and the nozzles suitably spaced to cause thrust augmentation according to the ejector principle.
REFERENCES:
patent: Re31591 (1984-05-01), Drakeley
patent: 3096954 (1963-07-01), Bauger et al.
patent: 3099423 (1963-07-01), Wilde et al.
patent: 3159362 (1964-12-01), Laing
patent: 3212731 (1965-10-01), Kappus
patent: 3258206 (1966-06-01), Simonson
patent: 3310948 (1967-03-01), Culp
patent: 3348380 (1967-10-01), Rees
patent: 3380661 (1968-04-01), Markowski
patent: 3491970 (1970-01-01), Maguire
patent: 3545701 (1970-12-01), Bertin
patent: 3611725 (1971-10-01), Short
patent: 3664611 (1972-05-01), Harris
patent: 3770227 (1973-10-01), Von Ohain et al.
patent: 3819134 (1974-06-01), Throndson
patent: 3830451 (1974-08-01), Fosness
patent: 3831887 (1974-08-01), Fosness
patent: 3860200 (1975-01-01), Petrushka
patent: 3893638 (1975-07-01), Kelly
patent: 3941335 (1976-03-01), Viets
patent: 4171112 (1979-10-01), Harvey
patent: 4205813 (1980-06-01), Evans et al.
patent: 4235397 (1980-10-01), Compton
patent: 4248041 (1981-02-01), Wilde et al.
patent: 4301980 (1981-10-01), Bradfield et al.
patent: 4343446 (1982-08-01), Langley
patent: 4391424 (1983-07-01), Bartoe, Jr.
patent: 4392621 (1983-07-01), Viets
National Aeronautics and Space Administration, Dynamic Pressure and Thrust Characteristics of Cold Jets Discharging from Several Exhaust Nozzles Designed for VTOL Downwash Suppression by: C. C. Higgins and T. W. Wainwright.
National Aeronautics and Space Administration, Exhaust Jet Wake and Thrust Characteristics of Several Nozzles Designed for VTOL Downwash Suppression Tests In and Out of Ground Effect with 70.degree. F. and 1200.degree. F. Nozzle Discharge Temperatures by: C. C. Higgins, D. P. Kelly and T. W. Wainwright.
Boeing of Canada Ltd.
Ellis Christopher P.
Peters Jr. Joseph F.
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