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A flight maneuverable gas turbine exhaust nozzle is provided with cooperating variable internal converging-diverging flaps to provide area control. A flap downstream of the converging-diverging flap provides flight maneuver vectoring as well as external exhaust expansion control. A vertical take-off...

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Bibliographische Detailangaben
Hauptverfasser:	OWEN NASH,DUDLEY, GERALD BEAVERS,ROBERT, CLAYTON BURGE,JOSEPH, MANUEL CASTELLS,ONOFRE TAMA, IRA PARKER,ALAN
Format:	Patent
Sprache:	ger
Schlagworte:	AEROPLANES AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES COSMONAUTICS HEATING HELICOPTERS HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A flight maneuverable gas turbine exhaust nozzle is provided with cooperating variable internal converging-diverging flaps to provide area control. A flap downstream of the converging-diverging flap provides flight maneuver vectoring as well as external exhaust expansion control. A vertical take-off and landing capability is provided by deployment of a rotating bonnet-type deflector which diverts the exhaust stream downward around one side of the exhaust nozzle. The nozzle throat rotates with the deflector to produce efficient turning of the exhaust stream.