Pulse detonation bypass engine propulsion pod
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United States of America Patent
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-
Dec 30, 2003
Grant Date -
Nov 14, 2002
app pub date -
Mar 21, 2002
filing date -
Oct 27, 1999
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
A propulsion pod for a twin tube, rotary inlet valve, pulse detonation engine includes a shared, two-dimensional, low aspect ratio wedge nozzle in which each side of the wedge is transitioned into the discharge end of the detonation tubes of the engine. The nozzle design results in a quasi-separate exhaust flow path with two separate nozzle throat areas, one for each detonation tube. Actuation of the center wedge of the nozzle provides pitch vectoring of the exhaust. Actuation of flaps integrated into the side walls of the nozzle provides yaw vectoring. The detonation tubes are cooled by flowing bypass air over cooling means coupled to the detonation tubes.
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