Two-dimensional supersonic nozzle thrust vectoring using staggered ramps
AssigneeThe Regents of the University of California
InventorsCarlos F. Montes, Roger L. Davis
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Abstract
A system and method for vectoring the thrust of a supersonic, air-breathing engine. A thrust vectoring mechanism uses two asymmetrically staggered ramps; one placed at the throat, the other positioned at the exit lip of the nozzle of the engine to re-direct exhaust flow off-axis with the nozzle.
Claims21
An apparatus for vectoring thrust of a air-breathing engine comprising a nozzle having an inlet, exit, and a throat, disposed between the inlet and exit, the apparatus comprising:
- first and second deployable ramps;
- wherein the first ramp is disposed on an internal wall of the nozzle at or near the throat;
- wherein the second ramp is and the positioned at or near the exit of the nozzle;
- and
- wherein the first and second ramps are configured to redirect exhaust flow of the nozzle.
A thrust-vectored, air-breathing engine, comprising:
- a nozzle having an inlet, exit, and a throat, disposed between the inlet and exit, the apparatus comprising:
- first and second deployable ramps;
- wherein the first ramp is disposed on an internal wall of the nozzle at or near the throat;
- wherein the second ramp is and the positioned at or near the exit of the nozzle;
- and
- wherein the first and second ramps are configured to redirect exhaust flow of the nozzle.
A method for vectoring thrust of a air-breathing engine comprising a nozzle having an inlet, exit, and a throat, disposed between the inlet and exit, the method comprising:
- deploying first and second deployable ramps within the nozzle;
- wherein the first ramp is disposed on an internal wall of the nozzle at or near the throat;
- wherein the second ramp is and the positioned at or near the exit of the nozzle;
- and
- redirecting an exhaust flow of the nozzle.
Dependencies are inferred from the claim text.