Shockwave mitigation system for supersonic aircraft
AssigneeNctar, LLC
InventorJohn B. Schlaerth, JR.
Life of this patent
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Abstract
A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume having a first average velocity from an engine, and expelling a bypass exhaust plume having a second average velocity from the engine, the first average velocity greater than the second average velocity, so that the bypass exhaust plume inhibits coalescence of an engine exhaust plume compression shockwave.
Claims31
A method of shock wave mitigation in supersonic vehicles, comprising:
- generating an earthward propagating wing compression shockwave from a curved wing;
- expelling a first supersonic exhaust plume having a first average velocity from an engine, the engine having an engine housing;
- reflecting a majority of the earthward propagating wing compression shockwave back towards the curved wing using the engine;
- expelling a bypass exhaust plume having a second average velocity adjacent to the first supersonic exhaust plume, the second average velocity being slower than the first average velocity;
- and
- inhibiting coalescence of an engine exhaust plume compression shockwave extending from the first supersonic exhaust plume using the bypass exhaust plume.
The method of 1, wherein the engine is selected from the group consisting of a jet engine, turbojet engine, ramjet engine, scramjet engine, high bypass turbojet, variable cycle engine, and adaptive-cycle engine.
A method of supersonic thrust generation, comprising:
- generating a thrust supersonic exhaust plume having a first average velocity from an engine;
- and
- expelling a bypass exhaust plume having a second average velocity from the engine, the first average velocity greater than the second average velocity;
- wherein the bypass exhaust plume inhibits coalescence of a supersonic exhaust plume compression shockwave extending from the first supersonic exhaust plume.
The method of 19, wherein the bypass exhaust plume is generated from a source selected from the group consisting of (i) bleed air taps from a compressor in the engine, (ii) bleed air taps at inlet shock ramps disposed at a front of the engine.
An air vehicle, comprising:
- a fuselage,
- an engine comprising an exhaust plume nozzle;
- a bypass plume nozzle disposed adjacent to the exhaust plume nozzle;
- and
- a curved supersonic wing coupled to the fuselage, the curved supersonic wing curving about the engine.
A method of shock wave mitigation in supersonic vehicles, comprising:
- generating an earthward propagating wing compression wave region from a curved wing;
- expelling a first supersonic exhaust plume having a first average velocity from an engine, the engine having an engine housing;
- translating the engine to expel the first supersonic exhaust plume immediately upstream from the earthward propagating wing compression wave region;
- wherein the earthward propagating wing compression wave region is inhibited from coalescing into a compression shockwave by the first supersonic exhaust plume.
Dependencies are inferred from the claim text.