Patent US3610604A successfully refreshed from Google Patents.
Patent US4168044A successfully refreshed from Google Patents.
US4168044A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Energy conserving supersonic aircraft
Assignee: Vehicle Research Corp
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Filing: 1976-12-06
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Granted: 1979-09-18
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Expires: 1996-12-06
Abstract
Abstract This invention is an extension of my system to recover into useful work the energy normally wasted by a supersonic aircraft in its shock wave mechanism. This system utilizes the excess propulsive jet velocity in a sheet below the wing to form a planar vortex flap which acts as a pressure shield. The present improvement extends the pressure generating forward concave wing undersurface of this system into an upward reflexed aft surface so as to benefit from the increased pressure provided by the downstream upwash vortex field. This allows the aft portion of the wing to serve as the energy recovery section by achieving the pressure required for lift on the undersurface of this aft wing portion at a lesser angle with reduced drag. This stream-wise series of functions specifies the wing undersurface as concave, convex, and concave sequentially in the flow direction, thus corresponding to the upper element of a planar supersonic nozzle. The jet manifold and its continuing vortex flap below comprise a reflecting concave, convex, concave lower element. Thus the underwing surface and vortex flap together comprise a planar converging/diverging nozzle, generating the pressure increase under the wing required for lift and recovering this pressure into velocity at the wing trailing edge. The vortex flap then simulates an extended chord wing, imparting downward momentum to a greater mass of airbelow, thereby operating at a reduced angle with less drag.
Inventors
- 👤 Scott C. Rethorst
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 16:09
CPC Classifications
B; B64; B64C; B64C23/00; B64C23/06; Y; Y02; Y02T; Y02T50/00; Y02T50/10
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
214 words
An aircraft having a wing and a nozzle said wing having a lower surface and an upper surface, said lower surface having forward concave, convex, and aft concave curvature sequentially in the stream direction, the two said surfaces together comprising a net positive angle of attack; and said nozzle is a manifold having an outside shell flat on its bottom and concave upward on the forward portion of its top, generating the compression associated with its volume in a layer of air above, balancing the compression generated in said layer by the wing itself, said nozzle having an outlet which is transversely elongate relative to the aircraft and through which in operation a supersonic stream of fluid is emitted, said outlet extending throughout substantially the entire span of the leading edge of the wing, said nozzle being spaced below the leading edge thereby forming an elongate gap between said leading edge and said nozzle through which said layer of air streams and is compressed by said wing lower surface, and wherein a vortex flap is generated on the interface between said compressed layer of air and said nozzle stream, providing pressure on the lower surface of the wing required for lift at a net reduced angle of attack with less drag during supersonic flight.
Claim 2
Dependent Claim
214 words
An aircraft having a wing and a nozzle said wing having a lower surface and an upper surface, said lower surface having forward concave, convex, and aft concave curvature sequentially in the stream direction, the two said surfaces together comprising a net positive angle of attack; and said nozzle is a manifold having an outside shell flat on its bottom and concave upward on the forward portion of its top, generating the compression associated with its volume in a layer of air above, balancing the compression generated in said layer by the wing itself, said nozzle having an outlet which is transversely elongate relative to the aircraft and through which in operation a supersonic stream of fluid is emitted, said outlet extending throughout substantially the entire span of the leading edge of the wing, said nozzle being spaced below the leading edge thereby forming an elongate gap between said leading edge and said nozzle through which said layer of air streams and is compressed by said wing lower surface, and wherein a vortex flap is generated on the interface between said compressed layer of air and said nozzle stream, providing pressure on the lower surface of the wing required for lift at a net reduced angle of attack with less drag during supersonic flight.
Claim 3
Dependent Claim
186 words
An aircraft having a wing and a nozzle said wing having a lower surface and an upper surface, said lower surface having forward concave, convex, and aft concave curvature sequentially in the stream direction, the two said surfaces together comprising a net positive angle of attack; and said nozzle is a manifold coupled to receive in operation fan air from a plurality of fan jet engines, said nozzle having an outlet which is transversely elongate relative to the aircraft and through which in operation a supersonic stream of fluid is emitted, said outlet extending throughout substantially the entire span of the leading edge of the wing, said nozzle being spaced below the leading edge thereby forming an elongate gap between said leading edge and said nozzle through which a layer of air streams and is compressed by said wing lower surface, and wherein a vortex flap is generated on the interface between said compressed layer of air and said nozzle stream, providing pressure on the lower surface of the wing required for lift at a net reduced angle of attack with less drag during supersonic flight.
Claim 4
Dependent Claim
186 words
An aircraft having a wing and a nozzle said wing having a lower surface and an upper surface, said lower surface having forward concave, convex, and aft concave curvature sequentially in the stream direction, the two said surfaces together comprising a net positive angle of attack; and said nozzle is a manifold coupled to receive in operation fan air from a plurality of fan jet engines, said nozzle having an outlet which is transversely elongate relative to the aircraft and through which in operation a supersonic stream of fluid is emitted, said outlet extending throughout substantially the entire span of the leading edge of the wing, said nozzle being spaced below the leading edge thereby forming an elongate gap between said leading edge and said nozzle through which a layer of air streams and is compressed by said wing lower surface, and wherein a vortex flap is generated on the interface between said compressed layer of air and said nozzle stream, providing pressure on the lower surface of the wing required for lift at a net reduced angle of attack with less drag during supersonic flight.
Claim 5
Dependent Claim
281 words
An aircraft having a wing and a nozzle said wing having a lower surface and an upper surface, said lower surface having forward concave, convex, and aft concave curvature sequentially in the stream direction, the two said surfaces together comprising a net positive angle of attack; and said nozzle having an outlet which is transversely elongate relative to the aircraft and through which in operation a supersonic stream of fluid is emitted, said outlet extending throughout substantially the entire span of the leading edge of the wing, said nozzle being spaced below the leading edge thereby forming an elongate gap between said leading edge and said nozzle through which a layer of air streams and is compressed by said wing lower surface, and wherein a vortex flap is generated on the interface between said compressed layer of air and said nozzle stream, providing pressure on the lower surface of the wing required for lift at a net reduced angle of attack with less drag during supersonic flight, said nozzle having an outside shell and being located so that said supersonic stream of fluid emitted therefrom intercepts said compressed layer of air generated by said forward concave wing lower surface, whereas a stronger and steeper shock wave generated at the wing leading edge due to an atmospheric gust will be intercepted by tbe nozzle outside shell, reflected back upwards to said aft concave wing lower surface, and cancelled by expansion, and wherein the energy decay into heat by said shock wave, contained within said compression layer, will serve as a gust alleviation device or shock absorber providing a reduction in the loads and passenger discomfort normally experienced with a conventional wing system.
Claim 6
Dependent Claim
281 words
An aircraft having a wing and a nozzle said wing having a lower surface and an upper surface, said lower surface having forward concave, convex, and aft concave curvature sequentially in the stream direction, the two said surfaces together comprising a net positive angle of attack; and said nozzle having an outlet which is transversely elongate relative to the aircraft and through which in operation a supersonic stream of fluid is emitted, said outlet extending throughout substantially the entire span of the leading edge of the wing, said nozzle being spaced below the leading edge thereby forming an elongate gap between said leading edge and said nozzle through which a layer of air streams and is compressed by said wing lower surface, and wherein a vortex flap is generated on the interface between said compressed layer of air and said nozzle stream, providing pressure on the lower surface of the wing required for lift at a net reduced angle of attack with less drag during supersonic flight, said nozzle having an outside shell and being located so that said supersonic stream of fluid emitted therefrom intercepts said compressed layer of air generated by said forward concave wing lower surface, whereas a stronger and steeper shock wave generated at the wing leading edge due to an atmospheric gust will be intercepted by tbe nozzle outside shell, reflected back upwards to said aft concave wing lower surface, and cancelled by expansion, and wherein the energy decay into heat by said shock wave, contained within said compression layer, will serve as a gust alleviation device or shock absorber providing a reduction in the loads and passenger discomfort normally experienced with a conventional wing system.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1982-09-17 | 1983-03-19 | 1983-09-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-09-17 | 1987-03-19 | 1987-09-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-09-17 | 1991-03-19 | 1991-09-18 | $7700.00 | Window Closed / Lapsed |