Patent US497857A successfully refreshed from Google Patents.
Patent US3596852A successfully refreshed from Google Patents.
US3596852A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Supersonic aircraft
Assignee: Individual
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Filing: 1968-07-19
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Granted: 1971-08-03
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Expires: 1988-07-19
Abstract
Abstract A supersonic aircraft having retractable wings and stabilizer controls wherein the leading edge of the airfoil is a continuous air inlet and the fuselage and all remaining portions of the aircraft are situated largely downstream of the air inlet, the aircraft being substantially T-shaped in configuration, a large portion of the shock wave generated by the aircraft being received into the air inlet. At least a portion of the jet exhaust is deflected into the shock wave produced by the aircraft at supersonic speeds for the purpose of disrupting the shock wave. Rapid deceleration of the aircraft from supersonic to sonic speeds obtained by extension of retractable airfoils and stabilizers.
Inventors
- 👤 George H Wakefield
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 22:32
CPC Classifications
B; B64; B64C; B64C30/00
Claims Analysis
Total Claims: 17
Claim 1
Independent Claim
39 words
A method of disrupting shock waves produced by an aircraft flying at supersonic speeds which comprises directing a stream of jet exhaust into the shock wave produced by the aircraft at sufficient velocity to substantially distort the shock wave.
Claim 2
Independent Claim
39 words
A method of disrupting shock waves produced by an aircraft flying at supersonic speeds which comprises directing a stream of jet exhaust into the shock wave produced by the aircraft at sufficient velocity to substantially distort the shock wave.
Claim 3
Dependent Claim
33 words
A method in accordance with claim 1 wherein said stream''s cross section taken in a plane perpendicular to the direction of said stream is elongated in the vertical sense relative to the aircraft.
Claim 4
Dependent Claim
23 words
A method in accordance with claim 1 wherein said stream comprises only part of the jet exhaust produced by the aircraft''s jet engine.
Claim 5
Independent Claim
80 words
A method of weakening and dissipating the shock and boom waves which are produced principally by the lift of an aircraft traveling at supersonic speeds, which comprises selectively diverting a portion of the exhaust flow from the aircraft''s jet engines downward relative to the normal aft flow thereof and into the shock-wave layer of said aircraft thereby forming a corrugation in said shock-wave layer as it is being formed whereby the boom-producing effects of said shock wave layer are disrupted.
Claim 6
Independent Claim
80 words
A method of weakening and dissipating the shock and boom waves which are produced principally by the lift of an aircraft traveling at supersonic speeds, which comprises selectively diverting a portion of the exhaust flow from the aircraft''s jet engines downward relative to the normal aft flow thereof and into the shock-wave layer of said aircraft thereby forming a corrugation in said shock-wave layer as it is being formed whereby the boom-producing effects of said shock wave layer are disrupted.
Claim 7
Dependent Claim
23 words
A method in accordance with claim 4 wherein said diverted flow is diverted from a location proximate the lateral axis of said aircraft.
Claim 8
Dependent Claim
22 words
A method in accordance with claim 4 wherein said diverted flow is diverted from proximate the trailing edge of the aircraft''s airfoil.
Claim 9
Independent Claim
39 words
A method of disrupting shock waves formed by a supersonic aircraft which comprises directing a high velocity fluid jet into the area of lowest pressure aft of the aircraft with sufficient force to substantially disrupt the shock wave patterns.
Claim 10
Independent Claim
39 words
A method of disrupting shock waves formed by a supersonic aircraft which comprises directing a high velocity fluid jet into the area of lowest pressure aft of the aircraft with sufficient force to substantially disrupt the shock wave patterns.
Claim 11
Dependent Claim
21 words
A method in accordance with claim 7 wherein said fluid jet comprises the exhaust jet stream of the aircraft''s jet engines.
Claim 12
Dependent Claim
78 words
A jet deflector for the jet engine of a supersonic aircraft comprising a pipe adapted to receive a portion of the jet exhaust from said engine and direct same into the supersonic shock wave formed by said aircraft when flying at supersonic speeds, the deflector being disposed behind a runner member depending from the underside of the aircraft''s airfoil, said runner member adapted to divide the relative wind around the exhaust from said pipe and around said pipe.
Claim 13
Dependent Claim
78 words
A jet deflector for the jet engine of a supersonic aircraft comprising a pipe adapted to receive a portion of the jet exhaust from said engine and direct same into the supersonic shock wave formed by said aircraft when flying at supersonic speeds, the deflector being disposed behind a runner member depending from the underside of the aircraft''s airfoil, said runner member adapted to divide the relative wind around the exhaust from said pipe and around said pipe.
Claim 14
Dependent Claim
84 words
A supersonic aircraft which comprises a fuselage and a supersonic airfoil connected to said fuselage entirely in front thereof, an air inlet completely across the leading edge of said airfoil, jet engines housed within said airfoil, tail pipes for thrust from said engines adjacent the trailing edge of said airfoil, the lateral axis of said aircraft being proximate said tail pipes, and means for adjusting said tail pipes selectively to produce thrust horizontally and at angles downward and obliquely downward relative to said airfoil.
Claim 15
Dependent Claim
84 words
A supersonic aircraft which comprises a fuselage and a supersonic airfoil connected to said fuselage entirely in front thereof, an air inlet completely across the leading edge of said airfoil, jet engines housed within said airfoil, tail pipes for thrust from said engines adjacent the trailing edge of said airfoil, the lateral axis of said aircraft being proximate said tail pipes, and means for adjusting said tail pipes selectively to produce thrust horizontally and at angles downward and obliquely downward relative to said airfoil.
Claim 16
Independent Claim
108 words
The method of greatly reducing and eliminating the kinetic energy losses produced as form and wave drag by aircraft flying at supersonic speeds which consists of first ram compressing the undisturbed air met by the aircraft in an air inlet that extends across and covers the leading edge of a supersonic shaped airfoil and then conducting only the centermost portion of this low velocity compressed air laterally within said air inlet to miss the downstream located fuselage and into thrust producing jet engines housed within said airfoil, the other portion of said ram compressed air conducted straight through said airfoil and straight through other similarly housed jet engines.
Claim 17
Independent Claim
108 words
The method of greatly reducing and eliminating the kinetic energy losses produced as form and wave drag by aircraft flying at supersonic speeds which consists of first ram compressing the undisturbed air met by the aircraft in an air inlet that extends across and covers the leading edge of a supersonic shaped airfoil and then conducting only the centermost portion of this low velocity compressed air laterally within said air inlet to miss the downstream located fuselage and into thrust producing jet engines housed within said airfoil, the other portion of said ram compressed air conducted straight through said airfoil and straight through other similarly housed jet engines.
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) | 1974-08-02 | 1975-02-01 | 1975-08-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-08-02 | 1979-02-01 | 1979-08-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-08-02 | 1983-02-01 | 1983-08-03 | $7700.00 | Window Closed / Lapsed |