US3794274A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Aircraft structure to reduce sonic boom intensity
Assignee: Individual
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Filing: 1969-12-19
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Granted: 1974-02-26
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Expires: 1989-12-19
Abstract
Abstract The structure of a fuselage of an aircraft having a plurality of apertures therein which permit high pressure air to be received within the confines of the exterior portion of said fuselage, and means within said fuselage adapted to direct and control the flow of said air until the energy thereof has been substantially reduced or same is emitted through carefully situated ports. The effective cross-sectional area of the nose portion of said fuselage is thereby substantially reduced so as to cause a similar reduction of the drag upon said aircraft.
Inventors
- 👤 O Eknes
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-09 23:12
CPC Classifications
B; B64; B64C; B64C23/00; B64C23/04
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
176 words
An aircraft adapted to fly faster than the speed of sound, said aircraft comprising: a fuselage having an outer surface and an inner surface coincident therewith but separated therefrom; means adapted to structurally connect said outer and inner surfaces so that said surfaces define a passageway for the streamflow of air, which passageway terminates at the tail portion of said aircraft; a plurality of apertures at the nose portion of said outer surface and situated thereon in such a manner as not to unduly interfere with the soundness of the aerodynamic structure of said aircraft; hollow channels provided within the wings of said aircraft and adapted to connect said passageway to engine compressors carried by said wings; valves integral within said channels and adapted to control the flow of air therethrough to said compressors, which air has theretofore entered the said passageway through said apertures from the exterior of said aircraft; and an exit port provided in the tail portion of said aircraft and adapted to permit the controlled discharge of the streamflow of air therefrom.
Claim 2
Dependent Claim
176 words
An aircraft adapted to fly faster than the speed of sound, said aircraft comprising: a fuselage having an outer surface and an inner surface coincident therewith but separated therefrom; means adapted to structurally connect said outer and inner surfaces so that said surfaces define a passageway for the streamflow of air, which passageway terminates at the tail portion of said aircraft; a plurality of apertures at the nose portion of said outer surface and situated thereon in such a manner as not to unduly interfere with the soundness of the aerodynamic structure of said aircraft; hollow channels provided within the wings of said aircraft and adapted to connect said passageway to engine compressors carried by said wings; valves integral within said channels and adapted to control the flow of air therethrough to said compressors, which air has theretofore entered the said passageway through said apertures from the exterior of said aircraft; and an exit port provided in the tail portion of said aircraft and adapted to permit the controlled discharge of the streamflow of air therefrom.
Claim 3
Dependent Claim
54 words
An aircraft structure as defined in claim 1 above, wherein the tail portion of said aricraft is substantially removed relative to the passenger and baggage area of said aircraft so that an expansion chamber is formed therebetween resulting in a substantial pressure differential within said passageway between the nose portion and exit port thereof.
Claim 4
Dependent Claim
43 words
An aircraft structure as defined in claim 1 above, wherein the said exit port is established in such a manner as to direct the streamflow of air therefrom in a predetermined direction relative to the longitudinal and horizontal axes of the said aircraft.
Claim 5
Dependent Claim
38 words
An aircraft structure as defined in claim 3 above, wherein the said exit port is established in such a manner as to be adapted to direcT the streamflow of air therefrom in various directions at any particular time.
Claim 6
Dependent Claim
58 words
An aircraft structure as defined in claim 3 above, wherein the said outlet ports are placed in the tail portion of said aircraft and substantially removed from the passenger or baggage areas thereof so that an expansion chamber is formed thereby which results in a substantial pressure differential within said passageway between said nose portion and said ports.
Claim 7
Dependent Claim
65 words
An aircraft structure as defined in claim 1 above, wherein an additional surface is provided conincidentally with and between said outer surface and inner surface so that two passageways are defined within said aircraft, one passageway for reception of the streamflow of air through the said apertures of said nose portion, and the other passageway for reception of high pressure air from the said fuselage.
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) | 1977-02-25 | 1977-08-27 | 1978-02-26 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-02-25 | 1981-08-27 | 1982-02-26 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-02-25 | 1985-08-27 | 1986-02-26 | $7700.00 | Window Closed / Lapsed |