US4267990A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Method for steering an aircraft
Assignee: Airbus Defence and Space GmbH
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Filing: 1978-11-09
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Granted: 1981-05-19
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Expires: 1998-11-09
Abstract
Abstract The present aircraft steering method makes use of additional lift gained byontrolling the separating of vortical flows from the leading edges of the wings for the purpose of controlling the aircraft about its pitch axis, its roll axis, and its yaw axis. The vortical flows are selectively or differentially separated from the leading edge of the wings by raising or lowering leading edge flaps and/or blowing a flowing medium over the wing surfaces substantially in parallel to the leading edge.
Inventors
- 👤 Werner Staudacher
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 17:53
CPC Classifications
B; B64; B64C; B64C23/00; B64C23/06; B64C9/00; Y; Y02; Y02T; Y02T50/00; Y02T50/10
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
129 words
A method for steering an aircraft having a fuselage and two wings, by controlling the separation of vortical air flow at the leading edge of said wings by blowing means, comprising the steps of providing position variable blowing means in the aircraft fuselage adjacent to the leading edge of both wings whereby the angle of the blowing direction may be varied relative to a line extending perpendicularly to the roll axis of the aircraft fuselage, blowing a flowing medium laterally outwardly from said blowing means over said aircraft wings substantially in parallel to said leading edge of said aircraft wings, and differentially controlling the angular position of said blowing means whereby said aircraft may be controlled with respect to its roll axis, its pitch axis, and its yaw axis.
Claim 2
Independent Claim
129 words
A method for steering an aircraft having a fuselage and two wings, by controlling the separation of vortical air flow at the leading edge of said wings by blowing means, comprising the steps of providing position variable blowing means in the aircraft fuselage adjacent to the leading edge of both wings whereby the angle of the blowing direction may be varied relative to a line extending perpendicularly to the roll axis of the aircraft fuselage, blowing a flowing medium laterally outwardly from said blowing means over said aircraft wings substantially in parallel to said leading edge of said aircraft wings, and differentially controlling the angular position of said blowing means whereby said aircraft may be controlled with respect to its roll axis, its pitch axis, and its yaw axis.
Claim 3
Dependent Claim
37 words
The method of claim 1, wherein said differential controlling of the angular position of said blowing means occurs substantially symmetrically relative to said roll axis and in combination with differentially controlling the magnitude of the blowing impulse.
Claim 4
Dependent Claim
37 words
The method of claim 1, wherein said differential controlling of the angular position of said blowing means occurs substantially non-symmetrically relative to said roll axis and in combination with differentially controlling the magnitude of the blowing impulse.
Claim 5
Independent Claim
196 words
A method for steering an aircraft having a fuselage and two wings, by controlling the separation of vortical air flow from the leading edge of said wings, comprising the steps of securing leading edge flap means with a rear edge thereof to a respective hinging axis along the leading edge of each of said wings for a differentiable up and down movement of said leading edge flap means relative to a horizontal plane extending through said hinging axis, providing position variable blowing means in the aircraft fuselage adjacent to the leading edge of both wings whereby the angle of the blowing direction may be varied relative to a line extending perpendicularly to the roll axis of the aircraft fuselage when blowing a flowing medium laterally outwardly from said fuselage across the surfaces of each of said wings, activating said leading edge flap means up or down relative to the horizontal, activating said blowing means to blow said flowing medium over said aircraft wings substantially in parallel to the leading edge of said wings and differentially controlling both said activating operations for steering the aircraft relative to its roll axis, its pitch axis, and its yaw axis.
Claim 6
Independent Claim
196 words
A method for steering an aircraft having a fuselage and two wings, by controlling the separation of vortical air flow from the leading edge of said wings, comprising the steps of securing leading edge flap means with a rear edge thereof to a respective hinging axis along the leading edge of each of said wings for a differentiable up and down movement of said leading edge flap means relative to a horizontal plane extending through said hinging axis, providing position variable blowing means in the aircraft fuselage adjacent to the leading edge of both wings whereby the angle of the blowing direction may be varied relative to a line extending perpendicularly to the roll axis of the aircraft fuselage when blowing a flowing medium laterally outwardly from said fuselage across the surfaces of each of said wings, activating said leading edge flap means up or down relative to the horizontal, activating said blowing means to blow said flowing medium over said aircraft wings substantially in parallel to the leading edge of said wings and differentially controlling both said activating operations for steering the aircraft relative to its roll axis, its pitch axis, and its yaw axis.
Claim 7
Dependent Claim
40 words
The method of claim 4, wherein said controlling of said leading edge flap means is performed substantially symmetrically relative to the respective wing and wherein said controlling of said blowing is also performed substantially symmetrically relative to the respective wing.
Claim 8
Dependent Claim
39 words
The method of claim 4, wherein said controlling of said leading edge flap means is performed substantially symmetrically relative to said leading edge and wherein said controlling of said blowing is performed substantially unsymmetrically relative to the respective wing.
Claim 9
Dependent Claim
39 words
The method of claim 4, wherein said controlling of said leading edge flap means is performed substantially unsymmetrically relative to said leading edge, and wherein said controlling of said blowing is performed substantially symmetrically relative to the respective wing.
Claim 10
Dependent Claim
39 words
The method of claim 4, wherein said controlling of said leading edge flap means is performed substantially unsymmetrically relative to said leading edge, and wherein said controlling of said blowing is performed substantially unsymmetrically relative to the respective wing.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1984-05-18 | 1984-11-17 | 1985-05-19 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-05-18 | 1988-11-17 | 1989-05-19 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-05-18 | 1992-11-17 | 1993-05-19 | $7700.00 | Window Closed / Lapsed |