US4247062A
Expired / Lapsed
US
⏱️ 0.0 years remaining
High efficiency vertical tail assembly combined with a variable wing geometry
Assignee: Airbus Defence and Space GmbH
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Filing: 1978-11-27
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Granted: 1981-01-27
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Expires: 1998-11-27
Abstract
Abstract A high efficiency vertical tail unit is combined with a variable wing geory for large angles of attack, primarily for all-wing aircraft such as delta-type craft. The vertical tail unit is hinged for adjustment about an axis substantially parallel to the longitudinal axis of the fuselage. The outer wing portions are connected, at an angle, with a vertical tail unit which is directed vertically downward in its normal position. The assembly comprising an outer wing portion and a vertical tail unit is rotatable about the parallel axis whereby three different wing types may be realized in the same craft.
Inventors
- 👤 Hartmut Brueckner
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 20:22
CPC Classifications
B; B64; B64C; B64C5/00; B64C5/08
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
197 words
A high efficiency vertical tail assembly for an all-wing craft having a longitudinal axis and comprising a fuselage and two wings, said wings defining a common plane extending laterally away from said fuselage, each wing having a respective wing tip, said vertical tail assembly consisting of two identical vertical tail units, one vertical tail unit being provided for each of said wing tips, each vertical tail unit consisting of its wing tip (2) and of a vertical tail surface (1) rigidly connected to the wing tip so as to include a given angle (τ) between the wing tip and the vertical tail surface, whereby in the normal position the wing tip extends in said common plane and the vertical tail surface extends downwardly from said common plane, and pivotal connecting means operatively connecting each vertical tail unit to its wing, said pivotal connecting means having an axis extending substantially in parallel to said longitudinal axis of the craft, whereby each vertical tail unit may be tilted out of said normal position so that the wing tip extends upwardly from said common plane and the vertical tail surface extends in said common plane to form the wing tip.
Claim 2
Dependent Claim
197 words
A high efficiency vertical tail assembly for an all-wing craft having a longitudinal axis and comprising a fuselage and two wings, said wings defining a common plane extending laterally away from said fuselage, each wing having a respective wing tip, said vertical tail assembly consisting of two identical vertical tail units, one vertical tail unit being provided for each of said wing tips, each vertical tail unit consisting of its wing tip (2) and of a vertical tail surface (1) rigidly connected to the wing tip so as to include a given angle (τ) between the wing tip and the vertical tail surface, whereby in the normal position the wing tip extends in said common plane and the vertical tail surface extends downwardly from said common plane, and pivotal connecting means operatively connecting each vertical tail unit to its wing, said pivotal connecting means having an axis extending substantially in parallel to said longitudinal axis of the craft, whereby each vertical tail unit may be tilted out of said normal position so that the wing tip extends upwardly from said common plane and the vertical tail surface extends in said common plane to form the wing tip.
Claim 3
Dependent Claim
13 words
The assembly of claim 1, wherein said given angle (τ) is substantially 90°.
Claim 4
Dependent Claim
66 words
The assembly of claim 1, further comprising drive means arranged in each wing and operatively connected to its respective vertical tail unit consisting of the wing tip (2), the vertical tail surface (1) and the respective pivotal connecting means, for rotating the respective vertical tail unit about an axis (5) extending in the wing substantially at a right angle to the longitudinal axis of the craft.
References Cited (Backward Citations)
US3104079A
Cited
GB934286A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1984-01-27 | 1984-07-28 | 1985-01-27 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-01-27 | 1988-07-28 | 1989-01-27 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-01-27 | 1992-07-28 | 1993-01-27 | $7700.00 | Window Closed / Lapsed |