US3883093A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Aircraft control elements
Assignee: Airbus Group SAS
•
Filing: 1972-02-02
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Granted: 1975-05-13
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Expires: 1992-02-02
Abstract
Abstract An aircraft control element which is a rigid flap secured to a longitudinal portion of a wing by at least one axially disposed elongated torsion element. The torsion element has rigid end parts and a twistable center with one end part rigidly secured to the flap and the other end part secured to aircraft structure.
Inventors
- 👤 Andre Violleau
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 19:21
CPC Classifications
B; B64; B64C; B64C9/00; B64C9/02; Y; Y02; Y02T; Y02T50/00; Y02T50/40; Y10; Y10T; Y10T428/00; Y10T428/24; Y10T428/24149
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
65 words
In an aircraft control element attached to an aircraft structure comprising at least one flap pivoting around an axis pArallel to its span, the improvement that the flap is rigidly secured to a longitudinal portion of at least two symmetrically, axially disposed elongated torsion elements, another longitudinal portion of each such element being separate from the first portion and rigidly secured to the aircraft structure.
Claim 2
Dependent Claim
65 words
In an aircraft control element attached to an aircraft structure comprising at least one flap pivoting around an axis pArallel to its span, the improvement that the flap is rigidly secured to a longitudinal portion of at least two symmetrically, axially disposed elongated torsion elements, another longitudinal portion of each such element being separate from the first portion and rigidly secured to the aircraft structure.
Claim 3
Dependent Claim
23 words
The improved element of claim 1, wherein the elongated elements are each cylindrical and received in a correspondingly shaped channel in the flap.
Claim 4
Dependent Claim
45 words
The improved element of claim 2, wherein the elongated elements are each tubular and each has rigid portions enabling it to be secured to the flap and to the structure respectively, the rigid portions of each element being separated by at least one twistable portion.
Claim 5
Dependent Claim
38 words
The improved element of claim 3 wherein the flap is rigidly secured to the inner ends of two elongated tubular elements whose rigid outer ends project beyond the flap and engage in the channel with the aircraft structure.
Claim 6
Dependent Claim
34 words
The improved element of claim 4, wherein the tubular elongated elements are identical and a lever for operating the control element is secured thereto at the centre of the span of the control element.
Claim 7
Dependent Claim
44 words
The improved element of claim 4, wherein the channel diameter is similar to the diameter of the tubular elements and the channel has at its ends a sealing element between each of the rigid ends of the tubular element and the channel inside wall.
Claim 8
Dependent Claim
15 words
The improved element of claim 2 wherein the channel is provided inside a flap-reinforcing stringer.
Claim 9
Dependent Claim
27 words
The improved element of claim 7, wherein the stringer consists of two halves which are assembled together and each of which is formed with a hemi-cylindrical recess.
Claim 10
Dependent Claim
41 words
The improved element of claim 7, wherein the flap consists of elements cut from blocks of cellular substance which are assembled to the stringer, an assembly of stringer halves, and said cellular substance elements being made rigid by a stuck-on cladding.
Claim 11
Dependent Claim
31 words
The improved element of claim 1, wherein the elongated torsion elements comprise mineral fibres formed by mineral filaments agglomerated by a polymerisable resin, the fibres being agglomerated by a cross-linked elastomer.
Claim 12
Dependent Claim
20 words
The improved element of claim 1, wherein the elongated torsion elements comprise high-strength metal wires agglomerated by a cross-linked elastomer.
Claim 13
Dependent Claim
43 words
The improved element of claim 10, wherein the fibres extend over the whole length of each of the elongated torsion elements, and rigid portions attaching said flap to the aircraft structure are formed by local agglomeration of the fibres by a polymerisable resin.
Claim 14
Dependent Claim
13 words
The improved element of claim 12, wherein said rigid portions include annular elements.
Claim 15
Dependent Claim
44 words
The improved element of claim 11, wherein the wires extend over the whole length of each of the elongated torsion elements and rigid portions attaching said flap to the aircraft structure are produced by local agglomeration of the metal wires by a polymerisable resin.
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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) | 1978-05-12 | 1978-11-11 | 1979-05-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-05-12 | 1982-11-11 | 1983-05-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-05-12 | 1986-11-11 | 1987-05-13 | $7700.00 | Window Closed / Lapsed |