US3584813A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Airfoil bridle apparatus
Assignee: Individual
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Filing: 1968-06-26
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Granted: 1971-06-15
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Expires: 1988-06-26
Abstract
Abstract The present invention relates to a bridle assembly for use with a semirigid airfoil supported by an aircraft fuselage. The airfoil includes a spar defining a rigid leading edge, a cable defining a trailing edge, and flexible material interconnecting the spar and cable and defining a spanwise camber distribution. The bridle assembly includes at least one bridle cable secured to the airfoil trailing edge cable, with the assembly being secured in tension to the fuselage, to create tension in the airfoil flexible material and retard changes in its camber distribution.
Inventors
- 👤 Thomas E Sweeney
- 👤 Robert A Ormiston
- 👤 Walter Barry Nixon
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 00:47
CPC Classifications
B; B64; B64C; B64C3/00; B64C3/38; Y; Y02; Y02T; Y02T50/00; Y02T50/10
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
84 words
Apparatus for an aircraft having a fuselage comprising: an airfoil supported by the fuselage, said airfoil including a rigid leading edge, a cable defining a trailing edge, and flexible material interconnecting the leading and trailing edges defining n initial airfoil chamber distribution along the length thereof and for the eNtire distance between said leading and trailing edges; and means for retarding changes in said camber distribution during flight conditions including at least one means in tension connected to said cable defining said trailing edge.
Claim 2
Dependent Claim
84 words
Apparatus for an aircraft having a fuselage comprising: an airfoil supported by the fuselage, said airfoil including a rigid leading edge, a cable defining a trailing edge, and flexible material interconnecting the leading and trailing edges defining n initial airfoil chamber distribution along the length thereof and for the eNtire distance between said leading and trailing edges; and means for retarding changes in said camber distribution during flight conditions including at least one means in tension connected to said cable defining said trailing edge.
Claim 3
Dependent Claim
45 words
Apparatus according to claim 1, wherein said airfoil cable extends between a tip end of said airfoil and a root end, said retarding means comprising a bridle assembly including at least one bridle cable having an end thereof secured to the airfoil trailing edge cable.
Claim 4
Dependent Claim
95 words
Apparatus for an aircraft having a fuselage comprising: an airfoil supported by the fuselage, said airfoil including a rigid leading edge, a cable extending between a tip end of said airfoil and a root end defining a trailing edge, and flexible material interconnecting the leading and trailing edges defining an initial airfoil camber distribution along the length thereof; and means for retarding changes in said camber distribution during flight conditions, said retarding means comprising a bridle assembly including at least one bridle cable secured in tension between the airfoil trailing edge cable and the fuselage.
Claim 5
Dependent Claim
95 words
Apparatus for an aircraft having a fuselage comprising: an airfoil supported by the fuselage, said airfoil including a rigid leading edge, a cable extending between a tip end of said airfoil and a root end defining a trailing edge, and flexible material interconnecting the leading and trailing edges defining an initial airfoil camber distribution along the length thereof; and means for retarding changes in said camber distribution during flight conditions, said retarding means comprising a bridle assembly including at least one bridle cable secured in tension between the airfoil trailing edge cable and the fuselage.
Claim 6
Dependent Claim
131 words
Apparatus for an aircraft having a fuselage, comprising: a fuselage having a central longitudinal axis, an airfoil having a wing tip and being supported by the fuselage, said airfoil including a rigid spar defining a leading edge of the airfoil, a cable extending from a root point at the fuselage at one end thereof to said wing tip at its opposite end, said cable defining a trailing edge of the airfoil, and flexible material interconnecting the leading and trailing edges and defining a variable aerodynamic airfoil form between said leading and trailing edges; and means including a force transmitting means connected between said airfoil trailing edge and said fuselage for inducing a tension in said material in a direction substantially parallel to said axis to control the camber of the airfoil.
Claim 7
Dependent Claim
131 words
Apparatus for an aircraft having a fuselage, comprising: a fuselage having a central longitudinal axis, an airfoil having a wing tip and being supported by the fuselage, said airfoil including a rigid spar defining a leading edge of the airfoil, a cable extending from a root point at the fuselage at one end thereof to said wing tip at its opposite end, said cable defining a trailing edge of the airfoil, and flexible material interconnecting the leading and trailing edges and defining a variable aerodynamic airfoil form between said leading and trailing edges; and means including a force transmitting means connected between said airfoil trailing edge and said fuselage for inducing a tension in said material in a direction substantially parallel to said axis to control the camber of the airfoil.
Claim 8
Dependent Claim
133 words
Apparatus for an aircraft having a fuselage, comprising: a fuselage having a central longitudinal axis, an airfoil having a wing tip and being supported by the fuselage, said airfoil including a rigid spar defining a leading edge of the airfoil, a cable extending from a root point at the fuselage at one end thereof to said wing tip at its opposite end, said cable defining a trailing edge of the airfoil, and flexible material interconnecting the leading and trailing edges and defining an aerodynamic airfoil form; and a bridle assembly including a plurality of interconnected cables, said bridle assembly secured in tension at one end to said trailing edge cable and at its opposite end to said fuselage for inducing a tension in said material in a direction substantially parallel to said axis.
Claim 9
Dependent Claim
133 words
Apparatus for an aircraft having a fuselage, comprising: a fuselage having a central longitudinal axis, an airfoil having a wing tip and being supported by the fuselage, said airfoil including a rigid spar defining a leading edge of the airfoil, a cable extending from a root point at the fuselage at one end thereof to said wing tip at its opposite end, said cable defining a trailing edge of the airfoil, and flexible material interconnecting the leading and trailing edges and defining an aerodynamic airfoil form; and a bridle assembly including a plurality of interconnected cables, said bridle assembly secured in tension at one end to said trailing edge cable and at its opposite end to said fuselage for inducing a tension in said material in a direction substantially parallel to said axis.
Claim 10
Dependent Claim
37 words
Aircraft apparatus according to claim 5, wherein said bridle assembly comprises two cables secured to said trailing edge cable at two spaced points for biasing the trailing edge cable rearwardly and downwardly with respect to said airfoil.
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) | 1974-06-14 | 1974-12-14 | 1975-06-15 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-06-14 | 1978-12-14 | 1979-06-15 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-06-14 | 1982-12-14 | 1983-06-15 | $7700.00 | Window Closed / Lapsed |