US3984070A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Wingtip vortex dissipator for aircraft
Assignee: National Aeronautics and Space Administration
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Filing: 1974-05-24
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Granted: 1976-10-05
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Expires: 1994-05-24
Abstract
Abstract A means for attenuating the vortex created at aircraft wingtips which consists of a retractable planar surface transverse to the airstream and attached downstream of the wingtip which creates a positive pressure gradient just downstream from the wing. The positive pressure forces a break up of the rotational air flow of the vortex.
Inventors
- 👤 James C. Patterson, Jr.
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 22:12
CPC Classifications
B; B64; B64C; B64C23/00; B64C23/06; B64C23/065; Y; Y02; Y02T; Y02T50/00; Y02T50/10
Claims Analysis
Total Claims: 13
Claim 1
Independent Claim
65 words
An apparatus for dissipating a lift-induced vortex generator by an airstream flowing past an aircraft wing having a leading edge and a trailing edge comprising: a positive pressure gradient producing means; said gradient producing means being a drogue structure having a surface transverse to the airstream, and an attachment means of aerodynamic design which attaches said drogue structure downstream of the origin of the vortex.
Claim 2
Independent Claim
65 words
An apparatus for dissipating a lift-induced vortex generator by an airstream flowing past an aircraft wing having a leading edge and a trailing edge comprising: a positive pressure gradient producing means; said gradient producing means being a drogue structure having a surface transverse to the airstream, and an attachment means of aerodynamic design which attaches said drogue structure downstream of the origin of the vortex.
Claim 3
Dependent Claim
27 words
An apparatus for dissipating an aircraft lift-induced vortex as in claim 1 wherein the attachment means includes deployment means for selectively deploying and retracting the drogue structure.
Claim 4
Dependent Claim
21 words
An apparatus for dissipating an aircraft lift induced vortex as in claim 1 wherein the drogue structure is a drogue chute.
Claim 5
Dependent Claim
27 words
An apparatus for dissipating an aircraft lift-induced vortex as in claim 1 wherein the drogue structure is a spline configuration of plates which simulate a planar surface.
Claim 6
Dependent Claim
38 words
An apparatus for dissipating an aircraft lift-induced vortex as in claim 1 wherein the drogue structure has a diameter at least 60% of the mean distance between the leading edge and the trailing edge of the aircraft wing.
Claim 7
Dependent Claim
33 words
An apparatus for dissipating an aircraft lift-induced vortex as in claim 1 wherein the drogue structure is mounted downstream of the wing trailing edge a distance approximating the diameter of the drogue structure.
Claim 8
Dependent Claim
33 words
An apparatus for dissipating an aircraft lift-induced vortex as in claim 5 wherein the drogue structure is mounted downstream of the wing trailing edge a distance approximating the diameter of the drogue structure.
Claim 9
Dependent Claim
33 words
An apparatus for dissipating an aircraft lift-induced vortex as in claim 2 wherein the drogue structure is a spline configuration of plates which simulate a planar surface and wherein each plate is retractable.
Claim 10
Dependent Claim
36 words
An apparatus for dissipating an aircraft lift-induced vortex as in claim 8 wherein the configuration of plates is shaped to form a unitary aerodynamic surface with the attachment means when the configuration of plates is retracted.
Claim 11
Dependent Claim
44 words
An apparatus for dissipating an aircraft lift-induced vortex as in claim 2 wherein the drogue structure is a spline configuration of plates which simulate a planar surface, and wherein each plate is hinged; and wherein the deployment means is an array of actuator means.
Claim 12
Dependent Claim
37 words
An apparatus for dissipating an aircraft lift-induced vortex as in claim 10 wherein the configuration of plates is shaped to form a unitary aerodynamic surface with the attachment means when the configuration of plates are folded down.
Claim 13
Dependent Claim
28 words
An apparatus for dissipating an aircraft lift-induced vortex as in claim 2 including means for covering said deployment means to provide an aerodynamically clean surface when not deployed.
References Cited (Backward Citations)
US2075817A
Cited
US2421870A
Cited
US2612332A
Cited
FR1209801A
Cited
US2678785A
Cited
FR1564026A
Cited
US3596854A
Cited
US3881669A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1979-10-05 | 1980-04-05 | 1980-10-05 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1983-10-05 | 1984-04-05 | 1984-10-05 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1987-10-05 | 1988-04-05 | 1988-10-05 | $7700.00 | Window Closed / Lapsed |