US4032087A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Aircraft spoiler system
Assignee: Individual
•
Filing: 1976-06-03
•
Granted: 1977-06-28
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Expires: 1996-06-03
Abstract
Abstract An aircraft spoiler system consisting of semi-circular rods disposed within the leading edge of an aircraft wing and rotatably carried thereby so that in the inactive position the substantially flat surfaces are flush with the wing surface and in its most active position the flat surfaces are at right angles to the wing surface with approximately half of the rods extending above the wing surface, acting in a manner to eliminate the lift of the wing, i.e., as spoilers. The rods are controlled by a pair of magnetic clutches which connect the spoiler rods to a rotary solenoid when a toggle switch is thrown by the pilot. The spoilers have mechanical spring returns which automatically retract them when the switch is in its "off" position or in the event of a power failure. A retro-fit mounting is provided for fitting the spoilers on existing wing section.
Inventors
- 👤 Prentiss B. Cleaves
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 12:42
CPC Classifications
B; B64; B64C; B64C3/00; B64C3/58
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
178 words
An aircraft spoiler system comprising: a retro-fit mounting having a geometry of a predetermined aircraft wing leading edge, said retro-fit mounting being fixedly attached to the leading edge of an aircraft wing providing an extension thereof; at least one spoiler rod having one substantially flat surface portion, said at least one spoiler rod disposed within said retro-fit mounting and rotatably carried thereby, said spoiler rod having a geometry for being flush with the surface of said retro-fit mounting on one extreme rotative position; a control system disposed within said retro-fit mounting for controlling the axial rotative position of said at least one spoiler rod, said control system including a switch operated rotary solenoid having a rotational mechanical output, said rotary solenoid being operable for rotating said mechanical output incrementally when electrically energized, at least one electrically operated clutch coupled to said rotary solenoid output, said at least one electrically operated clutch being mechanically coupled to said at least one spoiler rod; and switch means electrically coupled to said rotary solenoid and said electrically operated clutch for actuation thereof.
Claim 2
Dependent Claim
178 words
An aircraft spoiler system comprising: a retro-fit mounting having a geometry of a predetermined aircraft wing leading edge, said retro-fit mounting being fixedly attached to the leading edge of an aircraft wing providing an extension thereof; at least one spoiler rod having one substantially flat surface portion, said at least one spoiler rod disposed within said retro-fit mounting and rotatably carried thereby, said spoiler rod having a geometry for being flush with the surface of said retro-fit mounting on one extreme rotative position; a control system disposed within said retro-fit mounting for controlling the axial rotative position of said at least one spoiler rod, said control system including a switch operated rotary solenoid having a rotational mechanical output, said rotary solenoid being operable for rotating said mechanical output incrementally when electrically energized, at least one electrically operated clutch coupled to said rotary solenoid output, said at least one electrically operated clutch being mechanically coupled to said at least one spoiler rod; and switch means electrically coupled to said rotary solenoid and said electrically operated clutch for actuation thereof.
Claim 3
Dependent Claim
44 words
The aircraft spoiler system of Claim 1 and further including: a limit switch electrically coupled between said switch means and said rotary solenoid for disabling said rotary solenoid when said at least one spoiler rod has been rotated in a predetermined number of degrees.
Claim 4
Dependent Claim
105 words
An aircraft spoiler system comprising: a retro-fit mounting having a geometry of a predetermined aircraft wing leading edge, said retro-fit mounting being fixedly attached to the leading edge of an aircraft wing providing an extension thereof; at least one spoiler rod having one substantially flat surface portion, said at least one spoiler rod disposed within said retro-fit mounting and rotatably carried thereby, said spoiler rod having a geometry for being flush with the surface of said retro-fit mounting in one extreme rotative position; and a control system disposed within said retro-fit mounting for controlling the axial rotative position of said at least one spoiler rod.
Claim 5
Dependent Claim
105 words
An aircraft spoiler system comprising: a retro-fit mounting having a geometry of a predetermined aircraft wing leading edge, said retro-fit mounting being fixedly attached to the leading edge of an aircraft wing providing an extension thereof; at least one spoiler rod having one substantially flat surface portion, said at least one spoiler rod disposed within said retro-fit mounting and rotatably carried thereby, said spoiler rod having a geometry for being flush with the surface of said retro-fit mounting in one extreme rotative position; and a control system disposed within said retro-fit mounting for controlling the axial rotative position of said at least one spoiler rod.
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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) | 1980-06-27 | 1980-12-27 | 1981-06-28 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-06-27 | 1984-12-27 | 1985-06-28 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-06-27 | 1988-12-27 | 1989-06-28 | $7700.00 | Window Closed / Lapsed |