US4470569A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Locking, redundant slat drive mechanism
Assignee: McDonnell Douglas Corp
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Filing: 1981-12-28
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Granted: 1984-09-11
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Expires: 2001-12-28
Abstract
Abstract A slat system in which the slats are supported on tracks and the slats are actuated by a simple bell crank linkage oriented so that its plane of motion is parallel to the wing chord reference plane. The mechanism retracts to a collapsed over-center position and extends to an over-center position so as to lock the slat into the retract or extend positions. Each slat segment is driven by two identical mechanisms tied together by a synchronization link which provides redundancy. Either actuator can drive the surface alone, as the second actuator is driven through the synchronization lever, in case of power loss to the second actuator.
Inventors
- 👤 James R. Shaffer
- 👤 Louis T. Kramer
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 08:22
CPC Classifications
B; B64; B64C; B64C9/00; B64C9/14; B64C9/22
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
340 words
An aircraft wing having internal structure, a leading edge slat support and actuation system for extending the slat segments from a stowed position to an extend position, comprising: a pair of tracks mounted in parallel, spanwise spaced relationship for chordwise movement and attached at the leading end to said slat segment; a base fitting attached to said wing structure; a bell crank pivotally attached at one end to said base fitting; a push rod pivotally attached at a point at the free end of said bell crank and connected to said slat segment so that in the full extend position of said slat, the center of said point attaching said push rod to said bell crank is positioned past a line drawn between the center of the attach point of said push rod to said slat and the center of the attach point of said bell crank to said base fitting, whereby said actuation system for extending the slat segments is in an over-center position to mechanically lock said actuation system in the extend position; a linkage assembly formed by a first link and second link pivotally attached to form an intermediate hinge and said intermediately hinged first and second links pivotally attached between said bell crank and said base fitting so that when said slat system is in the full retract position said intermediate hinge point lies on the side in the direction of further retraction of said slat mechanism from a line drawn between the two attach points of said intermediately hinged first and second links to said bell crank and said base fitting whereby said intermediately hinged first and second links are in an over-center position to mechanically lock said mechanism in the retract position; and an actuator connected between said base fitting and said bell crank whereby extension of said actuator rotates said bell crank, extending said push rod which is attached to said slat segment, causing said slat segment to translate on said track and having over-center locking provisions in both retract and extend positions.
Claim 2
Dependent Claim
340 words
An aircraft wing having internal structure, a leading edge slat support and actuation system for extending the slat segments from a stowed position to an extend position, comprising: a pair of tracks mounted in parallel, spanwise spaced relationship for chordwise movement and attached at the leading end to said slat segment; a base fitting attached to said wing structure; a bell crank pivotally attached at one end to said base fitting; a push rod pivotally attached at a point at the free end of said bell crank and connected to said slat segment so that in the full extend position of said slat, the center of said point attaching said push rod to said bell crank is positioned past a line drawn between the center of the attach point of said push rod to said slat and the center of the attach point of said bell crank to said base fitting, whereby said actuation system for extending the slat segments is in an over-center position to mechanically lock said actuation system in the extend position; a linkage assembly formed by a first link and second link pivotally attached to form an intermediate hinge and said intermediately hinged first and second links pivotally attached between said bell crank and said base fitting so that when said slat system is in the full retract position said intermediate hinge point lies on the side in the direction of further retraction of said slat mechanism from a line drawn between the two attach points of said intermediately hinged first and second links to said bell crank and said base fitting whereby said intermediately hinged first and second links are in an over-center position to mechanically lock said mechanism in the retract position; and an actuator connected between said base fitting and said bell crank whereby extension of said actuator rotates said bell crank, extending said push rod which is attached to said slat segment, causing said slat segment to translate on said track and having over-center locking provisions in both retract and extend positions.
Claim 3
Dependent Claim
28 words
The aircraft wing leading edge slat system of claim 1 further comprising a biasing means to bias said intermediately hinged first and second links in said over-center position.
Claim 4
Dependent Claim
63 words
The aircraft wing leading edge slat system of claim 2 wherein there are at least two essentially similar linkage mechanisms spaced between said pair of tracks and said at least two linkage mechanisms are tied together by a synchronizing link whereby powered actuation of one linkage mechanism drives all remaining linkage mechanisms even though the remaining linkage mechanisms have lost their power sources.
Claim 5
Dependent Claim
30 words
The aircraft wing leading edge slat system of claim 3 wherein each of said actuators driving each of said linkage mechanisms is powered from independent sources to provide further redundancy.
Claim 6
Dependent Claim
34 words
The aircraft wing leading edge slat system of claim 1 or 2 wherein said push rod is provided with self-aligning means at both ends and means to adjust the length of said push rod.
Claim 7
Dependent Claim
21 words
The aircraft wing leading edge slat system of claim 1 wherein said pair of tracks supporting said slat segments are curved.
Claim 8
Dependent Claim
29 words
The aircraft wing leading edge slat system of claim 1 further comprising a stop to limit the travel of said hinged first and second links in the over-center position.
References Cited (Backward Citations)
US1653903A
Cited
US2218114A
Cited
US2282516A
Cited
US2298264A
Cited
US3486720A
Cited
GB2073681A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1987-09-11 | 1988-03-12 | 1988-09-11 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-09-11 | 1992-03-12 | 1992-09-11 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-09-11 | 1996-03-12 | 1996-09-11 | $7700.00 | Window Closed / Lapsed |