US4426607A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Differential linkage apparatus for an aircraft series servoactuator apparatus
Assignee: Honeywell Inc
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Filing: 1982-03-12
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Granted: 1984-01-17
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Expires: 2002-03-12
Abstract
Abstract In a servoactuator system for an aircraft, a strapdown series servoactuator having an external linkage assembly is coupled between the pilot's control stick and a control surface member. The external linkage assembly includes a differential link and servo link having specially tapered stop surfaces adapted to be varied in dimensions to accommodate a wide variety of installations, which stop surfaces cooperate with fixed stops on the servoactuator housing whereby to provide a variety of pilot authority limits and series servo authority limits depending upon particular installation requirements.
Inventors
- 👤 Homer D. Black
- 👤 Charles R. Stribley
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-23 15:27
CPC Classifications
B; B64; B64C; B64C13/00; B64C13/24; B64C13/38
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
269 words
A series servoactuator for installation in an aircraft comprising: (a) a servomotor having a housing adapted to be secured to the airframe and coupled between a pilot's control linkage and a control surface linkage and including a servomotor output drive shaft extending from a side wall of said housing, (b) first and second pairs of stop means fixed on said housing side wall, each pair being symmetrically angularly spaced relative to said drive shaft, (c) a servo drive link secured to said drive shaft having first stop engaging surfaces thereon adapted to engage said first pair of housing stop means for limiting the authority of said servomotor, (d) an elongated differential link having one end pivotally mounted on said servo drive link, having its opposite end pivotally connected to said control surface linkage and having an intermediate point thereon pivotally connected to said pilot's control linkage, said differential link having second stop engaging surfaces thereon adapted to engage said second pair of housing stop means for limiting the authority of said pilot's control linkage, said second stop engaging surfaces of said differential link having a contour such that when they engage one or the other of said second housing stop means, any motion of said servo link will result in no effective motion of said differential link and control surface linkage; and said differential link being further characterized in that said second stop engaging surfaces comprise flange means laterally extending from the differential link, the lateral dimension thereof being variable between predetermined values dependent upon the authority limits required by the pilot's control linkage of a particular aircraft installation.
Claim 2
Dependent Claim
269 words
A series servoactuator for installation in an aircraft comprising: (a) a servomotor having a housing adapted to be secured to the airframe and coupled between a pilot's control linkage and a control surface linkage and including a servomotor output drive shaft extending from a side wall of said housing, (b) first and second pairs of stop means fixed on said housing side wall, each pair being symmetrically angularly spaced relative to said drive shaft, (c) a servo drive link secured to said drive shaft having first stop engaging surfaces thereon adapted to engage said first pair of housing stop means for limiting the authority of said servomotor, (d) an elongated differential link having one end pivotally mounted on said servo drive link, having its opposite end pivotally connected to said control surface linkage and having an intermediate point thereon pivotally connected to said pilot's control linkage, said differential link having second stop engaging surfaces thereon adapted to engage said second pair of housing stop means for limiting the authority of said pilot's control linkage, said second stop engaging surfaces of said differential link having a contour such that when they engage one or the other of said second housing stop means, any motion of said servo link will result in no effective motion of said differential link and control surface linkage; and said differential link being further characterized in that said second stop engaging surfaces comprise flange means laterally extending from the differential link, the lateral dimension thereof being variable between predetermined values dependent upon the authority limits required by the pilot's control linkage of a particular aircraft installation.
Claim 3
Dependent Claim
55 words
The series servoactuator as set forth in claim 1 wherein said servo link is further characterized in that said first stop engaging surfaces comprise flange means laterally extending from the servo link, the lateral dimension thereof being variable between predetermined values dependent upon the authority limits required by the servomotor of a particular aircraft installation.
Claim 4
Dependent Claim
51 words
The series servoactuator as set forth in claims 1 and 2 wherein said housing sidewall including said first and second stop means is detachably secured to said servomotor housing and replaceable with another housing sidewall having first and second stop means at different symmetrical angular dispositions relative to said drive shaft.
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) | 1987-01-16 | 1987-07-18 | 1988-01-17 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-01-16 | 1991-07-18 | 1992-01-17 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-01-16 | 1995-07-18 | 1996-01-17 | $7700.00 | Window Closed / Lapsed |