US3554469A
Expired / Lapsed
US
⏱️ 0.0 years remaining
High resolution control system
Assignee: RTX Corp
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Filing: 1969-09-09
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Granted: 1971-01-12
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Expires: 1989-09-09
Abstract
Abstract A high resolution control system for aircraft, such as a helicopter, in which a mechanical control system for translating motion from a pilot operated input member to a remotely located output member has a mechanical connection between the input member and the output member including a walking beam located adjacent the output member and means for providing a second input supplied directly to said walking beam in response to an electrical system producing an error signal by comparing a first signal generated in response to displacement of the input member with a feedback signal generated in response to displacement of the walking beam. The invention described herein was made in the course of or under a contract or subcontract thereunder with the Department of the Navy.
Inventors
- 👤 Robert J Snow
- 👤 Gregory Bochnak
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 16:06
CPC Classifications
B; B64; B64C; B64C27/00; B64C27/32
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
142 words
A high resolution tail rotor pitch control system for helicopters including in combination a first movable input member, a movable output member, means responsive to movement of said input member for providing a first electrical signal, means responsive to movement of said output member for providing a feedback signal, means for comparing said first and feedback signals to provide an error signal, and means responsive to movement of said first movable member and to the error signal for positioning said output member including a differential linkage mechanism, said mechanism including a second input link responsive to said error signal pivoted on fixed aircraft structure, and a walking beam pivoted intermediate its length on said second input member and operatively connected at points spaced from its pivot on said second input link with both said first movable input member and said output member.
Claim 2
Dependent Claim
142 words
A high resolution tail rotor pitch control system for helicopters including in combination a first movable input member, a movable output member, means responsive to movement of said input member for providing a first electrical signal, means responsive to movement of said output member for providing a feedback signal, means for comparing said first and feedback signals to provide an error signal, and means responsive to movement of said first movable member and to the error signal for positioning said output member including a differential linkage mechanism, said mechanism including a second input link responsive to said error signal pivoted on fixed aircraft structure, and a walking beam pivoted intermediate its length on said second input member and operatively connected at points spaced from its pivot on said second input link with both said first movable input member and said output member.
Claim 3
Dependent Claim
132 words
A high resolution tail rotor pitch control system including a pilot operated control member, a tail rotor pitch control servo, a mechanical connection between said member and said servo including a walking beam having a pivotal support adjacent said servo and having an operating connection with said servo on one side and an operating connection with said member on the other side of its pivot, an electrical input sensor responsive to movements of said member an electrical output sensor responsive to movements of said walking beam, means for comparing the electrical outputs of said sensors to obtain an error signal, and means responsive to said error signal for providing a corrective movement of said walking beam to produce a high degree of resolution between the movements of said member and said servo.
Claim 4
Dependent Claim
132 words
A high resolution tail rotor pitch control system including a pilot operated control member, a tail rotor pitch control servo, a mechanical connection between said member and said servo including a walking beam having a pivotal support adjacent said servo and having an operating connection with said servo on one side and an operating connection with said member on the other side of its pivot, an electrical input sensor responsive to movements of said member an electrical output sensor responsive to movements of said walking beam, means for comparing the electrical outputs of said sensors to obtain an error signal, and means responsive to said error signal for providing a corrective movement of said walking beam to produce a high degree of resolution between the movements of said member and said servo.
Claim 5
Dependent Claim
155 words
A high resolution tail rotor pitch control system including a pilot operated member, a tail rotor pitch control servo, a mechanical connection between said member and said servo including a walking beam pivoted adjacent said servo and having an operating connection with said servo on one side and an operatiNg connection with said member on the other side of its pivot, an input sensor responsive to movements of said member having an electrical output, an output sensor responsive to movements of said walking beam having an electrical output, means for comparing the electrical outputs of said sensors to obtain an error signal, a secondary input arm pivoted on fixed aircraft structure having an operative connection with said walking beam, and actuating means for said input arm energized by said error signal providing a corrective movement of said walking beam to produce a high degree of resolution between the movements of said member and said servo.
Claim 6
Dependent Claim
155 words
A high resolution tail rotor pitch control system including a pilot operated member, a tail rotor pitch control servo, a mechanical connection between said member and said servo including a walking beam pivoted adjacent said servo and having an operating connection with said servo on one side and an operatiNg connection with said member on the other side of its pivot, an input sensor responsive to movements of said member having an electrical output, an output sensor responsive to movements of said walking beam having an electrical output, means for comparing the electrical outputs of said sensors to obtain an error signal, a secondary input arm pivoted on fixed aircraft structure having an operative connection with said walking beam, and actuating means for said input arm energized by said error signal providing a corrective movement of said walking beam to produce a high degree of resolution between the movements of said member and said servo.
Claim 7
Dependent Claim
22 words
The control system of claim 3 in which the walking beam is pivotally mounted intermediate its ends on the secondary input arm.
Claim 8
Dependent Claim
162 words
A high resolution tail rotor pitch control system for a helicopter including a pilot operated member, an input sensor operatively connected to said member and having an electrical output proportional to movement of said member, a tail rotor pitch control servo, an output sensor operatively connected to said servo and having an electrical output proportional to movement of said servo, input means providing a mechanical connection between said member and said servo including a differential linkage located adjacent said servo, said linkage including a walking beam and a second input member pivoted at one end on fixed aircraft structure, said walking beam being pivoted intermediate its ends on said second input member at a point spaced from the pivotal support of the latter, a differential amplifier receiving the electrical output from both said sensors and producing therefrom an error signal, and an extensible actuator receiving said error signal and having an operative connection with the free end of said second input member.
Claim 9
Dependent Claim
162 words
A high resolution tail rotor pitch control system for a helicopter including a pilot operated member, an input sensor operatively connected to said member and having an electrical output proportional to movement of said member, a tail rotor pitch control servo, an output sensor operatively connected to said servo and having an electrical output proportional to movement of said servo, input means providing a mechanical connection between said member and said servo including a differential linkage located adjacent said servo, said linkage including a walking beam and a second input member pivoted at one end on fixed aircraft structure, said walking beam being pivoted intermediate its ends on said second input member at a point spaced from the pivotal support of the latter, a differential amplifier receiving the electrical output from both said sensors and producing therefrom an error signal, and an extensible actuator receiving said error signal and having an operative connection with the free end of said second input member.
Claim 10
Dependent Claim
79 words
The control system of claim 5 in which said input means includes a linkage having a pivotal connection to one end of said walking beam remote from the pivotal support for the latter, a spring biased centering mechanism including a cylinder pivotally supported on fixed aircraft structure and a spring biased cylinder rod pivotally connected to said walking beam at a point somewhat closer to the pivot of the latter than the pivot of said linkage on said beam.
References Cited (Backward Citations)
US3228478A
Cited
US3396597A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1974-01-11 | 1974-07-13 | 1975-01-12 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-01-11 | 1978-07-13 | 1979-01-12 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-01-11 | 1982-07-13 | 1983-01-12 | $7700.00 | Window Closed / Lapsed |