Patent US4477043A successfully refreshed from Google Patents.
US4477043A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Biodynamic resistant control stick
Assignee: United States, UNITED STATES AIR FORCE THE, Secretary of
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Filing: 1982-12-15
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Granted: 1984-10-16
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Expires: 2002-12-15
Abstract
Abstract An improvement to an aircraft control stick is disclosed. Movement of an aircraft may generate a force which undesirably causes the aircraft pilot to deflect the aircraft's control stick, which thereby results in the aircraft deviating from the desired flight path. The present invention includes a processor-based system which employs an algorithm that generates a signal for causing the control stick to resist such forces. The invention includes a spring and damper connected to the control stick so that the spring constant and damping ratio may be varied.
Inventors
- 👤 Daniel W. Repperger
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 11:50
CPC Classifications
G; G05; G05G; G05G9/00; G05G9/02; G05G9/04; G05G9/047; B; B64; B64C; B64C13/00; B64C13/02; B64C13/04; B64C13/042; B64C13/0421; G05G2009/04766
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
220 words
An aircraft control system which comprises: (a) a pilot operable member pivotally connected to the aircraft and adapted so that movement thereof causes deflection of control surfaces of the aircraft; (b) a force sensor connected to the aircraft for generating a force signal proportional to a given force acting on the aircraft; (c) a processor embodying an algorithm capable of translating said force signal representing said given force acting on said aircraft into a processed signal representing a resistant force correlated with a particular biodynamic force generated by the aircraft pilot's arm on said pilot operable member due to said given force on said aircraft, said processor, upon receiving said force signal from said force sensor, being capable of performing said translation and generating said processed signal; (d) resilient means connected to the aircraft and to said pilot operable member; and (e) an actuator connected to the aircraft and to said pilot operable member by said resilient means, said actuator being capable of receiving said processed signal and, in response to said signal, of adjusting said resilient means so as to impose said resistant force upon said pilot operable member and null out said biodynamic force acting on said member induced by the action of said given force on the aircraft, as exerted through the arm of the aircraft pilot.
Claim 2
Dependent Claim
220 words
An aircraft control system which comprises: (a) a pilot operable member pivotally connected to the aircraft and adapted so that movement thereof causes deflection of control surfaces of the aircraft; (b) a force sensor connected to the aircraft for generating a force signal proportional to a given force acting on the aircraft; (c) a processor embodying an algorithm capable of translating said force signal representing said given force acting on said aircraft into a processed signal representing a resistant force correlated with a particular biodynamic force generated by the aircraft pilot's arm on said pilot operable member due to said given force on said aircraft, said processor, upon receiving said force signal from said force sensor, being capable of performing said translation and generating said processed signal; (d) resilient means connected to the aircraft and to said pilot operable member; and (e) an actuator connected to the aircraft and to said pilot operable member by said resilient means, said actuator being capable of receiving said processed signal and, in response to said signal, of adjusting said resilient means so as to impose said resistant force upon said pilot operable member and null out said biodynamic force acting on said member induced by the action of said given force on the aircraft, as exerted through the arm of the aircraft pilot.
Claim 3
Dependent Claim
21 words
The control system of claim 1 which further includes a damper connected to the aircraft and to said pilot operable member.
Claim 4
Dependent Claim
45 words
The system of claim 2 wherein said damper has a variable damping coefficient, and wherein said processor is adapted to produce a damping signal, said damper being adapted to receive said damping signal and to vary its damping coefficient in response to said damping signal.
Claim 5
Dependent Claim
57 words
The control system of claim 1 wherein said resilient means is connected to said pilot operable member at its midpoint and wherein said actuator is connected to said resilient means, at its opposite ends, thereby permitting said actuator to vary the resistant force of said resilient means causing the pilot operable member to resist the biodynamic force.
Claim 6
Dependent Claim
32 words
The control system of claim 4 wherein said resilient means is a spring and said resilient force is determined by a spring constant setting of said spring as adjusted by said actuator.
References Cited (Backward Citations)
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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) | 1987-10-16 | 1988-04-16 | 1988-10-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-10-16 | 1992-04-16 | 1992-10-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-10-16 | 1996-04-16 | 1996-10-16 | $7700.00 | Window Closed / Lapsed |