Patent US4632341A successfully refreshed from Google Patents.
US4632341A
Expired / Lapsed
US
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Stabilizing force feedback in bio-actuated control systems
Assignee: United States Department of the Air Force
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Filing: 1985-02-06
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Granted: 1986-12-30
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Expires: 2005-02-06
Abstract
Abstract A biomechanical feedback arrangement wherein a varying force tending to improve the neuromotor tracking response of a human subject, particularly in the presence of lateral or front-back G force fields, is added to the test subject input member of a feedback control system. Use of the biomechanical feedback in a high-performance aircraft and in a ground-based simulator apparatus is also disclosed, along with comparison results from simulator testing of human subjects.
Inventors
- 👤 Daniel W. Repperger
- 👤 Donald G. McCollor
- 👤 William G. Gruesbeck
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-23 17:53
CPC Classifications
B; B64; B64C; B64C13/00; B64C13/02; B64C13/04; B64C13/042; B64C13/0421
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
132 words
Aircraft lateral tracking improvement apparatus comprising: aircraft maneuvering controls located adjacent a pilot supporting seat in an aircraft cockpit apparatus; means for conveying a prescribed lateral course to be tracked and a tracking error signal to said pilot; means for generating a signal representing the incurred G force acceleration of said aircraft along an axis lateral of said pilot; means including predetermined twelve to fifteen Hertz frequency agonistic to antagonistic muscle transfer tremor attenuation means for generating a maneuvering control bias electrical signal in response to said lateral G force acceleration signal; and bias force transducer means connected with said maneuvering controls and responsive to said bias electrical signal for applying a muscle tremor attenuation lateral bias force supplementary to one of said agonistic and antagonistic muscle forces to said maneuvering controls.
Claim 2
Dependent Claim
132 words
Aircraft lateral tracking improvement apparatus comprising: aircraft maneuvering controls located adjacent a pilot supporting seat in an aircraft cockpit apparatus; means for conveying a prescribed lateral course to be tracked and a tracking error signal to said pilot; means for generating a signal representing the incurred G force acceleration of said aircraft along an axis lateral of said pilot; means including predetermined twelve to fifteen Hertz frequency agonistic to antagonistic muscle transfer tremor attenuation means for generating a maneuvering control bias electrical signal in response to said lateral G force acceleration signal; and bias force transducer means connected with said maneuvering controls and responsive to said bias electrical signal for applying a muscle tremor attenuation lateral bias force supplementary to one of said agonistic and antagonistic muscle forces to said maneuvering controls.
Claim 3
Dependent Claim
17 words
The apparatus of claim 1 wherein said aircraft cockpit apparatus comprises a single control stick operated aircraft.
Claim 4
Dependent Claim
32 words
The apparatus of claim 2 further including arm restraint means connected with said cockpit apparatus for stabilizing the maneuvering control operating arm of said pilot during occurrence of said G force acceleration.
Claim 5
Dependent Claim
27 words
The apparatus of claim 3 wherein said means for conveying a prescribed course and a tracking error signal to said pilot include visual observation by said pilot.
Claim 6
Dependent Claim
30 words
The apparatus of claim 4 wherein said means for supplying a biasing force is connected to decrease the pilot exertion required during said agonistic to antagonistic muscle pair transfer movements.
Claim 7
Dependent Claim
18 words
The apparatus of claim 5 wherein said biasing force urges said maneuvering controls toward a neutral control position.
Claim 8
Dependent Claim
18 words
The apparatus of claim 1 wherein said aircraft cockpit apparatus is a portion of a flight simulator trainer.
Claim 9
Dependent Claim
21 words
The apparatus of claim 7 wherein said means for conveying in said flight simulator trainer includes an electronically controlled flight display.
Claim 10
Dependent Claim
39 words
The apparatus of claim 8 wherein said signal responsive to incurred G force acceleration is responsive to pilot manipulation of maneuvering controls in said flight simulator and to a simulation of aircraft characteristics in response to said pilot manipulation.
Claim 11
Dependent Claim
29 words
The apparatus of claim 9 wherein said predetermined algorithm includes frequency selective means responsive to a tremor movement signal in the range of 12 to 15 Hertz natural frequency.
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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) | 1989-12-29 | 1990-06-30 | 1990-12-30 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1993-12-29 | 1994-06-30 | 1994-12-30 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1997-12-29 | 1998-06-30 | 1998-12-30 | $7700.00 | Window Closed / Lapsed |