Patent US4387430A successfully refreshed from Google Patents.
US4387430A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Pitch stick force inhibit of aircraft automatic outer loop
Assignee: RTX Corp
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Filing: 1981-03-30
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Granted: 1983-06-07
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Expires: 2001-03-30
Abstract
Abstract In an aircraft automatic flight control system, a flight path controlling, full authority outer loop actuator (37) operated in response to the integral (41) of commands thereto, is shutdown (111, 113-115) in response to the sensing (31, 32) of force on the related pilot control member (27). After removal of force (118), the outer loop is continued to be shut down for a time interval (119) to allow the aircraft to resettle toward the trim point before building up error in the integrator, unless high input demand (122) is indicated.
Inventors
- 👤 David J. Verzella
- 👤 William C. Fischer
- 👤 Don L. Adams
- 👤 Stuart C. Wright
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 10:11
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/0055; G05D1/0061
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
209 words
A system for positioning attitude-controlling aerodynamic surfaces in a control axis of an aircraft, comprising: control means responsive to force applied by a pilot to position said aerodynamic surfaces; force means responsive to said control means for providing a force signal indicative of the pilot applying force to said control means; a sensor indicative of a parameter of aircraft flight related to said control axis for providing a parameter signal indicative of the magnitude thereof; actuator means having a full authority outer loop portion and a fast, limited authority inner loop portion and responsive to input command signals applied thereto for positioning said aerodynamic surfaces; and signal processing means connected for response to said sensor and to said force means, for providing a reference signal indicative of a desired magnitude of said parameter, for providing to said actuator means a first command signal indicative of the difference between said parameter signal and said reference signal, and a second command signal indicative of the magnitude and sense of the rate of change of said parameter signal; characterized by said signal processing means comprising means for inhibiting provision of said first command signal to said outer loop portion of said actuator means in response to the presence of said force signal.
Claim 2
Independent Claim
209 words
A system for positioning attitude-controlling aerodynamic surfaces in a control axis of an aircraft, comprising: control means responsive to force applied by a pilot to position said aerodynamic surfaces; force means responsive to said control means for providing a force signal indicative of the pilot applying force to said control means; a sensor indicative of a parameter of aircraft flight related to said control axis for providing a parameter signal indicative of the magnitude thereof; actuator means having a full authority outer loop portion and a fast, limited authority inner loop portion and responsive to input command signals applied thereto for positioning said aerodynamic surfaces; and signal processing means connected for response to said sensor and to said force means, for providing a reference signal indicative of a desired magnitude of said parameter, for providing to said actuator means a first command signal indicative of the difference between said parameter signal and said reference signal, and a second command signal indicative of the magnitude and sense of the rate of change of said parameter signal; characterized by said signal processing means comprising means for inhibiting provision of said first command signal to said outer loop portion of said actuator means in response to the presence of said force signal.
Claim 3
Dependent Claim
38 words
A system according to claim 1 characterized by said signal processing means comprising means for inhibiting provision of said first command signal to said outer loop portion for a period of time following termination of said force signal.
Claim 4
Dependent Claim
19 words
A system according to claim 2 characterized by said period of time being on the order of several seconds.
Claim 5
Dependent Claim
59 words
A system according to claim 2 characterized by said signal processing means comprising means for providing said first command signal to said outer loop portion of said actuator means during said period of time in response to the summation of said first command signal with a function of said second command signal being in excess of a predetermined magnitude.
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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) | 1986-06-06 | 1986-12-06 | 1987-06-07 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1990-06-06 | 1990-12-06 | 1991-06-07 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1994-06-06 | 1994-12-06 | 1995-06-07 | $7700.00 | Window Closed / Lapsed |