Patent US4387431A successfully refreshed from Google Patents.
US4387431A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Roll attitude 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 (FIG. 4) the application of force to a control member (35R, FIG. 5) forces (222, 216, 217, 212, 213) the flight path controlling, full authority outer loop to be disengaged. Once disengaged by force, the outer loop remains disengaged (224) until force is removed (225) and a signal indicates (226) a need to reestablish the outer loop. Reestablishment may be indicated by beeping (228) or by the controlled attitude (54R, 55R) being restored to within a predetermined level (230).
Inventors
- 👤 Stuart C. Wright
- 👤 Don L. Adams
- 👤 William C. Fischer
- 👤 David J. Verzella
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 07:49
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/08; G05D1/0808; G05D1/0858
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
233 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 said force means, for providing a parameter reference signal indicative of the flight parameter desired for the aircraft in said control axis, 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 and indefinitely after termination of said force signal until said first command signal is less than a predetermined magnitude.
Claim 2
Independent Claim
233 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 said force means, for providing a parameter reference signal indicative of the flight parameter desired for the aircraft in said control axis, 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 and indefinitely after termination of said force signal until said first command signal is less than a predetermined magnitude.
Claim 3
Dependent Claim
27 words
A system according to claim 1 characterized by said predetermined magnitude being on the order of a few percent of the full authority of said actuator means.
Claim 4
Dependent Claim
88 words
A system according to claim 1 including beeper means selectively operable by the pilot of the aircraft to provide a beep signal indicative of a selected direction of desired change in said flight parameter, characterized by said signal processing means comprising means for adjusting said parameter reference signal at a substantially constant rate in a direction corresponding to the direction indicated by said beep signal, and for inhibiting provision of said first command signal indefinitely after termination of said force signal until the presence of said beep signal.
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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 |