US4387432A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Pulsed aircraft actuator
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, proportional commands (54, 55) provided to fast, limited authority inner loop actuators (12, 13) are integrated (41), and when the integrator output indicates that the inner loop actuators 12, 13 have been driven a certain percentage of their authority, a comparator (130, 132) activates a pulse generator (137, 138) to provide timed excitation of an actuator (150), thereby to position the aircraft control system outer loop by a commensurate increment. Driving the actuator for a longer time than the desired pulse width is detected (165-169) and causes automatic shutdown (190) of the actuator. Resetting the integrator at the start of each pulse (162, 104), and pulse-controlled gating of the pulse circuits (172, 135, 136) allow sensing of authority transitions which occur within a pulse, and permit a subsequent pulse in response thereto.
Inventors
- 👤 William C. Fischer
- 👤 Don L. Adams
- 👤 David J. Verzella
- 👤 Stuart C. Wright
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 17:25
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/08; G05D1/0808; G05D1/0816; G05D1/0833
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
373 words
A system for automatically positioning aerodynamic surfaces in a control axis of an aircraft, comprising: a sensor responsive to a parameter of aircraft flight related to said control axis for providing a parameter signal indicative of the magnitude thereof; a fast, inner loop actuator for changing the position of said aerodynamic surfaces across a limited authority range of positions which is a fraction of the total permissible range of positions thereof; an outer loop actuator connected to said inner loop actuator for adjusting the position of said inner loop actuator relative to the position of said control surfaces throughout a full authority range of positions equal to the total permissible range of positions thereof, to thereby reposition the center of said limited authority range relative to said full authority range; and signal processing means for providing a reference signal indicative of a desired magnitude of said parameter, and responsive to said sensor, for providing a proportional command signal of a first sense indicative of the magnitude and sense of the difference between said parameter signal and said reference signal to adjust the position of said inner loop actuator and therefore of said control surfaces in a first direction, depending on the sense of said difference to cause said parameter signal to approach equally with said reference signal, for providing to said inner loop actuator, a rate command signal indicative of the magnitude and sense of the rate of change of said parameter signal to adjust the position of said control surfaces in a second direction, depending on the sense of said rate of change, to cause the rate of change of said parameter signal to approach nil, and for providing said proportional command signal to said inner loop actuator; characterized by said signal processing means comprising means for providing an integral signal representing an integral function of said proportional command signal, for providing an excess signal indicative of said integral signal exceeding a predetermined magnitude, for providing, in response to said excess signal, a reset signal and an outer loop command signal of a fixed magnitude and predetermined duration and of said first sense to said outer loop actuator, and for resetting said integral function to nil in response to said reset signal.
Claim 2
Independent Claim
373 words
A system for automatically positioning aerodynamic surfaces in a control axis of an aircraft, comprising: a sensor responsive to a parameter of aircraft flight related to said control axis for providing a parameter signal indicative of the magnitude thereof; a fast, inner loop actuator for changing the position of said aerodynamic surfaces across a limited authority range of positions which is a fraction of the total permissible range of positions thereof; an outer loop actuator connected to said inner loop actuator for adjusting the position of said inner loop actuator relative to the position of said control surfaces throughout a full authority range of positions equal to the total permissible range of positions thereof, to thereby reposition the center of said limited authority range relative to said full authority range; and signal processing means for providing a reference signal indicative of a desired magnitude of said parameter, and responsive to said sensor, for providing a proportional command signal of a first sense indicative of the magnitude and sense of the difference between said parameter signal and said reference signal to adjust the position of said inner loop actuator and therefore of said control surfaces in a first direction, depending on the sense of said difference to cause said parameter signal to approach equally with said reference signal, for providing to said inner loop actuator, a rate command signal indicative of the magnitude and sense of the rate of change of said parameter signal to adjust the position of said control surfaces in a second direction, depending on the sense of said rate of change, to cause the rate of change of said parameter signal to approach nil, and for providing said proportional command signal to said inner loop actuator; characterized by said signal processing means comprising means for providing an integral signal representing an integral function of said proportional command signal, for providing an excess signal indicative of said integral signal exceeding a predetermined magnitude, for providing, in response to said excess signal, a reset signal and an outer loop command signal of a fixed magnitude and predetermined duration and of said first sense to said outer loop actuator, and for resetting said integral function to nil in response to said reset signal.
Claim 3
Dependent Claim
66 words
A system according to claim 1 characterized by said signal processing means comprising means for successively providing said outer loop command signal in response to initiation of said excess signal in the absence of said outer loop command signal or in response to termination of said outer loop command signal in response to initiation of said excess signal being concurrent with said outer loop command signal.
Claim 4
Dependent Claim
60 words
A system according to claim 1 characterized by said signal processing means comprising means for providing a shut down signal in response to said outer loop command signal being of a duration in excess of said predetermined duration, and for inhibiting provision of said outer loop command signal to said outer loop actuator in response to said shut down signal.
Claim 5
Dependent Claim
102 words
A system according to claim 1 characterized by said signal processing means comprising means for providing an inner loop centering signal to said inner loop actuator as a function of said integral signal, whereby said inner loop is driven in said first direction as said integral function builds up and is driven in a direction opposite to said first direction as said outer loop actuator is driven in said first direction, whereby the position of said inner loop actuator is adjusted to be substantially at the center of said limited authority range without significant perturbation of the position of said control surfaces.
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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 |