US3761691A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Runway alignment system utilizing a lateral acceleration signal
Assignee: Collins Radio Co
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Filing: 1972-11-24
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Granted: 1973-09-25
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Expires: 1992-11-24
Abstract
Abstract A landing control system utilizing a lateral acceleration signal in formulation of roll steering command such that a decrab maneuver effects a ''''wing down into the wind'''' forward slip maneuver, maintaining runway alignment.
Inventors
- 👤 E Schultz
- 👤 E Hattendorf
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 21:15
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607; G05D1/0653; G05D1/0676; G05D1/02; G05D1/0202; G05D1/0204
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
96 words
An aircraft control system comprising signal combining means for additively combining signals respectively proportional to displacement and rate of change to displacement of said aircraft from a predefined course line and for subtractively combining a signal proportional to aircraft roll attitude, the output from said signal combining means comprising a roll steering command signal, and means for further combining with said roll attitude signal a further signal of predetermined sense and proportional to lateral acceleration of the aircraft about a lateral body axis of said craft passing substantially through the center of gravity of said craft.
Claim 2
Dependent Claim
96 words
An aircraft control system comprising signal combining means for additively combining signals respectively proportional to displacement and rate of change to displacement of said aircraft from a predefined course line and for subtractively combining a signal proportional to aircraft roll attitude, the output from said signal combining means comprising a roll steering command signal, and means for further combining with said roll attitude signal a further signal of predetermined sense and proportional to lateral acceleration of the aircraft about a lateral body axis of said craft passing substantially through the center of gravity of said craft.
Claim 3
Dependent Claim
28 words
A control system as defined in claim 1 wherein said lateral acceleration signal comprises the output from a lateral accelerometer fixed to the body axis of the craft.
Claim 4
Dependent Claim
29 words
A control system as defined in claim 2 further comprising low pass filtering means through which said lateral accelerometer signal is passed prior to application to said combining means.
Claim 5
Dependent Claim
65 words
A control system as defined in claim 2 further comprising means for developing a yaw steering command signal proportional to the existing aircraft crab angle at experienced aircraft altitudes beneath a predetermined altitude, and aircraft yaw axis control means responsive to said yaw steering command signal to effect a lateral acceleration of said aircraft to produce a proportional sensed output signal from said lateral accelerometer.
Claim 6
Dependent Claim
33 words
A control system as defined in claim 4 further comprising means for damping said yaw steering command signal with a signal proportional to the time rate of change of said aircraft crab angle.
Claim 7
Dependent Claim
66 words
A control system as defined in claim 5 wherein said yaw steering command signal developing means comprises a further signal combining means receiving a first input signal proportional to the aircraft course datum signal defined as the difference between a preselected aircraft heading and the instantaneously experienced aircraft heading and a second input signal proportional to the time rate of change of said course datum signal.
Claim 8
Dependent Claim
29 words
A control system as defined in claim 6 comprising low pass filtering means through which said yaw steering command signal is passed to said aircraft yaw axis control means.
Claim 9
Dependent Claim
49 words
A control system as defined in claim 6 comprising a signal switching means through which said yaw steering command signal is selectively applied to said aircraft yaw axis control means, and means for closing said switching means when the altitude of said aircraft is less than said predetermined altitude.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-09-24 | 1977-03-26 | 1977-09-25 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-09-24 | 1981-03-26 | 1981-09-25 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-09-24 | 1985-03-26 | 1985-09-25 | $7700.00 | Window Closed / Lapsed |