US3955071A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Windshear detection system
Assignee: Boeing Co
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Filing: 1974-09-20
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Granted: 1976-05-04
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Expires: 1994-09-20
Abstract
Abstract A system for processing signals representative of airspeed error and inertial longitudinal acceleration of an aircraft to provide an output signal representative of windshear induced acceleration which is filtered to remove the high frequency components and which may be utilized to indicate the presence of windshear to a pilot who can then respond by resetting the thrust to maintain airspeed, or alternatively the output signal is utilized to correct the inertial damping signal of an airspeed control system under windshear conditions.
Inventors
- 👤 Antonius A. Lambregts
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 12:42
CPC Classifications
G; G06; G06G; G06G7/00; G06G7/48; G06G7/57; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607; G05D1/0615; G05D1/063
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
131 words
An aircraft instrument comprising first means for providing a first signal representative of the airspeed deviation of an aircraft from a preselected command speed; second means for providing a second signal representative of the inertial longitudinal acceleration of the aircraft; third means for processing said first and second signals, said third means including washout and lag circuit means for providing an output signal representative of the difference between the lagged inertial longitudinal acceleration and the lagged rate of change of airspeed deviation; and fourth means connected to the output of said third means, said fourth means comprising a rate limited lag circuit for providing at the output thereof the low frequency signal component of said output signal of said third means, said low frequency signal component indicative of a windshear condition.
Claim 2
Dependent Claim
131 words
An aircraft instrument comprising first means for providing a first signal representative of the airspeed deviation of an aircraft from a preselected command speed; second means for providing a second signal representative of the inertial longitudinal acceleration of the aircraft; third means for processing said first and second signals, said third means including washout and lag circuit means for providing an output signal representative of the difference between the lagged inertial longitudinal acceleration and the lagged rate of change of airspeed deviation; and fourth means connected to the output of said third means, said fourth means comprising a rate limited lag circuit for providing at the output thereof the low frequency signal component of said output signal of said third means, said low frequency signal component indicative of a windshear condition.
Claim 3
Independent Claim
76 words
A method for providing a windshear correction signal component of an inertial damping signal in an automatic speed control system of an aircraft, said method comprising the steps of: deriving a first signal representative of the lagged rate of change of the deviation of airspeed from a selected command signal; deriving a second signal representative of lagged inertial damping, and further subtracting said first signal from said second signal to provide said windshear correction signal component.
Claim 4
Independent Claim
76 words
A method for providing a windshear correction signal component of an inertial damping signal in an automatic speed control system of an aircraft, said method comprising the steps of: deriving a first signal representative of the lagged rate of change of the deviation of airspeed from a selected command signal; deriving a second signal representative of lagged inertial damping, and further subtracting said first signal from said second signal to provide said windshear correction signal component.
Claim 5
Dependent Claim
37 words
The method of claim 2 further including the steps of: filtering said windshear correction signal component with a rate limited lag circuit for noise content in the frequency range higher than the range of desired control frequencies.
Claim 6
Dependent Claim
34 words
The method of claim 3 comprising: correcting said inertial damping signal of said automatic speed control system for windshear by subtracting the output of said rate limited lag circuit from said inertial damping signal.
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) | 1979-05-04 | 1979-11-03 | 1980-05-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1983-05-04 | 1983-11-03 | 1984-05-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1987-05-04 | 1987-11-03 | 1988-05-04 | $7700.00 | Window Closed / Lapsed |