US4079905A
Expired / Lapsed
US
⏱️ 0.0 years remaining
System for providing an indication of wind shear
Assignee: Safe Flight Instrument LLC
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Filing: 1977-02-07
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Granted: 1978-03-21
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Expires: 1997-02-07
Abstract
Abstract The output of a transducer providing a signal representing the instantaneous airspeed of an aircraft is differentiated and fed to a summing device. Also fed to the summing device are a signal representing the horizontal acceleration of the aircraft which is subtracted from the instantaneous airspeed signal, and a signal in accordance with the downdraft drift angle of the aircraft which is added to the instantaneous airspeed signal. The output of the summing device represents the magnitude of the wind shear condition (rate of change of wind velocity) as modified by a downdraft drift angle signal. This output signal is fed to appropriate indicator apparatus which may comprise an appropriate display, a peak magnitude storage device, a warning device including a dangerous wind condition and/or a telemetering device providing a reading to a ground station for use in advising other aircraft.
Inventors
- 👤 Leonard M. Greene
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-23 18:56
CPC Classifications
G; G06; G06G; G06G7/00; G06G7/48; G06G7/78; G01; G01P; G01P13/00; G01P13/02; G01P13/025; G01P3/00; G01P3/02; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607; G05D1/0615
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
132 words
A system for generating a wind shear signal representing the wind shear condition encountered by an aircraft modified by the downdraft drift angle of the aircraft, comprising: means for generating a signal representing the rate of change of the instantaneous airspeed of the aircraft, means for generating a signal representing the horizontal inertial acceleration of the aircraft, means for generating a signal representing the downdraft drift angle of the aircraft, means for subtracting the horizontal inertial acceleration signal from the rate of change of instantaneous airspeed signal and adding the downdraft drift angle signal to the rate of change of instantaneous airspeed signal to provide an output signal representing wind shear modified by aircraft downdraft drift angle, and means for processing said output signal to provide an indication representing the magnitude thereof.
Claim 2
Independent Claim
132 words
A system for generating a wind shear signal representing the wind shear condition encountered by an aircraft modified by the downdraft drift angle of the aircraft, comprising: means for generating a signal representing the rate of change of the instantaneous airspeed of the aircraft, means for generating a signal representing the horizontal inertial acceleration of the aircraft, means for generating a signal representing the downdraft drift angle of the aircraft, means for subtracting the horizontal inertial acceleration signal from the rate of change of instantaneous airspeed signal and adding the downdraft drift angle signal to the rate of change of instantaneous airspeed signal to provide an output signal representing wind shear modified by aircraft downdraft drift angle, and means for processing said output signal to provide an indication representing the magnitude thereof.
Claim 3
Dependent Claim
21 words
The device of claim 1 wherein said processing means comprises a display for directly displaying the magnitude of the output signal.
Claim 4
Dependent Claim
39 words
The system of claim 1 wherein said processing means comprises a warning device for generating a warning signal and detector means responsive to the output signal for actuating said warning device when the output signal exceeds a predetermined value.
Claim 5
Dependent Claim
58 words
The device of claim 1 wherein said processing means comprises peak detector for providing a peak output signal in accordance with the peak value of said output signal, storage means for storing the peak output signal of said detector means and display means for providing a display in accordance with the peak signal stored in said storage means.
Claim 6
Dependent Claim
22 words
The system of claim 1 wherein said processing means comprises a telemetering transmitter for transmitting said output signal to a ground station.
Claim 7
Dependent Claim
47 words
The system of claim 1 wherein said means for generating a signal in accordance with the rate of change of airspeed comprises an instantaneous airspeed transducer for providing an output signal in accordance with instantaneous airspeed and differentiator means for differentiating the output signal from said transducer.
Claim 8
Dependent Claim
76 words
The system of claim 1 wherein said means for generating a signal in accordance with aircraft horizontal acceleration comprises an accelerometer mounted along a fuselage reference line of said aircraft and having an output representing accelerations along said reference line, means for generating a signal in accordance with the pitch of said aircraft and means for subtracting said signal in accordance with aircraft pitch from the output of said accelerometer representing accelerations along said reference line.
Claim 9
Dependent Claim
93 words
The system of claim 6 wherein said means for generating a signal in accordance with the downdraft drift angle of the aircraft comprises a vertcial accelerometer, means for damping signal in accordance with the downdraft drift angle, means for generating a signal in accordance with aircraft vertical acceleration not due to vertical air currents, means for subtracting said last mentioned signal from the damped signal in accordance with the downdraft drift angle to provide a difference signal, and means for dividing said diffference signal by the output signal from said instantaneous airspeed transducer.
Claim 10
Dependent Claim
45 words
The system of claim 1 and further including automatic throttle controls for the aircraft and means for selectively coupling the output signal to said automatic throttle controls to thereby cause the thrust of the aircraft to be automatically modified in response to said output 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) | 1981-03-20 | 1981-09-19 | 1982-03-21 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1985-03-20 | 1985-09-19 | 1986-03-21 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1989-03-20 | 1989-09-19 | 1990-03-21 | $7700.00 | Window Closed / Lapsed |