Patent US3814912A successfully refreshed from Google Patents.
US3814912A
Expired / Lapsed
US
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Gust compensation for angle-of-attack reference aircraft speed control system
Assignee: Collins Radio Co
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Filing: 1973-01-04
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Granted: 1974-06-04
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Expires: 1993-01-04
Abstract
Abstract A system for deriving signals proportional to horizontal and vertical wind gust level each as the difference between an atmospheric measurement and an inertial reference and, by a threshold sensitive signal translator responsive only to negative ones of the derived signals, to subtract gust bias signals from the system angle-of-attack reference to compensate for those gust components which tend to reduce lift.
Inventors
- 👤 J Klein
- 👤 G Manke
- 👤 T Schuldt
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 23:31
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607; G05D1/0615; G05D1/063
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
134 words
In an angle-of-attack referenced autothrottle control system for aircraft wherein a throttle command signal is formulated from the discrepancy between an angle-of-attack reference signal and a signal corresponding to existing angle-of-attack, means for deriving a signal proportional to at least one of the horizontal and vertical aircraft velocity components from signals proportional to inertial input parameters, means for deriving a signal proportional to like aircraft velocity components from signals proportional to atmospheric input parameters, signal comparing means receiving said inertially and atmospherically derived aircraft velocity signals and deriving the algebraic difference therebetween as a derived wind gust level signal, and threshold sensitive means receiving said derived wind gust level signal and being responsive thereto to subtract an increment from said reference angle-of-attack signal upon said derived wind gust level signal exceeding a predetermined threshold.
Claim 2
Dependent Claim
134 words
In an angle-of-attack referenced autothrottle control system for aircraft wherein a throttle command signal is formulated from the discrepancy between an angle-of-attack reference signal and a signal corresponding to existing angle-of-attack, means for deriving a signal proportional to at least one of the horizontal and vertical aircraft velocity components from signals proportional to inertial input parameters, means for deriving a signal proportional to like aircraft velocity components from signals proportional to atmospheric input parameters, signal comparing means receiving said inertially and atmospherically derived aircraft velocity signals and deriving the algebraic difference therebetween as a derived wind gust level signal, and threshold sensitive means receiving said derived wind gust level signal and being responsive thereto to subtract an increment from said reference angle-of-attack signal upon said derived wind gust level signal exceeding a predetermined threshold.
Claim 3
Dependent Claim
44 words
A system as defined in claim 1 comprising signal translating means receiving said derived gust level signal and passing only those of a first sense to said threshold sensitive means to the exclusion of those of a sense opposite that of said first sense.
Claim 4
Dependent Claim
44 words
A system as defined in claim 2 wherein said threshold sensitive means comprises means for subtracting a gust bias level signal from said reference angle-of-attack signal upon a derived wind gust level, as passed by said signal translating means, exceeding a first predetermined threshold.
Claim 5
Dependent Claim
51 words
A system as defined in claim 2 wherein said threshold sensitive means comprises means for successively subtracting individual ones of a plurality of gust bias signal sources from said reference angle-of-attack signal upon said wind gust level, as passed by said signals translating means, exceeding respective successively higher predetermined threshold levels.
Claim 6
Dependent Claim
86 words
A system as defined in claim 2 wherein said means for deriving aircraft velocity components from inertial input parameters comprises means for deriving first and second high pass filtered inertial speed reference signals in both the vertical and horizontal directions from respective longitudinal and normal accelerometer input parameters; said means for deriving aircraft velocity components from atmospheric input parameters comprises means for deriving a vertical speed signal from pitch attitude and measured angle-of-attack input parameters and means for deriving a horizontal speed signal from calibrated airspeed.
Claim 7
Dependent Claim
120 words
A system as defined in claim 5 wherein said means for deriving said inertial speed references comprises first means for combining output signals from a longitudinal accelerometer and a normal accelerometer, low pass filtering means receiving the output from said first means for combining; said means for deriving said velocity components from atmospheric input parameters comprising means for subtractively combining the output signal from an angle-of-attack sensor and a signal proportional to aircraft flight path angle, further means for combining said flight path angle signal and a signal proportional to calibrated airspeed, high-pass filtering means receiving the output of said further means for combining; and said signal comparing means receiving the respective outputs from said low-pass and high-pass filtering means.
Claim 8
Dependent Claim
44 words
A system as defined in claim 6 wherein said threshold sensitive means comprises means for subtracting a gust bias level signal from said reference angle-of-attack signal upon a derived wind gust level as passed by said signal translating means, exceeding a first predetermined threshold.
Claim 9
Dependent Claim
51 words
A system as defined in claim 6 wherein said threshold sensitive means comprises means for successively subtracting individual ones of a plurality of gust bias signal sources from said reference angle-of-attack signal upon said wind gust level, as passed by said signal translating means, exceeding respective successively higher predetermined threshold levels.
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) | 1977-06-03 | 1977-12-03 | 1978-06-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-06-03 | 1981-12-03 | 1982-06-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-06-03 | 1985-12-03 | 1986-06-04 | $7700.00 | Window Closed / Lapsed |