Patent US3353854A successfully refreshed from Google Patents.
US4245805A
Expired / Lapsed
US
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Turbulence compensated throttle control system for aircraft having throttle command signal path control means responsive to engine rating control and flare initiation
Assignee: Boeing Co
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Filing: 1977-11-25
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Granted: 1981-01-20
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Expires: 1997-11-25
Abstract
Abstract Command from engine rating control prevents throttle position from exceeding the value at which the engine operates at its rated power. Flare initiation changes the throttle command signal from a closed loop control signal to a fixed number of degrees per second retard rate, thereby overriding an aft limit switch signal allowing throttles to reach the idle position. A servo feedback arrangement utilizes a tachometer signal and an engine PLA (power lever angle) signal to optimize servo performance and overcome undesired control cable characteristics.
Inventors
- 👤 Leonard P. Stephan
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 10:07
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607; G05D1/0615; G05D1/063
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
127 words
In combination in an aircraft throttle control system having a throttle command path for an engine: an integrator circuit, a throttle servo motor, throttle means including clutch means, and control cables coupled in series in said throttle command path to said engine; the improvement comprising, a multiple feedback path including first and second feedback paths for minimizing the impact of control cable hysteresis on the performance of said throttle control system including, a first feedback path including tachometer means coupled between said throttle servo motor and said throttle means to said throttle command path upstream from said integrator circuit; and, a second feedback path containing power lever angle information coupled between said control cables and said engine to said throttle command path downstream from said integrator circuit.
Claim 2
Dependent Claim
127 words
In combination in an aircraft throttle control system having a throttle command path for an engine: an integrator circuit, a throttle servo motor, throttle means including clutch means, and control cables coupled in series in said throttle command path to said engine; the improvement comprising, a multiple feedback path including first and second feedback paths for minimizing the impact of control cable hysteresis on the performance of said throttle control system including, a first feedback path including tachometer means coupled between said throttle servo motor and said throttle means to said throttle command path upstream from said integrator circuit; and, a second feedback path containing power lever angle information coupled between said control cables and said engine to said throttle command path downstream from said integrator circuit.
Claim 3
Dependent Claim
30 words
The invention according to claim 1 wherein said first feedback path includes a signal gain of 0.1 relative to a signal gain of 0.9 provided in said second feedback path.
Claim 4
Dependent Claim
48 words
The invention according to claim 1 wherein said multiple feedback path including said first and second feedback paths further includes switching means responsive to signal representative of engine rating control engage for opening the power lever angle feedback path and providing unity gain in the tachometer signal path.
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) | 1984-01-20 | 1984-07-21 | 1985-01-20 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-01-20 | 1988-07-21 | 1989-01-20 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-01-20 | 1992-07-21 | 1993-01-20 | $7700.00 | Window Closed / Lapsed |