B - Operations – Transporting – 64 – D
Patent
B - Operations, Transporting
64
D
B64D 31/06 (2006.01) G05D 1/00 (2006.01) G05D 1/08 (2006.01)
Patent
CA 2116236
A helicopter engine fuel control anticipates changes in main rotor torque in response to lateral cyclic pitch commands; to thereby minimize engine and main rotor speed droop and overspeed during left and right roll maneuvers. A fuel compensation signal (100,101) is summed with a helicopter fuel control (52) fuel command signal (67) in response both to a lateral cyclic pitch command signal (LCP) (107) from a pilot operated cyclic pitch control exceeding a left or right threshold magnitude (201, 210) and a total lateral cyclic pitch command signal (TCP) (108) from a lateral cyclic pitch control sys- tem exceeding a left or right threshold magnitude (202; 207, 215, 220): The anagnitude of the fuel compensation signal is dependent upon the direction of TCP and LCP, e:g., left or right; and helicopter roll acceleration (115). Alternatively, the magnitude and duration of the fuel compensation signal is dependent upon the rate of change in commanded lateral cyclic pitch (107, 400, 407): A limiter (120) limits the magnitude of the fuel compensation signal. The fuel compensa- tion signal is overridden (127, 125, 103) When it is increasing fuel flow (303) during rotor overspeed (128, 301); and when it is decrea- sing fuel flow (311) if rotor acceleration (130, 133) is negative (310) during rotor droop (128, 301).
Driscoll Joseph T.
Ebert Frederick J.
Graham Byron Jr.
Sweet David H.
Ogilvy Renault Llp/s.e.n.c.r.l.,s.r.l.
United Technologies Corporation
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