摘要 |
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).
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