Helicopter engine control having lateral cyclic pitch anticipati

Details Helicopter engine control having lateral cyclic pitch anticipati Helicopter engine control having lateral cyclic pitch anticipati

1992-08-26

1993-11-30

Huppert, Michael S.

Aeronautics and astronautics

Aircraft, heavier-than-air

Helicopter or auto-rotating wing sustained, i.e., gyroplanes

244182, 364434, B64C 1134, B64C 2757, G05D 108

Patent

active

052658260

ABSTRACT:
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 system exceeding a left or right threshold magnitude (202,207,215,220). The magnitude of the fuel compensation signal is dependant 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 dependant 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 compensation signal is overridden (127,125,103) when it is increasing fuel flow ( 303) during rotor overspeed (128,301), and when it is decreasing fuel flow (311) if rotor acceleration (130,133) is negative (310) during rotor droop (128,301).

REFERENCES:
patent: 4488236 (1984-12-01), Morrison et al.
patent: 4493465 (1985-01-01), Howlett et al.
patent: 4807129 (1989-02-01), Perks
patent: 4912642 (1990-03-01), Larsen et al.
patent: 4947334 (1990-08-01), Massey et al.
patent: 4998202 (1991-03-01), Walsh et al.

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