Helicopter, high rotor load speed enhancement

Details Helicopter, high rotor load speed enhancement Helicopter, high rotor load speed enhancement

1989-05-19

1991-03-05

Lall, Parshotam S.

Boots, shoes, and leggings

60 39282, 244182, F02C 908

Patent

active

049982028

ABSTRACT:
A helicopter engine speed reference (66) is increased (113, 103-105) in response to heavy rotor loading (108). The reference speed is faded up (113, 104) at a rather rapid rate to 107% of rated speed (114). After a fixed time interval (118), reduced rotor loading (119) will cause the reference speed to be faded down slowly (120, 103-105) to rated speed (121). If torque exceeds 111% of rated torque (117), the reference speed is similarly faded down (120, 103-105).

REFERENCES:
patent: 4286324 (1981-08-01), Ingram
patent: 4344141 (1982-08-01), Yates
patent: 4423593 (1984-01-01), Zagranski et al.
patent: 4488236 (1984-12-01), Morrison et al.
patent: 4522026 (1985-06-01), Peterson et al.
patent: 4716531 (1987-12-01), Saunders et al.
patent: 4716719 (1988-01-01), Takahashi et al.

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