Flight control system especially for helicopters

Details Flight control system especially for helicopters Flight control system especially for helicopters

1983-03-28

1986-02-25

Chin, Gary

Boots, shoes, and leggings

244 1713, B64C 1300

Patent

active

045731250

ABSTRACT:
A flight control system including a mechanical control link (10) may have herent destabilizing characteristics. Such inherent characteristics may be caused by play in the mechanical control link of the system, by friction losses, by elasticity phenomena, and by hysteresis effects. For neutralizing such inherent effects a flight control system is provided with an internal control circuit (20) having an integration stage (36) followed by an amplifier (38) providing a control correction signal (y) at its output. The control correction signal (y) is supplied to an electro-hydraulic control drive (40) which applies the correction signal (y) to a signal combining stage (42) at the input of the mechanical control link (10). The input to the integration stage is an internal control deviation signal (e) which includes a signal component (x) representing the destabilizing inherent characteristics and a signal component (w) representing flight control closed loop input signals providing a respective reference signal (w). The operation of the integration stage is such that the correction signal (y) rises rapidly even in response to small deviation signals (e) for achieving the neutralizing.

REFERENCES:
patent: 3696282 (1972-10-01), Hirokawa et al.
patent: 4198017 (1980-04-01), Murray
patent: 4214300 (1980-07-01), Barlow et al.
patent: 4313165 (1982-01-01), Clelford et al.
patent: 4336594 (1982-06-01), Masuzawa et al.
patent: 4366422 (1982-12-01), Rhodes

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