Approach to hover control system for helicopters

Details Approach to hover control system for helicopters Approach to hover control system for helicopters

1987-12-21

1989-01-31

Barefoot, Galen

Aeronautics and astronautics

Aircraft, heavier-than-air

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

244186, B64C 1316

Patent

active

048011100

ABSTRACT:
An improved apparatus for automatic deceleration of a helicopter to substantially zero air speed from a glide slope descent. Parameters available in a typical helicopter automatic flight control system, such as vertical speed, glide slope error, longitudinal acceleration, and pitch attitude are blended together in a manner as to approximate helicopter ground speed which is then used in a control law computation to decelerate the helicopter to a near hover speed as the vehicle approaches a preset altitude minimum.

REFERENCES:
patent: 2830291 (1958-04-01), Hecht et al.
patent: 3126474 (1964-03-01), Zweibel et al.
patent: 3627238 (1971-12-01), Menn
patent: 3665465 (1972-05-01), Miller
patent: 4354237 (1982-10-01), Lambregts et al.
patent: 4551804 (1985-11-01), Clark et al.
patent: 4740899 (1988-04-01), McElreath

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