Electrically controlled elevator

Details Electrically controlled elevator Electrically controlled elevator

1979-05-17

1981-12-08

Broome, Harold

Aeronautics and astronautics

Aircraft, heavier-than-air

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

244178, 318564, 318584, B64C 1144

Patent

active

043043755

ABSTRACT:
A helicopter elevator (12, 13) is driven by an electrical actuator (20) to position the elevator (12, 13) to an optimum angle of incidence for given flight conditions. The actuator (20) is included within a servo loop which responds to a command signal derived from an electronics module (69). Transducers which measure longitudinal cyclic position (40), collective pitch position (41) and air speed (42) generate signals which are summed in a summation unit (43). The output of the summation unit (43) is passed through a signal multiplier (45) which has the gain thereof set inversely proportional to air speed. A trigger unit (56) activates the signal multiplier (45) at an air speed above a preset threshold. An integrator (54) integrates the sum of the outputs of the longitudinal cyclic position transducer (40) and air speed transducer (42) to compensate for different center of gravity aircraft loadings. Duplicate electronic systems are provided to drive a pair of servo motors (36a, 36b) with brakes provided to lock the actuator (20) when an electronic failure is detected.

REFERENCES:
patent: 3584814 (1971-06-01), Murphy
patent: 4032083 (1977-06-01), Maciolek
patent: 4095763 (1978-06-01), Builta
patent: 4103848 (1978-08-01), Johnson, Jr. et al.

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