ELECTRICALLY CONTROLLED ELEVATOR

摘要

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