Direct Drive Control Valve for Fly-by-Wire Flight Control System Actuators.

摘要

The development of a high force linear motor suitable for directly actuating an aircraft hydraulic power control valve used on a flight control system actuator is described. A breadboard unit was fabricated and tested and met the 80 lb. midpoint force requirement with an input of 4.4 amperes (1.1 amps/coil). A modified F-4 aileron actuator incorporating the force motor and position LVDT's met the frequency response requirements. Three sets of brassboard equipment each consisting of a modified F-4 aileron actuator incorporating a new force motor and position LVDT's and an electronic control box were designed, fabricated and tested. One set was subjected to and satisfactorily completed flightworthiness tests. The remaining are available for flight testing. (Author)