Abstract: A system for backdriving the flight deck controllers of a fly-by-wire aircraft that is under autopilot control to provide a pilot with tactile and visual feedback of autopilot activity. The system, distributed between the aircraft primary flight computers and the autopilot flight computer, uses actuators mechanically coupled to each flight deck controller to position the flight deck controller to mimic manual operation of the flight control surfaces. Additionally, the system allows smooth disengagement of the autopilot and transfer of the aircraft to pilot control when the pilot takes control of any flight deck controller by moving it from a backdrive system-commanded position by a predetermined displacement for a predetermined time.

Abstract: A system for backdriving the flight deck controllers of a fly-by-wire aircraft that is under autopilot control to provide a pilot with tactile and visual feedback of autopilot activity. The system, distributed between the aircraft primary flight computers and the autopilot flight computer, uses actuators mechanically coupled to each flight deck controller to position the flight deck controller to mimic manual operation of the flight control surfaces. Additionally, the system allows smooth disengagement of the autopilot and transfer of the aircraft to pilot control when the pilot takes control of any flight deck controller by moving it from a backdrive system-commanded position by a predetermined displacement for a predetermined time.

Abstract: A redundant, multi-channel fly-by-wire control system for use in an aircraft is disclosed. The system includes a left flight control channel (60), a center flight control channel (80) and a right flight control channel (90). Each control channel is capable of flying the aircraft in the event the other two channels fail. Included within each control channel is an actuator controller electronics unit (ACE (62, 82, 92)), which transmits a series of pilot control transducer signals to a set of primary flight computers (64, 84, and 94). The primary flight computers combine the pilot control transducer signals with data obtained from an air data and inertial reference unit (145) to generate a set of flight surface commands. Each ACE selects a set of flight surface commands to control the movement of a set of flight control surfaces on the aircraft.

Abstract: A pair of input sense signals are processed and passed to inputs of two servo amplifiers. The amplifier outputs are summed and converted to a corresponding hydraulic pressure in a T-valve. Transducers monitor the produced pressure and provide feedback signals to the servo amplifiers. A comparator compares the servo amplifier outputs and activates a warning device if the signal difference therebetween exceeds a threshold level. Equalizer circuitry processes the comparator output and provides correction signals to the servo amplifier inputs to wash-out offset effects.

Abstract: An aircraft spoiler control system wherein each of a plurality of spoilers is driven by an electrically responsive actuator. Sense signals representative of the aircraft's control wheel rotation, speedbrake lever deflection, flap position and air/ground status are processed by logic which produces a corresponding control signal for each actuator. Fault detection circuitry switches in a back-up actuator control signal if a fault occurs in the active control circuit.