A flight control actuation system comprises a controller, electromechanical
actuator and a pneumatic actuator. During normal operation, only the
electromechanical actuator is needed to operate a flight control surface.
When the electromechanical actuator load level exceeds 40 amps positive,
the controller activates the pneumatic actuator to offset
electromechanical actuator loads to assist the manipulation of flight
control surfaces. The assistance from the pneumatic load assist actuator
enables the use of an electromechanical actuator that is smaller in size
and mass, requires less power, needs less cooling processes, achieves high
output forces and adapts to electrical current variations. The flight
control actuation system is adapted for aircraft, spacecraft, missiles,
and other flight vehicles, especially flight vehicles that are large in
size and travel at high velocities.
