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.
Flight control actuation system
2006-03-07
Miscellaneous
No indication
English
Flight Control Actuation System
NTIS | 2004
|Flight control actuation system
NTRS | 2004
|Electromechanical Flight Control Actuation
SAE Technical Papers | 1977
|Digital Flight Control Actuation
SAE Technical Papers | 1995
|Electromechanical flight control actuation
Tema Archive | 1977
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