|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/194; 244/228; 244/0994|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 13 인용 특허 : 12|
An aircraft flight surface control system and method simultaneously provides the benefits of both an active/active system architecture and in active/standby system architecture. The system is preferably implemented using hydraulic actuator assemblies and electromechanical actuator assemblies coupled to the same flight control surface. During normal system operations the electromechanical actuator assemblies are energized to supply a relatively minimal force to associated flight control surfaces. In effect, the electromechanical actuators, although energi...
What is claimed is: 1. An aircraft flight control surface actuation system, comprising:an electromechanical actuator assembly adapted to be selectively supplied with electrical current and, upon receipt of the electrical current, to supply a force to a flight control surface;a hydraulic actuator assembly adapted to selectively receive a supply of hydraulic fluid and, upon receipt of the hydraulic fluid, to supply a force to the flight control surface;a hydraulic actuator control adapted to receive a position command signal representative of a commanded f...