|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/195 ; 244/076A ; 244/227 ; 701/03|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 76 인용 특허 : 0|
A fault tolerant actuation system (12) for flight control systems is provided. The fault tolerant actuation system (12) includes a plurality of primary flight computers (14a, 14b, and 14c) with corresponding power control units (24a, 24b, and 24c). Each power control unit includes a remote electronic unit (18a, 18b, and 18c), an electro-hydraulic servo valve (26a, 26b, and 26c), and an actuator (28a, 28b, and 28c). The actuators are linked to a flight control surface (30) to control its position. The electro-hydraulic servo valves (26a, 26b, and 26c) and...
[ The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:] [1.] A fault tolerant actuation system for a flight control system comprising:a plurality of primary flight computers, each of said plurality of primary flight computers generating an actuator command to direct the position of a flight control surface;a plurality of power control units, each of said plurality of power control units coupled to a corresponding primary flight computer of said plurality of primary flight computers for receiving ...