|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||91/363A ; 91/509 ; 244/194 ; 318/564|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 35 인용 특허 : 11|
An aircraft flight control system for use with a dual or tandem hydraulic actuator coupled to a flight control surface through an actuating rod. Each half of the tandem actuator is controlled by a respective electrohydraulic servovalve. Each electrohydraulic servovalve is controlled by signals applied to either of two actuating coils. Control signals are applied to the actuating coils from three controllers. The control signals are generated as a function of the difference between the flight control signal and a feedback signal indicative of the position...
A hydraulic flight control system comprising: a tandem hydraulic actuator having an actuating rod connected to a pair of pistons mounted in respective first and second cylinders; first and second electrohydraulic servovalves controlling the flow of hydraulic fluid into and out of said first and second hydraulic cylinders, respectively, each of said electrohydraulic servovalves being controlled by a pair of actuating coils; first, second and third controller means receiving a flight control signal, said first controller means having a control channel that...