|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/322 ; 244/327|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 7 인용 특허 : 3|
An actuator system for use in positioning control surfaces on a missile in response to steering commands. The actuator system raising the control surfaces such as missile fins from a retracted position in the missile outwardly to the deployed position and rotating the fins for controlling and steering the missile.
A missile control surface actuator system for controlling and steering fins on a missile, the actuator system comprising: a high pressure gas source; a high pressure manifold connected to the gas source; a pressure regulator connected between the high pressure source and the high pressure manifold for regulating the amount of high pressure gas to the manifold; a first and second fill line connected at one end to the manifold; a first and second fill valve connected in the first and second fill lines for controlling the amount of gas received from the man...