|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 10 인용 특허 : 6|
A lateral-thrust control device for a four-quadrant final-phase guidance control of a missile having lateral-thrust nozzles (10) communicating with a solid-fuel gas generator (13). Each of the nozzles has a valve member (22, 38), whose open and closed states are controlled by a common actuator (12, 30) which is rotatable and axially displaceable to select one nozzle to be supplied with gas from the gas generator while the other nozzles are closed according to the required flight mode. The actuator is configured such that each of the lateral-thrust nozzle...
[ What is claimed is:] [1.]1. A lateral thrust control apparatus for a missile comprising:a plurality of lateral thrust nozzles on the missile for communicating with a gas generator to produce a lateral thrust on the missile,a valve for each nozzle so that the nozzle is opened and closed, anda common actuator to operate each valve between open and closed positions for the respective nozzle to control flow of gases from said gas generator to said nozzles,said actuator being supported for reciprocal travel along an axis and for rotation movement around sai...