|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/322 ; 102/384 ; 244/316|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 21 인용 특허 : 8|
A guidance method is provided for the terminal portion of the trajectory of a guided missile having a sensor and comprising two sections coupled together by a central shaft and free to rotate with respect to one another about the longitudinal axis of the missile; one section comprises a drive means for controlling the roll attitude of this section and a gas generator which feeds a nozzle for providing a transverse throat force and the other section has a stabilizing tail unit formed by a set of fins able to be opened out.
A method for guiding a missile during a terminal portion of the missile\s trajectory, said missile having a sensor with a beam said sensor being sensitive to energy radiated by a potential target comprising the following steps for seeking the target: (a) immobilizing the beam of the sensor along the longitudinal axis of the missile; (b) imparting to the missile: a rotation about the longitudinal axis of the missile at a given angular roll speed, and a spiral line movement in order that the beam of the sensor describes a surface of revolution by creating ...