|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||102/489 ; 102/357 ; 102/377 ; 102/393|
|§371/§102 date||19950926 (19950926)|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 8 인용 특허 : 9|
An apparatus and method for separating a warhead to be delivered to a target from a carrier missile flying at high speed in a first aerodynamic trajectory include a rocket motor attached to the warhead in the carrier missile and an ejection tube positioned obliquely in the carrier missile rearwardly and upwardly with respect to a longitudinal axis of the carrier missile from which the warhead is ejected by the rocket motor into a second aerodynamic trajectory having a substantially higher maximum flight altitude then the first trajectory. The warhead is ...
A method of separating a warhead to be delivered to a target from a carrier missile carrying warheads therein and flying at high speed in a first aerodynamic trajectory, said method comprising the steps of: ejecting said warhead from said carrier missile rearwardly and upwardly at an oblique angle to said first aerodynamic trajectory to a desired second aerodynamic trajectory by means of a rocket motor connected therewith, the ejection velocity of said rocket motor and said warhead being adjusted in relation to the flight speed of the carrier missile to ...