|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||102/378 ; 60/271|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 9 인용 특허 : 2|
A device for altering the after body shape of a missile configuration so as to reduce the ballistic flight drag coefficient after booster burnout and including linear shaped charge cutting device for severing a portion of a nozzle exit cone just aft of a fixed boattail configuration on the outer surface of the missile to allow boundary layer air flow to flow smoothly over the boattail and thereby reduce the base drag on the missile during the coast phase thereof.
A missile having a rocket motor structure with a nozzle structure attached thereto, said nozzle structure having an outwardly tapering outer surface, a frustaconical boattail structure mounted over and about an end portion of said rocket motor structure and a forward portion of said rocket nozzle structure, said boattail structure having an outward surface that tapers inwardly from a forward portion to a point of tangency with the outwardly tapering outer surface of said rocket nozzle, means about said rocket nozzle at said point of tangency and mounted ...