|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02K-009/95 F02K-009/12 F02K-009/14 F02K-009/08 F02K-009/28 C06B-045/10|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 19|
Solid propellant systems include a main propellant and a secondary propellant in contact with the first propellant that exhibits autoignition temperatures of at least about 100° F. lower than the autoignition temperature of the main propellant. The secondary propellant of the present invention is most advantageously employed with conventional AP-containing solid propellant formulations as the main propellant, especially formulations containing both AP, an energetic solid, and a binder. In especially preferred forms, the secondary propellant will include ...
1. A solid rocket motor propellant system comprising: (a) an ammonium perchlorate-based main propellant which comprises, based on the total weight of the main propellant, between about 65 to about 92 wt. % ammonium perchlorate (AP), between about 8 to about 25 wt. % of an inert binder, and optionally, between about 5 to about 20 wt. % of aluminum powder; and(b) a secondary propellant in the form of a strip in localized contact with said main propellant of a compressed mass of a composition which comprises, based on the total weight of the secondary prope...