|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||149/199 ; 149/2 ; 149/196 ; 149/1992|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 5 인용 특허 : 0|
Composite rocket propellants, in which the base component is a functionally terminated rubber, and case-bonded rocket motors containing same, are provided, wherein cross-link density at, and adjacent at least a portion of the initial propellant burning surface is lower than that throughout the remainder of the propellant to provide greater strain capability at the initial burning surface together with greater propellant strength for higher mass ratio and improved case bonding than possible utilizing a single “compromise”propellant cross-link density of t...
A process for the manufacture of a cured, rubber base composite rocket propellant having a lower cross-link density at and adjacent at least a portion of its initial burning surface than throughout the remainder of the propellant, which process comprises (a) partially curing in its entirety an uncured composite propellant composition comprising solid oxidizer and a binder system containing a carboxy terminated rubber, hydroxy terminated rubber, mercapto terminated rubber or amine terminated rubber and a curing agent therefor until sufficient cross-linkin...