|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||149/194 ; 149/199|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 5 인용 특허 : 0|
Solid rocket motor propellant formulations are provided which are capable of burning at at least two selected burn rates. The burn rate is controlled by controlling the pressure at which the propellant burns. For example, it is possible to mechanically modify the container, such as a rocket motor casing, in which the propellant is held in order to modify the pressure under which the propellant burns. Alternatively, the propellant may be configured or molded such that the pressure changes at a chosen time due to the process of burning the propellant. The ...
A solid rocket motor propellant comprising: from about 6% to about 10% binder, said binder consisting essentially of hydroxy-terminated polybutadiene binder; from about 65% to about 90% ammonium perchlorate; and from about 0.3% to about 5.0% refractory oxide selected from the group consisting of TiO2, and SiO2; said propellant formulated such that it burns at at least two stable burn rates over at least two corresponding pressure ranges such that the propellant provides boost-sustain operation when burned in a solid rocket motor.