|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02K-009/28 F02K-007/18 F02K-009/26|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 14|
A selectable ramjet propulsion system for propelling a rocket or missile includes a gas generator adjacent a booster. A frangible diaphragm is disposed between the gas generator and the booster. The booster and fuel gas generator can be operated in normal sequence, or operated at the same time in order to increase the thrust produced for short-range missions. A logic circuit contained on the rocket or missile determines a time to rupture the frangible diaphragm based on whether or not the distance to the target exceeds a threshold distance.
1. A selectable ramjet propulsion system for propelling a missile, comprising: a variable flow ducted rocket having a gas generator, a combustor, a frangible diaphragm, and an inlet duct, wherein the a gas generator has a center-perforated grain solid rocket propellant, wherein the center-perforated grain solid rocket propellant of the gas generator is a ramjet fuel, wherein the gas generator is adjacent the combustor, wherein the combustor has a center-perforated grain solid rocket propellant, wherein the frangible diaphragm is disposed between said gas...