|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||102/291 ; 60/248 ; 60/254|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 7 인용 특허 : 0|
Solid propellant combustion apparatus such as a rocket motor, incorporating a combustion termination valve for providing two combustion phases from a single propellant charge system, the valve comprising a valve body (50) surrounding an opening (52) in the pressure vessel of the combustion apparatus, a valve member (60), retaining means (65) for releasably retaining said valve member in sealing engagement with the valve body whereby to hold the valve closed during a first combustion phase, valve opening means (68) operable on command for releasing said r...
[ We claim:] [1.] A solid propellant combustion apparatus comprising:a pressure vessel,a solid propellant charge within the pressure vessel for generating combustion gases, anda combustion termination valve located in an opening between the interior and exterior of the pressure vessel, the valve, operable on command, comprising a means for terminating a first combustion phase of the propellant charge by causing rapid depressurisation of the interior of the pressure vessel through the release of combustion gases through said opening, and on further comman...