|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/225 ; 60/270R|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 5 인용 특허 : 0|
A two-stage ramjet engine including an aft end, ejectable, boost stage-combustor/nozzle assembly for initially accelerating from low-to-mid-supersonic launching speeds to high supersonic speeds, and mounted in a tandem arrangement immediately aft of a separate, forward end-cruise stage-combustor/nozzle assembly positioned directly behind an inlet-diffuser section for subsequently further accelerating from high supersonic to hypersonic speeds after ejecting the entire boost stage.
A two-stage ramjet comprising: an inlet-diffuser section; a forward cruise stage disposed immediately downstream of, or made integral with said inlet-diffuser section and having a cruise-combustion chamber and relatively small, cruise exhaust nozzle specifically optimized for producing cruise flight varying between predesigned relatively high supersonic and hypersonic flight speeds; and an aft boost stage tandem mounted to the rear of said forward cruise stage and including a boost-combustion chamber and relatively large, boost-exhaust nozzle expressly o...