|국가/구분||United States(US) Patent 등록|
|§371/§102 date||19981028 (19981028)|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 3 인용 특허 : 2|
A rocket engine system comprising a single nozzle having a curved profile in axial section. In order to enable a control of the flow separation occurring within the nozzle outlet, the outlet portion in transverse section has a radius, the length of which varies such that the transverse section transitions smoothly from a circular nozzle throat to a polygonal outlet section.
[ What is claimed is:] [1.] A rocket engine system comprising:a single rocket engine nozzle, extending from a rocket engine to an ultimate downstream terminus of a rocket vehicle, with an outlet portion having an axis and a curved profile in axial section, which outlet portion in transverse section has a radius with a length that varies periodically, wherein said length variation increases distally along the axis to a maximum such that a polygonal circumferential shape is obtained.