发明名称 Deployable rocket engine nozzle
摘要 The nozzle cap (12) has a first part (13) fixed to the motor, and a relatively moveable second part (14) with larger diameter. A closed volume (15) is charged with a gaseous fluid to move the second part from storage to operational position. The closed volume is at least partially formed by a rolled diaphragm arrangement located between the moveable cap part and a stationary part of the propulsion unit (10) or the vehicle. The arrangement contains one diaphragm (16), which extends mainly rotary-symmetrical relative to the longitudinal axis of the propulsion unit and completely around the nozzle cap. A second diaphragm (17) forms an additional seal for the volume.
申请公布号 EP1460259(A1) 申请公布日期 2004.09.22
申请号 EP20040006296 申请日期 2004.03.17
申请人 EADS SPACE TRANSPORTATION GMBH 发明人 KRETSCHMER, JOACHIM
分类号 F02K9/97;(IPC1-7):F02K9/97 主分类号 F02K9/97
代理机构 代理人
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