Invention Grant
US08220249B2 Rocket nozzle and control method for combustion gas flow in rocket engine
有权
火箭发动机燃烧气体流量的火箭喷嘴和控制方法
- Patent Title: Rocket nozzle and control method for combustion gas flow in rocket engine
- Patent Title (中): 火箭发动机燃烧气体流量的火箭喷嘴和控制方法
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Application No.: US12200265Application Date: 2008-08-28
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Publication No.: US08220249B2Publication Date: 2012-07-17
- Inventor: Tatsuya Kimura , Yoshihiro Kawamata , Kenichi Niu
- Applicant: Tatsuya Kimura , Yoshihiro Kawamata , Kenichi Niu
- Applicant Address: JP Tokyo
- Assignee: Mitsubishi Heavy Industries, Ltd.
- Current Assignee: Mitsubishi Heavy Industries, Ltd.
- Current Assignee Address: JP Tokyo
- Agency: Westerman, Hattori, Daniels & Adrian, LLP
- Priority: JP2008-069502 20080318
- Main IPC: B64G1/40
- IPC: B64G1/40
Abstract:
A rocket nozzle includes a dual-bell nozzle and a gas introducing section configured to introduce gas into space surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle bell-shaped and surrounding an upstream portion of the space, and a second stage nozzle bell-shaped and surrounding a downstream portion of the space. The dual-bell nozzle has an inflection point between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet.
Public/Granted literature
- US20090235639A1 ROCKET NOZZLE AND CONTROL METHOD FOR COMBUSTION GAS FLOW IN ROCKET ENGINE Public/Granted day:2009-09-24
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