JP6805741B2 - ロケット噴射器 - Google Patents
ロケット噴射器 Download PDFInfo
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- JP6805741B2 JP6805741B2 JP2016218755A JP2016218755A JP6805741B2 JP 6805741 B2 JP6805741 B2 JP 6805741B2 JP 2016218755 A JP2016218755 A JP 2016218755A JP 2016218755 A JP2016218755 A JP 2016218755A JP 6805741 B2 JP6805741 B2 JP 6805741B2
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- injection
- fuel
- rocket
- injection plate
- injector
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Description
3 ロケット噴射器
5 噴射器本体
7 噴射板
7a 噴射面
8 噴射エレメント(ノズル)
12 燃料供給室(燃料室)
71 多孔部
72A,72B 中実部
C 燃焼室
Claims (5)
- 燃焼室に面する噴射面を流体状の燃料によって冷却するロケット噴射器であって、
前記噴射面を備えた噴射板と、
前記噴射板を貫通し、少なくとも前記燃料を前記燃焼室内に噴射するノズルと、
前記噴射板を挟んで前記燃焼室とは反対側に設けられると共に、前記燃料を収容する燃料室と、を備え、
前記噴射板は、前記燃料室内の前記燃料が前記噴射面側に向けて透過可能な多孔部と、前記多孔部に比べて流体の透過性が低い中実部とを備え、前記多孔部と前記中実部とは一体構造であり、
前記噴射板は、前記燃焼室に面する噴射面と、前記噴射面に対して反対側であり、前記燃料室内に露出している裏面とを備え、
前記多孔部は、前記裏面から前記噴射面にかけて前記燃料が滲み出る空隙を備えている、ロケット噴射器。 - 前記中実部は、前記多孔部よりも密度が大きく、
前記多孔部と前記中実部とは3D積層造形による前記一体構造である、請求項1記載のロケット噴射器。 - 前記燃料室が設けられた噴射器本体を備え、
前記噴射器本体に接続された前記噴射板の外縁領域は前記中実部である、請求項1または2記載のロケット噴射器。 - 前記噴射面において、前記ノズルを囲んで前記ノズルに接続された領域は前記中実部である請求項1〜3のいずれか一項記載のロケット噴射器。
- 請求項1〜4のいずれか一項記載の前記ロケット噴射器と、前記ロケット噴射器に接続された燃焼室ライナーと、を備えたロケット燃焼器。
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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JP2016218755A JP6805741B2 (ja) | 2016-11-09 | 2016-11-09 | ロケット噴射器 |
Applications Claiming Priority (1)
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JP2016218755A JP6805741B2 (ja) | 2016-11-09 | 2016-11-09 | ロケット噴射器 |
Publications (2)
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JP2018076813A JP2018076813A (ja) | 2018-05-17 |
JP6805741B2 true JP6805741B2 (ja) | 2020-12-23 |
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JP2016218755A Active JP6805741B2 (ja) | 2016-11-09 | 2016-11-09 | ロケット噴射器 |
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JP (1) | JP6805741B2 (ja) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US11998984B2 (en) * | 2018-04-01 | 2024-06-04 | Astrobotic Technology, Inc. | Additively manufactured non-uniform porous materials and components in-situ with fully material, and related methods, systems and computer program product |
DE102021109484A1 (de) | 2021-04-15 | 2022-10-20 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Triebwerkseinheit für einen Raketenantrieb und Brennkammervorrichtung |
CN114087089A (zh) * | 2021-11-19 | 2022-02-25 | 北京航天试验技术研究所 | 一种高效点火锥面喷注器 |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2495280A1 (fr) * | 1980-12-01 | 1982-06-04 | Deutsche Forsch Luft Raumfahrt | Generateur de vapeur |
DE19730674A1 (de) * | 1997-07-17 | 1999-01-21 | Deutsch Zentr Luft & Raumfahrt | Brennkammer und Verfahren zur Herstellung einer Brennkammer |
US6513331B1 (en) * | 2001-08-21 | 2003-02-04 | General Electric Company | Preferential multihole combustor liner |
US7128532B2 (en) * | 2003-07-22 | 2006-10-31 | The Boeing Company | Transpiration cooling system |
JP2008101534A (ja) * | 2006-10-19 | 2008-05-01 | Japan Aerospace Exploration Agency | 滲み出し冷却ロケット燃焼器 |
JP2013133711A (ja) * | 2011-12-26 | 2013-07-08 | Ihi Corp | ロケット噴射器及びロケット燃焼器 |
US9939156B2 (en) * | 2013-06-05 | 2018-04-10 | Siemens Aktiengesellschaft | Asymmetric baseplate cooling with alternating swirl main burners |
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2016
- 2016-11-09 JP JP2016218755A patent/JP6805741B2/ja active Active
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JP2018076813A (ja) | 2018-05-17 |
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