JP5992722B2 - スラスタ装置及び宇宙機 - Google Patents
スラスタ装置及び宇宙機 Download PDFInfo
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- JP5992722B2 JP5992722B2 JP2012113428A JP2012113428A JP5992722B2 JP 5992722 B2 JP5992722 B2 JP 5992722B2 JP 2012113428 A JP2012113428 A JP 2012113428A JP 2012113428 A JP2012113428 A JP 2012113428A JP 5992722 B2 JP5992722 B2 JP 5992722B2
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- 239000003380 propellant Substances 0.000 claims description 79
- 239000003054 catalyst Substances 0.000 claims description 40
- 229910000990 Ni alloy Inorganic materials 0.000 claims description 17
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 10
- 239000003795 chemical substances by application Substances 0.000 claims description 2
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 18
- 238000000354 decomposition reaction Methods 0.000 description 10
- 238000009413 insulation Methods 0.000 description 8
- 239000002245 particle Substances 0.000 description 5
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 3
- 229910017052 cobalt Inorganic materials 0.000 description 3
- 239000010941 cobalt Substances 0.000 description 3
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 3
- 229910052741 iridium Inorganic materials 0.000 description 3
- GKOZUEZYRPOHIO-UHFFFAOYSA-N iridium atom Chemical compound [Ir] GKOZUEZYRPOHIO-UHFFFAOYSA-N 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000010936 titanium Substances 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 230000003197 catalytic effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000004043 responsiveness Effects 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/26—Guiding or controlling apparatus, e.g. for attitude control using jets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/401—Liquid propellant rocket engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/405—Ion or plasma engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/411—Electric propulsion
- B64G1/415—Arcjets or resistojets
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
- F02K9/343—Joints, connections, seals therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/605—Reservoirs
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/68—Decomposition chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/94—Re-ignitable or restartable rocket- engine plants; Intermittently operated rocket-engine plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05C2201/00—Metals
- F05C2201/04—Heavy metals
- F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
- F05C2201/0466—Nickel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/133—Titanium
Landscapes
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Chemical & Material Sciences (AREA)
- Remote Sensing (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Automation & Control Theory (AREA)
- Catalysts (AREA)
- Physical Or Chemical Processes And Apparatus (AREA)
Description
このようなスラスタにおいて、推進薬が推薬弁から極細チューブを通して触媒層に供給された時の分解反応時に生じる触媒の局所的な劣化を防止するとともに、推薬弁の応答性や安全性を向上させる技術が開発されている(特許文献1)。
例えば、推進薬としてヒドラジンを用い、触媒層としてアルミナ粒子に触媒であるイリジウムを担持させた触媒粒子を用いた一液スラスタにおいては、触媒層は900℃程度の高温に達するのに対し、推薬弁は120℃程度の温度に抑える必要がある。
請求項3のスラスタ装置では、請求項1又は2において、前記柱部の先端に雌ネジが螺刻されており、雄ネジが螺刻されたNi合金からなるファスナを当該柱部の先端に締結することで、当該柱部と前記チャンバとを接続することを特徴としている。
このように、高温化する触媒層側は耐熱性の高いNi合金で構成し、比較的低温に保つ必要のある推薬弁との間には熱伝導率が低く断熱性の高いTi合金で構成された支持部材を介在させることで、触媒層から推薬弁への断熱性を確保することができる。さらに当該支持部材は柱部でチャンバを支持する構成であることで、推薬弁側へ熱伝達する領域を最小限に抑えることができ、断熱性を向上させることができる。
図1には本発明の一実施形態に係るスラスタ装置の全体斜視図が、図2(a)(b)にはスラスタ装置の拡大分解斜視図及び拡大分解側面図がそれぞれ示されており、以下これらの図に基づき説明する。
図1に示すスラスタ1は、姿勢制御及び軌道制御のために宇宙機に複数搭載されている一液触媒式スラスタである。
チャンバ8は内部に触媒層を保持している。図示しないが、触媒層は例えばアルミナ粒子に触媒であるイリジウムを担持させた触媒粒子がメッシュ材により保持されている。円筒状をなしているチャンバ8の先端には、チャンバ8の軸方向に対して垂直方向に開口したノズル10が設けられている。また、チャンバ8はノズル10の一部を突出させた状態でカバー12により覆われている。
以下、当該支持部材20について詳しく説明する。
触媒層は分解反応により900℃程度の高温となり、その熱は触媒層を保持しているチャンバ8から導入管6及び導入管フランジ26、各ファスナ36a、36b、36c等に伝達されるが、これらの各部材はNi合金であることでこの熱を許容できる。
このように、高温化する触媒層側は耐熱性の高いNi合金で構成し、比較的低温に保つ必要のある推薬弁4側にはTi合金の支持部材20を介在させ、3本の柱部30a、30b、30cによりチャンバ8を支持することで、触媒層から推薬弁4への断熱性を確保することができる。
上記実施形態では、支持部材20は3本の柱部30a、30b、30cによりチャンバ8を支持しているが、柱部の数はこれに限られるものではなく、4本以上の柱部としても構わない。
また、上記実施形態のノズル10は、チャンバ8の軸方向に対して垂直方向に開口しているが、ノズル10の向きはこれに限られるものではなく、例えば軸方向に開口したものであっても構わない。
2 タンク
4 推薬弁
6 導入管(推進薬導入部)
8 チャンバ
10 ノズル
20 支持部材
22 推薬弁フランジ
24 チャンバフランジ
26 導入管フランジ
30a、30b、30c 柱部
32a、32b、32c 雌ネジ
34a、34b、34c 貫通孔
36a、36b、36c ファスナ
Claims (4)
- 推薬弁から推進薬導入部を介して推進薬を触媒層に導入することで、分解ガスによる推力を発生させるスラスタ装置であって、
内部に前記触媒層を保持し、Ni合金からなるチャンバと、
前記推薬弁から前記チャンバへと接続され、Ni合金からなる前記推進薬導入部と、
前記推進薬導入部の一端と一体をなしているNi合金からなる導入管フランジと、
前記チャンバと前記推薬弁との間にてTi合金からなる複数の柱部を介してチャンバを支持し、Ti合金からなる推薬弁フランジと、
を備え、
前記推薬弁フランジには、前記導入管フランジの形状に沿って凹部が形成され、組み付け時には当該凹部に前記導入管フランジが嵌合されることを特徴とするスラスタ装置。 - 前記柱部は3本であることを特徴とする請求項1記載のスラスタ装置。
- 前記柱部の先端に雌ネジが螺刻されており、雄ネジが螺刻されたNi合金からなるファスナを当該柱部の先端に締結することで、当該柱部と前記チャンバとを接続することを特徴とする請求項1又は2記載のスラスタ装置。
- 請求項1から3のいずれかに記載のスラスタ装置が、前記推薬弁フランジを介して取り付けられていることを特徴とする宇宙機。
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2012113428A JP5992722B2 (ja) | 2012-05-17 | 2012-05-17 | スラスタ装置及び宇宙機 |
EP13158905.3A EP2664774B1 (en) | 2012-05-17 | 2013-03-13 | Thruster and spacecraft |
US13/834,493 US9376987B2 (en) | 2012-05-17 | 2013-03-15 | Thruster and spacecraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2012113428A JP5992722B2 (ja) | 2012-05-17 | 2012-05-17 | スラスタ装置及び宇宙機 |
Publications (2)
Publication Number | Publication Date |
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JP2013238208A JP2013238208A (ja) | 2013-11-28 |
JP5992722B2 true JP5992722B2 (ja) | 2016-09-14 |
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Application Number | Title | Priority Date | Filing Date |
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JP2012113428A Active JP5992722B2 (ja) | 2012-05-17 | 2012-05-17 | スラスタ装置及び宇宙機 |
Country Status (3)
Country | Link |
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US (1) | US9376987B2 (ja) |
EP (1) | EP2664774B1 (ja) |
JP (1) | JP5992722B2 (ja) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
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US9493252B2 (en) * | 2013-06-28 | 2016-11-15 | Busek Co., Inc. | Long life thruster |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3807657A (en) * | 1972-01-31 | 1974-04-30 | Rca Corp | Dual thrust level monopropellant spacecraft propulsion system |
US4069664A (en) * | 1974-01-24 | 1978-01-24 | Hughes Aircraft Company | Monopropellant thruster |
GB1470664A (en) * | 1974-08-02 | 1977-04-21 | Secr Defence | Spacecraft thruster devices |
US4324096A (en) * | 1979-04-23 | 1982-04-13 | Hughes Aircraft Company | Hydrazine thruster |
US4577461A (en) * | 1983-06-22 | 1986-03-25 | Cann Gordon L | Spacecraft optimized arc rocket |
JPS61291752A (ja) * | 1985-06-17 | 1986-12-22 | Nissan Motor Co Ltd | ロケツトノズル |
JPH0318657A (ja) * | 1989-06-14 | 1991-01-28 | Keishi Shishino | ロケットモータ |
JPH0542343A (ja) * | 1991-08-06 | 1993-02-23 | Kobe Steel Ltd | Mg合金鋳造用金型 |
JPH0641715A (ja) * | 1992-05-25 | 1994-02-15 | Nippon Steel Corp | チタン合金バルブの製造方法 |
US5568723A (en) * | 1992-09-08 | 1996-10-29 | Olin Corporation | Long life catalytic gas generator for space propulsion applications |
DE4310821C2 (de) * | 1993-04-02 | 1996-03-14 | Daimler Benz Aerospace Ag | Lichtbogen-Strahltriebwerk |
DE69812014T2 (de) * | 1997-08-29 | 2003-12-24 | Hughes Electronics Corp | Raketenmotor mit einem Verbindungsstück zwischen Verbrennungskammer und Injektor |
DE69841644D1 (de) * | 1997-08-29 | 2010-06-10 | Hughes Electronics Corp | Raketenantrieb mit einer Stufenstruktur des Innenraums |
JP2004092449A (ja) * | 2002-08-30 | 2004-03-25 | Mitsubishi Heavy Ind Ltd | 飛行体のスラスタ |
JP2004195756A (ja) * | 2002-12-17 | 2004-07-15 | Matsushita Electric Ind Co Ltd | 光ディスク基板用金型 |
DE112006000769C5 (de) * | 2005-03-28 | 2022-08-18 | Kyocera Corporation | Hartmetall und Schneidwerkzeug |
US20080064914A1 (en) * | 2005-03-28 | 2008-03-13 | Fokema Mark D | Thermally stable catalyst and process for the decomposition of liquid propellants |
JP5137192B2 (ja) | 2008-04-15 | 2013-02-06 | 株式会社Ihiエアロスペース | 一液スラスタ |
-
2012
- 2012-05-17 JP JP2012113428A patent/JP5992722B2/ja active Active
-
2013
- 2013-03-13 EP EP13158905.3A patent/EP2664774B1/en active Active
- 2013-03-15 US US13/834,493 patent/US9376987B2/en active Active
Also Published As
Publication number | Publication date |
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US9376987B2 (en) | 2016-06-28 |
EP2664774B1 (en) | 2016-07-20 |
JP2013238208A (ja) | 2013-11-28 |
US20130305687A1 (en) | 2013-11-21 |
EP2664774A2 (en) | 2013-11-20 |
EP2664774A3 (en) | 2015-05-06 |
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