JP4317456B2 - 伸縮可能な放熱器を備える宇宙機 - Google Patents
伸縮可能な放熱器を備える宇宙機 Download PDFInfo
- Publication number
- JP4317456B2 JP4317456B2 JP2003559862A JP2003559862A JP4317456B2 JP 4317456 B2 JP4317456 B2 JP 4317456B2 JP 2003559862 A JP2003559862 A JP 2003559862A JP 2003559862 A JP2003559862 A JP 2003559862A JP 4317456 B2 JP4317456 B2 JP 4317456B2
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- Prior art keywords
- radiator
- spacecraft
- communication antenna
- main body
- main communication
- Prior art date
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- Expired - Lifetime
Links
- 238000005516 engineering process Methods 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 230000037237 body shape Effects 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
-
- 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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
-
- 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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
- B64G1/2221—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the manner of deployment
- B64G1/2222—Folding
-
- 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
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
- B64G1/503—Radiator panels
-
- 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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Environmental & Geological Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Biodiversity & Conservation Biology (AREA)
- Health & Medical Sciences (AREA)
- Environmental Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Toxicology (AREA)
- Details Of Aerials (AREA)
- Aerials With Secondary Devices (AREA)
- Photovoltaic Devices (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Description
本発明に係る宇宙機は、本体と、該本体に対して所定の方向を有する少なくとも一つの主通信アンテナと、該主アンテナと反対方向の視野を有する少なくとも一つの無指向性アンテナと、前記本体と結合された軸回りに移動することによって、前記本体に格納された格納位置と展開位置との間で展開可能とされた少なくとも一つの発熱器とを備えてなる宇宙機において、前記展開軸が前記無指向性アンテナの前記視野の軸線方向と平行であり、かつ前記主アンテナが配された面と平行である、前記本体の面のうち一つの面内に実質的に位置しており、前記展開軸が、前記放熱器が太陽電池パネルが配された表面に対して当接される前記格納位置から、前記放熱器の格納時に該放熱器を保持する面の実質的に延長面内で、略180度の角度にわたって展開できるように配されていることを特徴とする。
14 主通信アンテナ
25 放熱器
26 無指向性アンテナ
30 反転軸
Claims (8)
- 本体(10)と、
該本体(10)に対して所定の方向を有する少なくとも1つの主通信アンテナ(14)と、
少なくとも1つの放熱器(25)であって、前記放熱器(25)が前記本体(10)に対して保持される格納位置と、展開軸(30)が前記宇宙機の前記本体(10)に結合され、且つ太陽電池パネル(12)を配する前記本体の第1の面(24)の平面内に実質的に位置付けられる展開位置との間で、それぞれの展開軸(30)に関して展開することによって展開可能である前記少なくとも1つの放熱器(25)と、
を有している宇宙機であって、
前記展開軸(30)は、前記放熱器(25)が、前記太陽電池パネル(12)を配された前記第1の面(24)に対して当接される前記格納位置から、前記放熱器(25)が、前記放熱器の格納時に前記放熱器(25)が保持される面に対して、前記第1の面(24)の平面内に実質的に延在する前記展開位置まで、略180度の角度にわたって展開するように方向付けされる宇宙機において、
前記宇宙機は、前記少なくとも1つの主通信アンテナ(14)の視野に対して反対側の視野を有している少なくとも1つの無指向性アンテナ(26)をさらに有し、
前記展開位置における前記放熱器(25)は、前記少なくとも1つの主通信アンテナ(14)の視野の側に対して反対である前記少なくとも1つの主通信アンテナ(14)の側に、前記少なくとも1つの主通信アンテナ(14)を配する、又は前記少なくとも1つの主通信アンテナ(14)を配する前記本体(10)の面に平行である、前記本体(10)の第2の面に対して前記本体(10)の外側に突出していることを特徴とする宇宙機。 - 請求項1に記載の宇宙機であって、
人工衛星を備え、
前記少なくとも1つの主通信アンテナ(14)が前記本体(10)の東側面又は西側面上に配され、前記少なくとも1つの主通信アンテナの視野が地球に向けられ、
前記格納位置で、前記放熱器(25)が前記本体(10)の北側面又は南側面に対して保持され、
前記展開軸(30)が、前記人工衛星の前記本体(10)に結合され、前記放熱器(25)が格納時に保持された前記北側面又は南側面の平面内に実質的に位置し、
前記展開軸(30)が、前記格納位置から前記放熱器(25)が前記本体(10)から東又は西に向けて展開する前記展開された位置まで略180度の角度にわたって前記放熱器(25)が展開するように方向付けられることを特徴とする宇宙機。 - 請求項1又は2に記載の宇宙機であって、
前記放熱器(25)の傾斜角が140度から180度とされていることを特徴とする宇宙機。 - 請求項2に記載の宇宙機であって、
前記北側面及び前記南側面の各面に、少なくとも1つの放熱器(25)が配されていることを特徴とする宇宙機。 - 請求項2又は4に記載の宇宙機であって、
前記展開軸(30)は、地球の方向に対して略45度に傾斜するように配され、
前記放熱器が地球の方向に対する人工衛星の長さと略等しい全長を有していることを特徴とする宇宙機。 - 請求項1又は3に記載の宇宙機であって、
前記展開軸(30)は、前記展開軸(30)が位置付けられる前記本体(10)の前記第1の面(24)の平面内に前記少なくとも1つの主通信アンテナ(14)を配する前記本体(10)の前記第2の面に略平行に方向付けられることを特徴とする宇宙機。 - 請求項1又は3に記載の宇宙機であって、
前記展開軸(30)は、前記少なくとも1つの主通信アンテナ(14)を配する、前記本体(10)の前記第2の面の方向に対して略45度に傾斜され、前記展開軸(30)が、前記本体(10)の前記第1の面(24)の前記平面内で位置付けられることを特徴とする宇宙機。 - 請求項4に記載の宇宙機であって、
前記北側面及び前記南側面の各面に、2つの放熱器(25)が配されており、
展開された位置で前記本体(10)から東側に向けて一の放熱器を展開し、西川に向けて他の放熱器を展開することを特徴とする宇宙機。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0200006A FR2834274B1 (fr) | 2002-01-02 | 2002-01-02 | Vehicule spatial a radiateurs deployables |
PCT/FR2002/004428 WO2003059740A1 (fr) | 2002-01-02 | 2002-12-18 | Vehicule spatial a radiateurs deployables |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2005514270A JP2005514270A (ja) | 2005-05-19 |
JP2005514270A5 JP2005514270A5 (ja) | 2008-11-27 |
JP4317456B2 true JP4317456B2 (ja) | 2009-08-19 |
Family
ID=8871135
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2003559862A Expired - Lifetime JP4317456B2 (ja) | 2002-01-02 | 2002-12-18 | 伸縮可能な放熱器を備える宇宙機 |
Country Status (8)
Country | Link |
---|---|
US (1) | US7036772B2 (ja) |
EP (1) | EP1461248B1 (ja) |
JP (1) | JP4317456B2 (ja) |
CN (1) | CN1321860C (ja) |
AU (1) | AU2002364459A1 (ja) |
DE (1) | DE60212709T2 (ja) |
FR (1) | FR2834274B1 (ja) |
WO (1) | WO2003059740A1 (ja) |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7602349B2 (en) * | 2006-02-24 | 2009-10-13 | Lockheed Martin Corporation | System of stowing and deploying multiple phased arrays or combinations of arrays and reflectors |
US7874520B2 (en) * | 2006-03-21 | 2011-01-25 | Lockheed Martin Corporation | Satellite with deployable, articulatable thermal radiators |
US8714492B2 (en) | 2012-02-07 | 2014-05-06 | Lockheed Martin Corporation | Non-interfering deployable radiator arrangement for geo spacecraft |
US8960608B2 (en) | 2012-02-07 | 2015-02-24 | Lockheed Martin Corporation | Deployable radiator having an increased view factor |
CN102700728B (zh) * | 2012-06-18 | 2014-08-13 | 上海卫星工程研究所 | 一种卫星太阳电池阵在轨被遮挡的确定方法及其应用 |
FR2996526B1 (fr) | 2012-10-05 | 2015-05-15 | Thales Sa | Satellite a modules de charge utile deployables |
FR3006298B1 (fr) * | 2013-06-03 | 2016-10-14 | Astrium Sas | Vehicule spatial comprenant au moins un couple de bras porteurs muni d'un module creux de montage et procede pour la mise en oeuvre d'un tel vehicule |
US9352856B1 (en) * | 2013-12-04 | 2016-05-31 | Space Systems/Loral, Llc | Axially grooved crossing heat pipes |
US9878808B2 (en) * | 2015-01-08 | 2018-01-30 | The Boeing Company | Spacecraft and spacecraft radiator panels with composite face-sheets |
FR3031969B1 (fr) * | 2015-01-27 | 2017-01-27 | Airbus Defence & Space Sas | Satellite artificiel et procede de remplissage d'un reservoir de gaz propulsif dudit satellite artificiel |
US10118717B2 (en) * | 2015-06-02 | 2018-11-06 | Airbus Defence And Space Sas | Artificial Satellite |
US10018426B2 (en) | 2016-05-12 | 2018-07-10 | The Boeing Company | Composite heat pipes and sandwich panels, radiator panels, and spacecraft with composite heat pipes |
CN106347714B (zh) * | 2016-08-31 | 2018-06-12 | 北京空间飞行器总体设计部 | 一种具备在轨弹抛功能的舱外辐射器防护罩系统 |
CN110015444A (zh) * | 2019-03-29 | 2019-07-16 | 上海卫星工程研究所 | 中高轨道零倾角合成孔径雷达卫星构型 |
CN114408224B (zh) * | 2021-12-20 | 2024-05-17 | 中国航天科工集团八五一一研究所 | 一种空间可回收式折叠机构 |
US12017806B2 (en) * | 2022-01-21 | 2024-06-25 | Maxar Space Llc | Satellite with modular radiator panels |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5833175A (en) * | 1995-12-22 | 1998-11-10 | Hughes Electronics Corporation | Spacecraft with large east-west dimensions |
US5927654A (en) * | 1997-05-16 | 1999-07-27 | Lockheed Martin Corp. | Spacecraft with active antenna array protected against temperature extremes |
US6378809B1 (en) | 1997-10-10 | 2002-04-30 | Space Systems | AFT deployable thermal radiators for spacecraft |
US6311931B1 (en) * | 1999-12-17 | 2001-11-06 | The Boeing Company | Bi-directional momentum bias spacecraft attitude control |
US6854510B2 (en) * | 2001-04-24 | 2005-02-15 | Space Systems/Loral, Inc. | Spacecraft radiator system and method using cross-coupled deployable thermal radiators |
-
2002
- 2002-01-02 FR FR0200006A patent/FR2834274B1/fr not_active Expired - Lifetime
- 2002-12-18 WO PCT/FR2002/004428 patent/WO2003059740A1/fr active IP Right Grant
- 2002-12-18 JP JP2003559862A patent/JP4317456B2/ja not_active Expired - Lifetime
- 2002-12-18 EP EP02799822A patent/EP1461248B1/fr not_active Expired - Fee Related
- 2002-12-18 DE DE60212709T patent/DE60212709T2/de not_active Expired - Lifetime
- 2002-12-18 AU AU2002364459A patent/AU2002364459A1/en not_active Abandoned
- 2002-12-18 CN CNB028266021A patent/CN1321860C/zh not_active Expired - Fee Related
-
2004
- 2004-06-18 US US10/871,934 patent/US7036772B2/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
WO2003059740A1 (fr) | 2003-07-24 |
EP1461248A1 (fr) | 2004-09-29 |
DE60212709T2 (de) | 2007-02-22 |
FR2834274B1 (fr) | 2004-04-02 |
CN1321860C (zh) | 2007-06-20 |
FR2834274A1 (fr) | 2003-07-04 |
EP1461248B1 (fr) | 2006-06-21 |
US20050023415A1 (en) | 2005-02-03 |
AU2002364459A1 (en) | 2003-07-30 |
CN1610628A (zh) | 2005-04-27 |
US7036772B2 (en) | 2006-05-02 |
JP2005514270A (ja) | 2005-05-19 |
DE60212709D1 (de) | 2006-08-03 |
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