On-orbit Experiment Plan of Loop Heat Pipe and the Test Results of Ground Test
Abstract It is becoming increasingly difficult to meet the challenging thermal control requirements of modern spacecraft missions with only existing thermal control devices such as conventional heat pipes. A loop heat pipe (LHP) is an effective method to overcome some of these thermal control constr...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Okamoto, Atsushi [verfasserIn] |
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| Format: |
E-Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2019 |
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| Schlagwörter: |
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| Anmerkung: |
© Springer Nature B.V. 2019 |
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| Übergeordnetes Werk: |
Enthalten in: Microgravity science and technology - Heidelberg : Springer, 2007, 31(2019), 3 vom: 23. Mai, Seite 327-337 |
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| Übergeordnetes Werk: |
volume:31 ; year:2019 ; number:3 ; day:23 ; month:05 ; pages:327-337 |
| Links: |
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| DOI / URN: |
10.1007/s12217-019-9703-4 |
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| Katalog-ID: |
SPR025400355 |
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| 520 | |a Abstract It is becoming increasingly difficult to meet the challenging thermal control requirements of modern spacecraft missions with only existing thermal control devices such as conventional heat pipes. A loop heat pipe (LHP) is an effective method to overcome some of these thermal control constraints. The LHP is a passive two-phase heat transfer device that utilizes the evaporation and condensation of a working fluid to transfer heat and capillary force to circulate the fluid. The LHP can transport much heat for a long distance against gravity and has many other excellent characteristics, such as high controllability of operating temperature and a shutdown function. In this study, LHPs for space application have been developing. As a part of the study, a bread board model (BBM) of LHP was designed and fabricated. As a result of an on-ground test of the BBM, it was confirmed that the BBM fulfilled all requirement (e.g. maximum heat transport rate, minimum required heat load for start-up, operating temperature control and shutdown function). To adopt the LHP as a heat transfer device in practical spacecraft mission, the thermal characteristics under micro-gravity conditions should be examined in advance. An on-orbit experiment of a LHP radiator system is planned. This paper describes the test plan of on-orbit experiment of a LHP radiator system on the International Space Station (ISS) and the results of thermal vacuum test of flight model for on-orbit experiment on ground. | ||
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| 650 | 4 | |a On-orbit experiment |7 (dpeaa)DE-He213 | |
| 700 | 1 | |a Miyakita, Takeshi |4 aut | |
| 700 | 1 | |a Nagano, Hosei |4 aut | |
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10.1007/s12217-019-9703-4 doi (DE-627)SPR025400355 (SPR)s12217-019-9703-4-e DE-627 ger DE-627 rakwb eng Okamoto, Atsushi verfasserin (orcid)0000-0003-2725-9189 aut On-orbit Experiment Plan of Loop Heat Pipe and the Test Results of Ground Test 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Springer Nature B.V. 2019 Abstract It is becoming increasingly difficult to meet the challenging thermal control requirements of modern spacecraft missions with only existing thermal control devices such as conventional heat pipes. A loop heat pipe (LHP) is an effective method to overcome some of these thermal control constraints. The LHP is a passive two-phase heat transfer device that utilizes the evaporation and condensation of a working fluid to transfer heat and capillary force to circulate the fluid. The LHP can transport much heat for a long distance against gravity and has many other excellent characteristics, such as high controllability of operating temperature and a shutdown function. In this study, LHPs for space application have been developing. As a part of the study, a bread board model (BBM) of LHP was designed and fabricated. As a result of an on-ground test of the BBM, it was confirmed that the BBM fulfilled all requirement (e.g. maximum heat transport rate, minimum required heat load for start-up, operating temperature control and shutdown function). To adopt the LHP as a heat transfer device in practical spacecraft mission, the thermal characteristics under micro-gravity conditions should be examined in advance. An on-orbit experiment of a LHP radiator system is planned. This paper describes the test plan of on-orbit experiment of a LHP radiator system on the International Space Station (ISS) and the results of thermal vacuum test of flight model for on-orbit experiment on ground. Loop Heat Pipe (dpeaa)DE-He213 Thermal Control (dpeaa)DE-He213 Satellite (dpeaa)DE-He213 Heat transfer (dpeaa)DE-He213 On-orbit experiment (dpeaa)DE-He213 Miyakita, Takeshi aut Nagano, Hosei aut Enthalten in Microgravity science and technology Heidelberg : Springer, 2007 31(2019), 3 vom: 23. Mai, Seite 327-337 (DE-627)556726928 (DE-600)2403671-7 1875-0494 nnns volume:31 year:2019 number:3 day:23 month:05 pages:327-337 https://dx.doi.org/10.1007/s12217-019-9703-4 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 31 2019 3 23 05 327-337 |
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10.1007/s12217-019-9703-4 doi (DE-627)SPR025400355 (SPR)s12217-019-9703-4-e DE-627 ger DE-627 rakwb eng Okamoto, Atsushi verfasserin (orcid)0000-0003-2725-9189 aut On-orbit Experiment Plan of Loop Heat Pipe and the Test Results of Ground Test 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Springer Nature B.V. 2019 Abstract It is becoming increasingly difficult to meet the challenging thermal control requirements of modern spacecraft missions with only existing thermal control devices such as conventional heat pipes. A loop heat pipe (LHP) is an effective method to overcome some of these thermal control constraints. The LHP is a passive two-phase heat transfer device that utilizes the evaporation and condensation of a working fluid to transfer heat and capillary force to circulate the fluid. The LHP can transport much heat for a long distance against gravity and has many other excellent characteristics, such as high controllability of operating temperature and a shutdown function. In this study, LHPs for space application have been developing. As a part of the study, a bread board model (BBM) of LHP was designed and fabricated. As a result of an on-ground test of the BBM, it was confirmed that the BBM fulfilled all requirement (e.g. maximum heat transport rate, minimum required heat load for start-up, operating temperature control and shutdown function). To adopt the LHP as a heat transfer device in practical spacecraft mission, the thermal characteristics under micro-gravity conditions should be examined in advance. An on-orbit experiment of a LHP radiator system is planned. This paper describes the test plan of on-orbit experiment of a LHP radiator system on the International Space Station (ISS) and the results of thermal vacuum test of flight model for on-orbit experiment on ground. Loop Heat Pipe (dpeaa)DE-He213 Thermal Control (dpeaa)DE-He213 Satellite (dpeaa)DE-He213 Heat transfer (dpeaa)DE-He213 On-orbit experiment (dpeaa)DE-He213 Miyakita, Takeshi aut Nagano, Hosei aut Enthalten in Microgravity science and technology Heidelberg : Springer, 2007 31(2019), 3 vom: 23. Mai, Seite 327-337 (DE-627)556726928 (DE-600)2403671-7 1875-0494 nnns volume:31 year:2019 number:3 day:23 month:05 pages:327-337 https://dx.doi.org/10.1007/s12217-019-9703-4 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 31 2019 3 23 05 327-337 |
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10.1007/s12217-019-9703-4 doi (DE-627)SPR025400355 (SPR)s12217-019-9703-4-e DE-627 ger DE-627 rakwb eng Okamoto, Atsushi verfasserin (orcid)0000-0003-2725-9189 aut On-orbit Experiment Plan of Loop Heat Pipe and the Test Results of Ground Test 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Springer Nature B.V. 2019 Abstract It is becoming increasingly difficult to meet the challenging thermal control requirements of modern spacecraft missions with only existing thermal control devices such as conventional heat pipes. A loop heat pipe (LHP) is an effective method to overcome some of these thermal control constraints. The LHP is a passive two-phase heat transfer device that utilizes the evaporation and condensation of a working fluid to transfer heat and capillary force to circulate the fluid. The LHP can transport much heat for a long distance against gravity and has many other excellent characteristics, such as high controllability of operating temperature and a shutdown function. In this study, LHPs for space application have been developing. As a part of the study, a bread board model (BBM) of LHP was designed and fabricated. As a result of an on-ground test of the BBM, it was confirmed that the BBM fulfilled all requirement (e.g. maximum heat transport rate, minimum required heat load for start-up, operating temperature control and shutdown function). To adopt the LHP as a heat transfer device in practical spacecraft mission, the thermal characteristics under micro-gravity conditions should be examined in advance. An on-orbit experiment of a LHP radiator system is planned. This paper describes the test plan of on-orbit experiment of a LHP radiator system on the International Space Station (ISS) and the results of thermal vacuum test of flight model for on-orbit experiment on ground. Loop Heat Pipe (dpeaa)DE-He213 Thermal Control (dpeaa)DE-He213 Satellite (dpeaa)DE-He213 Heat transfer (dpeaa)DE-He213 On-orbit experiment (dpeaa)DE-He213 Miyakita, Takeshi aut Nagano, Hosei aut Enthalten in Microgravity science and technology Heidelberg : Springer, 2007 31(2019), 3 vom: 23. Mai, Seite 327-337 (DE-627)556726928 (DE-600)2403671-7 1875-0494 nnns volume:31 year:2019 number:3 day:23 month:05 pages:327-337 https://dx.doi.org/10.1007/s12217-019-9703-4 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 31 2019 3 23 05 327-337 |
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10.1007/s12217-019-9703-4 doi (DE-627)SPR025400355 (SPR)s12217-019-9703-4-e DE-627 ger DE-627 rakwb eng Okamoto, Atsushi verfasserin (orcid)0000-0003-2725-9189 aut On-orbit Experiment Plan of Loop Heat Pipe and the Test Results of Ground Test 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Springer Nature B.V. 2019 Abstract It is becoming increasingly difficult to meet the challenging thermal control requirements of modern spacecraft missions with only existing thermal control devices such as conventional heat pipes. A loop heat pipe (LHP) is an effective method to overcome some of these thermal control constraints. The LHP is a passive two-phase heat transfer device that utilizes the evaporation and condensation of a working fluid to transfer heat and capillary force to circulate the fluid. The LHP can transport much heat for a long distance against gravity and has many other excellent characteristics, such as high controllability of operating temperature and a shutdown function. In this study, LHPs for space application have been developing. As a part of the study, a bread board model (BBM) of LHP was designed and fabricated. As a result of an on-ground test of the BBM, it was confirmed that the BBM fulfilled all requirement (e.g. maximum heat transport rate, minimum required heat load for start-up, operating temperature control and shutdown function). To adopt the LHP as a heat transfer device in practical spacecraft mission, the thermal characteristics under micro-gravity conditions should be examined in advance. An on-orbit experiment of a LHP radiator system is planned. This paper describes the test plan of on-orbit experiment of a LHP radiator system on the International Space Station (ISS) and the results of thermal vacuum test of flight model for on-orbit experiment on ground. Loop Heat Pipe (dpeaa)DE-He213 Thermal Control (dpeaa)DE-He213 Satellite (dpeaa)DE-He213 Heat transfer (dpeaa)DE-He213 On-orbit experiment (dpeaa)DE-He213 Miyakita, Takeshi aut Nagano, Hosei aut Enthalten in Microgravity science and technology Heidelberg : Springer, 2007 31(2019), 3 vom: 23. Mai, Seite 327-337 (DE-627)556726928 (DE-600)2403671-7 1875-0494 nnns volume:31 year:2019 number:3 day:23 month:05 pages:327-337 https://dx.doi.org/10.1007/s12217-019-9703-4 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 31 2019 3 23 05 327-337 |
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10.1007/s12217-019-9703-4 doi (DE-627)SPR025400355 (SPR)s12217-019-9703-4-e DE-627 ger DE-627 rakwb eng Okamoto, Atsushi verfasserin (orcid)0000-0003-2725-9189 aut On-orbit Experiment Plan of Loop Heat Pipe and the Test Results of Ground Test 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Springer Nature B.V. 2019 Abstract It is becoming increasingly difficult to meet the challenging thermal control requirements of modern spacecraft missions with only existing thermal control devices such as conventional heat pipes. A loop heat pipe (LHP) is an effective method to overcome some of these thermal control constraints. The LHP is a passive two-phase heat transfer device that utilizes the evaporation and condensation of a working fluid to transfer heat and capillary force to circulate the fluid. The LHP can transport much heat for a long distance against gravity and has many other excellent characteristics, such as high controllability of operating temperature and a shutdown function. In this study, LHPs for space application have been developing. As a part of the study, a bread board model (BBM) of LHP was designed and fabricated. As a result of an on-ground test of the BBM, it was confirmed that the BBM fulfilled all requirement (e.g. maximum heat transport rate, minimum required heat load for start-up, operating temperature control and shutdown function). To adopt the LHP as a heat transfer device in practical spacecraft mission, the thermal characteristics under micro-gravity conditions should be examined in advance. An on-orbit experiment of a LHP radiator system is planned. This paper describes the test plan of on-orbit experiment of a LHP radiator system on the International Space Station (ISS) and the results of thermal vacuum test of flight model for on-orbit experiment on ground. Loop Heat Pipe (dpeaa)DE-He213 Thermal Control (dpeaa)DE-He213 Satellite (dpeaa)DE-He213 Heat transfer (dpeaa)DE-He213 On-orbit experiment (dpeaa)DE-He213 Miyakita, Takeshi aut Nagano, Hosei aut Enthalten in Microgravity science and technology Heidelberg : Springer, 2007 31(2019), 3 vom: 23. Mai, Seite 327-337 (DE-627)556726928 (DE-600)2403671-7 1875-0494 nnns volume:31 year:2019 number:3 day:23 month:05 pages:327-337 https://dx.doi.org/10.1007/s12217-019-9703-4 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 31 2019 3 23 05 327-337 |
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Okamoto, Atsushi @@aut@@ Miyakita, Takeshi @@aut@@ Nagano, Hosei @@aut@@ |
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A loop heat pipe (LHP) is an effective method to overcome some of these thermal control constraints. The LHP is a passive two-phase heat transfer device that utilizes the evaporation and condensation of a working fluid to transfer heat and capillary force to circulate the fluid. The LHP can transport much heat for a long distance against gravity and has many other excellent characteristics, such as high controllability of operating temperature and a shutdown function. In this study, LHPs for space application have been developing. As a part of the study, a bread board model (BBM) of LHP was designed and fabricated. As a result of an on-ground test of the BBM, it was confirmed that the BBM fulfilled all requirement (e.g. maximum heat transport rate, minimum required heat load for start-up, operating temperature control and shutdown function). To adopt the LHP as a heat transfer device in practical spacecraft mission, the thermal characteristics under micro-gravity conditions should be examined in advance. An on-orbit experiment of a LHP radiator system is planned. 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Okamoto, Atsushi |
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Okamoto, Atsushi misc Loop Heat Pipe misc Thermal Control misc Satellite misc Heat transfer misc On-orbit experiment On-orbit Experiment Plan of Loop Heat Pipe and the Test Results of Ground Test |
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On-orbit Experiment Plan of Loop Heat Pipe and the Test Results of Ground Test Loop Heat Pipe (dpeaa)DE-He213 Thermal Control (dpeaa)DE-He213 Satellite (dpeaa)DE-He213 Heat transfer (dpeaa)DE-He213 On-orbit experiment (dpeaa)DE-He213 |
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on-orbit experiment plan of loop heat pipe and the test results of ground test |
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On-orbit Experiment Plan of Loop Heat Pipe and the Test Results of Ground Test |
| abstract |
Abstract It is becoming increasingly difficult to meet the challenging thermal control requirements of modern spacecraft missions with only existing thermal control devices such as conventional heat pipes. A loop heat pipe (LHP) is an effective method to overcome some of these thermal control constraints. The LHP is a passive two-phase heat transfer device that utilizes the evaporation and condensation of a working fluid to transfer heat and capillary force to circulate the fluid. The LHP can transport much heat for a long distance against gravity and has many other excellent characteristics, such as high controllability of operating temperature and a shutdown function. In this study, LHPs for space application have been developing. As a part of the study, a bread board model (BBM) of LHP was designed and fabricated. As a result of an on-ground test of the BBM, it was confirmed that the BBM fulfilled all requirement (e.g. maximum heat transport rate, minimum required heat load for start-up, operating temperature control and shutdown function). To adopt the LHP as a heat transfer device in practical spacecraft mission, the thermal characteristics under micro-gravity conditions should be examined in advance. An on-orbit experiment of a LHP radiator system is planned. This paper describes the test plan of on-orbit experiment of a LHP radiator system on the International Space Station (ISS) and the results of thermal vacuum test of flight model for on-orbit experiment on ground. © Springer Nature B.V. 2019 |
| abstractGer |
Abstract It is becoming increasingly difficult to meet the challenging thermal control requirements of modern spacecraft missions with only existing thermal control devices such as conventional heat pipes. A loop heat pipe (LHP) is an effective method to overcome some of these thermal control constraints. The LHP is a passive two-phase heat transfer device that utilizes the evaporation and condensation of a working fluid to transfer heat and capillary force to circulate the fluid. The LHP can transport much heat for a long distance against gravity and has many other excellent characteristics, such as high controllability of operating temperature and a shutdown function. In this study, LHPs for space application have been developing. As a part of the study, a bread board model (BBM) of LHP was designed and fabricated. As a result of an on-ground test of the BBM, it was confirmed that the BBM fulfilled all requirement (e.g. maximum heat transport rate, minimum required heat load for start-up, operating temperature control and shutdown function). To adopt the LHP as a heat transfer device in practical spacecraft mission, the thermal characteristics under micro-gravity conditions should be examined in advance. An on-orbit experiment of a LHP radiator system is planned. This paper describes the test plan of on-orbit experiment of a LHP radiator system on the International Space Station (ISS) and the results of thermal vacuum test of flight model for on-orbit experiment on ground. © Springer Nature B.V. 2019 |
| abstract_unstemmed |
Abstract It is becoming increasingly difficult to meet the challenging thermal control requirements of modern spacecraft missions with only existing thermal control devices such as conventional heat pipes. A loop heat pipe (LHP) is an effective method to overcome some of these thermal control constraints. The LHP is a passive two-phase heat transfer device that utilizes the evaporation and condensation of a working fluid to transfer heat and capillary force to circulate the fluid. The LHP can transport much heat for a long distance against gravity and has many other excellent characteristics, such as high controllability of operating temperature and a shutdown function. In this study, LHPs for space application have been developing. As a part of the study, a bread board model (BBM) of LHP was designed and fabricated. As a result of an on-ground test of the BBM, it was confirmed that the BBM fulfilled all requirement (e.g. maximum heat transport rate, minimum required heat load for start-up, operating temperature control and shutdown function). To adopt the LHP as a heat transfer device in practical spacecraft mission, the thermal characteristics under micro-gravity conditions should be examined in advance. An on-orbit experiment of a LHP radiator system is planned. This paper describes the test plan of on-orbit experiment of a LHP radiator system on the International Space Station (ISS) and the results of thermal vacuum test of flight model for on-orbit experiment on ground. © Springer Nature B.V. 2019 |
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On-orbit Experiment Plan of Loop Heat Pipe and the Test Results of Ground Test |
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Miyakita, Takeshi Nagano, Hosei |
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| score |
7.399457 |