Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8932043
L. Fontani, M. Migliaro, M. Inversi, M. Bacci, F. Bigongiari, F. Petroni, Elena Casali, M. Triggianese, D. Levacq
This paper presents a compact and configurable DC/DC converter able to generate several isolated output voltages starting from 28V or 50V input bus voltage and conceived to be used mainly as power supply of spacecraft payloads/instruments of ESA missions. The DC-DC converter has been designed to be both compact and configurable, in order to comply with different needs. The idea is to make the design of such converter available together with a complete list of the well-known qualified parts, a board layout and all the necessary analysis like WCA, FMECA, PSA, reliability and radiation analysis. In this way the end-user is fully aware of the implementation and limitations of the power supply. Since one of the main requirement of a Power supply is the compactness, the effort of the project has been mainly devoted to reduce the size and the mass of the converter. For this purpose, a dedicated ASIC has been developed in order to integrate inside a single chip multiple functions, including protections, and avoiding any failure propagation outside the module.
{"title":"DC2I, Configurable and compact isolated Multi-output DC-DC converter","authors":"L. Fontani, M. Migliaro, M. Inversi, M. Bacci, F. Bigongiari, F. Petroni, Elena Casali, M. Triggianese, D. Levacq","doi":"10.1109/ESPC.2019.8932043","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932043","url":null,"abstract":"This paper presents a compact and configurable DC/DC converter able to generate several isolated output voltages starting from 28V or 50V input bus voltage and conceived to be used mainly as power supply of spacecraft payloads/instruments of ESA missions. The DC-DC converter has been designed to be both compact and configurable, in order to comply with different needs. The idea is to make the design of such converter available together with a complete list of the well-known qualified parts, a board layout and all the necessary analysis like WCA, FMECA, PSA, reliability and radiation analysis. In this way the end-user is fully aware of the implementation and limitations of the power supply. Since one of the main requirement of a Power supply is the compactness, the effort of the project has been mainly devoted to reduce the size and the mass of the converter. For this purpose, a dedicated ASIC has been developed in order to integrate inside a single chip multiple functions, including protections, and avoiding any failure propagation outside the module.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"69 1","pages":"1-7"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"73196889","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8932067
M. Carbone, Fernando Javier Pinto Marin, E. Lapena, F. Gómez-Carpintero, K. Hirche, S. Morand, M. Marin, Sylvain Prevot, Alexandre Guidoin, N. Neugnot, Mario Gomez Alonso, Miguel Rodríguez Álvarez
GaN technology has gained interest and is becoming widely commercially available due to their superior performances in power conversion applications. The paper shall promote the need for European GaN technology and boost R&D in the technological and reliability field for space. The paper will provide a clear overview on the technology, reliability, radiation, application and market.
{"title":"An overview of GaN FET Technology, Reliability, Radiation and Market for future Space Application","authors":"M. Carbone, Fernando Javier Pinto Marin, E. Lapena, F. Gómez-Carpintero, K. Hirche, S. Morand, M. Marin, Sylvain Prevot, Alexandre Guidoin, N. Neugnot, Mario Gomez Alonso, Miguel Rodríguez Álvarez","doi":"10.1109/ESPC.2019.8932067","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932067","url":null,"abstract":"GaN technology has gained interest and is becoming widely commercially available due to their superior performances in power conversion applications. The paper shall promote the need for European GaN technology and boost R&D in the technological and reliability field for space. The paper will provide a clear overview on the technology, reliability, radiation, application and market.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"7 1","pages":"1-4"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"75619132","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8932088
Xiangan You, Xiaofeng Sun, Jing-ming Fei, Minghua Zhang, Bin-bin Zhang, Tao Chen, Yuqi Qin, Nana Rong, Chengan Wan
This paper discusses the evaluation and prototyping of a 12V/3.3V Gallium-Nitride (GaN) point-of-load converter for satellite applications. Traditional power converters used in spacecraft are designed with silicon devices, and there are limitations in efficiency, package parasitic, and thermal management that must be addressed at frequencies above 500kHz. GaN HEMTs have advantages of TID tolerance, shorter turn-on/off time, and lower driving loss. By utilizing GaN HEMTs, switching frequency of 2MHz is selected to trade off volume and efficiency. Low parasitic loop inductance is realized by appropriate layout, and the peak voltage of the switches has been reduced. With the 3-D integration architecture, the junction-to-board thermal resistance has been reduced, and 20A output current is realized in a volume of $15times 15times 5.5mathrm{mm}^{3}$. Calculations, simulations and experimental results are provided to evaluate the performance of the converter.
{"title":"A Gallium-Nitride Point-of-load DC-DC Converter for Space Applications","authors":"Xiangan You, Xiaofeng Sun, Jing-ming Fei, Minghua Zhang, Bin-bin Zhang, Tao Chen, Yuqi Qin, Nana Rong, Chengan Wan","doi":"10.1109/ESPC.2019.8932088","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932088","url":null,"abstract":"This paper discusses the evaluation and prototyping of a 12V/3.3V Gallium-Nitride (GaN) point-of-load converter for satellite applications. Traditional power converters used in spacecraft are designed with silicon devices, and there are limitations in efficiency, package parasitic, and thermal management that must be addressed at frequencies above 500kHz. GaN HEMTs have advantages of TID tolerance, shorter turn-on/off time, and lower driving loss. By utilizing GaN HEMTs, switching frequency of 2MHz is selected to trade off volume and efficiency. Low parasitic loop inductance is realized by appropriate layout, and the peak voltage of the switches has been reduced. With the 3-D integration architecture, the junction-to-board thermal resistance has been reduced, and 20A output current is realized in a volume of $15times 15times 5.5mathrm{mm}^{3}$. Calculations, simulations and experimental results are provided to evaluate the performance of the converter.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"11 1","pages":"1-6"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"75891811","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8932020
M. Kroon, E. Bongers, Cyril Cavel, C. Baur, Francesco Faleg, S. Riva
The JUICE spacecraft will operate in an unprecedented environment of low solar intensity, low temperature and very high radiation fluence. Common approaches for power analyses would introduce a large uncertainty in the power prediction and assuming worst-case degradation and loss factors would result in a non-compliance on power. This paper reports the techniques used to accurately predict the solar array power during various phases of the mission. The power cases include a hot-case prediction at Closest Sun Approach (0.64 AU) and Low-Intensity, Low-Temperature (LILT) predictions at Jupiter Orbit Insertion (5.42 AU) and End-of-Life (EOL) (5.03 AU). The begin-of-life cell data were based on LILT performance measurements on ca. 40 cells. The mission particle dose is expressed in terms of Displacement Damage Dose (DDD) for the 3G28 solar cell. Solar cell degradation data measured under LILT conditions are compared with AMO degradation data. Due to the significant spread in LILT radiation test data, a Monte-Carlo analysis was performed to estimate a current mismatch factor at EOL.
{"title":"Low-Intensity Low-Temperature (LILT) Power prediction of JUICE solar array","authors":"M. Kroon, E. Bongers, Cyril Cavel, C. Baur, Francesco Faleg, S. Riva","doi":"10.1109/ESPC.2019.8932020","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932020","url":null,"abstract":"The JUICE spacecraft will operate in an unprecedented environment of low solar intensity, low temperature and very high radiation fluence. Common approaches for power analyses would introduce a large uncertainty in the power prediction and assuming worst-case degradation and loss factors would result in a non-compliance on power. This paper reports the techniques used to accurately predict the solar array power during various phases of the mission. The power cases include a hot-case prediction at Closest Sun Approach (0.64 AU) and Low-Intensity, Low-Temperature (LILT) predictions at Jupiter Orbit Insertion (5.42 AU) and End-of-Life (EOL) (5.03 AU). The begin-of-life cell data were based on LILT performance measurements on ca. 40 cells. The mission particle dose is expressed in terms of Displacement Damage Dose (DDD) for the 3G28 solar cell. Solar cell degradation data measured under LILT conditions are compared with AMO degradation data. Due to the significant spread in LILT radiation test data, a Monte-Carlo analysis was performed to estimate a current mismatch factor at EOL.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"7 1","pages":"1-5"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"85511076","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8931979
S. Riva, C. Baur, S. Verstaen, Francesco Faleg, P. Zanella, Paolo Fidanzati, L. Proserpio, Ludovico Sora, E. Bongers, Christophe Sabourin, Arielle Chastel
In the frame of the JUICE (JUpiter ICy moon Explorer) mission, Leonardo Spa has been selected as PVA supplier of the Solar Array module. Due to the demanding environmental and general requirements, it was necessary to develop specific technological solutions to fulfill the low temperature, low sun intensity and very high radiation levels linked to the Jovian specific environment. The paper illustrates this development process, successfully verified with engineering coupons and then applied to full-scale qualification model, which test campaign is currently ongoing.
{"title":"The JUICE Photovoltaic Assembly - from prequalification coupons to full-scale qualification model","authors":"S. Riva, C. Baur, S. Verstaen, Francesco Faleg, P. Zanella, Paolo Fidanzati, L. Proserpio, Ludovico Sora, E. Bongers, Christophe Sabourin, Arielle Chastel","doi":"10.1109/ESPC.2019.8931979","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931979","url":null,"abstract":"In the frame of the JUICE (JUpiter ICy moon Explorer) mission, Leonardo Spa has been selected as PVA supplier of the Solar Array module. Due to the demanding environmental and general requirements, it was necessary to develop specific technological solutions to fulfill the low temperature, low sun intensity and very high radiation levels linked to the Jovian specific environment. The paper illustrates this development process, successfully verified with engineering coupons and then applied to full-scale qualification model, which test campaign is currently ongoing.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"13 12 1","pages":"1-6"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82875057","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8931982
F. Forrisi, Erik Mache, Alan Mallmann, Martin Blaser
Since 2015 ASP-Equipment is in charge to develop modular and compact High Voltage Power Supply (HVPS) dealing with sensitive cost/mass reduction, and high rate production/test. In order to improve the level of integration and at the same time optimize efficiency and thermal management, the adopted architecture implements 3 key points: high switching frequency, Gallium Nitride (GaN) switches [1] and planar transformer [2] which allow to reduce the mass/volume and to reach high efficiency and a very high integration capability. The size of the converter is further reduced by means of the use of digital control [4] which offers many advantages including simplification of the power management, easy adjustment of sequencing and soft start function, rejection of input/output transients and reduction of the parts count. The delivery rate and the reduction of the recurring cost play a key role in the new space market, for this reason only SMT parts have been selected which allow strongly reducing manufacturing, assembly, integration and test (MAIT) time/costs. Thanks to the new concept a mass reduction of 50% (compared to the classical Silicon MOSFET based architecture) is achieved. The proposed solution reaches a power density in the range of 2kW/kg. Electric Propulsion (EP) is the typical application for such HVPS [5]. In this frame a prototype 1.2kV/1.2kW has been developed.
{"title":"Compact Low Cost High Voltage Power Supply for Space Applications","authors":"F. Forrisi, Erik Mache, Alan Mallmann, Martin Blaser","doi":"10.1109/ESPC.2019.8931982","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931982","url":null,"abstract":"Since 2015 ASP-Equipment is in charge to develop modular and compact High Voltage Power Supply (HVPS) dealing with sensitive cost/mass reduction, and high rate production/test. In order to improve the level of integration and at the same time optimize efficiency and thermal management, the adopted architecture implements 3 key points: high switching frequency, Gallium Nitride (GaN) switches [1] and planar transformer [2] which allow to reduce the mass/volume and to reach high efficiency and a very high integration capability. The size of the converter is further reduced by means of the use of digital control [4] which offers many advantages including simplification of the power management, easy adjustment of sequencing and soft start function, rejection of input/output transients and reduction of the parts count. The delivery rate and the reduction of the recurring cost play a key role in the new space market, for this reason only SMT parts have been selected which allow strongly reducing manufacturing, assembly, integration and test (MAIT) time/costs. Thanks to the new concept a mass reduction of 50% (compared to the classical Silicon MOSFET based architecture) is achieved. The proposed solution reaches a power density in the range of 2kW/kg. Electric Propulsion (EP) is the typical application for such HVPS [5]. In this frame a prototype 1.2kV/1.2kW has been developed.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"15 1","pages":"1-5"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79049656","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8932070
N. Khorchef, R. Kimber
This paper aims to highlight the key parameters of AlSat-1B solar panels and discuss the design of body-mounted solar panels assembly used as heritage for SSTL-100 bus to build AlSat-1B. It provides an overview of the AlSat-1B GaAs/Ge solar cells on aluminum faceskin solar panels and provides the key specifications of power system to meet the mission design requirements. The paper also addresses the electrical and mechanical design modifications performed on AlSat-1B solar panels and changes from previous SSTL-100 bus heritage. The solar panels have been successfully acceptance tested at bench and spacecraft levels and are currently in operation for three years. The in-orbit telemetry data show the panels work within nominal design limits.
{"title":"AlSat-1B Solar Array Assembly Design and Flight Qualification","authors":"N. Khorchef, R. Kimber","doi":"10.1109/ESPC.2019.8932070","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932070","url":null,"abstract":"This paper aims to highlight the key parameters of AlSat-1B solar panels and discuss the design of body-mounted solar panels assembly used as heritage for SSTL-100 bus to build AlSat-1B. It provides an overview of the AlSat-1B GaAs/Ge solar cells on aluminum faceskin solar panels and provides the key specifications of power system to meet the mission design requirements. The paper also addresses the electrical and mechanical design modifications performed on AlSat-1B solar panels and changes from previous SSTL-100 bus heritage. The solar panels have been successfully acceptance tested at bench and spacecraft levels and are currently in operation for three years. The in-orbit telemetry data show the panels work within nominal design limits.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"9 1","pages":"1-7"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"84321246","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8932049
P. J. Martínez, E. Maset, D. Gilabert, E. Sanchis-Kilders
This paper focus on the study of dynamic resistance $(mathrm{R}_{mathrm{dyn}})$ over commercial Gallium Nitride High Electromobility Transistors (GaN HEMTs) devices. The first part shows a study of the main mechanism causing $mathrm{R}_{mathrm{dyn}}$, showing that depending on the structure, stress time, voltage applied and switching conditions, the $mathrm{R}_{mathrm{dyn}}$ can suffer a relevant increase. Also, it is demonstrated how the use of soft-switching conditions can alleviate trapping effects. Finally, due to the interest over these devices for future space applications, the effects of gamma radiation over the $mathrm{R}_{mathrm{dyn}}$ has been studied.
{"title":"Dynamic $mathrm{R}_{mathrm{ON}}$ evaluation of commercial GaN HEMT under different switching and radiation conditions","authors":"P. J. Martínez, E. Maset, D. Gilabert, E. Sanchis-Kilders","doi":"10.1109/ESPC.2019.8932049","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932049","url":null,"abstract":"This paper focus on the study of dynamic resistance $(mathrm{R}_{mathrm{dyn}})$ over commercial Gallium Nitride High Electromobility Transistors (GaN HEMTs) devices. The first part shows a study of the main mechanism causing $mathrm{R}_{mathrm{dyn}}$, showing that depending on the structure, stress time, voltage applied and switching conditions, the $mathrm{R}_{mathrm{dyn}}$ can suffer a relevant increase. Also, it is demonstrated how the use of soft-switching conditions can alleviate trapping effects. Finally, due to the interest over these devices for future space applications, the effects of gamma radiation over the $mathrm{R}_{mathrm{dyn}}$ has been studied.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"35 1","pages":"1-5"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"88199986","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8932066
A. Bermudez-Garcia, P. Voarino, R. Cariou, L. Vauche, Karim Medjoubi, C. Jany, O. Raccurt
Concentrating PhotoVoltaics (CPV) can increase the efficiency of power systems in space while reducing their cost. This paper presents the first concentrator prototype using III-V/Si cells for space applications. This new approach will significantly reduce cost by concentrating sunlight then decreasing cell material, and in particular using III-V/Si triple-junction (3J) cells will allow the usage of Silicon, which is an abundant, twice less dense and low-cost material than the typically used Germanium. The efficiency of III-V/Si solar cells used is 25.7% @AM0. In our refractive module design, Compound Parabolic Concentrator (CPC), twelve 1.5x13mm2 cells are embedded in a Dow Corning® 93-500 silicone optics that provides an ∼8x concentration factor with an optical efficiency of 68%. Additionally, this linear-focus lens enables the use of single-axis sun tracking.
{"title":"First space concentrator prototype using III-V/Si cells","authors":"A. Bermudez-Garcia, P. Voarino, R. Cariou, L. Vauche, Karim Medjoubi, C. Jany, O. Raccurt","doi":"10.1109/ESPC.2019.8932066","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932066","url":null,"abstract":"Concentrating PhotoVoltaics (CPV) can increase the efficiency of power systems in space while reducing their cost. This paper presents the first concentrator prototype using III-V/Si cells for space applications. This new approach will significantly reduce cost by concentrating sunlight then decreasing cell material, and in particular using III-V/Si triple-junction (3J) cells will allow the usage of Silicon, which is an abundant, twice less dense and low-cost material than the typically used Germanium. The efficiency of III-V/Si solar cells used is 25.7% @AM0. In our refractive module design, Compound Parabolic Concentrator (CPC), twelve 1.5x13mm2 cells are embedded in a Dow Corning® 93-500 silicone optics that provides an ∼8x concentration factor with an optical efficiency of 68%. Additionally, this linear-focus lens enables the use of single-axis sun tracking.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"17 1","pages":"1-7"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"83492193","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8932039
A. Lindner, Carola Oberhüttinzer, C. Paarmann, Jens Müller, S. Strandmoe, Ian Costello
The Solar Orbiter (SolO) mission is a joint ESA and NASA interdisciplinary mission to study the sun. The spacecraft will orbit the sun in a moderately elliptical orbit. It will, amongst other things, investigate the near sun heliosphere environment and its magnetized atmosphere by using in-situ measurements very close to the sun to improve our understanding of solar and heliospheric processes. The Solar Orbiter spacecraft will approach the sun close to 0.28 AU. While the Solar Orbiter solar array design is, to a large extent, based on the design of the BepiColombo Mercury Planetary Orbiter solar array, the thermal shields and rear side foil is very specific for this mission. Solar Orbiter is equipped with unique and highly sensitive remote-sensing and in-situ sensors which require limiting the radiated electromagnetic emission. Additionally, the mission requires that optical and thermal reflections to the spacecraft are minimized. Some solar array heat shields have to withstand temperatures of more than 450°C, whereas others are designed such that the temperature is below 270°C to keep the structures within their qualified temperature range and simultaneously fulfil sunlight reflection requirements. This paper describes the Solar Orbiter solar array design in general and the thermal shield design in detail with its challenges to cope both the thermal and stray light requirements.
{"title":"Solar Orbiter Solar Array - Exceptional Design for a Hot Mission","authors":"A. Lindner, Carola Oberhüttinzer, C. Paarmann, Jens Müller, S. Strandmoe, Ian Costello","doi":"10.1109/ESPC.2019.8932039","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932039","url":null,"abstract":"The Solar Orbiter (SolO) mission is a joint ESA and NASA interdisciplinary mission to study the sun. The spacecraft will orbit the sun in a moderately elliptical orbit. It will, amongst other things, investigate the near sun heliosphere environment and its magnetized atmosphere by using in-situ measurements very close to the sun to improve our understanding of solar and heliospheric processes. The Solar Orbiter spacecraft will approach the sun close to 0.28 AU. While the Solar Orbiter solar array design is, to a large extent, based on the design of the BepiColombo Mercury Planetary Orbiter solar array, the thermal shields and rear side foil is very specific for this mission. Solar Orbiter is equipped with unique and highly sensitive remote-sensing and in-situ sensors which require limiting the radiated electromagnetic emission. Additionally, the mission requires that optical and thermal reflections to the spacecraft are minimized. Some solar array heat shields have to withstand temperatures of more than 450°C, whereas others are designed such that the temperature is below 270°C to keep the structures within their qualified temperature range and simultaneously fulfil sunlight reflection requirements. This paper describes the Solar Orbiter solar array design in general and the thermal shield design in detail with its challenges to cope both the thermal and stray light requirements.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"24 1","pages":"1-7"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79190744","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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