Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8931981
M. Vázquez, N. Núñez, C. Algora
To evaluate the reliability of space solar cells from Accelerated Life Tests (ALT) in laboratory have important difficulties due the presence in space of stressors that are not present in terrestrial environment and that must be emulated simultaneously in laboratory. To overcome these difficulties in this paper we propose a sequential ALT for space solar cells.
{"title":"Evaluation of the reliability of space solar cells by means of Sequential Accelerated Life Tests","authors":"M. Vázquez, N. Núñez, C. Algora","doi":"10.1109/ESPC.2019.8931981","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931981","url":null,"abstract":"To evaluate the reliability of space solar cells from Accelerated Life Tests (ALT) in laboratory have important difficulties due the presence in space of stressors that are not present in terrestrial environment and that must be emulated simultaneously in laboratory. To overcome these difficulties in this paper we propose a sequential ALT for space solar cells.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"101 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":"77357762","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.2019.8931998
W. Lu, Bao-Xing Wang, Chunyang Zhao, Hongtao Chen, Kai Wang, Taifeng Zhang
Simulation plays an important role in the design and analysis of the satellite power conditioning unit (PCU). For the 20kW high-power PCU, a modular system with a 100V fully regulated bus is designed and simulated, which contains sequential switching shunt regulators (S3Rs), battery charge-discharge regulators (BCDRs), bus capacitors and a bus control. Steady and dynamic performances of the bus voltage are simulated under various working conditions, showing that the designed PCU can meet the requirement of the 20kW payload. Moreover, a 20kW PCU prototype is developed and tested, which further demonstrates the validity of the simulation result.
{"title":"Simulation and Experimental Study of High-Power Power Conditioning Unit","authors":"W. Lu, Bao-Xing Wang, Chunyang Zhao, Hongtao Chen, Kai Wang, Taifeng Zhang","doi":"10.1109/ESPC.2019.8931998","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931998","url":null,"abstract":"Simulation plays an important role in the design and analysis of the satellite power conditioning unit (PCU). For the 20kW high-power PCU, a modular system with a 100V fully regulated bus is designed and simulated, which contains sequential switching shunt regulators (S3Rs), battery charge-discharge regulators (BCDRs), bus capacitors and a bus control. Steady and dynamic performances of the bus voltage are simulated under various working conditions, showing that the designed PCU can meet the requirement of the 20kW payload. Moreover, a 20kW PCU prototype is developed and tested, which further demonstrates the validity of the simulation result.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"54 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":"78603985","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.2019.8932057
Nayoung Lee, Tae-Yoon Kim, Ju-Young Lee, Sang-Kyoo Han, Tae-Jin Chung, J. Choi
Satellite DC/DC power converters are required to have EMI compatibility as well as high reliability. Since the EMI noise level of the DC/DC converter should be satisfied within the electromagnetic compatibility (EMC) requirement, it is essential to have a large EMI filter in front of it. For fundamentally addressing this problem, the zero-ripple reduction technique has been studied to significantly reduce the ripple on the converter input current, which is the major source of the EMI noise. The active clamp forward with a continuous input current waveform (CACF) converter, which is applied the zero ripple technique on the primary side of the converter, shows greatly reduced input current ripple. In this paper, it is compared that the EMI noise measurement for the CACF converter and the conventional active clamp forward (ACF) converter to confirm the improved EMI noise performance of the CACF converter.
{"title":"Improved EMI noise performance by the reduced input ripple of the Satellite converter","authors":"Nayoung Lee, Tae-Yoon Kim, Ju-Young Lee, Sang-Kyoo Han, Tae-Jin Chung, J. Choi","doi":"10.1109/ESPC.2019.8932057","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932057","url":null,"abstract":"Satellite DC/DC power converters are required to have EMI compatibility as well as high reliability. Since the EMI noise level of the DC/DC converter should be satisfied within the electromagnetic compatibility (EMC) requirement, it is essential to have a large EMI filter in front of it. For fundamentally addressing this problem, the zero-ripple reduction technique has been studied to significantly reduce the ripple on the converter input current, which is the major source of the EMI noise. The active clamp forward with a continuous input current waveform (CACF) converter, which is applied the zero ripple technique on the primary side of the converter, shows greatly reduced input current ripple. In this paper, it is compared that the EMI noise measurement for the CACF converter and the conventional active clamp forward (ACF) converter to confirm the improved EMI noise performance of the CACF converter.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"46 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":"85753099","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.2019.8931976
D. Mourembles, B. Buergler, L. Gajewski, Ashley Cooke, C. Barchasz
The Lithium-Sulfur Cells for Space Applications (LiSSA) project was funded by the European Space Agency (ESA) and was conducted between 2016 and 2018. The project was led by OXIS in collaboration with CEA and Airbus Defence & Space (ADS). The primary aim was to further develop OXIS Energy's lithium-sulfur (Li-S) technology for high energy density batteries for geostationary earth orbit (GEO) satellites. At the start of the project, OXIS's Ultra Light cells were already capable of achieving 300–400 Wh/kg for at least 40 cycles at 100% DoD. An energy density of 400 Wh/kg and GEO cycle life of 1350 cycles until 80% beginning-of-life (BoL) was targeted for the LiSSA Project. Such a cell would offer substantial mass advantages to GEO satellites developed by ADS and launched by ESA. The mass savings would allow for increased satellite payloads and/or significant cost reduction with reduced fuel usage.
{"title":"Li-S Cells for Space Applications (LISSA)","authors":"D. Mourembles, B. Buergler, L. Gajewski, Ashley Cooke, C. Barchasz","doi":"10.1109/ESPC.2019.8931976","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931976","url":null,"abstract":"The Lithium-Sulfur Cells for Space Applications (LiSSA) project was funded by the European Space Agency (ESA) and was conducted between 2016 and 2018. The project was led by OXIS in collaboration with CEA and Airbus Defence & Space (ADS). The primary aim was to further develop OXIS Energy's lithium-sulfur (Li-S) technology for high energy density batteries for geostationary earth orbit (GEO) satellites. At the start of the project, OXIS's Ultra Light cells were already capable of achieving 300–400 Wh/kg for at least 40 cycles at 100% DoD. An energy density of 400 Wh/kg and GEO cycle life of 1350 cycles until 80% beginning-of-life (BoL) was targeted for the LiSSA Project. Such a cell would offer substantial mass advantages to GEO satellites developed by ADS and launched by ESA. The mass savings would allow for increased satellite payloads and/or significant cost reduction with reduced fuel usage.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"44 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":"79954153","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.2019.8932036
A. Gabriele, V. Centonze, D. Lobifaro, C. Attanasio, G. Maiullari, A. Costa
This paper presents a “Medium Power” compact, light and low cost PCDU (Power Control and Distribution Unit) which has been designed as a modular and configurable equipment for Low Earth Orbit (LEO) missions with a maximum power capability of 1500 W. The PCDU supports a maximum of 4 independent power inputs (up to 75 V), and provides a 28 V unregulated power bus. Maximum Power Point Tracking (MPPT) is independently performed on each input; MPPT relies on buck regulators with direct drive capability, operating in ‘N+1’ cold redundancy. The latter feature, together with the full cold redundancy of the Control Unit inside the PCDU, makes the device fully compliant with the Single Point of Failure free requirement. Moreover, the passive balancing managed by the PCDU guarantees the correct distribution of the cells charge, and contributes in improving the battery reliability. The unregulated bus is protected and distributed through nominal plus redundant LCL/RLCL and fuse protected lines for heaters and HDRMs. A cross-strapped architecture allows to control both nominal and redundant protected outputs from the nominal or redundant section of the unit, at the same time maximizing the PCDU availability. The PCDU, which is fully monitored, controlled and configured through the N+R CAN bus, can be easily tailored for various missions since its functionalities are segregated in different and specific stackable electronic boards (no backplane is used), and FPGAs are programmable. Finally, to balance the equipment radiation hardness and reliability figure versus costs, the PCDU has been designed with a mixed approach: COTS based supported by Sitael heritage [1] [2] and scheduled radiation tests, and the usage of MIL/Space qualified components for critical functions.
{"title":"A Power Control and Distribution Unit for Small Satellite Platforms","authors":"A. Gabriele, V. Centonze, D. Lobifaro, C. Attanasio, G. Maiullari, A. Costa","doi":"10.1109/ESPC.2019.8932036","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932036","url":null,"abstract":"This paper presents a “Medium Power” compact, light and low cost PCDU (Power Control and Distribution Unit) which has been designed as a modular and configurable equipment for Low Earth Orbit (LEO) missions with a maximum power capability of 1500 W. The PCDU supports a maximum of 4 independent power inputs (up to 75 V), and provides a 28 V unregulated power bus. Maximum Power Point Tracking (MPPT) is independently performed on each input; MPPT relies on buck regulators with direct drive capability, operating in ‘N+1’ cold redundancy. The latter feature, together with the full cold redundancy of the Control Unit inside the PCDU, makes the device fully compliant with the Single Point of Failure free requirement. Moreover, the passive balancing managed by the PCDU guarantees the correct distribution of the cells charge, and contributes in improving the battery reliability. The unregulated bus is protected and distributed through nominal plus redundant LCL/RLCL and fuse protected lines for heaters and HDRMs. A cross-strapped architecture allows to control both nominal and redundant protected outputs from the nominal or redundant section of the unit, at the same time maximizing the PCDU availability. The PCDU, which is fully monitored, controlled and configured through the N+R CAN bus, can be easily tailored for various missions since its functionalities are segregated in different and specific stackable electronic boards (no backplane is used), and FPGAs are programmable. Finally, to balance the equipment radiation hardness and reliability figure versus costs, the PCDU has been designed with a mixed approach: COTS based supported by Sitael heritage [1] [2] and scheduled radiation tests, and the usage of MIL/Space qualified components for critical functions.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"64 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":"86711376","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.2019.8932005
A. Tambini, F. Antonini, N. Melega, G. Mariotti, V. Centonze, A. Gabriele
Coming right after the launch of the ESEO spacecraft, uHETsat will be the second mission based on the use of SITAEL S-50/75 microsatellite platform for IOV/IOD purposes. In this case the subject of the In Orbit Validation will be SITAEL HT100 Hall Effect Thruster (HET) -one of the smallest of its kind-that for the first time will be embarked and operated onboard a small platform. Starting from its predecessor, the spacecraft has undergone a series of updates and upgrades necessary to comply with the new set of mission requirements. Although some of the AODCS equipment has changed compared to ESEO [1], most of the efforts in the adaptation of the Power System (PS) were spent to handle the power required by the propulsion subsystem for its proper functioning. The PS re-design included a new set of deployable Solar Arrays (SA), a revised Power Management Board (PMB) and Power Distribution Unit (PDU), and a larger battery that will allow the mission to accomplish its goals: 2000 ignitions and 1000 hours of firing for the propulsion subsystem. Main objectives for this re-design activity have been the improvement of the overall reliability through a meticulous review of the components selection, at the same time preserving the single failure tolerance and the low cost approach (hybrid automatic-manual) in terms of manufacturing. The uHETsat PS is currently being accepted for flight and all its components have been tested as EQM showing the capability of the system to support both platform and payload operations. After a brief overview of the uHETsat mission, the focus will be moved to the PS architecture description, redundancies strategy and the single point failure free design approach.
{"title":"uHETsat small Power System for high demanding payloads","authors":"A. Tambini, F. Antonini, N. Melega, G. Mariotti, V. Centonze, A. Gabriele","doi":"10.1109/ESPC.2019.8932005","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932005","url":null,"abstract":"Coming right after the launch of the ESEO spacecraft, uHETsat will be the second mission based on the use of SITAEL S-50/75 microsatellite platform for IOV/IOD purposes. In this case the subject of the In Orbit Validation will be SITAEL HT100 Hall Effect Thruster (HET) -one of the smallest of its kind-that for the first time will be embarked and operated onboard a small platform. Starting from its predecessor, the spacecraft has undergone a series of updates and upgrades necessary to comply with the new set of mission requirements. Although some of the AODCS equipment has changed compared to ESEO [1], most of the efforts in the adaptation of the Power System (PS) were spent to handle the power required by the propulsion subsystem for its proper functioning. The PS re-design included a new set of deployable Solar Arrays (SA), a revised Power Management Board (PMB) and Power Distribution Unit (PDU), and a larger battery that will allow the mission to accomplish its goals: 2000 ignitions and 1000 hours of firing for the propulsion subsystem. Main objectives for this re-design activity have been the improvement of the overall reliability through a meticulous review of the components selection, at the same time preserving the single failure tolerance and the low cost approach (hybrid automatic-manual) in terms of manufacturing. The uHETsat PS is currently being accepted for flight and all its components have been tested as EQM showing the capability of the system to support both platform and payload operations. After a brief overview of the uHETsat mission, the focus will be moved to the PS architecture description, redundancies strategy and the single point failure free design approach.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"1 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":"89545241","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.2019.8932072
G. Gabetta, Davide Cospito, R. Campesato, M. Casale, E. F. Lisbona
CESI has combined the high efficiency, radiation hardness and reliability of the III-V compound triple junction solar cells with a low cost approach developing a peculiar triple junction solar cell targeting 28% efficiency, radiation hardness typical of this class of solar cells and at the same time a significant cost advantage. Such solar cells have recently passed the LEO and GEO qualification according to the ECSS standard at bare cell level and are currently under GEO and LEO qualification as solar cell assemblies.
{"title":"Qualification of low cost triple junction GaInP/GaAs/Ge solar cell assemblies with external bypass diode connected by insulated cell P/diode N interconnects","authors":"G. Gabetta, Davide Cospito, R. Campesato, M. Casale, E. F. Lisbona","doi":"10.1109/ESPC.2019.8932072","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932072","url":null,"abstract":"CESI has combined the high efficiency, radiation hardness and reliability of the III-V compound triple junction solar cells with a low cost approach developing a peculiar triple junction solar cell targeting 28% efficiency, radiation hardness typical of this class of solar cells and at the same time a significant cost advantage. Such solar cells have recently passed the LEO and GEO qualification according to the ECSS standard at bare cell level and are currently under GEO and LEO qualification as solar cell assemblies.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"130 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":"89813847","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.2019.8932014
G. Jüngst, A. Gras, C. Baur
For accurate electric performance measurements of multi-junction solar cells at AM0 illumination conditions under simulated light, the most important parameter to be controlled is the effective irradiance of their individual sub-cells. The AM0 equivalent irradiance conditions once established on a solar simulator at standard cell temperature, i.e. 25°C, might not be fulfilled at certain temperatures when performing electrical measurements on triple junction (3J) GaInP2/ InGaAs/Ge space cells in a wide cell temperature range from −175°C to +140°C, and therefore might entail erroneous electrical cell parameter results. In a study on different solar simulators at INTA-Spasolab the effective irradiance under such AM0 illumination conditions are determined for 3J solar cells at different temperatures. The solar simulator spectra are analyzed by determining those spectral zones affecting the most to required AM0 illumination conditions at low and high temperatures. This analysis demonstrates that the influences of the respective solar simulator spectrum are more associated with specific wavelength zones rather than the solar simulator classification in fixed wavelength bins.
{"title":"AM0 Irradiance Conditions for Electrical Performance Measurements of Triple Junction Cells at Extreme Low and High Temperatures","authors":"G. Jüngst, A. Gras, C. Baur","doi":"10.1109/ESPC.2019.8932014","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932014","url":null,"abstract":"For accurate electric performance measurements of multi-junction solar cells at AM0 illumination conditions under simulated light, the most important parameter to be controlled is the effective irradiance of their individual sub-cells. The AM0 equivalent irradiance conditions once established on a solar simulator at standard cell temperature, i.e. 25°C, might not be fulfilled at certain temperatures when performing electrical measurements on triple junction (3J) GaInP2/ InGaAs/Ge space cells in a wide cell temperature range from −175°C to +140°C, and therefore might entail erroneous electrical cell parameter results. In a study on different solar simulators at INTA-Spasolab the effective irradiance under such AM0 illumination conditions are determined for 3J solar cells at different temperatures. The solar simulator spectra are analyzed by determining those spectral zones affecting the most to required AM0 illumination conditions at low and high temperatures. This analysis demonstrates that the influences of the respective solar simulator spectrum are more associated with specific wavelength zones rather than the solar simulator classification in fixed wavelength bins.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"71 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":"82865224","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.2019.8932003
C. Zimmermann, F. Schlerka, C. Nömayr, Rainer Müller, H. Nesswetter, A. Übner, Marco Gruber, Christian Grünwald
Airbus is currently developing the Eurostar Neo telecommunication platform, supported by ESA in the frame of the ARTES 14 program. It is capable to support payloads up to 25 kW, which required major advances in the thermal as well as the electrical subsystem. The first telecommunication satellites based on the Eurostar Neo platform will be the Eutelsat Hotbird satellites 13F and G, to be launched in 2021. One of the central newly developed subsystems for Eurostar Neo is a solar array that is capable to deliver ≈ 50% more power in the same volume and with the same weight. This is achieved through a hybrid array concept, which combines a conventional rigid panel array with lightweight, semi-rigid lateral panels. This central element of the new array features a wealth of new technologies, ranging from a charge dissipative substrate and C-spring hinges with electrical functionality to new ion-erosion resistant Al interconnects and 4-junction solar cells with 28.5% efficiency at 1×1015 1MeV e-/cm2. The design of the semi-rigid photovoltaic assembly (PVA) is outlined in detail, as well as the results of key qualification tests on component and on PVA level. In contrast to classical arrays, PVA level testing required not only thermal cycle testing, but also the verification of new loads like sine-vibration testing under vacuum. Finally, the potential for further evolution of this array concept is discussed.
{"title":"Development and Qualification of the Eurostar Neo Solar Array","authors":"C. Zimmermann, F. Schlerka, C. Nömayr, Rainer Müller, H. Nesswetter, A. Übner, Marco Gruber, Christian Grünwald","doi":"10.1109/ESPC.2019.8932003","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932003","url":null,"abstract":"Airbus is currently developing the Eurostar Neo telecommunication platform, supported by ESA in the frame of the ARTES 14 program. It is capable to support payloads up to 25 kW, which required major advances in the thermal as well as the electrical subsystem. The first telecommunication satellites based on the Eurostar Neo platform will be the Eutelsat Hotbird satellites 13F and G, to be launched in 2021. One of the central newly developed subsystems for Eurostar Neo is a solar array that is capable to deliver ≈ 50% more power in the same volume and with the same weight. This is achieved through a hybrid array concept, which combines a conventional rigid panel array with lightweight, semi-rigid lateral panels. This central element of the new array features a wealth of new technologies, ranging from a charge dissipative substrate and C-spring hinges with electrical functionality to new ion-erosion resistant Al interconnects and 4-junction solar cells with 28.5% efficiency at 1×1015 1MeV e-/cm2. The design of the semi-rigid photovoltaic assembly (PVA) is outlined in detail, as well as the results of key qualification tests on component and on PVA level. In contrast to classical arrays, PVA level testing required not only thermal cycle testing, but also the verification of new loads like sine-vibration testing under vacuum. Finally, the potential for further evolution of this array concept is discussed.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"22 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":"78969414","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.2019.8932027
M. Kroon, E. Bongers, K. Bubeck
Very sensitive magnetic instruments on the JUICE spacecraft require an extremely low magnetic field emission of the various subsystems. The JUICE solar array includes a photovoltaic assembly and various mechanisms with a magnetic signature. The design of the photovoltaic assembly has been optimised not only with respect to magnetic moment, but also with respect to the emitted magnetic field, by applying the so-called back-wiring technique, alternating string polarity etc. The remanent magnetic field of the mechanisms (hinges, eddy-current damper, hold-down & release mechanism) was tested including a process for demagnetisation. In addition, the temperature coefficient for the magnetic moment was measured, down to the operational temperature of −130°C. The eddy-current damper was also subjected to a field-induced magnetisation test. All the contributors were included in a model to calculate the magnetic field at the instrument location.
{"title":"Magnetic tests and analysis of JUICE solar array","authors":"M. Kroon, E. Bongers, K. Bubeck","doi":"10.1109/ESPC.2019.8932027","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932027","url":null,"abstract":"Very sensitive magnetic instruments on the JUICE spacecraft require an extremely low magnetic field emission of the various subsystems. The JUICE solar array includes a photovoltaic assembly and various mechanisms with a magnetic signature. The design of the photovoltaic assembly has been optimised not only with respect to magnetic moment, but also with respect to the emitted magnetic field, by applying the so-called back-wiring technique, alternating string polarity etc. The remanent magnetic field of the mechanisms (hinges, eddy-current damper, hold-down & release mechanism) was tested including a process for demagnetisation. In addition, the temperature coefficient for the magnetic moment was measured, down to the operational temperature of −130°C. The eddy-current damper was also subjected to a field-induced magnetisation test. All the contributors were included in a model to calculate the magnetic field at the instrument location.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"11 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":"84999391","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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