Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8932068
G. Salinas, J. Oliver, Javier Muñoz-Antón, Arturo Fernández, R. Prieto
The dissipation of the generated power losses of on-board magnetic components is a major concern regarding the thermal management of the power systems. In this study, two planar transformers designed for common space power converters are chosen as representative samples to analyze the effect of different elements on heat transfer (vias, connectors to a baseplate, gap filler pads, glue, integration in the main PCB). 3D thermal simulations are used to quantify it. It has been found out that the contribution of vias to heat transfer can reach a 8.9%, and the use of metallic connectors, window filling or gap filler pads can reduce the maximum temperature rise between 18.4% and 57.4%. Additionally, a simplified 2D model is proposed as a fast solution to characterize the thermal behavior of planar transformers and determine if a design is valid or if it requires any modification. Finally, some guidelines to address the thermal management of these components are explained.
{"title":"Thermal Management of planar magnetics for Spacecrafts: characterization and modeling","authors":"G. Salinas, J. Oliver, Javier Muñoz-Antón, Arturo Fernández, R. Prieto","doi":"10.1109/ESPC.2019.8932068","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932068","url":null,"abstract":"The dissipation of the generated power losses of on-board magnetic components is a major concern regarding the thermal management of the power systems. In this study, two planar transformers designed for common space power converters are chosen as representative samples to analyze the effect of different elements on heat transfer (vias, connectors to a baseplate, gap filler pads, glue, integration in the main PCB). 3D thermal simulations are used to quantify it. It has been found out that the contribution of vias to heat transfer can reach a 8.9%, and the use of metallic connectors, window filling or gap filler pads can reduce the maximum temperature rise between 18.4% and 57.4%. Additionally, a simplified 2D model is proposed as a fast solution to characterize the thermal behavior of planar transformers and determine if a design is valid or if it requires any modification. Finally, some guidelines to address the thermal management of these components are explained.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"20 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":"83354391","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.2019.8932090
R. Cariou, B. Boulanger, P. Voarino, Yannick Roujol, R. Couderc, Honorine Boirard, E. Rapp, F. Bourcier
Standard space solar arrays consist of solar cells protected by coverglass, glued individually on rigid substrate. The solar cells / substrate bonding interface quality is crucial since trapped air bubbles at this interface can cause strong cell damages once under vacuum. In this study, we show that transient electroluminescence can be used as a fast and nondestructive characterization tool to map the solar cells rear-side gluing interface defects.
{"title":"Characterization of solar array's cells to substrate bonding interface","authors":"R. Cariou, B. Boulanger, P. Voarino, Yannick Roujol, R. Couderc, Honorine Boirard, E. Rapp, F. Bourcier","doi":"10.1109/ESPC.2019.8932090","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932090","url":null,"abstract":"Standard space solar arrays consist of solar cells protected by coverglass, glued individually on rigid substrate. The solar cells / substrate bonding interface quality is crucial since trapped air bubbles at this interface can cause strong cell damages once under vacuum. In this study, we show that transient electroluminescence can be used as a fast and nondestructive characterization tool to map the solar cells rear-side gluing interface defects.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"29 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":"74181044","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.2019.8932092
A. Aho, Arttu Hietalahti, M. Guina, M. Raappana, R. Isoaho, T. Aho, V. Polojärvi, A. Tukiainen, Elina Anttola, Severi Mäkelä, Jarno Reuna
A lattice-matched four-junction solar cell on a GaAs substrate, for space applications, is demonstrated. The solar cell incorporates MBE grown GaInP, GaAs, GaInNAsSb and GaInNAsSb junctions with band-gaps of 1.9 eV, 1.4 eV, 1.2 eV and 0.9 eV, respectively. For AMO illumination, the cell exhibited a maximum efficiency of 27%. For this performance, a high collection efficiency for the bottom cell is required. The high efficiency and current generation for the four-junction solar cell is primarily enabled by achieving a very low background doping level $(sim 5times 10^{14}mathbf{cm}^{-3})$ and high charge carrier lifetimes (2–4 ns) for the GaInNAsSb bottom junction. Achieving an efficiency of 33% is deemed possible by further reduction of reflection, shadowing and transmission losses.
{"title":"High Efficiency Lattice-Matched 4J Space Solar Cells on GaAs","authors":"A. Aho, Arttu Hietalahti, M. Guina, M. Raappana, R. Isoaho, T. Aho, V. Polojärvi, A. Tukiainen, Elina Anttola, Severi Mäkelä, Jarno Reuna","doi":"10.1109/ESPC.2019.8932092","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932092","url":null,"abstract":"A lattice-matched four-junction solar cell on a GaAs substrate, for space applications, is demonstrated. The solar cell incorporates MBE grown GaInP, GaAs, GaInNAsSb and GaInNAsSb junctions with band-gaps of 1.9 eV, 1.4 eV, 1.2 eV and 0.9 eV, respectively. For AMO illumination, the cell exhibited a maximum efficiency of 27%. For this performance, a high collection efficiency for the bottom cell is required. The high efficiency and current generation for the four-junction solar cell is primarily enabled by achieving a very low background doping level $(sim 5times 10^{14}mathbf{cm}^{-3})$ and high charge carrier lifetimes (2–4 ns) for the GaInNAsSb bottom junction. Achieving an efficiency of 33% is deemed possible by further reduction of reflection, shadowing and transmission losses.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"8 1","pages":"1-3"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"75424696","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.2019.8932008
Celina Desparoir-Kossiavas
In order to satisfy the goal of harness mass and volume saving, the last generation of Thales Alenia Space GEO Telecom satellite family was designed with an electrical power architecture based on primary current returns flowing through the satellite structure between the PCU (Power Conditioning Unit) of the service module and mainly the equipment of the telecom payload. Compared to an usual current return via twisted pairs wiring for which impedances along the current paths and conducted/radiated EMC aspects including magnetic momentum are well managed by electrical designers, the validation of a concept where return currents paths are scattered across the service and payload modules structures requires to identify the mapping of the different currents and their associated electrical and magnetic fields in order to verify there is no electrical or electromagnetic interference that could disrupt the proper functioning of the satellite. For this purpose a 3D electrical modeling of the overall structure including all conductive elements that may be traversed by return currents between the PCU ground reference point and the ones of the other equipment was built to be used for electrical and EMC simulations using CST studio tool. This paper presents: •the method followed for the establishment of the 3D model with CATIA import interface, the selected level of granularity of the structural elements, the electrical models and stimuli used for the simulations. •the different types of simulation performed allowing the verification that the satellite electrical, EMC and functional performances are still compliant with requirements and if it is not the case to study modifications of the structure elements grounding and bonding in order to recover the compliance. •The main lessons learnt on using Software for this type of analysis and conclusion.
{"title":"GEO TELECOM SATELLITE STRUCTURE PRIMARY CURRENT RETURNS MAPPING ANALYSIS","authors":"Celina Desparoir-Kossiavas","doi":"10.1109/ESPC.2019.8932008","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932008","url":null,"abstract":"In order to satisfy the goal of harness mass and volume saving, the last generation of Thales Alenia Space GEO Telecom satellite family was designed with an electrical power architecture based on primary current returns flowing through the satellite structure between the PCU (Power Conditioning Unit) of the service module and mainly the equipment of the telecom payload. Compared to an usual current return via twisted pairs wiring for which impedances along the current paths and conducted/radiated EMC aspects including magnetic momentum are well managed by electrical designers, the validation of a concept where return currents paths are scattered across the service and payload modules structures requires to identify the mapping of the different currents and their associated electrical and magnetic fields in order to verify there is no electrical or electromagnetic interference that could disrupt the proper functioning of the satellite. For this purpose a 3D electrical modeling of the overall structure including all conductive elements that may be traversed by return currents between the PCU ground reference point and the ones of the other equipment was built to be used for electrical and EMC simulations using CST studio tool. This paper presents: •the method followed for the establishment of the 3D model with CATIA import interface, the selected level of granularity of the structural elements, the electrical models and stimuli used for the simulations. •the different types of simulation performed allowing the verification that the satellite electrical, EMC and functional performances are still compliant with requirements and if it is not the case to study modifications of the structure elements grounding and bonding in order to recover the compliance. •The main lessons learnt on using Software for this type of analysis and conclusion.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"7 1","pages":"1-3"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"73342066","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.2019.8932080
Subburaj Thiruvengadam, F. Farmakis, C. Elmasides, Dimitris Tsiplakides, S. Balomenou, W. Brevet, B. Samaniego, M. Nestoridi
Two different pouch cell designs (design A and B) of high energy density Li-ion batteries composed of novel Si anode material were studied under at low temperature. The pouch cells demonstrated different behavior in terms of initial capacity, cycle life stability and capacity retention in comparison with their respective behavior at room temperatures. In particular, design A cells exhibited a capacity retention of more than 65% when cycled at −40 °C (compared to 20°C) and it was able to deliver stable cycle life up to 40 cycles. On the other hand, design B cells showed lower discharge capacity retention of 44% (with respect to 20°C) and they lost only 20% of initial capacity retention of −40°C after 80 cycles. Though design A cell was able to deliver higher capacities at low temperature, the stability of cycle life is short. From transport properties investigation, with the aid of Continuous Voltage (CV) mode and Depth of Discharge (DoD) analysis at various cycles, cell design A exhibited better transport properties than design B. It is also revealed that, higher internal resistance of design B cell was responsible for the lower capacity at −40°C. Finally, extracted parameters from charging potential and current curves over time allowed us to further investigate the performance of the cells as a function of the number of cycles.
{"title":"Innovative lithium-ion pouch cell operating at low temperature (−40°C): comparison of different cell designs","authors":"Subburaj Thiruvengadam, F. Farmakis, C. Elmasides, Dimitris Tsiplakides, S. Balomenou, W. Brevet, B. Samaniego, M. Nestoridi","doi":"10.1109/ESPC.2019.8932080","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932080","url":null,"abstract":"Two different pouch cell designs (design A and B) of high energy density Li-ion batteries composed of novel Si anode material were studied under at low temperature. The pouch cells demonstrated different behavior in terms of initial capacity, cycle life stability and capacity retention in comparison with their respective behavior at room temperatures. In particular, design A cells exhibited a capacity retention of more than 65% when cycled at −40 °C (compared to 20°C) and it was able to deliver stable cycle life up to 40 cycles. On the other hand, design B cells showed lower discharge capacity retention of 44% (with respect to 20°C) and they lost only 20% of initial capacity retention of −40°C after 80 cycles. Though design A cell was able to deliver higher capacities at low temperature, the stability of cycle life is short. From transport properties investigation, with the aid of Continuous Voltage (CV) mode and Depth of Discharge (DoD) analysis at various cycles, cell design A exhibited better transport properties than design B. It is also revealed that, higher internal resistance of design B cell was responsible for the lower capacity at −40°C. Finally, extracted parameters from charging potential and current curves over time allowed us to further investigate the performance of the cells as a function of the number of cycles.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"74 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":"72728965","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.2019.8932029
R. Buckle
In order to utilise COTS cells for Space batteries, it is important to determine the best operating areas for each type of cell. This will not be the same for each cell type, or for the different market segments (e.g. LEO, GEO). ABSL have considerable life test data to determine the sensitivity of COTS to a range of factors in cycling and storage. This paper shows some of the results and considerations for battery sizing, and highlights issues with data extrapolation and subsequent risks to programs.
{"title":"Life Testing of COTS Cells for Optimum Battery Sizing","authors":"R. Buckle","doi":"10.1109/ESPC.2019.8932029","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932029","url":null,"abstract":"In order to utilise COTS cells for Space batteries, it is important to determine the best operating areas for each type of cell. This will not be the same for each cell type, or for the different market segments (e.g. LEO, GEO). ABSL have considerable life test data to determine the sensitivity of COTS to a range of factors in cycling and storage. This paper shows some of the results and considerations for battery sizing, and highlights issues with data extrapolation and subsequent risks to programs.","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":"75048353","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.2019.8932061
{"title":"ESPC 2019 Committees","authors":"","doi":"10.1109/espc.2019.8932061","DOIUrl":"https://doi.org/10.1109/espc.2019.8932061","url":null,"abstract":"","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"1 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77387791","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.2019.8931975
Liu Honglin, Luc Sanchez, Wei Qiang, Xing Jie, Y. Wentao, Huang Zhi, Zhang Xuan
The application of Li-ion battery on China large geostationary communications satellite platform will reduce the electrical power subsystem mass and volume, enhance platform capability and increase economy. This article introduces application solution of Li-ion batteries applied on the large, long life and high reliability GEO communications satellite platform. By analyzing in-orbit telemetry from the first flight satellite which launched on 12th, October 2015, Li-ion batteries thermal behavior, battery management results, battery flight performance, cell voltage consistency and balance function are verified. The results can be referred for the recurrent large geostationary communication satellite.
{"title":"Lithium-ion Battery Flight Experience Return on China Large GEO Communication Satellite","authors":"Liu Honglin, Luc Sanchez, Wei Qiang, Xing Jie, Y. Wentao, Huang Zhi, Zhang Xuan","doi":"10.1109/ESPC.2019.8931975","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931975","url":null,"abstract":"The application of Li-ion battery on China large geostationary communications satellite platform will reduce the electrical power subsystem mass and volume, enhance platform capability and increase economy. This article introduces application solution of Li-ion batteries applied on the large, long life and high reliability GEO communications satellite platform. By analyzing in-orbit telemetry from the first flight satellite which launched on 12th, October 2015, Li-ion batteries thermal behavior, battery management results, battery flight performance, cell voltage consistency and balance function are verified. The results can be referred for the recurrent large geostationary communication satellite.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"348 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":"79709370","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.2019.8932050
S. Pappalardo, Carmelo Ardizzone, Orazio Principato, Agatino Alessandro, I. Mirabella, F. Tonicello
This paper provides a detailed overview of the qualification activities including the radiation tests (both TID and SEE) of the RHRPMPOL01 IC device, a radiation hardened 7A synchronous step-down monolithic switching regulator with high precision internal voltage reference and integrated power MOSFETs for synchronous conversion. The device is the outcome of a development activity entitled “Miniaturised core element for Point of Load (PoL) conversion”, ESA TRP contract n. 4000107184/12/NL/LVH with STMicroelectronics.
{"title":"RHRPMPOLS01 Point of Load: Qualification & Radiation Tests","authors":"S. Pappalardo, Carmelo Ardizzone, Orazio Principato, Agatino Alessandro, I. Mirabella, F. Tonicello","doi":"10.1109/ESPC.2019.8932050","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932050","url":null,"abstract":"This paper provides a detailed overview of the qualification activities including the radiation tests (both TID and SEE) of the RHRPMPOL01 IC device, a radiation hardened 7A synchronous step-down monolithic switching regulator with high precision internal voltage reference and integrated power MOSFETs for synchronous conversion. The device is the outcome of a development activity entitled “Miniaturised core element for Point of Load (PoL) conversion”, ESA TRP contract n. 4000107184/12/NL/LVH with STMicroelectronics.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"18 1","pages":"1-8"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"80824640","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.2019.8932023
P. Voarino, A. Ritou, B. Boulanger, Caroline Seraine, R. Couderc, Honorine Boirard, E. Rapp
Concentrator photovoitaics technology can be a cost-effective solution for powering specific spatial missions. Compared to classical concentrators, micro-optical systems reduces the weight, the need in materials and the cost of solar arrays while increasing the efficiency [1]. This work describes a new concept especially dedicated to space application: a linear Total Internal Reflection (TIR) module, operating at a low concentration (7.6 X), and called SLIT (Space Linear TIR) module. Requiring no deployment system for optics, extremely angular independent, the efficiency of the first prototype is around 18% and preliminary thermal tests enhance a stable behavior for optics.
{"title":"A space self-integrated micro-concentrator design: the SLIT","authors":"P. Voarino, A. Ritou, B. Boulanger, Caroline Seraine, R. Couderc, Honorine Boirard, E. Rapp","doi":"10.1109/ESPC.2019.8932023","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932023","url":null,"abstract":"Concentrator photovoitaics technology can be a cost-effective solution for powering specific spatial missions. Compared to classical concentrators, micro-optical systems reduces the weight, the need in materials and the cost of solar arrays while increasing the efficiency [1]. This work describes a new concept especially dedicated to space application: a linear Total Internal Reflection (TIR) module, operating at a low concentration (7.6 X), and called SLIT (Space Linear TIR) module. Requiring no deployment system for optics, extremely angular independent, the efficiency of the first prototype is around 18% and preliminary thermal tests enhance a stable behavior for optics.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"23 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":"82066916","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}
京公网安备 11010802042870号
京ICP备2023020795号-1
扫码关注我们
求助内容：
应助结果提醒方式：