Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8932006
Cédric Colonna, P. Dubus, D. Labrousse
To be compatible with all the existing spacecraft, 3D PLUS is developing a Front end power converter, which works from DC18V to DC110V for the input voltage, from DC3V for the output voltage and from 0W to 50W for the output power. The transformer design is critical because it should not penalize the operation of the converter in a reduced size. This document will first define the topology of the transformer. It will then discuss the different loss models chosen to optimize the sizing. An optimization combining multi-physical finite element computation and a multi-objective genetic optimization algorithm will then be introduced. After a comparison between different materials int term of occupied surface with fixed maximum heating, we will conclude this study by presenting the realization and implementation of our transformer.
{"title":"Transformer optimization for 3D PLUS Universal RCN Front End converter","authors":"Cédric Colonna, P. Dubus, D. Labrousse","doi":"10.1109/ESPC.2019.8932006","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932006","url":null,"abstract":"To be compatible with all the existing spacecraft, 3D PLUS is developing a Front end power converter, which works from DC18V to DC110V for the input voltage, from DC3V for the output voltage and from 0W to 50W for the output power. The transformer design is critical because it should not penalize the operation of the converter in a reduced size. This document will first define the topology of the transformer. It will then discuss the different loss models chosen to optimize the sizing. An optimization combining multi-physical finite element computation and a multi-objective genetic optimization algorithm will then be introduced. After a comparison between different materials int term of occupied surface with fixed maximum heating, we will conclude this study by presenting the realization and implementation of our transformer.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"26 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":"84339779","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.2019.8931977
Franz Stoegerer, T. Panhofer
High performance processing boards using ASICs and reconfigurable FPGAs require particular power supplies with voltages below 1 V and current capabilities up to 50 A. High efficiency is mandatory for low power consumption and thermal reasons and is considered as most important goal for the DCDC converter. Off-the-shelf radiation hardened point-of-load (POL) converters are not optimized for such an application. Most devices are limited to approximately 10 A and show maximum efficiency at approximately half load current. Only a few parts offer the possibility for parallel operation to increase the current capability. Apart from the non-isolating POL converters also high-current supplies based on an isolated converter topology with good efficiency are available on the market. The efficiency of both concepts relies on high-performance/low-on-resistance FETs, and GaN technology seems to be a very attractive solution. This paper evaluates discrete designs of a non-isolating POL converter and an isolating converter based on GaN FETs regarding their suitability for low voltage/high current applications. Beside of theoretical investigations, experimental results gained from laboratory prototypes are presented.
{"title":"High-Efficiency Low Voltage/High Current Power Supplies for High Performance Digital Equipment by using GaN FET Technology","authors":"Franz Stoegerer, T. Panhofer","doi":"10.1109/ESPC.2019.8931977","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931977","url":null,"abstract":"High performance processing boards using ASICs and reconfigurable FPGAs require particular power supplies with voltages below 1 V and current capabilities up to 50 A. High efficiency is mandatory for low power consumption and thermal reasons and is considered as most important goal for the DCDC converter. Off-the-shelf radiation hardened point-of-load (POL) converters are not optimized for such an application. Most devices are limited to approximately 10 A and show maximum efficiency at approximately half load current. Only a few parts offer the possibility for parallel operation to increase the current capability. Apart from the non-isolating POL converters also high-current supplies based on an isolated converter topology with good efficiency are available on the market. The efficiency of both concepts relies on high-performance/low-on-resistance FETs, and GaN technology seems to be a very attractive solution. This paper evaluates discrete designs of a non-isolating POL converter and an isolating converter based on GaN FETs regarding their suitability for low voltage/high current applications. Beside of theoretical investigations, experimental results gained from laboratory prototypes are presented.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"8 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":"81591992","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.2019.8932073
G. Siefer, E. Fehrenbacher, M. Schachtner, A. Wekkeli
Calibrated measurements of solar cells at low temperatures are of specific interest for various space missions, for example to Mars and Jupiter. In the past 15 years, several hundred triple-junction and component solar cells have been measured at the solar cell calibration laboratory at Fraunhofer ISE (CalLab PV Cells), mainly in the frame of the European Space Agency (ESA) programs ExoMars and JUICE. To allow for measurements at temperatures as low as 123 K a specially developed cryostat setup is being used. This paper summarizes the main challenges and findings in respect to measurement procedures and calibration of solar cells under low temperature conditions, including the mounting of the solar cells, control of the correct solar cell temperature, and definition of the correct illumination spectrum and intensity.
{"title":"Accurate Solar Cell Measurements at Low Temperatures using a Cryostat","authors":"G. Siefer, E. Fehrenbacher, M. Schachtner, A. Wekkeli","doi":"10.1109/ESPC.2019.8932073","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932073","url":null,"abstract":"Calibrated measurements of solar cells at low temperatures are of specific interest for various space missions, for example to Mars and Jupiter. In the past 15 years, several hundred triple-junction and component solar cells have been measured at the solar cell calibration laboratory at Fraunhofer ISE (CalLab PV Cells), mainly in the frame of the European Space Agency (ESA) programs ExoMars and JUICE. To allow for measurements at temperatures as low as 123 K a specially developed cryostat setup is being used. This paper summarizes the main challenges and findings in respect to measurement procedures and calibration of solar cells under low temperature conditions, including the mounting of the solar cells, control of the correct solar cell temperature, and definition of the correct illumination spectrum and intensity.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"59 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":"80503270","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.2019.8932047
Alex Clarke, R. Buckle
The Space market can be segmented according to the requirements applicable to specific applications. For example, LEO missions are characterised by the requirement for a high number of cycles at low DoD, whereas GEO missions require the battery to be cycled at high DoD. These different drivers mean that one cell type may not be optimal for all types of mission, in terms of minimising the mass and volume of the battery. This paper discusses ABSL's expanded cell portfolio, and how the requirements of the various applications are met by the identified cell types
{"title":"Identification of COTS Cells to Meet Space Market Segment Requirements","authors":"Alex Clarke, R. Buckle","doi":"10.1109/ESPC.2019.8932047","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932047","url":null,"abstract":"The Space market can be segmented according to the requirements applicable to specific applications. For example, LEO missions are characterised by the requirement for a high number of cycles at low DoD, whereas GEO missions require the battery to be cycled at high DoD. These different drivers mean that one cell type may not be optimal for all types of mission, in terms of minimising the mass and volume of the battery. This paper discusses ABSL's expanded cell portfolio, and how the requirements of the various applications are met by the identified cell types","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"397 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":"85023699","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.2019.8932076
Zhang Xuan, Kang Qing, Y. Wentao, Xing Jie, Li Feng, You Xiangan
In order to measure power utilization ratio of solar arrays under Maximum Power Point Tracking(MPPT) and three different Direct Energy Transfer(DET) solutions quantitatively, this paper defines two power indices, energy loss percentage(ELP) and energy excess percentage(EEP), as the basis of satellite power system design. This paper also gives the calculation of these two indices based on the feature of joint-operation of PV and batteries, the control efficiency and the design margin. On the basis of ELP and EPP, two applicable cases of MPPT and DET architecture are analyzed. Computation results show that ELP of MPPT is better while EEP of DET is more competitive.
{"title":"Power Assessment Indices of Solar Arrays under MPPT and DET methods for Spacecraft","authors":"Zhang Xuan, Kang Qing, Y. Wentao, Xing Jie, Li Feng, You Xiangan","doi":"10.1109/ESPC.2019.8932076","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932076","url":null,"abstract":"In order to measure power utilization ratio of solar arrays under Maximum Power Point Tracking(MPPT) and three different Direct Energy Transfer(DET) solutions quantitatively, this paper defines two power indices, energy loss percentage(ELP) and energy excess percentage(EEP), as the basis of satellite power system design. This paper also gives the calculation of these two indices based on the feature of joint-operation of PV and batteries, the control efficiency and the design margin. On the basis of ELP and EPP, two applicable cases of MPPT and DET architecture are analyzed. Computation results show that ELP of MPPT is better while EEP of DET is more competitive.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"1 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":"86524994","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.2019.8931999
F. Pintacuda, S. Massett, E. Vitanza, M. Muschitiello, V. Cantarella
This paper report the Failure Analysis results performed on SiC Mosfet with SEGR and PIGS failure after SEE test. The analysis discovered a hot spot in the SiC junction at the SEGR fail point.
{"title":"SEGR and PIGS Failure Analysis of SiC Mosfet","authors":"F. Pintacuda, S. Massett, E. Vitanza, M. Muschitiello, V. Cantarella","doi":"10.1109/ESPC.2019.8931999","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931999","url":null,"abstract":"This paper report the Failure Analysis results performed on SiC Mosfet with SEGR and PIGS failure after SEE test. The analysis discovered a hot spot in the SiC junction at the SEGR fail point.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"14 4 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":"78207612","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.2019.8932064
Laurence Perino-Gallice, O. Masson, M. Bel, F. Fusalba
“The space revolution is being led by more than Musk and Bezos”, Backstage, aerospace leaders and their suppliers already work on design to cost engineering using automatized processes and working to qualify COTS within Lean manufacturing method. In 2014, CEA did propose the use of Commercial Off The Shelf (COTS) 18650 Li-ion cells to manufacture competitive aerospace batteries (without modifications for space use managing space qualification at system level) and in 2015 the use of Lean 6 sigma manufacturing approach based on its automotive/terrestrial industry experience to respond new space requirements. Our development phase continuously challenged Design to Cost & Design to Industrialization (Series Manufacturing). As a result, the battery product integrates COTS 18650 Li-ion cells and hardware. Its price breakdown targeted for competitive product industrialization is reached under space qualification. Manufactured within an Iso 8 clean room for space use, a Manufacturing Execution System (MES) manages its industrial quality. Our tool, sized for fast prototyping and transfer towards industry, eases demonstration to industrialization maturity assessments (time & cost to market). We built a battery assembly line from scratch to operation in 8 months and, following an ISO10005 completed with EN9100 quality plan, we space qualified its processes in 15 months, product ready for launch within 24 months. First flight models integrate OneWeb constellation satellites set for launch Feb. 2019. By now, recurring products for space applications are continuously running through standards processes. CEA demonstrated its industry-oriented results with a highly agile battery assembly line transfer, proving shorten assembly times with means to analyze factory performance and process improvements under space standards. Manufacturing data under the production method necessary to manufacture high-performance batteries to power satellites constellation are discussed in this paper. This approach is applicable for other space equipment.
{"title":"Batteries for Satellites Constellation, using Lean Manufacturing for Space Industry","authors":"Laurence Perino-Gallice, O. Masson, M. Bel, F. Fusalba","doi":"10.1109/ESPC.2019.8932064","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932064","url":null,"abstract":"“The space revolution is being led by more than Musk and Bezos”, Backstage, aerospace leaders and their suppliers already work on design to cost engineering using automatized processes and working to qualify COTS within Lean manufacturing method. In 2014, CEA did propose the use of Commercial Off The Shelf (COTS) 18650 Li-ion cells to manufacture competitive aerospace batteries (without modifications for space use managing space qualification at system level) and in 2015 the use of Lean 6 sigma manufacturing approach based on its automotive/terrestrial industry experience to respond new space requirements. Our development phase continuously challenged Design to Cost & Design to Industrialization (Series Manufacturing). As a result, the battery product integrates COTS 18650 Li-ion cells and hardware. Its price breakdown targeted for competitive product industrialization is reached under space qualification. Manufactured within an Iso 8 clean room for space use, a Manufacturing Execution System (MES) manages its industrial quality. Our tool, sized for fast prototyping and transfer towards industry, eases demonstration to industrialization maturity assessments (time & cost to market). We built a battery assembly line from scratch to operation in 8 months and, following an ISO10005 completed with EN9100 quality plan, we space qualified its processes in 15 months, product ready for launch within 24 months. First flight models integrate OneWeb constellation satellites set for launch Feb. 2019. By now, recurring products for space applications are continuously running through standards processes. CEA demonstrated its industry-oriented results with a highly agile battery assembly line transfer, proving shorten assembly times with means to analyze factory performance and process improvements under space standards. Manufacturing data under the production method necessary to manufacture high-performance batteries to power satellites constellation are discussed in this paper. This approach is applicable for other space equipment.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"7 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":"75116045","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.2019.8932078
M. Triggianese, H. Carbonnier, F. Tonicello
The Middlebrook's criteria is used in the ECSS-E-ST −20C (European Cooperation for Space Standardization - Electrical and Electronic) to guarantee the stability of cascaded power systems. It is worth noticing that the non-compliance to Middlebrook's criterion does not represent a necessary condition for stability, therefore when not satisfied, additional analysis might be necessary to check the stability margins. It is however a very conservative approach. Other less conservative methods have been proposed for the interconnection of feedback controlled DC/DC converters. Among others, a revised criterion is considered in this paper and different study-cases are analyzed to demonstrate the typical situations that a power engineer is facing with cascaded DC-DC power supplies.
{"title":"Revised stability criteria for cascaded DC-DC converters in space applications","authors":"M. Triggianese, H. Carbonnier, F. Tonicello","doi":"10.1109/ESPC.2019.8932078","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932078","url":null,"abstract":"The Middlebrook's criteria is used in the ECSS-E-ST −20C (European Cooperation for Space Standardization - Electrical and Electronic) to guarantee the stability of cascaded power systems. It is worth noticing that the non-compliance to Middlebrook's criterion does not represent a necessary condition for stability, therefore when not satisfied, additional analysis might be necessary to check the stability margins. It is however a very conservative approach. Other less conservative methods have been proposed for the interconnection of feedback controlled DC/DC converters. Among others, a revised criterion is considered in this paper and different study-cases are analyzed to demonstrate the typical situations that a power engineer is facing with cascaded DC-DC power supplies.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"157 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":"73921010","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.2019.8932032
Elisa Mostacciuolo, F. Vasca, Silvio Baccari, L. Iannelli, Salvatore Sagnelli, Raffaele Luisi, V. Stanzione
A model-based optimization of the charging process of batteries in small satellites is proposed. The battery is considered as part of an electrical power system with a peak power tracker architecture and an unregulated bus. Real data are used to determine the parameters of the dynamic model of the system. The battery charging optimization is obtained through the minimization of a cost function which weights charging time, energy losses and temperature variations by taking into account also the dynamic model. Simulation results show the validity of the proposed solution in terms of performance and computational effort for different missions power load, irradiance and temperature operating conditions.
{"title":"An optimization strategy for battery charging in small satellites","authors":"Elisa Mostacciuolo, F. Vasca, Silvio Baccari, L. Iannelli, Salvatore Sagnelli, Raffaele Luisi, V. Stanzione","doi":"10.1109/ESPC.2019.8932032","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932032","url":null,"abstract":"A model-based optimization of the charging process of batteries in small satellites is proposed. The battery is considered as part of an electrical power system with a peak power tracker architecture and an unregulated bus. Real data are used to determine the parameters of the dynamic model of the system. The battery charging optimization is obtained through the minimization of a cost function which weights charging time, energy losses and temperature variations by taking into account also the dynamic model. Simulation results show the validity of the proposed solution in terms of performance and computational effort for different missions power load, irradiance and temperature operating conditions.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"41 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":"88223312","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.2019.8932000
A. Vanessa, Clemente Jacky, Jérémy Hyvert, Godon Aurelie, P. J. Paul, Remy Stéphane, Borthomieu Yannick
There are two major challenges for Saft to develop a battery design for LEO satellite constellation which is out of the ordinary: lean production as well as a disruptive cost approach. Those main ideas will be the primordial drivers from the beginning to the end of the project. To reach the target, Saft is looking for answers to: how to build more efficiently and quickly, how to pack more simply and how to be able to run in parallel huge number to blocks? Saft core business is in energy storage system. Hence, it will use its in-house COTS cell called MP xlr for the fabrication of batteries for constellation purposes. MP xlr cells has demonstrated 1800 cycles @ 100% DOD while retaining 70% of its initial capacity. The performance of the MP xlr cell evaluated at 20% DOD and 30% DOD LEO cycling also shows a very good trend in EODV similarly to VES16 cell a space dedicated cell. Moreover, MP xlr cell exhibits stable internal resistance over cycle life which gives a significant advantage at battery level from the voltage stability to heat generation that is constant over the life.
为低轨卫星星座开发不同寻常的电池设计，对于Saft来说有两个主要挑战:精益生产和颠覆性成本方法。这些主要想法将是项目从开始到结束的原始驱动因素。为了实现这一目标，Saft正在寻找以下问题的答案:如何更高效、更快速地构建，如何更简单地打包，以及如何能够并行运行大量的区块?Saft的核心业务是储能系统。因此，它将使用其内部的COTS电池，称为MP xlr，用于制造星座用途的电池。mpxlr电池已在100% DOD下进行了1800次循环，同时保留了70%的初始容量。MP xlr电池在20% DOD和30% DOD LEO循环下的性能也显示出与VES16电池(空间专用电池)类似的EODV非常好的趋势。此外，mpxlr电池在整个循环寿命期间表现出稳定的内阻，这在电池水平上具有显著的优势，从电压稳定性到在整个寿命期间恒定的发热。
{"title":"MP XLR battery range for constellation","authors":"A. Vanessa, Clemente Jacky, Jérémy Hyvert, Godon Aurelie, P. J. Paul, Remy Stéphane, Borthomieu Yannick","doi":"10.1109/ESPC.2019.8932000","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932000","url":null,"abstract":"There are two major challenges for Saft to develop a battery design for LEO satellite constellation which is out of the ordinary: lean production as well as a disruptive cost approach. Those main ideas will be the primordial drivers from the beginning to the end of the project. To reach the target, Saft is looking for answers to: how to build more efficiently and quickly, how to pack more simply and how to be able to run in parallel huge number to blocks? Saft core business is in energy storage system. Hence, it will use its in-house COTS cell called MP xlr for the fabrication of batteries for constellation purposes. MP xlr cells has demonstrated 1800 cycles @ 100% DOD while retaining 70% of its initial capacity. The performance of the MP xlr cell evaluated at 20% DOD and 30% DOD LEO cycling also shows a very good trend in EODV similarly to VES16 cell a space dedicated cell. Moreover, MP xlr cell exhibits stable internal resistance over cycle life which gives a significant advantage at battery level from the voltage stability to heat generation that is constant over the life.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"13 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":"90773227","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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