Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8931985
F. Pintacuda, V. Cantarella, M. Muschitiello, S. Massetti
This study shall be considered as preparatory work supporting the planned development of discrete European radiation-hardened SiC power-MOSFETs for space applications. It's based on prototyping and manufacturing elementary structures that have been submitted to DC, AC, stability characterizations and radiation tests, in order to study the contributions of any basic element that composes the MOSFET structure to radiation sensitivity in a dedicated way.
{"title":"Prototyping and characterization of radiation hardened SiC MOS structures","authors":"F. Pintacuda, V. Cantarella, M. Muschitiello, S. Massetti","doi":"10.1109/ESPC.2019.8931985","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931985","url":null,"abstract":"This study shall be considered as preparatory work supporting the planned development of discrete European radiation-hardened SiC power-MOSFETs for space applications. It's based on prototyping and manufacturing elementary structures that have been submitted to DC, AC, stability characterizations and radiation tests, in order to study the contributions of any basic element that composes the MOSFET structure to radiation sensitivity in a dedicated way.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"17 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":"87854241","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.2019.8931988
M. Bekemans, François Bronchart, T. Scalais, A. Franke
The present paper describes several technological topics featured in a new prototype of anode/beam supply for 5 kW Power Processing Unit (PPU), dedicated to be compatible with many thruster types and operating modes thanks to a configurable output stage and wide output voltage range. The achievements in terms of power density and cost reduction are attributed to a new electrical topology (Dual Active Bridge) allowing better current form factor and hence lower losses, but also to wide-bandgap semiconductors and to a new, high-power, high-voltage transformer. A versatile digital control has been implemented to be compatible with all output configurations and to use additional degree of freedom in the control loop to minimize certain losses.
{"title":"Configurable High Voltage Power Supply for Full Electric Propulsion Spacecraft","authors":"M. Bekemans, François Bronchart, T. Scalais, A. Franke","doi":"10.1109/ESPC.2019.8931988","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931988","url":null,"abstract":"The present paper describes several technological topics featured in a new prototype of anode/beam supply for 5 kW Power Processing Unit (PPU), dedicated to be compatible with many thruster types and operating modes thanks to a configurable output stage and wide output voltage range. The achievements in terms of power density and cost reduction are attributed to a new electrical topology (Dual Active Bridge) allowing better current form factor and hence lower losses, but also to wide-bandgap semiconductors and to a new, high-power, high-voltage transformer. A versatile digital control has been implemented to be compatible with all output configurations and to use additional degree of freedom in the control loop to minimize certain losses.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"31 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":"79207527","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.2019.8932001
Martin T. Arentsen, C. Bak, F. D. da Silva, S. Lorenzen
External Partial discharges (PDs) can occur in strong non-uniform electrical fields on electrical equipment. Usually, PDs are only considered in the design process of high voltage applications, where ionization is more likely to occur. Under certain ambient conditions, i.e. under low gaseous pressures, the dielectric strength of an insulation might be weakened, leading to onset of partial discharges - even at voltages below 1 kV. PDs are responsible of insulation deterioration, due to bombardment of ions formed by PDs, as well as chemical reactions by compounds formed during discharge process. Additionally, PDs can cause interference in communication systems. Therefore, PDs are also highly unwanted on electronics for space applications, where reliability is utmost important. The European Cooperation for Space Standardization issued a design handbook for electronics for space applications, in which PD magnitude limits are given. It discards the importance of external PDs, since it argues that no atmosphere will be present in outer space. While that is true, equipment that is under operation during launch of the space vessel, will experience a pressure drop from standard atmospheric pressure to near vacuum. Given a corona onset, an enhancement of the field in the vicinity of the cathode might occur, due to the relative low mobility of the formed positive ions, thereby transitioning the corona into a self-sustained PD. This paper therefore presents both predictive analytical tools for external PDs, applicable in the design process of equipment, as well as an experimental measurement setup to measure PDs in compliance with IEC 60270. Flux A/S design and manufacture magnetic components for space applications. They were unable to analyze a prototype design for PDs before manufacturing, and unable to measure PDs on manufactured prototypes. Collaboration was established between Flux A/S and Aalborg University to enable Flux to do so.
{"title":"External Partial Discharge Analysis in Design Process of Electrical Space Components","authors":"Martin T. Arentsen, C. Bak, F. D. da Silva, S. Lorenzen","doi":"10.1109/ESPC.2019.8932001","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932001","url":null,"abstract":"External Partial discharges (PDs) can occur in strong non-uniform electrical fields on electrical equipment. Usually, PDs are only considered in the design process of high voltage applications, where ionization is more likely to occur. Under certain ambient conditions, i.e. under low gaseous pressures, the dielectric strength of an insulation might be weakened, leading to onset of partial discharges - even at voltages below 1 kV. PDs are responsible of insulation deterioration, due to bombardment of ions formed by PDs, as well as chemical reactions by compounds formed during discharge process. Additionally, PDs can cause interference in communication systems. Therefore, PDs are also highly unwanted on electronics for space applications, where reliability is utmost important. The European Cooperation for Space Standardization issued a design handbook for electronics for space applications, in which PD magnitude limits are given. It discards the importance of external PDs, since it argues that no atmosphere will be present in outer space. While that is true, equipment that is under operation during launch of the space vessel, will experience a pressure drop from standard atmospheric pressure to near vacuum. Given a corona onset, an enhancement of the field in the vicinity of the cathode might occur, due to the relative low mobility of the formed positive ions, thereby transitioning the corona into a self-sustained PD. This paper therefore presents both predictive analytical tools for external PDs, applicable in the design process of equipment, as well as an experimental measurement setup to measure PDs in compliance with IEC 60270. Flux A/S design and manufacture magnetic components for space applications. They were unable to analyze a prototype design for PDs before manufacturing, and unable to measure PDs on manufactured prototypes. Collaboration was established between Flux A/S and Aalborg University to enable Flux to do so.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"136 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":"79606188","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.2019.8932041
Pablo Hernandez, E. Bertels, M. Fernández, M. Ruiter, K. Visser, M. K. Wolt
The Chinese Chang’ E 4 mission includes a relay satellite named Queqiao or Magpie Bridge from a Chinese folk tale, developed by the Chinese Academy of Space Technology (CAST). In May 2018, Queqiao was launched into halo orbit at the second Earth-Moon Lagrange point (~64000 km behind the moon), to provide direct communication between the Earth and the far side of the Moon. The satellite's main mission is to serve as a relay for the communication between Earth and the Chang' E 4 robotic mission that landed on the far side of the Moon. On board this satellite is the scientific payload Netherlands-China Low-Frequency Explorer (NCLE). This is a low-frequency radio astronomy instrument, which includes a power interface system developed in The Netherlands by the company Innovative Solutions in Space B.V. in cooperation with ASTRON, Radboud University and the Chinese National Space Science Center (NSSC). The instrument is designed to address a multitude of high-profile science cases. The NCLE payload was developed in less than a year to fit the tight schedule for the Chang'E 4 launch. Due to this limitation, CubeSat methodologies were proposed and selected to demonstrate that the combination of Commercial Off-The-Shelf (COTS) and low cost processes can satisfy the requirement for short period developments. This paper shows the results and calls for new opportunities, opening the market to new chances to accommodate low cost science demonstrators within bigger platforms or satellites much bigger than a standard CubeSat. Only, if it demonstrates that all safety requirements are compliant with the platform and the design is robust enough to avoid any failure propagation. NCLE envisages the usage of CubeSat technology and cheap components with innovative design approaches.
{"title":"Technology demonstration of using Cubesat methodologies for power control and distribution in a radio-astronomy instrument within the Chang'E 4 mission","authors":"Pablo Hernandez, E. Bertels, M. Fernández, M. Ruiter, K. Visser, M. K. Wolt","doi":"10.1109/ESPC.2019.8932041","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932041","url":null,"abstract":"The Chinese Chang’ E 4 mission includes a relay satellite named Queqiao or Magpie Bridge from a Chinese folk tale, developed by the Chinese Academy of Space Technology (CAST). In May 2018, Queqiao was launched into halo orbit at the second Earth-Moon Lagrange point (~64000 km behind the moon), to provide direct communication between the Earth and the far side of the Moon. The satellite's main mission is to serve as a relay for the communication between Earth and the Chang' E 4 robotic mission that landed on the far side of the Moon. On board this satellite is the scientific payload Netherlands-China Low-Frequency Explorer (NCLE). This is a low-frequency radio astronomy instrument, which includes a power interface system developed in The Netherlands by the company Innovative Solutions in Space B.V. in cooperation with ASTRON, Radboud University and the Chinese National Space Science Center (NSSC). The instrument is designed to address a multitude of high-profile science cases. The NCLE payload was developed in less than a year to fit the tight schedule for the Chang'E 4 launch. Due to this limitation, CubeSat methodologies were proposed and selected to demonstrate that the combination of Commercial Off-The-Shelf (COTS) and low cost processes can satisfy the requirement for short period developments. This paper shows the results and calls for new opportunities, opening the market to new chances to accommodate low cost science demonstrators within bigger platforms or satellites much bigger than a standard CubeSat. Only, if it demonstrates that all safety requirements are compliant with the platform and the design is robust enough to avoid any failure propagation. NCLE envisages the usage of CubeSat technology and cheap components with innovative design approaches.","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":"87407899","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.2019.8932017
G. Simonelli, C. Brandt, M. Rezazad
The ESA Aeolus satellite launched on 23 August 2018 has just completed its first year in orbit. This article presents the performance of the Aeolus Power System as observed via housekeeping data from satellite, accessed with WEBMUST, the web-based client for MUST Information System and used to access mission data by ESOC.
{"title":"Aeolus First Year in Orbit Power System Performance","authors":"G. Simonelli, C. Brandt, M. Rezazad","doi":"10.1109/ESPC.2019.8932017","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932017","url":null,"abstract":"The ESA Aeolus satellite launched on 23 August 2018 has just completed its first year in orbit. This article presents the performance of the Aeolus Power System as observed via housekeeping data from satellite, accessed with WEBMUST, the web-based client for MUST Information System and used to access mission data by ESOC.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"91 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":"78435152","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.2019.8932091
Eduardo Olmeda Diaz, J. Caudepon, S. Alia
This paper present the research, development and implementation of a Spacecraft model for the realization of an Electrical Power Subsystems (EPS) energy balance and sizing tool. Developed within the EcosimPro environment, this tool is able to conduct energy balance simulations for virtually any type of mission orbit and multiple power architectures. It comprehends mathematical models of key power units such as Batteries, Solar Arrays (SA) and Power Conditioning Units (PCU), while it also implements, in a multidisciplinary system concept, components to process SC orbit and attitude parameters, as well as dynamically changing thermal predictions.
{"title":"Satellite's Energy Balance, Modelling and Sizing Tool with Ecosimpro","authors":"Eduardo Olmeda Diaz, J. Caudepon, S. Alia","doi":"10.1109/ESPC.2019.8932091","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932091","url":null,"abstract":"This paper present the research, development and implementation of a Spacecraft model for the realization of an Electrical Power Subsystems (EPS) energy balance and sizing tool. Developed within the EcosimPro environment, this tool is able to conduct energy balance simulations for virtually any type of mission orbit and multiple power architectures. It comprehends mathematical models of key power units such as Batteries, Solar Arrays (SA) and Power Conditioning Units (PCU), while it also implements, in a multidisciplinary system concept, components to process SC orbit and attitude parameters, as well as dynamically changing thermal predictions.","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":"75696262","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.2019.8932056
Eveillard Fabien, D. Diane, Sougrati Moulay-Tahar, Guérin Katia
Lithium-ion batteries are widely used in spacecraft for their high volumetric and gravimetric energy densities thus enabling the conception of lightweight and compact devices. To improve this battery technology in terms of energy density, an urgent need for new cathode materials must be satisfied. Indeed, a performance limit was reached with intercalation materials; new electrochemical processes such as conversion type must be developed. In this work, we ran electrochemical tests on iron trifluorides based cathode materials which are engaged both in intercalation process and conversion one. Theoretically, these compounds, through intercalation process, can improve energy density of battery up to 252 Wh/kg and up to 467 Wh/kg through conversion process. Iron trifluorides have different allotropic phases, which can clearly favor good electrochemical processes but fluorides compounds and more particularly anhydrous ones are not easy to prepare. In this study, using various precursors and innovative gaseous fluorination, anhydrous forms of iron trifluorides have been prepared without any thermal post treatment while maintaining a good particle size. We will demonstrate that, by changing the precursors, morphology as well as structure of iron trifluoride can be tuned. Electrochemical tests in geostationary satellite conditions are promising and will be compared with NCA cathode used in the same electrochemical conditions as a commercial reference.
{"title":"ℌFeF3 as a cathode material in lithium ion batteries working in spacecraft conditions”","authors":"Eveillard Fabien, D. Diane, Sougrati Moulay-Tahar, Guérin Katia","doi":"10.1109/ESPC.2019.8932056","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932056","url":null,"abstract":"Lithium-ion batteries are widely used in spacecraft for their high volumetric and gravimetric energy densities thus enabling the conception of lightweight and compact devices. To improve this battery technology in terms of energy density, an urgent need for new cathode materials must be satisfied. Indeed, a performance limit was reached with intercalation materials; new electrochemical processes such as conversion type must be developed. In this work, we ran electrochemical tests on iron trifluorides based cathode materials which are engaged both in intercalation process and conversion one. Theoretically, these compounds, through intercalation process, can improve energy density of battery up to 252 Wh/kg and up to 467 Wh/kg through conversion process. Iron trifluorides have different allotropic phases, which can clearly favor good electrochemical processes but fluorides compounds and more particularly anhydrous ones are not easy to prepare. In this study, using various precursors and innovative gaseous fluorination, anhydrous forms of iron trifluorides have been prepared without any thermal post treatment while maintaining a good particle size. We will demonstrate that, by changing the precursors, morphology as well as structure of iron trifluoride can be tuned. Electrochemical tests in geostationary satellite conditions are promising and will be compared with NCA cathode used in the same electrochemical conditions as a commercial reference.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"41 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":"84972699","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.2019.8932038
H. Toyota, I. Shinohara
We found that the solar panel output current of JAXA's Venus explorer Akatsuki is below values expected from percentage of shadow during penumbras. We also found that a similar phenomenon occurs in JAXA's Van Allen radiation belts explorer Arase during Earth shadow penumbra. However, during a Lunar shadow penumbra, solar panel output current decreased in proportion to percentage of shadow. We consider that sunlight attenuated by the planetary atmosphere caused this decrease in current. As in the transit spectroscopy technique, planetary atmospheres could be characterized by trends in solar panel output current.
{"title":"Preliminary Study For Analyzing Planetary Atmosphere Using Solar Panel Output Current","authors":"H. Toyota, I. Shinohara","doi":"10.1109/ESPC.2019.8932038","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932038","url":null,"abstract":"We found that the solar panel output current of JAXA's Venus explorer Akatsuki is below values expected from percentage of shadow during penumbras. We also found that a similar phenomenon occurs in JAXA's Van Allen radiation belts explorer Arase during Earth shadow penumbra. However, during a Lunar shadow penumbra, solar panel output current decreased in proportion to percentage of shadow. We consider that sunlight attenuated by the planetary atmosphere caused this decrease in current. As in the transit spectroscopy technique, planetary atmospheres could be characterized by trends in solar panel output current.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"28 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":"85087080","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.2019.8932028
H. Carbonnier, H. Barde, Lorenzo Riga, A. Carre
Electrochemical Impedance Spectroscopy was conducted on Li-Ion cells using a simple square current waveform as excitation signal, instead of the traditional sinusoidal sweep. Using a sampling rate of 1 kHz and a square wave period of 40 seconds, exploitable EIS data ranging from 0.025 Hz to 25 Hz could be extracted, which corresponds to the region where most of the useful data lies. Sensitivity of the method to sampling rate, square wave period and test current was explained, together with the effect of measurement noise on the final results. It was shown how current satellite technology could be used to produce such datasets in order to better estimate Battery State of Charge (SOC), State of Health (SOH) and Remaining Useful Lifetime (RUL).
{"title":"Electrochemical Impedance Spectroscopy for Online Satellite Battery Monitoring Using Square Wave Excitation","authors":"H. Carbonnier, H. Barde, Lorenzo Riga, A. Carre","doi":"10.1109/ESPC.2019.8932028","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932028","url":null,"abstract":"Electrochemical Impedance Spectroscopy was conducted on Li-Ion cells using a simple square current waveform as excitation signal, instead of the traditional sinusoidal sweep. Using a sampling rate of 1 kHz and a square wave period of 40 seconds, exploitable EIS data ranging from 0.025 Hz to 25 Hz could be extracted, which corresponds to the region where most of the useful data lies. Sensitivity of the method to sampling rate, square wave period and test current was explained, together with the effect of measurement noise on the final results. It was shown how current satellite technology could be used to produce such datasets in order to better estimate Battery State of Charge (SOC), State of Health (SOH) and Remaining Useful Lifetime (RUL).","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"1 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":"82194681","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.2019.8931991
V. Knap, L. Vestergaard, D. Stroe
Satellites' mission lifetime is limited by the lifetime of the battery. Thus, it is necessary to assess in advance on the ground that the applied battery design will support long-term commercial missions. So far, the applied approaches are either over-simplified and cannot be used for long-term predictions, or they are too expensive (time wise or testing resources wise). A synthetic mission profile is developed in this work based on telemetry data, to create a representative profile considering real battery mission conditions and to allow for low cost and effective lifetime testing.
{"title":"Towards Validation of Battery Mission Lifetime for Nano-satellites: Fast, Cheap and Accurate Through a Representative Mission Profile","authors":"V. Knap, L. Vestergaard, D. Stroe","doi":"10.1109/ESPC.2019.8931991","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931991","url":null,"abstract":"Satellites' mission lifetime is limited by the lifetime of the battery. Thus, it is necessary to assess in advance on the ground that the applied battery design will support long-term commercial missions. So far, the applied approaches are either over-simplified and cannot be used for long-term predictions, or they are too expensive (time wise or testing resources wise). A synthetic mission profile is developed in this work based on telemetry data, to create a representative profile considering real battery mission conditions and to allow for low cost and effective lifetime testing.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"26 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":"85388246","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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