Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8931992
V. Banu, M. Popescu, P. Godignon
This paper introduces the newest proprietary concept called Delta-Reference voltage generator. It is able to generate sub-1V, high temperature compensated voltage reference implemented on silicon carbide (SiC) devices. Hereby, we experimentally demonstrate the functionality of Delta-Reference concept based on a large variety of temperature-dependent SiC devices. Delta-Reference is comparable to the well-known Bandgap-Reference in terms of temperature coefficient (TC), but our new approach is more versatile and comes with additional benefits, being a right candidate for a new generation of voltage reference addressed to high temperature, power management, and space applications.
{"title":"Delta Reference, the Latest High Temperature Compensated Voltage Reference Concept","authors":"V. Banu, M. Popescu, P. Godignon","doi":"10.1109/ESPC.2019.8931992","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931992","url":null,"abstract":"This paper introduces the newest proprietary concept called Delta-Reference voltage generator. It is able to generate sub-1V, high temperature compensated voltage reference implemented on silicon carbide (SiC) devices. Hereby, we experimentally demonstrate the functionality of Delta-Reference concept based on a large variety of temperature-dependent SiC devices. Delta-Reference is comparable to the well-known Bandgap-Reference in terms of temperature coefficient (TC), but our new approach is more versatile and comes with additional benefits, being a right candidate for a new generation of voltage reference addressed to high temperature, power management, and space applications.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"1 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":"88632925","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.2019.8932002
M. Raappana, A. Aho, T. Aho, R. Isoaho, Elina Anttola, Ninja Kajas, V. Polojärvi, A. Tukiainen, M. Guina
We report on the performance of front contact grids based on Ag, Al, and Au applied to III–V multijunction solar cells. We compare their suitability as grid metals from different perspectives, including price, mass-to-conductivity ratio, and abundance. The grid functionality was evaluated by performing charge transport experiments under simulated sunlight. The best solar cell performance was obtained for Ag contacts. On the other hand, Al and Ag provide the most cost-effective approach: when compared to Au, the cost for the grid material for equal conductivities is only about 1.1% for the Ag contacts, and 0.7% for Al.
{"title":"Performance of Solar Cell Grids based on Ag, Au, and Al for Cost-Effective Manufacturing","authors":"M. Raappana, A. Aho, T. Aho, R. Isoaho, Elina Anttola, Ninja Kajas, V. Polojärvi, A. Tukiainen, M. Guina","doi":"10.1109/ESPC.2019.8932002","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932002","url":null,"abstract":"We report on the performance of front contact grids based on Ag, Al, and Au applied to III–V multijunction solar cells. We compare their suitability as grid metals from different perspectives, including price, mass-to-conductivity ratio, and abundance. The grid functionality was evaluated by performing charge transport experiments under simulated sunlight. The best solar cell performance was obtained for Ag contacts. On the other hand, Al and Ag provide the most cost-effective approach: when compared to Au, the cost for the grid material for equal conductivities is only about 1.1% for the Ag contacts, and 0.7% for Al.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"2015 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":"87208848","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.2019.8932077
S. Riva, L. Serafini, S. Amos, M. Cimino, G. D'accolti, S. Durrant, P. Zanella, R. Romani, R. Contini, J. M. Arroyo, Juan Carlos Bahillo, Cristina Borque, Fernando del Campo, Jon Laguna
This paper describes the ExoMars Rover Solar Array Assembly (SAA), a unique equipment, different from anything developed before in Europe. The SAA is part of the Rover which will be launched as part of the European Space Agency's ExoMars Mission under subcontract to the mission prime Thales Alenia Space. Airbus UK has the responsibility of the vehicle, Leonardo of the solar Array including the electrical part, while Sener is responsible for the mechanism part. The ExoMars Rover and Surface Platform, respectively named Rosalind Franklin and Kazachok, planned for launch in 2020 is a large international cooperation between the European Space Agency and Roscosmos with a contribution from NASA. All potential critical requirements have been identified and covered by a specific qualification testing. The biggest challenge in terms of development and qualification efforts is related to surviving Mars planet environment (i.e. dust and wind) and the system mechanical and electrical constraints.
{"title":"The ExoMars Rover Solar Array Assembly","authors":"S. Riva, L. Serafini, S. Amos, M. Cimino, G. D'accolti, S. Durrant, P. Zanella, R. Romani, R. Contini, J. M. Arroyo, Juan Carlos Bahillo, Cristina Borque, Fernando del Campo, Jon Laguna","doi":"10.1109/ESPC.2019.8932077","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932077","url":null,"abstract":"This paper describes the ExoMars Rover Solar Array Assembly (SAA), a unique equipment, different from anything developed before in Europe. The SAA is part of the Rover which will be launched as part of the European Space Agency's ExoMars Mission under subcontract to the mission prime Thales Alenia Space. Airbus UK has the responsibility of the vehicle, Leonardo of the solar Array including the electrical part, while Sener is responsible for the mechanism part. The ExoMars Rover and Surface Platform, respectively named Rosalind Franklin and Kazachok, planned for launch in 2020 is a large international cooperation between the European Space Agency and Roscosmos with a contribution from NASA. All potential critical requirements have been identified and covered by a specific qualification testing. The biggest challenge in terms of development and qualification efforts is related to surviving Mars planet environment (i.e. dust and wind) and the system mechanical and electrical constraints.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"10 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":"80473085","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.2019.8932058
A. Gabriele, G. Palmisano, V. Centonze, C. Ciminelli
Latching Current Limiters are fundamental devices in satellite space power systems required to be Single Point Failure Free. They are used to protect and distribute power as described and required by the ECSS-E-ST-20-20C standard [1]. A crucial aspect of these devices is the current control loop aiming at limiting the current in case of overload or short circuit. On one hand the fastest possible response is required to LCLs when a load fault condition occurs; on the other hand a minimum stability criterion needs to be respected. This paper presents a comparison between three different topologies of control loop: the first one based on a resistive feedback with only a proportional action, the second featuring a topology based on an inductive feedback, with proportional and derivative action, and the third based on an Op Amp, with derivative and integral action. The comparison, mainly based on the ECSS standard, investigates both theoretical and experimental results. These latter derive from tests conducted on prototypes and/or boards intended to find application in space missions. The solution relying on resistive feedback offers a very simple and cost effective solution, while the architecture based on inductive feedback uses an inductor in series with the shunt resistor which results in a reduction of the Current Overshoot as practical experiments demonstrate. Finally, the Op Amp based topology offers a better control of the current limitation value over the other two solutions.
{"title":"A comparison between different LCL architectures in space power systems","authors":"A. Gabriele, G. Palmisano, V. Centonze, C. Ciminelli","doi":"10.1109/ESPC.2019.8932058","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932058","url":null,"abstract":"Latching Current Limiters are fundamental devices in satellite space power systems required to be Single Point Failure Free. They are used to protect and distribute power as described and required by the ECSS-E-ST-20-20C standard [1]. A crucial aspect of these devices is the current control loop aiming at limiting the current in case of overload or short circuit. On one hand the fastest possible response is required to LCLs when a load fault condition occurs; on the other hand a minimum stability criterion needs to be respected. This paper presents a comparison between three different topologies of control loop: the first one based on a resistive feedback with only a proportional action, the second featuring a topology based on an inductive feedback, with proportional and derivative action, and the third based on an Op Amp, with derivative and integral action. The comparison, mainly based on the ECSS standard, investigates both theoretical and experimental results. These latter derive from tests conducted on prototypes and/or boards intended to find application in space missions. The solution relying on resistive feedback offers a very simple and cost effective solution, while the architecture based on inductive feedback uses an inductor in series with the shunt resistor which results in a reduction of the Current Overshoot as practical experiments demonstrate. Finally, the Op Amp based topology offers a better control of the current limitation value over the other two solutions.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"51 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":"88418920","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.2019.8932044
M. Lee, A. Delboulbé, B. Loiseaux, J. Cholet, G. Lehoucq, B. Boulanger, Honorine Boirard, E. Rapp
Micro-concentration for space application enables the reduction of the cell surface and cost. We propose a new concept based on a static (without deployment) compact refractive micro-concentrator. The feasibility of the concept was demonstrated thanks to the realization of a concentrator module which was characterized electrically. To go further, cost and mass are key parameters. To reduce the mass the route is combining the reduction of the cell size to the reduction of the concentrator size/thickness. Subwavelength optics, a family of optics composed of structures with sizes that are smaller than the wavelength, are interesting candidates for flat and lightweight components which are applied to solar generator. We will also discuss possible manufacturing approaches for implementation of such concept.
{"title":"Application of micro-optics to solar generator: results and manufacturing routes","authors":"M. Lee, A. Delboulbé, B. Loiseaux, J. Cholet, G. Lehoucq, B. Boulanger, Honorine Boirard, E. Rapp","doi":"10.1109/ESPC.2019.8932044","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932044","url":null,"abstract":"Micro-concentration for space application enables the reduction of the cell surface and cost. We propose a new concept based on a static (without deployment) compact refractive micro-concentrator. The feasibility of the concept was demonstrated thanks to the realization of a concentrator module which was characterized electrically. To go further, cost and mass are key parameters. To reduce the mass the route is combining the reduction of the cell size to the reduction of the concentrator size/thickness. Subwavelength optics, a family of optics composed of structures with sizes that are smaller than the wavelength, are interesting candidates for flat and lightweight components which are applied to solar generator. We will also discuss possible manufacturing approaches for implementation of such concept.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"4 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":"91327715","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.2019.8932069
Karim Medjoubi, R. Cariou, J. Lefévre, L. Vauche, E. Veinberg-Vidal, C. Jany, Cedric Roasting, Vincent Amalbert, B. Boizot
In this study, we review the potential of III-V/Si solar cell technology for space applications. We present here the experimental results of wafer bonded 2-terminal III-V/Si solar cells electron irradiation. The Begin-Of-Life (BOL) and End-Of-Life (EOL) electrical performances, after 1-MeV electron irradiations, are characterized under AM0 spectrum, and the radiation hardness is compared in Normal Irradiance Room Temperature (NIRT) and Low Irradiance Low Temperature (LILT) conditions.
{"title":"III-V on Si solar cells behavior at NIRT and LILT conditions for space applications","authors":"Karim Medjoubi, R. Cariou, J. Lefévre, L. Vauche, E. Veinberg-Vidal, C. Jany, Cedric Roasting, Vincent Amalbert, B. Boizot","doi":"10.1109/ESPC.2019.8932069","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932069","url":null,"abstract":"In this study, we review the potential of III-V/Si solar cell technology for space applications. We present here the experimental results of wafer bonded 2-terminal III-V/Si solar cells electron irradiation. The Begin-Of-Life (BOL) and End-Of-Life (EOL) electrical performances, after 1-MeV electron irradiations, are characterized under AM0 spectrum, and the radiation hardness is compared in Normal Irradiance Room Temperature (NIRT) and Low Irradiance Low Temperature (LILT) conditions.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"57 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":"90314510","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.2019.8932062
Zhang Xuan, Zou Renwei, Li Feng, Xing Jie, Kang Qing, Zhang Wenshuan
LLC resonant converter, with high efficiency and good dynamic response, finds potential applications in secondary DC/DC converter for satellites. This paper proposes a digital implementation methods to achieve better transient performance based on natural trajectories for LLC converters during load change. In order to increase the reliability for satellites, this paper presents an optimal soft start-up process to minimize voltage and current stress. Validity of the proposed two control methods are verified by simulation and test results.
{"title":"Natural Trajectories and Digital Implementation of Load Dynamic and Soft Start-Up for LLC Converters","authors":"Zhang Xuan, Zou Renwei, Li Feng, Xing Jie, Kang Qing, Zhang Wenshuan","doi":"10.1109/ESPC.2019.8932062","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932062","url":null,"abstract":"LLC resonant converter, with high efficiency and good dynamic response, finds potential applications in secondary DC/DC converter for satellites. This paper proposes a digital implementation methods to achieve better transient performance based on natural trajectories for LLC converters during load change. In order to increase the reliability for satellites, this paper presents an optimal soft start-up process to minimize voltage and current stress. Validity of the proposed two control methods are verified by simulation and test results.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"12 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":"83745796","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.2019.8932053
S. Fereres, Sergio Escario, C. Prieto, S. de La Rosa
In-Situ Resource Utilization (ISRU) technologies for future deep-space exploration is a current hot topic considering planned lunar missions for the coming years. Energy generation and storage using regolith can be useful not only for future lunar human outposts but also to assist lunar mining or construction activities during the lunar night. Here we explore the design of a packed bed Thermal Energy Storage (TES) system using regolith as the storage media through a numerical model. System requirements are analyzed depending on landing sites and mission needs. Different heat transfer fluids (HTF) are evaluated for the TES charge/discharge, using media available from other complementary ISRU processes (i.e. oxygen/water production from lunar regolith) or gases indispensable for life support systems. Raw regolith of varied composition, several Earth materials and processed/reduced regolith are compared, and different TES integration options are discussed.
{"title":"Regolith Packed Bed Thermal Energy Storage for Lunar Night Survival","authors":"S. Fereres, Sergio Escario, C. Prieto, S. de La Rosa","doi":"10.1109/ESPC.2019.8932053","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932053","url":null,"abstract":"In-Situ Resource Utilization (ISRU) technologies for future deep-space exploration is a current hot topic considering planned lunar missions for the coming years. Energy generation and storage using regolith can be useful not only for future lunar human outposts but also to assist lunar mining or construction activities during the lunar night. Here we explore the design of a packed bed Thermal Energy Storage (TES) system using regolith as the storage media through a numerical model. System requirements are analyzed depending on landing sites and mission needs. Different heat transfer fluids (HTF) are evaluated for the TES charge/discharge, using media available from other complementary ISRU processes (i.e. oxygen/water production from lunar regolith) or gases indispensable for life support systems. Raw regolith of varied composition, several Earth materials and processed/reduced regolith are compared, and different TES integration options are discussed.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"23 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":"83756908","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.2019.8932081
D. Schofield
There is increasing interest in the use of Commercial Off-the-shelf (COTS) components in space, especially for relatively short (less than ten years) low earth orbit (LEO) missions. Using of COTS components can drastically reduce the lead time and cost. These devices however are not characterised for the space environment and how these components respond to the radiation environment encountered must be understood and appropriate mitigations must be taken during circuit design. A spacecraft power system will typically involve many stages of voltage conversion, and this is often most efficiently carried out using field-effect transistors (FETs). Of special concern is the destructive failure modes of silicon Metal Oxide Semiconductor Field Effect Transistors (MOSFETS) under heavy ion bombardment caused by rupture of the isolated gate. Due to the lack of manufacturer's data the susceptibility of COTS parts cannot predicted with any degree of accuracy. Expensive and time consuming testing is required to have confidence that these devices can be used, and the manufacturer of COTS components can make minor changes to the die that do not materially impact performance but lead the part to have a different response to radiation. An alternative to the use of silicon MOSFETs is to use gallium nitride (GaN) FETs. Whilst not completely immune to radiation damage they are much less susceptible to catastrophic failure. When coupled with tested drivers and control circuits, they can be employed in radiation tolerant power converters with efficiencies at least as good as their silicon counterparts. At SSTL, GaN based power converters ranging from 1W to 300W design are implemented. In this paper, the implementation of a 100W converter used to supply an isolated, regulated 20.3V to a transmitter will be described. The design has a conversion efficiency of up to 94% and occupies the space previously taken up by a much more expensive bought in ‘brick’ converter.
{"title":"Design and Implementation of a COTS, GaN–based Power Converter for Spacecraft Applications","authors":"D. Schofield","doi":"10.1109/ESPC.2019.8932081","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932081","url":null,"abstract":"There is increasing interest in the use of Commercial Off-the-shelf (COTS) components in space, especially for relatively short (less than ten years) low earth orbit (LEO) missions. Using of COTS components can drastically reduce the lead time and cost. These devices however are not characterised for the space environment and how these components respond to the radiation environment encountered must be understood and appropriate mitigations must be taken during circuit design. A spacecraft power system will typically involve many stages of voltage conversion, and this is often most efficiently carried out using field-effect transistors (FETs). Of special concern is the destructive failure modes of silicon Metal Oxide Semiconductor Field Effect Transistors (MOSFETS) under heavy ion bombardment caused by rupture of the isolated gate. Due to the lack of manufacturer's data the susceptibility of COTS parts cannot predicted with any degree of accuracy. Expensive and time consuming testing is required to have confidence that these devices can be used, and the manufacturer of COTS components can make minor changes to the die that do not materially impact performance but lead the part to have a different response to radiation. An alternative to the use of silicon MOSFETs is to use gallium nitride (GaN) FETs. Whilst not completely immune to radiation damage they are much less susceptible to catastrophic failure. When coupled with tested drivers and control circuits, they can be employed in radiation tolerant power converters with efficiencies at least as good as their silicon counterparts. At SSTL, GaN based power converters ranging from 1W to 300W design are implemented. In this paper, the implementation of a 100W converter used to supply an isolated, regulated 20.3V to a transmitter will be described. The design has a conversion efficiency of up to 94% and occupies the space previously taken up by a much more expensive bought in ‘brick’ converter.","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":"79007932","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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