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.2019.8932047
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.2019.8932054
S. Pappalardo, Carmelo Ardizzone, Orazio Principato, Agatino Alessandro, I. Mirabella, F. Tonicello, Michail Tourloukis
This paper discuss the development of a radiation hardened Pulse Width Modulation (PWM) controller designed and manufactured by STMicroelectronics, for aerospace applications. It provides a brief technical description of the design and features of the device highlighting the main elements. Finally, some typical application circuits together with a selection of interesting plots and waveforms are presented.
{"title":"RHPWM01 Radiation hardened dual channel current mode PWM","authors":"S. Pappalardo, Carmelo Ardizzone, Orazio Principato, Agatino Alessandro, I. Mirabella, F. Tonicello, Michail Tourloukis","doi":"10.1109/ESPC.2019.8932054","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932054","url":null,"abstract":"This paper discuss the development of a radiation hardened Pulse Width Modulation (PWM) controller designed and manufactured by STMicroelectronics, for aerospace applications. It provides a brief technical description of the design and features of the device highlighting the main elements. Finally, some typical application circuits together with a selection of interesting plots and waveforms are presented.","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":"79724794","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.2019.8932052
M. Persson, S. Petersen, B. Søderberg
A 200W rad-hard, high current, low output voltage DC/DC converter has been developed and qualified for use in a two for one cold redundant configuration supplying multiple parallel processor channels on-board a communication satellite. Best in class efficiency in excess of 93.5% is achieved and includes all housekeeping consumption as well as the loss in the active diode OR-ing circuit placed in series with the output.
{"title":"Efficient 200W Low Voltage DC/DC for Redundant On-Board Processing Systems","authors":"M. Persson, S. Petersen, B. Søderberg","doi":"10.1109/ESPC.2019.8932052","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932052","url":null,"abstract":"A 200W rad-hard, high current, low output voltage DC/DC converter has been developed and qualified for use in a two for one cold redundant configuration supplying multiple parallel processor channels on-board a communication satellite. Best in class efficiency in excess of 93.5% is achieved and includes all housekeeping consumption as well as the loss in the active diode OR-ing circuit placed in series with the output.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"23 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":"78469236","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.2019.8932060
A. H. Dida
Design for any satellite includes its electrical power needs and the system to supply them. The availability of solar energy has encouraged the development of solar cell arrays which are major structural element for providing power generation of many spacecraft. Solar cell array design must be instituted early in the development of satellite design mission. The high performance of satellite solar cell array design depends on the intensity of sunlight incident, the conversion efficiency of solar cells and the interaction of the array with satellite. The advances in technology are nowadays allowing the production of solar cells in different sizes and more importantly with increased efficiencies exceeding 30%. The most efficient technology for electricity generation from solar energy is multi-junction solar cells. Simplicity, relatively modest cost, and high reliability have caused these solar cells based on GaAs to be chosen for supplying the electrical power system of almost satellites. The aim of this research work was designed and modeled a useful tool for satellite solar array preliminary sizing and power system analysis of our spacecraft system. We had also simulated and compared a various solar cells to investigate their performance in terms of efficiency to select the adequate type of cells that should be chosen to insure performance at the required output to the end of the mission while minimizing costs. The useful tool of satellite solar array sizing was validated using data Alsat-1 project. The required area and weight of satellite solar array are calculated and selected to provide the required end-of-mission power without complicating installation of cells.
{"title":"Design and Modeling of useful Tool for Satellite Solar Array Preliminary Sizing and Power System Analysis","authors":"A. H. Dida","doi":"10.1109/ESPC.2019.8932060","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932060","url":null,"abstract":"Design for any satellite includes its electrical power needs and the system to supply them. The availability of solar energy has encouraged the development of solar cell arrays which are major structural element for providing power generation of many spacecraft. Solar cell array design must be instituted early in the development of satellite design mission. The high performance of satellite solar cell array design depends on the intensity of sunlight incident, the conversion efficiency of solar cells and the interaction of the array with satellite. The advances in technology are nowadays allowing the production of solar cells in different sizes and more importantly with increased efficiencies exceeding 30%. The most efficient technology for electricity generation from solar energy is multi-junction solar cells. Simplicity, relatively modest cost, and high reliability have caused these solar cells based on GaAs to be chosen for supplying the electrical power system of almost satellites. The aim of this research work was designed and modeled a useful tool for satellite solar array preliminary sizing and power system analysis of our spacecraft system. We had also simulated and compared a various solar cells to investigate their performance in terms of efficiency to select the adequate type of cells that should be chosen to insure performance at the required output to the end of the mission while minimizing costs. The useful tool of satellite solar array sizing was validated using data Alsat-1 project. The required area and weight of satellite solar array are calculated and selected to provide the required end-of-mission power without complicating installation of cells.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"82 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":"75958336","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.2019.8931994
Hélène Tricot, P. Brochard
“Sojourner” (NASA Pathfinder mission) was the very first tiny 10.6 kgs Martian rover landing on Mars 24 years ago. It was powered by solar panels backed by a primary battery [1]. The EXOMARS 2020 mission intends to land a new rover on the surface of Mars. It is a European Space Agency (ESA) program executed in cooperation with Russian Space Agency (Roscosmos) with contribution of NASA. The spacecraft is composed of a carrier module, a descent module developed by ThalesAleniaSpace in Italy in partnership with Lavochkin in Russia; and a Rover developed by Airbus DS UK under the prime contractor responsibility Thales Alenia Space Italia. The launch is scheduled for July 2020. Batteries - including cells - for the descent module and the rover [2] were developed and manufactured by Saft (F).
{"title":"EXOMARS 2020 mission Descent module & Rover batteries","authors":"Hélène Tricot, P. Brochard","doi":"10.1109/ESPC.2019.8931994","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931994","url":null,"abstract":"“Sojourner” (NASA Pathfinder mission) was the very first tiny 10.6 kgs Martian rover landing on Mars 24 years ago. It was powered by solar panels backed by a primary battery [1]. The EXOMARS 2020 mission intends to land a new rover on the surface of Mars. It is a European Space Agency (ESA) program executed in cooperation with Russian Space Agency (Roscosmos) with contribution of NASA. The spacecraft is composed of a carrier module, a descent module developed by ThalesAleniaSpace in Italy in partnership with Lavochkin in Russia; and a Rover developed by Airbus DS UK under the prime contractor responsibility Thales Alenia Space Italia. The launch is scheduled for July 2020. Batteries - including cells - for the descent module and the rover [2] were developed and manufactured by Saft (F).","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"19 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":"81526051","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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