Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8931987
D. Wilt, R. Hoheisel, A. Haas, P. Jenkins, J. Lorentzen, Casey Hare, Daniel T. Hernandez, A. Gras, G. Martínez, Lt. Justin Baker
The frequency of high altitude balloons flights for the purpose of AM0 calibration of solar cells has diminished substantially in the last decade. There is increasing interest in routine calibration flights to characterize the next generation of space solar cells, which have substantially different spectral response than the incumbent GaInP/InGaAs/Ge cells. This paper describes several ongoing efforts to restore high-altitude balloon solar cell calibration capability.
{"title":"High-Altitude Space Solar Cell Calibration on Small Balloons","authors":"D. Wilt, R. Hoheisel, A. Haas, P. Jenkins, J. Lorentzen, Casey Hare, Daniel T. Hernandez, A. Gras, G. Martínez, Lt. Justin Baker","doi":"10.1109/ESPC.2019.8931987","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931987","url":null,"abstract":"The frequency of high altitude balloons flights for the purpose of AM0 calibration of solar cells has diminished substantially in the last decade. There is increasing interest in routine calibration flights to characterize the next generation of space solar cells, which have substantially different spectral response than the incumbent GaInP/InGaAs/Ge cells. This paper describes several ongoing efforts to restore high-altitude balloon solar cell calibration capability.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"26 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":"83080420","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.2019.8932082
Mario Buffardo, E. Scione, Catalano Toni Fabio, Carlani Daniele, Ruà Emanuele Giovanni
The double insulation topic has become a very important issue in the satellite design since its implementation drives the sizing of the whole satellite electrical architecture. Different approaches and solutions have been proposed by Industry [2], according to specific need of each spacecraft design and requirements. According to ECSS-E-ST-20C [1]., a barrier against short circuit between conductors or circuit elements shall be guaranteed also after any credible single failure. In particular., the guideline is that all non-protected elements of a main bus distribution system shall implement an electrical double insulation up to the first protection device (e.g.: fuse., current breaker or current limiter).
{"title":"Implementation of double insulation at satellite level: an approach","authors":"Mario Buffardo, E. Scione, Catalano Toni Fabio, Carlani Daniele, Ruà Emanuele Giovanni","doi":"10.1109/ESPC.2019.8932082","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932082","url":null,"abstract":"The double insulation topic has become a very important issue in the satellite design since its implementation drives the sizing of the whole satellite electrical architecture. Different approaches and solutions have been proposed by Industry [2], according to specific need of each spacecraft design and requirements. According to ECSS-E-ST-20C [1]., a barrier against short circuit between conductors or circuit elements shall be guaranteed also after any credible single failure. In particular., the guideline is that all non-protected elements of a main bus distribution system shall implement an electrical double insulation up to the first protection device (e.g.: fuse., current breaker or current limiter).","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"20 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":"82081944","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.2019.8932071
K. Adams, B. Cardwell, Joshua Fedders
ABSL builds batteries using commercial off the shelf (COTS) lithium-ion cells of the 18650 form factor. The commercial applications of 18650 lithium-ion cells have grown tremendously over the last 20 years, and cell manufacturers continue to improve the state-of-the-art by increasing energy density (Wh/L) and specific energy (Wh/kg) of their products. The increasing mass efficiency of these cells has facilitated more widespread and cost-effective adoption of lithium-ion as a power source in portable applications, which in turn has inspired investment in the development of new cells with ever increasing energy density. For space applications, the benefits of using cells with the highest possible mass efficiency are well established. But for a variety of reasons - the most significant being the increased amount of stored electrochemical potential energy - high energy density cells pose additional challenges to safely integrate into a battery solution. This is particularly true for the risk of catastrophic failure related to a thermal runaway event, and specific requirements are typically levied against battery designs in human spaceflight applications through JSC 20793, “Crewed Space Vehicle Battery Safety Requirements”. In order to characterize the thermal runaway behavior of a high energy density cell selected for a human spaceflight program, ABSL carried out a progressive development testing campaign. Starting from loose single cells, the test campaign incrementally included flight-like design features intended to mitigate the observed thermal runaway behavior. The results of the testing were subsequently incorporated into the flight design and the next level of development testing. The test campaign culminated in summer 2019 with successful verification of the JSC 20793 requirements on the CDR battery design.
{"title":"Testing of Thermal Runaway Tolerant Battery Designs Utilizing High Energy Density 18650 Lithium Ion Cells","authors":"K. Adams, B. Cardwell, Joshua Fedders","doi":"10.1109/ESPC.2019.8932071","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932071","url":null,"abstract":"ABSL builds batteries using commercial off the shelf (COTS) lithium-ion cells of the 18650 form factor. The commercial applications of 18650 lithium-ion cells have grown tremendously over the last 20 years, and cell manufacturers continue to improve the state-of-the-art by increasing energy density (Wh/L) and specific energy (Wh/kg) of their products. The increasing mass efficiency of these cells has facilitated more widespread and cost-effective adoption of lithium-ion as a power source in portable applications, which in turn has inspired investment in the development of new cells with ever increasing energy density. For space applications, the benefits of using cells with the highest possible mass efficiency are well established. But for a variety of reasons - the most significant being the increased amount of stored electrochemical potential energy - high energy density cells pose additional challenges to safely integrate into a battery solution. This is particularly true for the risk of catastrophic failure related to a thermal runaway event, and specific requirements are typically levied against battery designs in human spaceflight applications through JSC 20793, “Crewed Space Vehicle Battery Safety Requirements”. In order to characterize the thermal runaway behavior of a high energy density cell selected for a human spaceflight program, ABSL carried out a progressive development testing campaign. Starting from loose single cells, the test campaign incrementally included flight-like design features intended to mitigate the observed thermal runaway behavior. The results of the testing were subsequently incorporated into the flight design and the next level of development testing. The test campaign culminated in summer 2019 with successful verification of the JSC 20793 requirements on the CDR battery design.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"1 1","pages":"1-7"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90284949","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.2019.8932015
Stanislav Gorelkov, S. Palecki, A. Heinzel
In this study, the behaviour of Polymer-Electrolyte Membrane (PEM) single cells with different types of MEA systems have been studied under thermal cycling with respect to structural and electrochemical changes. The cells have been insulated and exposed to repeated freeze-thaw cycles with a minimum temperature of −40°C inside an environmental chamber. To some extent, great differences between the degrees of damage could be found for the various types of MEA systems (e.g. catalyst coated membrane (CCM), catalyst coated substrate (CCS)).
{"title":"Effect of the cyclic freeze-thaw exposure on the performance of PEM fuel cells","authors":"Stanislav Gorelkov, S. Palecki, A. Heinzel","doi":"10.1109/ESPC.2019.8932015","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932015","url":null,"abstract":"In this study, the behaviour of Polymer-Electrolyte Membrane (PEM) single cells with different types of MEA systems have been studied under thermal cycling with respect to structural and electrochemical changes. The cells have been insulated and exposed to repeated freeze-thaw cycles with a minimum temperature of −40°C inside an environmental chamber. To some extent, great differences between the degrees of damage could be found for the various types of MEA systems (e.g. catalyst coated membrane (CCM), catalyst coated substrate (CCS)).","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"33 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":"73519587","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.2019.8932009
Eugene Schwanbeck, P. Dalton
The International Space Station (ISS) primary Electric Power System (EPS) was designed to utilize Nickel-Hydrogen (Ni-H2) batteries to store electrical energy. The electricity for the space station is generated by its solar arrays, which charge batteries during insolation for subsequent discharge during eclipse. The Ni-H2 batteries are designed to operate at a 35% depth of discharge (DOD) maximum during normal operation in a Low Earth Orbit. Since the oldest of the 48 Ni-H2 battery Orbital Replacement Units (ORUs) has been cycling since September 2006, these batteries are now approaching their end of useful life. In 2010, the ISS Program began the development of Lithium-Ion (Li-Ion) batteries to replace the Ni-H2 batteries. Now deployed, they are the largest Li-Ion batteries ever utilized for a human rated spacecraft.
{"title":"International Space Station Lithium-ion Batteries for Primary Electric Power System","authors":"Eugene Schwanbeck, P. Dalton","doi":"10.1109/espc.2019.8932009","DOIUrl":"https://doi.org/10.1109/espc.2019.8932009","url":null,"abstract":"The International Space Station (ISS) primary Electric Power System (EPS) was designed to utilize Nickel-Hydrogen (Ni-H2) batteries to store electrical energy. The electricity for the space station is generated by its solar arrays, which charge batteries during insolation for subsequent discharge during eclipse. The Ni-H2 batteries are designed to operate at a 35% depth of discharge (DOD) maximum during normal operation in a Low Earth Orbit. Since the oldest of the 48 Ni-H2 battery Orbital Replacement Units (ORUs) has been cycling since September 2006, these batteries are now approaching their end of useful life. In 2010, the ISS Program began the development of Lithium-Ion (Li-Ion) batteries to replace the Ni-H2 batteries. Now deployed, they are the largest Li-Ion batteries ever utilized for a human rated spacecraft.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"30 1","pages":"1-1"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"85991420","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.2019.8932093
E. Dawidowicz, Christiaan Beljaars, Frédéric Maloron, Daniel Bouric, Mikael Thibaudeau
This article presents the overall development philosophy followed to setup the PVA Factory 4.0, Thales Alenia Space (TAS) flagship for an Industry 4.0 production environment for the manufacturing and testing of Photo Voltaic Assemblies (PVA) in Belgium. Starting from a blank page, the process and means of this new facility were conceived and developed in a hardware-driven testing approach, relying on the extensive heritage of TAS for designing solar arrays and manufacturing of power electronics. Two main application cases have driven the development: (1) the heritage GEO PVA, which requires demonstrating equivalence to existing manufacturers solution in Fit-Form-Function. (2) “New Space” PVA with a requirement of high throughput, enabling a stronger design-for-manufacturing approach. This paper presents how we used a new way of assessing product quality inherited from other terrestrial industries, Advanced Product Quality Planning (APQP), to orient the development of the various process and means required to launch this new activity at TAS.
{"title":"PVA Factory 4.0: a hardware-driven approach to assess, develop and qualify Industry 4.0 processes and means for the manufacturing of Photo Voltaic Assemblies","authors":"E. Dawidowicz, Christiaan Beljaars, Frédéric Maloron, Daniel Bouric, Mikael Thibaudeau","doi":"10.1109/ESPC.2019.8932093","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932093","url":null,"abstract":"This article presents the overall development philosophy followed to setup the PVA Factory 4.0, Thales Alenia Space (TAS) flagship for an Industry 4.0 production environment for the manufacturing and testing of Photo Voltaic Assemblies (PVA) in Belgium. Starting from a blank page, the process and means of this new facility were conceived and developed in a hardware-driven testing approach, relying on the extensive heritage of TAS for designing solar arrays and manufacturing of power electronics. Two main application cases have driven the development: (1) the heritage GEO PVA, which requires demonstrating equivalence to existing manufacturers solution in Fit-Form-Function. (2) “New Space” PVA with a requirement of high throughput, enabling a stronger design-for-manufacturing approach. This paper presents how we used a new way of assessing product quality inherited from other terrestrial industries, Advanced Product Quality Planning (APQP), to orient the development of the various process and means required to launch this new activity at TAS.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"3 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":"91073923","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.2019.8932048
Pavlos Ramnalis, Spiridon Savvas, Alexandros Manoudis, L. Benetti, Luca Onida, L. Fontani, T. Misuri
The Microsatellite Electric Propulsion System (MEPS) program has been originated by the increasing need to provide a low cost and low power Electric Propulsion System (EPS) for small satellites (<300Kg). The propulsion system of MEPS consists of three main parts, the Thruster Units (TUs) composed of a Hall Effect Thruster (Rafael's CAM-200 or SITAEL's HT100) and a Cathode (Rafael's Heaterless Hollow Cathode RHHC), the Propellant Management and Tank Assembly (PMA/PTA) which performs the regulation of xenon mass flow rate from the tank to the TU inlet, and the Power Processing Unit (PPU) which provides the necessary power to drive the TUs and the PMA/PTA and implements the system control logic. The objective of this paper is to present the development status of MEPS PPU highlighting the design optimizations and simplifications that have been performed. Particular emphasis is aimed at the most indicative improvements and how all modifications contributed to the PPU budget in terms of number of components, mass, size and cost, without affecting system efficiency, performance and reliability. Aggregated results for PPU budget are thoroughly illustrated, by taking into account the overall optimizations and simplifications. The results are very promising and point to a reduction on overall number of components, mass, area and cost in the range of 15% - 33%, all very significant especially in space market.
{"title":"PPU Optimizations for a Low Power EPS","authors":"Pavlos Ramnalis, Spiridon Savvas, Alexandros Manoudis, L. Benetti, Luca Onida, L. Fontani, T. Misuri","doi":"10.1109/ESPC.2019.8932048","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932048","url":null,"abstract":"The Microsatellite Electric Propulsion System (MEPS) program has been originated by the increasing need to provide a low cost and low power Electric Propulsion System (EPS) for small satellites (<300Kg). The propulsion system of MEPS consists of three main parts, the Thruster Units (TUs) composed of a Hall Effect Thruster (Rafael's CAM-200 or SITAEL's HT100) and a Cathode (Rafael's Heaterless Hollow Cathode RHHC), the Propellant Management and Tank Assembly (PMA/PTA) which performs the regulation of xenon mass flow rate from the tank to the TU inlet, and the Power Processing Unit (PPU) which provides the necessary power to drive the TUs and the PMA/PTA and implements the system control logic. The objective of this paper is to present the development status of MEPS PPU highlighting the design optimizations and simplifications that have been performed. Particular emphasis is aimed at the most indicative improvements and how all modifications contributed to the PPU budget in terms of number of components, mass, size and cost, without affecting system efficiency, performance and reliability. Aggregated results for PPU budget are thoroughly illustrated, by taking into account the overall optimizations and simplifications. The results are very promising and point to a reduction on overall number of components, mass, area and cost in the range of 15% - 33%, all very significant especially in space market.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"39 8 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":"72968717","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.2019.8932086
A. Tambini, F. Antonini, A. De Luca, J. Szabó, H. Carbonnier, A. Bánfalvi, L. Csurgai-Horváth, Z. Váradi
The ESEO (European Student Earth Orbiter) spacecraft is a microsatellite platform launched on 3rd of December 2018, on board the Spaceflight's SSO-A (SmallSat Express), the dedicated rideshare mission from the Vandenberg Air Force Base in California (US). ESEO is part of ESA Academy's hands-on space programme designed to provide university students across Europe with the unique opportunity to gain significant practical experience in the design, development, launch and operations of a real space project. The Prime Industrial contractor, SITAEL, developed the satellite platform, performed the assembly integration and testing of the whole spacecraft, including the integration of the student-built payload and subsystems, and provided technical support to the student teams under ESA's coordination. The ESEO mission has a special value for the industry involved, since it validates in-orbit the SITAEL S-50 platform (50 kg including the payload), the smallest within the SITAEL products portfolio, representing a crucial milestone of the intensive work in designing, developing and manufacturing innovative multipurpose small satellites platforms. The Power System (PS) design has taken the advantage of a fruitful collaboration with the Budapest University of Technology and Economics (BME), who was in charge of the Power Distribution Unit (PDU), and with ESA as program coordinator who made available its experts. The PS design guidelines have been the reliability maximization in all platform modes and the single failure tolerance, with the overall cost reduction always in mind. Further, the reduced volume and size of this micro-platform represented an additional challenge to designers. The achievement of these objectives has been obtained thanks to the union of proven space solutions, adopted in many ESA missions, and the selection of industrial or military grade components with space heritage. After a brief overview of the ESEO mission, the focus will be moved to the PS architecture description, redundancies strategy and design approaches.
{"title":"ESEO Power System","authors":"A. Tambini, F. Antonini, A. De Luca, J. Szabó, H. Carbonnier, A. Bánfalvi, L. Csurgai-Horváth, Z. Váradi","doi":"10.1109/ESPC.2019.8932086","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932086","url":null,"abstract":"The ESEO (European Student Earth Orbiter) spacecraft is a microsatellite platform launched on 3rd of December 2018, on board the Spaceflight's SSO-A (SmallSat Express), the dedicated rideshare mission from the Vandenberg Air Force Base in California (US). ESEO is part of ESA Academy's hands-on space programme designed to provide university students across Europe with the unique opportunity to gain significant practical experience in the design, development, launch and operations of a real space project. The Prime Industrial contractor, SITAEL, developed the satellite platform, performed the assembly integration and testing of the whole spacecraft, including the integration of the student-built payload and subsystems, and provided technical support to the student teams under ESA's coordination. The ESEO mission has a special value for the industry involved, since it validates in-orbit the SITAEL S-50 platform (50 kg including the payload), the smallest within the SITAEL products portfolio, representing a crucial milestone of the intensive work in designing, developing and manufacturing innovative multipurpose small satellites platforms. The Power System (PS) design has taken the advantage of a fruitful collaboration with the Budapest University of Technology and Economics (BME), who was in charge of the Power Distribution Unit (PDU), and with ESA as program coordinator who made available its experts. The PS design guidelines have been the reliability maximization in all platform modes and the single failure tolerance, with the overall cost reduction always in mind. Further, the reduced volume and size of this micro-platform represented an additional challenge to designers. The achievement of these objectives has been obtained thanks to the union of proven space solutions, adopted in many ESA missions, and the selection of industrial or military grade components with space heritage. After a brief overview of the ESEO mission, the focus will be moved to the PS architecture description, redundancies strategy and design approaches.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"27 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":"81960700","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.2019.8932059
S. K. Bernard, O. Mansilla, L. Pearce, W. H. Newman, E. Thomson
This paper will go over the benefits and advantages of GaN over traditional silicon and summarize the Single Event Effects (SEE) testing that was done for Renesas' GaN FETs. This paper will also discuss the results of the SEE testing and what they mean with respect to a typical Geosynchronous Orbit (GEO) mission.
{"title":"Wide Bandgap Components for Space Applications","authors":"S. K. Bernard, O. Mansilla, L. Pearce, W. H. Newman, E. Thomson","doi":"10.1109/ESPC.2019.8932059","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932059","url":null,"abstract":"This paper will go over the benefits and advantages of GaN over traditional silicon and summarize the Single Event Effects (SEE) testing that was done for Renesas' GaN FETs. This paper will also discuss the results of the SEE testing and what they mean with respect to a typical Geosynchronous Orbit (GEO) mission.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"237 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":"80391870","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.2019.8932042
S. Lorenzen, L. Gregersen, M. Simpson
As electrical power propulsion units (PPU) have become a major part for the space industry the need for higher power components at higher voltages has increased. This digest is based on an European Space Agency (ESA) development contract: “Planar and encapsulated SMD inductive electronic component qualification”, contract number: “4000122089/17/ NL/CRS”. There are two design and development objectives of this project. First, high power high voltage (HPHV) components for the PPU and second being encapsulated inductive components. The project underwent four phases such as component specification, component design, production and verification testing. Firstly, a 5 kW case study of PPU technology was made to create a specification for the PPU inductive components. Thereafter, the electrical design was completed. This was followed by the production of the PPU components. The PPU components were manufactured and finalized by verification testing consisting of power burn-in, mechanical shock, vibration, and temperature loaded stress tests. The PPU components have been designed using the planar ferrite cores, which enables a high power component with a relatively low build height. The disadvantage of the planar core is the lack of bobbin, therefore aircoil winding technology has been utilized which gives a large design freedom. The transformer was designed and manufactured with a coil consisting of flat wire windings stacked on top of each other, while the inductor was designed and manufactured using copper foil windings. In order to develop encapsulated magnetics a collaboration with the company Sintex A/S was established. Sintex A/S specializes in making high precision custom shapes in metal and soft magnetic composite materials. In this collaboration, Sintex A/S is providing expertise and manufacturing of the ferrite component of the encapsulated inductor. Both the HPHV components and the encapsulated inductor have been designed, manufactured and verified by testing.
随着电力推进装置(PPU)成为航天工业的重要组成部分，对高电压、高功率元件的需求也在增加。本摘要基于欧洲航天局(ESA)的一项开发合同:“平面和封装SMD感应电子元件鉴定”，合同编号:“4000122089/17/ NL/CRS”。这个项目有两个设计和开发目标。首先是用于PPU的高功率高压(HPHV)组件，其次是封装的电感组件。该项目经历了组件规格、组件设计、生产和验证测试四个阶段。首先，对一个5kw的PPU技术案例进行了研究，以创建PPU电感元件的规范。此后，电气设计完成。接下来是PPU组件的生产。PPU组件的制造和最终确定通过验证测试，包括功率老化，机械冲击，振动和温度加载应力测试。PPU组件采用平面铁氧体铁芯设计，这使得组件具有相对较低的构建高度。平面铁芯的缺点是没有筒子，因此采用了气圈绕线技术，使设计自由度大。变压器的设计和制造是用一个由扁线绕组堆叠在一起的线圈组成的，而电感的设计和制造是用铜箔绕组。为了开发封装磁性材料，与Sintex a /S公司建立了合作关系。Sintex A/S专门从事金属和软磁复合材料的高精度定制形状。在此次合作中，Sintex A/S提供封装电感的铁氧体组件的专业知识和制造。HPHV组件和封装电感都经过了设计、制造和测试验证。
{"title":"Development of High Power, High Voltage Magnetic Components and Encapsulated Inductor for Power Propulsion Unit","authors":"S. Lorenzen, L. Gregersen, M. Simpson","doi":"10.1109/ESPC.2019.8932042","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932042","url":null,"abstract":"As electrical power propulsion units (PPU) have become a major part for the space industry the need for higher power components at higher voltages has increased. This digest is based on an European Space Agency (ESA) development contract: “Planar and encapsulated SMD inductive electronic component qualification”, contract number: “4000122089/17/ NL/CRS”. There are two design and development objectives of this project. First, high power high voltage (HPHV) components for the PPU and second being encapsulated inductive components. The project underwent four phases such as component specification, component design, production and verification testing. Firstly, a 5 kW case study of PPU technology was made to create a specification for the PPU inductive components. Thereafter, the electrical design was completed. This was followed by the production of the PPU components. The PPU components were manufactured and finalized by verification testing consisting of power burn-in, mechanical shock, vibration, and temperature loaded stress tests. The PPU components have been designed using the planar ferrite cores, which enables a high power component with a relatively low build height. The disadvantage of the planar core is the lack of bobbin, therefore aircoil winding technology has been utilized which gives a large design freedom. The transformer was designed and manufactured with a coil consisting of flat wire windings stacked on top of each other, while the inductor was designed and manufactured using copper foil windings. In order to develop encapsulated magnetics a collaboration with the company Sintex A/S was established. Sintex A/S specializes in making high precision custom shapes in metal and soft magnetic composite materials. In this collaboration, Sintex A/S is providing expertise and manufacturing of the ferrite component of the encapsulated inductor. Both the HPHV components and the encapsulated inductor have been designed, manufactured and verified by testing.","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":"75995038","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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