2019 European Space Power Conference (ESPC)最新文献_第3页

High-Altitude Space Solar Cell Calibration on Small Balloons 高空空间小型气球太阳能电池校准

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 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

引用次数: 0

Implementation of double insulation at satellite level: an approach 卫星级双重绝缘的实现:一种方法

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932082

Mario Buffardo, E. Scione, Catalano Toni Fabio, Carlani Daniele, Ruà Emanuele Giovanni

引用次数: 1

Testing of Thermal Runaway Tolerant Battery Designs Utilizing High Energy Density 18650 Lithium Ion Cells 利用高能量密度18650锂离子电池的耐热失控电池设计测试

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932071

K. Adams, B. Cardwell, Joshua Fedders

{"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}

引用次数: 0

Effect of the cyclic freeze-thaw exposure on the performance of PEM fuel cells 循环冻融暴露对PEM燃料电池性能的影响

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932015

Stanislav Gorelkov, S. Palecki, A. Heinzel

引用次数: 0

International Space Station Lithium-ion Batteries for Primary Electric Power System 国际空间站一次电力系统用锂离子电池

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/espc.2019.8932009

Eugene Schwanbeck, P. Dalton

引用次数: 4

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 PVA工厂4.0:一种硬件驱动的方法，用于评估、开发和鉴定光伏组件制造的工业4.0流程和方法

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932093

E. Dawidowicz, Christiaan Beljaars, Frédéric Maloron, Daniel Bouric, Mikael Thibaudeau

{"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}

引用次数: 0

PPU Optimizations for a Low Power EPS 低功耗EPS的PPU优化

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932048

Pavlos Ramnalis, Spiridon Savvas, Alexandros Manoudis, L. Benetti, Luca Onida, L. Fontani, T. Misuri

{"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}

引用次数: 0

ESEO Power System ESEO电力系统

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932086

A. Tambini, F. Antonini, A. De Luca, J. Szabó, H. Carbonnier, A. Bánfalvi, L. Csurgai-Horváth, Z. Váradi

{"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}

引用次数: 0

Wide Bandgap Components for Space Applications 用于空间应用的宽带隙元件

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932059

S. K. Bernard, O. Mansilla, L. Pearce, W. H. Newman, E. Thomson

引用次数: 0

Development of High Power, High Voltage Magnetic Components and Encapsulated Inductor for Power Propulsion Unit 动力推进装置大功率高压磁性元件及封装电感器的研制

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932042

S. Lorenzen, L. Gregersen, M. Simpson

{"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}

引用次数: 0