2019 European Space Power Conference (ESPC)最新文献_第7页

Evaluation of the reliability of space solar cells by means of Sequential Accelerated Life Tests 用顺序加速寿命试验方法评价空间太阳能电池的可靠性

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8931981

M. Vázquez, N. Núñez, C. Algora

引用次数: 1

Simulation and Experimental Study of High-Power Power Conditioning Unit 大功率功率调节装置的仿真与实验研究

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8931998

W. Lu, Bao-Xing Wang, Chunyang Zhao, Hongtao Chen, Kai Wang, Taifeng Zhang

引用次数: 0

Improved EMI noise performance by the reduced input ripple of the Satellite converter 通过减小卫星变换器的输入纹波，提高了电磁干扰噪声的性能

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932057

Nayoung Lee, Tae-Yoon Kim, Ju-Young Lee, Sang-Kyoo Han, Tae-Jin Chung, J. Choi

引用次数: 2

Li-S Cells for Space Applications (LISSA) 空间应用锂- s电池(LISSA)

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8931976

D. Mourembles, B. Buergler, L. Gajewski, Ashley Cooke, C. Barchasz

引用次数: 3

A Power Control and Distribution Unit for Small Satellite Platforms 一种用于小型卫星平台的功率控制与分配装置

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932036

A. Gabriele, V. Centonze, D. Lobifaro, C. Attanasio, G. Maiullari, A. Costa

{"title":"A Power Control and Distribution Unit for Small Satellite Platforms","authors":"A. Gabriele, V. Centonze, D. Lobifaro, C. Attanasio, G. Maiullari, A. Costa","doi":"10.1109/ESPC.2019.8932036","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932036","url":null,"abstract":"This paper presents a “Medium Power” compact, light and low cost PCDU (Power Control and Distribution Unit) which has been designed as a modular and configurable equipment for Low Earth Orbit (LEO) missions with a maximum power capability of 1500 W. The PCDU supports a maximum of 4 independent power inputs (up to 75 V), and provides a 28 V unregulated power bus. Maximum Power Point Tracking (MPPT) is independently performed on each input; MPPT relies on buck regulators with direct drive capability, operating in ‘N+1’ cold redundancy. The latter feature, together with the full cold redundancy of the Control Unit inside the PCDU, makes the device fully compliant with the Single Point of Failure free requirement. Moreover, the passive balancing managed by the PCDU guarantees the correct distribution of the cells charge, and contributes in improving the battery reliability. The unregulated bus is protected and distributed through nominal plus redundant LCL/RLCL and fuse protected lines for heaters and HDRMs. A cross-strapped architecture allows to control both nominal and redundant protected outputs from the nominal or redundant section of the unit, at the same time maximizing the PCDU availability. The PCDU, which is fully monitored, controlled and configured through the N+R CAN bus, can be easily tailored for various missions since its functionalities are segregated in different and specific stackable electronic boards (no backplane is used), and FPGAs are programmable. Finally, to balance the equipment radiation hardness and reliability figure versus costs, the PCDU has been designed with a mixed approach: COTS based supported by Sitael heritage [1] [2] and scheduled radiation tests, and the usage of MIL/Space qualified components for critical functions.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"64 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":"86711376","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: 3

uHETsat small Power System for high demanding payloads 小型电力系统适用于高要求的有效载荷

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932005

A. Tambini, F. Antonini, N. Melega, G. Mariotti, V. Centonze, A. Gabriele

{"title":"uHETsat small Power System for high demanding payloads","authors":"A. Tambini, F. Antonini, N. Melega, G. Mariotti, V. Centonze, A. Gabriele","doi":"10.1109/ESPC.2019.8932005","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932005","url":null,"abstract":"Coming right after the launch of the ESEO spacecraft, uHETsat will be the second mission based on the use of SITAEL S-50/75 microsatellite platform for IOV/IOD purposes. In this case the subject of the In Orbit Validation will be SITAEL HT100 Hall Effect Thruster (HET) -one of the smallest of its kind-that for the first time will be embarked and operated onboard a small platform. Starting from its predecessor, the spacecraft has undergone a series of updates and upgrades necessary to comply with the new set of mission requirements. Although some of the AODCS equipment has changed compared to ESEO [1], most of the efforts in the adaptation of the Power System (PS) were spent to handle the power required by the propulsion subsystem for its proper functioning. The PS re-design included a new set of deployable Solar Arrays (SA), a revised Power Management Board (PMB) and Power Distribution Unit (PDU), and a larger battery that will allow the mission to accomplish its goals: 2000 ignitions and 1000 hours of firing for the propulsion subsystem. Main objectives for this re-design activity have been the improvement of the overall reliability through a meticulous review of the components selection, at the same time preserving the single failure tolerance and the low cost approach (hybrid automatic-manual) in terms of manufacturing. The uHETsat PS is currently being accepted for flight and all its components have been tested as EQM showing the capability of the system to support both platform and payload operations. After a brief overview of the uHETsat mission, the focus will be moved to the PS architecture description, redundancies strategy and the single point failure free design approach.","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":"89545241","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

Qualification of low cost triple junction GaInP/GaAs/Ge solar cell assemblies with external bypass diode connected by insulated cell P/diode N interconnects 用绝缘电池P/二极管N互连连接外旁路二极管的低成本三结GaInP/GaAs/Ge太阳能电池组件的鉴定

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932072

G. Gabetta, Davide Cospito, R. Campesato, M. Casale, E. F. Lisbona

引用次数: 1

AM0 Irradiance Conditions for Electrical Performance Measurements of Triple Junction Cells at Extreme Low and High Temperatures 极低温和高温下三结电池电性能测量的AM0辐照度条件

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932014

G. Jüngst, A. Gras, C. Baur

{"title":"AM0 Irradiance Conditions for Electrical Performance Measurements of Triple Junction Cells at Extreme Low and High Temperatures","authors":"G. Jüngst, A. Gras, C. Baur","doi":"10.1109/ESPC.2019.8932014","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932014","url":null,"abstract":"For accurate electric performance measurements of multi-junction solar cells at AM0 illumination conditions under simulated light, the most important parameter to be controlled is the effective irradiance of their individual sub-cells. The AM0 equivalent irradiance conditions once established on a solar simulator at standard cell temperature, i.e. 25°C, might not be fulfilled at certain temperatures when performing electrical measurements on triple junction (3J) GaInP2/ InGaAs/Ge space cells in a wide cell temperature range from −175°C to +140°C, and therefore might entail erroneous electrical cell parameter results. In a study on different solar simulators at INTA-Spasolab the effective irradiance under such AM0 illumination conditions are determined for 3J solar cells at different temperatures. The solar simulator spectra are analyzed by determining those spectral zones affecting the most to required AM0 illumination conditions at low and high temperatures. This analysis demonstrates that the influences of the respective solar simulator spectrum are more associated with specific wavelength zones rather than the solar simulator classification in fixed wavelength bins.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"71 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":"82865224","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

Development and Qualification of the Eurostar Neo Solar Array “欧洲之星”新太阳能电池阵列的研制与鉴定

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932003

C. Zimmermann, F. Schlerka, C. Nömayr, Rainer Müller, H. Nesswetter, A. Übner, Marco Gruber, Christian Grünwald

{"title":"Development and Qualification of the Eurostar Neo Solar Array","authors":"C. Zimmermann, F. Schlerka, C. Nömayr, Rainer Müller, H. Nesswetter, A. Übner, Marco Gruber, Christian Grünwald","doi":"10.1109/ESPC.2019.8932003","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932003","url":null,"abstract":"Airbus is currently developing the Eurostar Neo telecommunication platform, supported by ESA in the frame of the ARTES 14 program. It is capable to support payloads up to 25 kW, which required major advances in the thermal as well as the electrical subsystem. The first telecommunication satellites based on the Eurostar Neo platform will be the Eutelsat Hotbird satellites 13F and G, to be launched in 2021. One of the central newly developed subsystems for Eurostar Neo is a solar array that is capable to deliver ≈ 50% more power in the same volume and with the same weight. This is achieved through a hybrid array concept, which combines a conventional rigid panel array with lightweight, semi-rigid lateral panels. This central element of the new array features a wealth of new technologies, ranging from a charge dissipative substrate and C-spring hinges with electrical functionality to new ion-erosion resistant Al interconnects and 4-junction solar cells with 28.5% efficiency at 1×1015 1MeV e-/cm2. The design of the semi-rigid photovoltaic assembly (PVA) is outlined in detail, as well as the results of key qualification tests on component and on PVA level. In contrast to classical arrays, PVA level testing required not only thermal cycle testing, but also the verification of new loads like sine-vibration testing under vacuum. Finally, the potential for further evolution of this array concept is discussed.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"22 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":"78969414","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: 1

Magnetic tests and analysis of JUICE solar array JUICE太阳能电池阵的磁性测试与分析

2019 European Space Power Conference (ESPC) Pub Date : 2019-09-01 DOI: 10.1109/ESPC.2019.8932027

M. Kroon, E. Bongers, K. Bubeck

引用次数: 1