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论文:2012,Vol:30,Issue(5):663-667 |
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引用本文： |
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张沥, 姚磊江, 王景深, 李斌, 童小燕. 超轻质太阳能电池嵌入式结构设计[J]. 西北工业大学 |
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Zhang Li, Yao Leijiang, Wang Jingshen, Li Bin, Tong Xiaoyan. Exploring Design of an Ultra-Light Photovoltaic Cell Embedded Structure[J]. Northwestern polytechnical university |
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| 超轻质太阳能电池嵌入式结构设计 |
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| 张沥1,2, 姚磊江1, 王景深1,2, 李斌1,2, 童小燕1 |
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1. 西北工业大学 无人机特种技术重点实验室, 陕西 西安 710072;
2. 西北工业大学 航空学院, 陕西 西安 710072 |
| 摘要: |
| 文章提出一种用于太阳能飞机的超轻质太阳能电池嵌入式蒙皮结构,以硬质聚氨酯泡沫作为机翼上蒙皮,太阳能电池片胶接在蒙皮上。对具有多块太阳能电池的嵌入式结构进行有限元分析,随着粘接点数的增加,结构的应力和位移均减小,当粘接点数增加到16点以后,应力和位移变化不大。通过增加硬质聚氨酯泡沫的厚度或利用玻璃纤维带进行局部加强均可改善结构的刚度,但后者效果更为明显。通过优选玻璃纤维带的参数,嵌入式结构的刚度有了极大提高。 |
| 关键词:
太阳能飞机
太阳能电池
硬质聚氨酯泡沫蒙皮
嵌入式结构
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| Exploring Design of an Ultra-Light Photovoltaic Cell Embedded Structure |
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| Zhang Li1,2, Yao Leijiang1, Wang Jingshen1,2, Li Bin1,2, Tong Xiaoyan1 |
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1. Laboratory of Science and Technology on UAV, Northwestern Polytechnical University, Xi'an 710072, China;
2. College of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China |
| Abstract: |
| Sections 1 through 3 of the full paper explain our exploration mentioned in the title, which we believehas succeeded in providing some useful results for conceptual design.Their core consists of:"To improve the struc-tural efficiency of solar powered aircraft, an ultra-light solar cell embedded structure was designed, in which solarcells were adhesively bonded to the upper wing skin made of rigid polyurethane foam (RPUF).Three-point ben-ding tests were carried out for both raw solar cells and cells encapsulated by epoxy.Then the stress and deformationof the embedded structure under air pressure was analyzed by FEM(finite element method) software.Local rein-forcement by glass fiber ribbons was used to improve the stiffness characteristic of the embedded structure.And thesize of the glass fiber ribbon was optimized according to the FEM results."The simulation results, presented in Ta-bles 4 through 6, and their analysis show preliminarily that: (1) the encapsulated solar cells have better flexibilityand are more suitable for embedded structures; (2) both the stress and deformation of the embedded structure de-crease with increasing number of bonded points between cell and skin until it reaches 16; (3) the reinforced struc-ture has remarkable stiffness improvement compared with the original design scheme; it decreases the structural de-formation by 93% with only 3% weight increment.Section 4 gives three preliminary conclusions with more detaileddescriptions. |
| Key words:
aircraft
computer simulation
computer software
efficiency
experiments
finite element method
photovoltaic cells
schematic diagrams
stiffness
structural analysis
structural design
structural op-timization
wings;RPUF (rigid polyurethane foam) skin
embedded structure
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| 收稿日期: 2011-11-24
修回日期:
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| DOI: |
| 通讯作者:
Email： |
| 作者简介: 张沥(1985-)，西北工业大学硕士研究生，主要从事飞行器结构设计研究。
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| 相关功能 |
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| 作者相关文章 |
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| 张沥 在本刊中的所有文章 |
| 姚磊江 在本刊中的所有文章 |
| 王景深 在本刊中的所有文章 |
| 李斌 在本刊中的所有文章 |
| 童小燕 在本刊中的所有文章 |
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参考文献: |
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[1] Andr�Noth.Design of Solar Powered Airplanes for Continuous Flight: Ph.D.Thesis.Z黵ich: ETH,2008
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[3] Boucher R J.History of Solar Flight.AIAA-1984-1429
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[5] Frulla G,Cestino E.Design,Manufacturing and Testing of a HALE-UAV Structural Demonstrator.Composite Structures,2008,83: 143-153
[6] Noth A,Engel W,Siegwart R.Design of an Ultra-Lightweight Autonomous Solar Airplane for Continuous Flight.Field andService Robotics,2006,441-452
[7] Carey P G,Aceves R C,Colella N J,et al.A Solar Module Fabrication Process for HALE Solar Electric UAVS.IEEE Photo-voltaic Specialists Conference,1994,2: 1963-1969
[8] Ron Laurenzo.Soaring on a Solar Impulse.Aerospace America,2009: 32-36
[9] Annabel Rapinett.Zephyr: A High Altitude Long Endurance Unmanned Air Vehicle.Guildford: University of Surrey,2009
[10] Rion J,Leterrier Y,et al.Ultra-Light Asymmetric Photovoltaic Sandwich Structures.Composites,2009,1-7 |
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1．成珂, 王忠伟, 周洲.太阳能飞机工作条件对太阳能电池性能的影响[J]. 西北工业大学, 2012,30(4): 535-540 |
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