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title大型宇宙機搭載用薄膜太陽電池の構造検討
Other TitleStructural consideration of thin film solar cell for large spacecraft
Author(jpn)相馬, 央令子; 田中, 孝治; 宮内, 雅彦; 横田, 力
Author(eng)Soma, Eriko; Tanaka, Koji; Miyauchi, Masahiko; Yokota, Riki
Author Affiliation(jpn)宇宙航空研究開発機構宇宙科学研究本部; 宇宙航空研究開発機構宇宙科学研究本部; 宇宙航空研究開発機構宇宙科学研究本部; 宇宙航空研究開発機構宇宙科学研究本部
Author Affiliation(eng)Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS); Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS); Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS); Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
Issue Date2009-06
PublisherInstitute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構宇宙科学研究本部
Publication titleSpace Energy Symposium
宇宙エネルギーシンポジウム
Volume28
Publication date2009-06
Languagejpn
eng
AbstractThe project for a spacecraft driven with hybrid propellant system, called solar powered sail, is now undergoing. The propellant system has two kinds of forces; one by solar photon from sun and another from high performance ion engine. The experiments of the hybrid propellant system and the very large thin film flexible power generation system are planned using a deployable ultra thin film solar sail of 50 m in diameter. The thin film solar batteries cover more than 10 % of the total sail area. This report describes the structural consideration and the space environmental evaluation of the thin film solar batteries for the solar powered sail called IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun), which is the small size demonstration project. In order to avoid the warpages of the thin film solar battery and to protect a surface of the solar battery, the three layer combination, polyimide film/thin film solar battery/the solar battery which is bonded upside down, was applied. This three layered battery was also glued on a polyimide film of 25 mm in thickness because it was necessary to obtain a high thermal emission rate of the battery. The three 220 x 320 mm sized batteries connected in series were utilized as a unit and 48 units installed on IKAROS. The total generated power was 360 W without any degradation due to ultra violet light. We confirmed the solar batteries could be controlled at the equilibrium temperature in space because it was in the working temperature range of the solar battery; 41.6 C with 1 Sun and 101.8 C with 2 Sun. The lifetime of the solar batteries at 100 C is now undergoing to assume the generation properties. The radiation test with electron and proton beams did not affect the generation properties, though the color of the protection layer was changed, resulting in the 20 % down of solar batteries in generation power. We keep performing the further evaluation to install the solar powered sail.
Description会議情報: 第28回宇宙エネルギーシンポジウム(2009年3月9日, 宇宙航空研究開発機構宇宙科学研究本部相模原キャンパス)
Meeting Information: The twenty-eight Space Energy Symposium (March 9, 2009. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara)
Document TypeConference Paper
JAXA Categoryシンポジウム・研究会
NCIDAN10324356
SHI-NOAA0064295004
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/20406


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