JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
title極低温環境における炭素繊維強化エポキシ樹脂積層板の基礎的力学特性 その1
Other TitleFundamental mechanical properties of carbon fiber reinforced epoxy laminates at cryogenic temperature: 1st report
Author(jpn)熊澤, 寿; 齋藤, 智広; 藤丸, 瑛里; 小川, 武史
Author(eng)Kumazawa, Hisashi; Saito, Tomohiro; Fujimaru, Eri; Ogawa, Takeshi
Author Affiliation(jpn)宇宙航空研究開発機構航空技術部門構造・複合材技術研究ユニット(JAXA); 青山学院大学; 青山学院大学; 青山学院大学
Author Affiliation(eng)Structures and Advanced Composite Research Unit, Aeronautical Technology Directorate, Japan Aerospace Exploration Agency (JAXA); Aoyama Gakuin University; Aoyama Gakuin University; Aoyama Gakuin University
Issue Date2018-11-29
Publisher宇宙航空研究開発機構(JAXA)
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構研究開発資料
JAXA Research and Development Memorandum
VolumeJAXA-RM-18-003
Start page1
End page28
Publication date2018-11-29
Languagejpn
eng
Abstractロケットなどの高性能化のための機体重量軽減に, 極低温液体推進剤タンクの複合材料化が効果的である. 本研究では, 炭素繊維エポキシ複合材料を材料とし, 極低温におけるCFRPクロスプライ積層板の弾性率, 破断強度, 内部損傷進展を冷凍機式極低温試験システムを用いて取得した. 極低温にて取得した試験結果は, 常温の結果と比較し, 液化推進剤がもたらす極低温が複合材料の基礎的力学特性に及ぼす影響を明らかにした. 極低温での複合材料積層板の力学的特性はその結果, 弾性率は, 極低温においてわずかに弾性率が上昇にとどまるが, 複合材料積層板の損傷発生応力と破断強度は常温に比べ極低温において顕著に低くなることが明らかとなった. また, 冷凍機式極低温試験について, ヒータを用いた温度調節手法, 極低温でのひずみ測定手法についても本報告にまとめた.
Incorporation of composite materials in cryogenic propellant tanks can potentially aid in developing high performance rockets. This study thus evaluates various aspects of carbon fiber reinforced epoxy laminates, such as elastic constants, failure strength, and development of internal damages, at cryogenic temperatures by employing a cryogenic testing system comprising a cryostat and a refrigerator. Test results obtained at cryogenic temperatures were compared with those at the room temperature for studying the effect of liquefied propellant's cryogenic temperature on the fundamental mechanical properties of composite materials. The obtained results indicate that compared to the room temperature, the damage initiation stress and failure strength of the composite laminates at cryogenic temperatures can decrease significantly, whereas the stiffness of the composite laminates at cryogenic temperatures can increase marginally. Furthermore, this study report also describes a method for temperature control through a heater system, and a method for stress measurement at cryogenic temperatures using the cryogenic testing system with the help of a refrigerator.
Description形態: カラー図版あり
Physical characteristics: Original contains color illustrations
Document TypeTechnical Report
JAXA Category研究開発資料
NASA Subject CategoryComposite Materials
ISSN(online)2433-2224
SHI-NOAA1830009000
Report NoJAXA-RM-18-003
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/900682


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