@techreport{oai:jaxa.repo.nii.ac.jp:00041230,
 author = {角田, 義秋 and 三本木, 茂夫 and 下河, 利行 and 濱口, 泰正 and 山本, 昌孝 and 三津間, 秀彦 and Kakuta, Yoshiaki and Sanbongi, Shigeo and Shimokawa, Toshiyuki and Hamaguchi, Yasumasa and Yamamoto, Masataka and Mitsuma, Hidehiko},
 month = {Nov},
 note = {本研究の目的は、小型の無人有翼宇宙往還機HOPE(H-2 Orbiting Plane)の主構造用候補材料として選択したカーボン/ポリイミド(T800H/PMR-15)複合材料の単層材特性データの取得と積層材強度を評価することである。室温(RT)および高温(300度C)下で、単層材の基本特性と擬似等方積層材(無孔、有孔)の引張や圧縮強度などを調べるために、種々の静強度試験を行った。単層材の基本特性には、引張強度、圧縮強度、層間せん断強度、破断ひずみ、弾性係数およびポアソン比などが含まれる。積層材に対する破壊強度の解析は、得られた単層材の基本特性をもとにして、無孔試験片の場合に最大応力則とTsai-Wu則、有孔試験片の場合にPoint Stress Criterion法とAverage Stress Criterion法をそれぞれ用いて予測した。これらの解析結果について、試験結果と比較し、検討した。, The objective of this study is to evaluate the material properties and laminate strength of a T800H/PMR-15 carbon/polyimide composite, which is selected as a candidate material for the primary structures of the unmanned small space vehicle HOPE (H-2 Orbiting Plane). Various static tests were conducted to obtain data on the material properties and the laminate strengths for the unnotched and circular-hole-notched specimens of a quasi-isotropic laminate. These tests were conducted at room temperature and a high temperature (300 C). The material property data include tension, compression, and short beam shear strengths, failure strain, elastic modulus, and Poisson's ratio. The first ply failure and the last ply failure strengths of the unnotched laminate are computed using the material property data obtained and the maximum stress and Tsai-Wu failure criteria. The strength of the laminate with a circular hole is predicted on the basis of the point stress and the average stress criteria. These analytical results are compared with the test results and discussed., 資料番号: AA0004261000, レポート番号: NAL TR-1254},
 title = {カーボン/ポリイミド(T800H/PMR-15)複合材料の室温および300度Cにおける静強度評価},
 year = {1994}
}