National Aerospace Laboratory Airframe Division
National Aerospace Laboratory Structural Mechanics Division
National Aerospace Laboratory Airframe Division
National Aerospace Laboratory Airframe Division
National Space Development Agency of Japan
National Space Development Agency of Japan
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.
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
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