| 摘要 |
PROBLEM TO BE SOLVED: To obtain a composite material honeycomb panel and a composite material skin 4 which have a function for reducing thermal stress caused by the difference between linear expansion coefficients of different materials generated in relation to a temperature variation on the orbit of a satellite. SOLUTION: A division part is formed in the composite material skin 1 of the honeycomb panel, and a material having rigidity lower than that of a composite material and ductility is arranged in the clearance. When tension is applied to the skin 1, the lower rigidity material shares in a load with the skin 1. When compression, shear, or flexure is applied, the skin 1 crushes the lower rigidity material to be contacted to transmit the load. By using a shape- memory alloy 2 as the lower rigidity material, shape restoration force by temperature is used. COPYRIGHT: (C)2004,JPO
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