立方体展開構造物の熱・構造の検討

抄録

Flexible deployment structure system are used for various spacecraft from the viewpoint of cost reduction of transportation by rocket. In this paper, the stress due to thermal strain was evaluated for the deployable cubic structure proposed in this study. First, we investigated the on-orbit temperature of the deployable cubic structure in the sun-synchronous LEO, and found that the temperature ranged from -90℃ to 98℃. Secondly, based on this thermal analysis result, the tensile test of the pillar member at -80℃ to 80℃ was performed, and the Young's modulus was changed by about 25%. Thirdly, thermal structure analysis was performed using on-orbit temperature analysis and tensile test results. The stress due to thermal strain was the largest at the eyelet part of the hinge joint. Although the stress of any member does not exceed the proof stress, it was found that there is little margin for eyelets.