超小型衛星のデオービットのためのインフレータブル膜面構造の提案

摘要

Recently developing nano satellites is quite active in universities as well as the space agencies and the industries. Therehas been growing fears that the space debri will increase because nano satellites has long orbit life even though theirmission life is short compared with large satellites. Thus the de-orbit system is required to the nano satellites. In thispaper, the de-orbit system using an inflatable membrane structure (ITM) is proposed, which achieves the orbit decent forthe de-orbit by using the aerodynamic drag effect. The engineering model of the ITM is fabricated, and the result of thevacuum testing and the deployment testing under the gravity is presented, which shows the availability of the proposedITM in space use. The proposed de-orbit system is available for typical nano satellite less than 10kg weight.