Origami-based Membrane Storage and Deployment Technology for De-orbiting Satellites

Paper number

IAC-13,B4,6A,4,x19838

Author

Prof. Hiraku Sakamoto, Tokyo Institute of Technology, Japan

Coauthor

Prof. Hiroshi Furuya, Tokyo Institute of Technology, Japan

Coauthor

Mr. Yasutaka Satou, Tokyo Institute of Technology, Japan

Coauthor

Prof. M.C. Natori, Waseda University, Japan

Coauthor

Mr. Akihito Watanabe, Sakase Adtech Co., Ltd., Japan

Coauthor

Mr. Nobuyoshi Kawabata, Sakase Adtech, Co., Ltd., Japan

Coauthor

Mr. Ryoji Sakai, Sakase Adtech, Co., Ltd., Japan

Coauthor

Dr. Nobukatsu Okuizumi, ISAS/JAXA, Japan

Coauthor

Dr. Osamu Mori, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Dr. Yoji Shirasawa, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Moto Takai, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Nobuhisa Katsumata, Waseda University, Japan

Coauthor

Dr. Ayako Torisaska, Aoyama Gakuin University, Japan

Coauthor

Prof. Ryu Funase, University of Tokyo, Japan

Year

2013

Abstract

This paper presents the innovative structural concept to deploy a membrane for de-orbiting small satellites. Based on the concept, our team is currently developing a component to deploy a 4.5m-size square membrane for a 100 kg-class small satellite to be launched in 2016. The significance of the concept, the details of a preliminary component design, and some results of tests using prototype models are reported. 
   In order to satisfy the 25-year rule, various de-orbiting methods have been proposed and some of them have been demonstrated in orbit. One prevailing approach for small satellites is to deploy a membrane using deployable booms made of convex tapes (carpenter tapes). This kind of design can make deployment mechanisms simple because the deployable booms themselves provide deployment force for both membrane and booms. However, the problem is that convex booms are often not stiff enough to prevent buckling during and after the deployment. The situation is made worse by the fact that conventional membrane folding patterns restrict the membrane to be connected only at the booms' tip, which causes the booms' buckling. In addition, conventional deployment mechanisms for convex booms often use violent deployment, which may cause the membrane to be torn. 
   In order to solve the abovementioned problems, this paper describes the membrane-deployment component that has three distinct features. First, an innovative membrane folding pattern, based on Japanese traditional Origami (the art of paper folding) concept, enables the membrane and the booms connected at multiple points along the boom length. This significantly relaxes the loading condition for the booms. Second, a new type of bi-convex boom has been invented that has much higher bending stiffness than conventional convex booms. And finally, the proposed step-wise deployment mechanisms realize the controlled deployment, which has less impact on the satellites attitude. The component is currently at the prototyping phase and has been tested on the ground.

Abstract document

IAC-13,B4,6A,4,x19838.brief.pdf

Manuscript document

IAC-13,B4,6A,4,x19838.pdf (🔒 authorized access only).

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