Deformation and Buckling Analysis of CFRP Bistable Deployable Boom for Application to Solar Array Paddle Support Members on Lunar Pressurized Rover

Paper number

IAC-25,C2,2,7,x99766

Author

Dr. Sho Kajihara, University of Tokyo, Japan

Coauthor

Mr. Shouya Yamashita, The University of TOKYO, Graduate school, Japan

Coauthor

Mr. Yuta Sunaga, Department of Engineering, The University of Tokyo, Japan

Coauthor

Dr. Tomohiro Yokozeki, University of Tokyo, Japan

Coauthor

Ms. Aoi Izumi, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Tomohiro Oya, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

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

Coauthor

Mr. Yoshihiko Katsuyama, Japan

Year

2025

Abstract

A pressurized rover is being considered for lunar exploration and utilization. To enable long-distance cruise, a thin-film solar cell array paddle (SAP) will be mounted on the rover and deployed to secure the solar energy. As one idea of the support structures and deployment mechanisms, an open-section thin-walled cylindrical boom made of Carbon Fiber Reinforced Plastics (CFRP), which has lightweight, high rigidity, and high storage capacity, is considered.
To be able to explore a large area of the lunar, it is necessary to increase the deployable angle of the SAP so that it can be deployed on the steep slope craters and at various latitudes from the polar region to the equator region. Therefore, to clarify the structural characteristics of the CFRP boom, the deformation and buckling analysis of a single boom using a finite element analysis model was performed. Point load considering the gravity load of the SAP was applied to the CFRP boom and nonlinear static analysis using incremental load control method was conducted. Various loading directions were examined, assuming the SAP will be tilted at various angles due to the latitude and slope. The results of deformation and buckling loads were validated by experimental tests, showing that the bistable boom is not symmetry due to its open cross section and bending-torsional coupling can be easily caused. Thus, the buckling load and buckling mode depend on the loading angle to the orientation of the boom open-section. 
In addition, we designed and created a 5 m size and 10 m size SAP model using multiple CFRP bistable booms using the developed finite element analysis model. Considering the magnitude of gravitational acceleration on the moon and on the ground, a dummy sheet weighing 1/6 of the solar cell sheet was attached to a stiff bar, and the bar was mounted on the multiple bistable booms. Both models demonstrated that the SAP can be deployed vertically by driving the booms. In the durability test, in which the 10 meter size model was deployed and then tilted, a tilt of 30 degrees in the out-of-plane direction and 10 degrees in the in-plane direction was achieved, as predicted by the finite element analysis.

Abstract document

IAC-25,C2,2,7,x99766.brief.pdf

Manuscript document

IAC-25,C2,2,7,x99766.pdf (🔒 authorized access only).

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