Abstract

A variable stiffness (VS) structure of the grid panels is designed for solar wing sandwich plates on satellite. The vibration resistance performances of the VS plate, constant stiffness (CS) plate are evaluated. First, a novel modal analysis model is proposed to investigate the relationship between the fundamental frequency and fiber angles. The fiber direction of grid panel is optimized with the constant curvature arc curves. Then, the equivalent model and the boundary conditions of the sandwich plates under the actual working conditions are built. The modal fundamental frequencies of the VS plate are improved by 31.18% after the optimization. Furthermore, a five-segment method for trajectory planning is proposed. Finally, a variable stiffness grid panel made by robotic fiber placement is realized, which verifies the accuracy of the manufacturing method and simulations.

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