Abstract
Flexible deployment mechanisms are widely used in the aerospace field. During the satellite antenna’s attitude adjustment and deployment process, vibration will greatly affect the accuracy of the satellite antenna profile after deployment. The finite element method (FEM) has the disadvantages of high calculation order, slow calculation speed and difficult optimization in the process of establishing the dynamic model of the flexible deployment mechanism. This paper uses the principle of the transfer matrix method to propose a calculation method for the natural frequency and vibration mode of a flexible deployment mechanism, which is used to calculate the vibration characteristics of a radial rib deployment antenna. Finally, its accuracy is verified by the finite element method (FEM).
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