The objective of the present study is to derive a dominant equation of our previously proposed two-dimensional-deployable linked panel structure in space, which expresses the relationship between the deployment motion and input moment by an actuator. This article presents a derivation sequence of the dominant equation by the general dynamic modeling of square panels and demonstrates its numerical calculation examples. This numerical experimentation may be useful for designing an actuator considering deployment time in space, especially for realization of a future Solar Power Satellite which consists of square solar panels.
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