The dynamic modeling and calculation of a large deployable space antenna truss are studied considering of gravity gradient. Based on the absolute nodal coordinate formulation method and the abso-lute nodal coordinate formulation reference node method, the rigid-flexible coupling dynamic model of the deployable structure is established. The energy-momentum conserving time integrator for calculating the dynamic equations is constructed by using discrete directional derivative. The orbital-attitude-de-formation coupling dynamic response of the large deployable space antenna with multiple modules is ob-tained. The presented method is verified by comparing the results with those of the classic example and the commercial software ADAMS.
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