Dynamics Modeling and Simulation of Spacecraft Solar Array

Flexible multibody system dynamics and Kane’s equation are introduced to establish the dynamic model of a spacecraft solar array.The panels are regarded as flexible bodies and modal analysis is made.Finite element method and modal condensation technique are adopted to discretize the panels. A model of solar array with four panels is analyzed as an illustrative example,all the four panels are considered as flexible bodies.Geometric modeling and deploying simulation of the array are carried out with ANSYS and ADAMS software. Simulation results such as the panels’deformation,angular displacement and angular velocity are got and the results are useful for the design and test of spacecraft solar array.