Optimization design of synchronization mechanism for deployment of spacecraft appendages

Dimensional synthesis of the synchronization mechanism for deployment of spacecraft appendages was carried out according to the requirements of the deployment motion. A set of independent variables were selected for deduction of the mathematical model of the mechanism that satisfies the position requirements of the panels in both stowed and deployed states, and the parametric deployment dynamics simulation model was developed for prediction of deployment kinematic and dynamic performances. An optimization model with the objective to minimize the maximum driving torque during the entire deployment process and the constraint to meet the stowed volume envelope requirements was then built. With the nonlinearity characteristic and discontinuous design space, the optimization problem was solved by using the simulated annealing algorithm. The optimal mechanism was finally obtained, which could reduce the maximum driving torque and improves the dynamic performance of the mechanism.