航天器附件联动展开机构优化设计

根据航天器附件展开运动功能要求,对联动展开机构进行了尺度综合,确立了一组独立的设计参数,推导了满足收拢和展开状态下基板位置要求的联动展开机构数学模型,并建立了参数化的机构展开动力学仿真模型,以对附件展开运动功能及动力学特性进行分析和验证,从而实现了机构的参数化设计与分析.在此基础上,以展开全程所需的最大驱动力矩最小化为目标,以满足收拢状态整体结构尺寸包络为约束条件,建立了联动展开机构优化模型,根据该优化问题的非线性特征以及设计空间的不连续性,采用模拟退火算法进行优化求解,最终得到了机构的最优尺寸,从而达到了降低展开驱动力矩、改善机构动力学性能的目的.

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.