基于多柔体动力学的飞行器多目标优化设计

Research on Multi-objective Optimization of Spacecraft Based on Flexible Multibody Systems Dynamics

研究了柔性航天器总体设计中基于结构与姿态控制的多目标优化问题。利用拉格朗日方程建立了刚柔耦合系统动力学模型,提出以附件质量和微分矩阵最大实特征值为目标函数的多目标优化问题;采用非支配排序进化求解算法(NSGA-II),对某柔性航天器进行了多目标优化分析设计;最优决策为具有一定规律性的空间曲线,该优化结果对柔性卫星的总体分析设计具有一定的指导意义。

This investigation is concerned with multiobjective optimization of flexible spacecraft design system based on structure and control objective. The mathematical model which consists of rigid platform and flexible appendages is derived by Lagrangian approach, and the two conflicting objective functions are considered for minimization： weight of the flexible appendages and maximum real part of eigenvalues of spacecraft systems. The NSGA- II approach is used for a numerical example, and the nondominated solutions set in the design space （Pareto optimal） have some interesting properties, which can be useful for flexible spacecraft.