Control-structure integrated multiobjective design for flexible spacecraft using MOEA/D
Control-structure integrated multiobjective design for flexible spacecraft using MOEA/D
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DOI：
10.1007/s00158-014-1053-7
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发表时间：
2014-02
影响因子：
3.9
通讯作者：
Zhiwei Feng;Qingbin Zhang;Qiangang Tang;Tao Yang;Jian-Qquan Ge
中科院分区：
文献类型：
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作者：
Zhiwei Feng;Qingbin Zhang;Qiangang Tang;Tao Yang;Jian-Qquan Ge
提出了一种柔性航天器控制结构一体化设计的多目标优化方法，以减小总质量，优化控制性能。利用拉格朗日原理和假设模态法推导了柔性航天器的运动方程。设计变量为柔性结构的结构尺寸和控制器参数。目标和约束由结构和控制性能指标推导而来。目标包括总质量、控制成本和振动能量，约束条件包括闭环系统的稳定性、沉降时间、超调量、最大控制和尖端的最大振动位移。提出了一种改进的基于分解的多目标进化算法（MOEA/D），并采用我们提出的混合约束处理方法进行优化。以具有对称安装柔性附件的航天器为例，进行了控制结构优化设计。仿真结果表明，柔性航天器控制结构一体化设计的多目标优化方法是可行和有效的，可以对结构和控制设计进行改进。
This paper proposes a multiobjective optimization method for the control-structure integrated design of flexible spacecraft to reduce the total mass and optimize the control performance. The equations of motion for flexible spacecraft are derived from the Lagrange’s principle and the assumed modes method. The design variables are the structural dimensions of the flexible structure and controller parameters. The objectives and constraints are derived from structure and control performance indexes. The objectives include total mass, control cost, and vibrational energy, and the constraints include the stability of the closed-loop system, settling time, overshoot, maximum control, and maximum vibrational displacement of the tip. A modified version of the multiobjective evolutionary algorithm based on decomposition (MOEA/D) with our proposed hybrid constraint handling method is proposed for optimization. As a case study, it has been applied to a spacecraft with symmetrically installed flexible appendages to find optimal tradeoffs in control-structure design. The simulation results show that the multiobjective optimization method for the control-structure integrated design of flexible spacecraft is feasible and effective, and could give an improvement of structural and control designs.