高超声速飞行器再入飞行段需要反推力器进行辅助姿态控制，控制力矩向气动舵面和反推力器的合理分配是再入飞行控制的一个关键问题。文章考虑燃料消耗、舵面偏转状态和误差三要素，将控制分配视为一个多目标优化的问题，提出了一种改进的多目标遗传算法。引入一种改进的模拟退火算法提高局部搜索能力；为保证种群的多样性，提出了一种改进的小生境技术，将距离参数设置为动态的函数，并引入种群的繁殖代数。分别设计燃料消耗、舵面偏转和误差的代价系数、约束条件等，获得多目标Pareto解集，并基于模糊逻辑，在最优解集中寻获最优解。通过仿真验证了方法的有效性。%The reentry of the hypersonic vehicle requires reaction thruster to assist attitude control. How to allocate the control moment to aerodynamic surfaces and reaction thruster properly is a key problem. The fuel consumption, the surface deflection and the error are considered in this paper. An improved multi-objective optimization genetic algorithm is proposed when regarding control allocation as a multi-objective optimization problem. A modified simu-lated annealing algorithm is introduced. An improved niche selection technology is put forward to maintain the popu-lation diversity. The distance parameter is set as a dynamic function and generation quantity of the population is in-troduced at the same time. The cost coefficient and constraint are designed respectively to obtain Pareto optimal so-lutions set. On the basis of fuzzy logic, the optimal solution is selected. Finally effectiveness is verified by simula-tion.
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