为解决传统航天器飞轮力矩分配策略会导致力矩分配不均而影响飞轮寿命的问题,建立了力矩分配问题的数学模型,对基于输出裕度的批量飞轮力矩优化分配策略进行了研究。首先,在考虑飞轮最大输出力矩受限情况下,推导出能量最优分配策略,以保证飞轮组的输出力矩方向不变;其次,为处理传统能量最优分配策略中可能出现的某个飞轮力矩过大而导致其寿命缩短的问题,提出了输出裕度概念,并建立了多目标优化模型,将多目标优化分配转为权系数的选择;再次,用权系数方法描述批量飞轮的性质,推导出一种系统能量和输出裕度双目标优化的分配策略。基于力矩输出裕度进行优化,可在优化航天器能量消耗的同时均衡各飞轮的输出力矩,节省能量并延长飞轮使用寿命,从而提高了航天器可靠性。针对八斜装飞轮的仿真结果验证了所提方法的有效性。 In order to solve the problem that the flywheel torque distribution strategy of traditional spacecraft will lead to the uneven torque distribution and affect the life of the flywheel, a mathematical model of torque distribution problem is established and the optimization strategy of batch flywheel torque distribution based on output margin is studied. First of all, considering the limitation of the maximum output torque of the flywheel, the optimal energy allocation strategy is deduced to ensure that the direction of the output torque of the flywheel group is unchanged. Secondly, to deal with a flywheel moment that may occur in the traditional optimal energy allocation strategy The concept of output margin is proposed and a multi-objective optimization model is established to convert the multi-objective optimization distribution to the choice of weight coefficient. Thirdly, the weight coefficient method is used to describe the properties of batch flywheel, A distribution strategy for bi-objective optimization of system energy and output margin is presented. Optimization based on torque output margin optimizes the spacecraft’s energy consumption while balancing the output torque of each flywheel, saving energy and extending the life of the flywheel, thereby improving the reliability of the spacecraft. The simulation results for the eight oblique flywheel verify the effectiveness of the proposed method.