对航天器模块划分主要依靠经验和定性方法的问题,构建了一种通用的模块划分数值优化方法。利用功能分解方法、相关性评价准则、设计矩阵与设计结构矩阵(DesignStructure Matrix,DSM)同步演化的机制获得了基于功能元的数值DSM;基于DSM构建了遵循公理化设计原理的通用优化模型;利用遗传-模拟退火算法获得了可对模块划分方式及数目进行同步优化的模块划分方法;给出了不同于优化目标的评价方法。仿真结果表明,该方法可将航天器划分为一系列内聚度高、耦合度低的模块。 The spacecraft module is mainly divided by experience and qualitative methods, and a universal numerical optimization method of module partition is constructed. The functional DSM was obtained based on the functional decomposition method, the correlation evaluation criteria, the design matrix and the design structure matrix (DSM), and the universal optimization model based on axiomatic design was constructed based on DSM. Genetic-simulated annealing algorithm can be divided into modules and the number of modules can be synchronized optimization method; given different from the optimization objectives of the evaluation method. The simulation results show that this method can divide the spacecraft into a series of modules with high cohesion and low coupling degree.