Abstract: To overcome the problem that spacecraft module identification mainly relies on experience and qualitative methods,a general numerical optimization for module identification method was constructed. Function units based numerical design structure matrix (DSM) was obtained by using functional decomposition method, relativity evaluation criteria and coevolution mechanism between design matrix and DSM. A general DSM based optimization model was constructed which conformed to axiomatic design axioms. A genetic-simulated annealing algorithm was used to construct a module identification method which could co-optimize the mode and the number of module identification. Finally, an evaluation method for different optimization targets was put forward. Simulation results show that the proposed method can divide a spacecraft into several modules with high cohesion degree and low coupling degree.

Key words: Design structure matrix, Genetic algorithm, Simulated annealing algorithm, Module identification, Spacecraft