Abstract: Abstract：The configuration and deployment of noncoplanar solar arrays are introduced briefly. Because of dynamic coupling effects, the deployment process of the noncoplanar solar arrays affects the attitude of the spacecraft. The angular momentum equation is analyzed and the joint path is parameterized by a cosine function. Then, the objective function is defined according to the variation of the spacecraft attitude. At last, genetic algorithm is adopted to search the optimal parameters which are used to obtain a path that when the noncoplanar configuration solar arrays deploy according to this path, its affect to the spacecraft will reduce to a relatively very small range. At last, one kind of noncoplanar configuration solar arrays is given, and the effectiveness of above method is verified by simulation results.

Key words: Keywords：noncoplanar configuration solar arrays, joint parameterization, genetic algorithm, path optimization