Abstract:

To design a long time stable satellite formation for saving fuel is very important work, so an optimization method to design a long time stable satellite formation under various perturbations is derived. Firstly the constraints between relative positions and velocities in Hill frame according to the specific mission are de-veloped by using the Hill’s equation. Secondly using the free relative positions or velocities as optimization variables, the optimization cost function is the sum of the relative mean orbit elements drift velocities under J2 perturbation.

Key words: spacecraft , design,  , satellite , formation,  , formation , optimization , design,  , genetic , algorithm,  , relative , orbit , elements