Abstract: With the increasing of multi-satellite network launch missions and increasing multiple window launch missions, a union design method of trajectory and guidance is proposed in this paper, which can adapt for multiple target orbits. In this innovate method, one theory trajectory for one target orbit is designed, making a hypothesis which the satellite’ sentry point position is maintained unchanging for other target orbits, and then the terminal guidance parameters with requirements of other orbits are generated, and lastly the target orbits are reached by iterative guidance. The simulation results indicate that relative to the traditional method, this method can greatly reduce the calculation amount while making little impact on carry capacity, and has strong adaptation for multiple target orbit missions. This method can also adapt for temporary slightly target orbit adjustment.