Study of Design and Optimization of Low-Thrust Transfer Trajectory with Planetary Aerogravity Assist

In this paper, the design and optimization problem of low-thrust transfer trajectory with planetary aerogravity assist is studied. To avoid numerical sensitivity, the equinoctial elements are utilized to describe spacecraft motion. The matching condition for design of aerogravity assist trajectory is presented through analyzing the characteristics of aerogravity assist. Then we have discussed the problem formulation of AGA trajectory optimization, and presented a hybrid optimization method, which combines direct with indirect method, and utilizes the costate to parameterize the thrust steering angles time histories. Finally, Taking rendezvous with a Ceres asteroid as an example, the preliminary scheme of transfer trajectory with Mars aerogravity assist is design and optimized by using this approach