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A deep-space exploration mission with low-thrust propulsion to rendezvouswith multiple asteroids is investigated. Indirect methods, based on the optimalcontrol theory, are implemented to optimize the fuel consumption. Theapplication of indirect methods for optimizing low-thrust trajectories betweentwo asteroids is briefly given. An effective method is proposed to provideinitial guesses for transfers between close near-circular near-coplanar orbits.The conditions for optimality of a multi-asteroid rendezvous mission aredetermined. The intuitive method of splitting the trajectories into severallegs that are solved sequentially is applied first. Then the results arepatched together by a scaling method to provide a tentative guess foroptimizing the whole trajectory. Numerical examples of optimizing three probeexploration sequences that contain a dozen asteroids each demonstrate thevalidity and efficiency of these methods.

Systematic Low-Thrust Trajectory Optimization for a Multi-Rendezvous Mission using Adjoint Scaling