Technique of target selection and profiles of transfer trajectory for Chinese asteroid exploring mission are studied systemically. A complete set of approaches to selecting mission targets and designing the transfer trajectory is proposed. First, when selecting a target for mission, some factors regarded as the scientific motivations are discussed. Then, when analyzing the accessibility of targets, instead of the classical strategy, the multiple gravity-assist strategy is provided. The suitable and possible targets, taking into account scientific value and technically feasible, are obtained via selection and estimation. When designing the transfer trajectory for exploring asteroid mission, an approach to selecting gravity-assist celestial body is proposed. Finally, according to the mission constraints, the trajectory profile with 2-years ∆V-EGA for exploring asteroid is presented. Through analyzing the trajectory profile, unexpected result that the trajectory would pass by two main-belts asteroids is found. So, the original proposal is extended to the multiple flybys mission. It adds the scientific return for asteroid mission. exploring asteroid, target selection, multiple flybys, transfer trajectory Citation: Cui P Y, Qiao D, Cui H T, et al. Target selection and transfer trajectories design for exploring asteroid mission.
In this paper, a low-thrust, multi-revolution orbit transfer under the constraint of a complex switch function is investigated. First, the effect of the switch function, especially that of a switch function with no prior information, is analyzed. Then, by utilizing the concept of the Lyapunov feedback control law, the semi-analytical expressions of suboptimal thrust angles are derived, and a near-optimal solution could approach the optimal solution by adjusting the five weights in the Lyapunov function using sequential quadratic programming (SQP). In the novel method, except for optimization of the weight factors in the Lyapunov function, no iteration is contained in the process of design and optimization, so the method is rapid and has good convergence. This method also overcomes the drawbacks about convergence of traditional calculus of variation (COV). It is an effective method for the design of low-thrust, multi-revolution orbit transfer with no prior information switch functions.
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