Segmented optimization method for multi-circle orbital transfer of electric propulsion spacecraft under multi-perturbation earth shadow constraint

Abstract

The invention discloses a segmented optimization method for multi-circle orbital transfer of an electric propulsion spacecraft under the constraint of a multi-perturbation earth shadow, and belongs to the field of spacecraft orbit dynamics and control. According to the method, a small-thrust orbit optimal control model considering multi-perturbation and earth shadow constraint is established, a small-thrust orbit optimal control model considering J2 perturbation long-term influence is established, and after the electric propulsion thrust amplitude and the J2 perturbation long-term item are increased by the same multiple, the overall orbit transfer process is segmented, so that overall multi-circle orbit transfer is close to the optimal, and the overall orbit transfer efficiency is improved. The robustness of a multi-circle orbital transfer overall optimization process can be ensured, and according to the segmentation result and the established low-thrust orbit optimal control model considering the multi-perturbation and the earth shadow constraint, the low-thrust orbit optimal control problem considering the multi-perturbation and the earth shadow constraint in each segment is solved in sequence; the optimization of the multi-circle orbital transfer of the electric propulsion spacecraft under the constraint of the multi-perturbation earth shadow is realized. The method has the advantages of being accurate in optimization, high in robustness, high in reliability, easy and convenient to implement and the like.

Description

technical field [0001] The invention relates to a segmental optimization method for multi-circle orbit change of an electric propulsion spacecraft under the constraint of multi-perturbation ground shadow, in particular to the optimal control of the spacecraft's low-thrust orbit, and belongs to the field of spacecraft orbit dynamics and control. Background technique [0002] Due to its high specific impulse, electric propulsion has important application value in orbital maneuvering of spacecraft. The electric propulsion orbit change of spacecraft is more fuel-efficient than the traditional chemical propulsion orbit change, so the use of electric propulsion orbit change will bring huge economic benefits, but its thrust is small, so the number of orbit changes is large and the time is very long, which will optimize the orbit. It brings great difficulties, especially considering the various perturbation effects and ground shadow constraints in the actual orbit change. Literatur...

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Problems solved by technology

[0003] In order to solve the problem that electric propulsion spacecraft is difficult to optimize multi-turn orbit under multi-perturbation ground shadow constraints, resulting in high fuel consumption, the main purpose of the present invention is to provide a multi-turn electric propulsion spacecraft under multi-perturbation ground shadow constraints The segmented optimization method of orbit change, by establishing the optimal control model of low-thrust orbit considering multi-perturbation and ground shadow constraints, makes long-term multi-turn orbit change more in line with engineering reality, and establishes a small The optimal control model of the thrust orbit, after increasing the electric propulsion thrust amplitude and the J2 perturbation long-term term by the same multiple, using this model to obtain the corresponding optimal orbit change, according to the change rule of the orbit elements of the optimal orbit change The overall orbit change process is segmented, so that the overall multi-turn orbit change is close to the optimal, and the robustness of the overall optimization process of the multi-turn orbit change can be guaranteed, and then according to the segmentation results and the established multi-perturbation and shadow constraints The optimal control model of the low-thrust orbit, which solves the optimal control problem of the low-thrust orbit considering multi-perturbation and earth shadow constraints in each segment in turn, realizes the optimization of the multi-turn orbit change of the electric propulsion spacecraft under the multi-perturbation earth shadow constraint

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