Multiple SSO Space Debris Flyby Trajectory Design Based on Cislunar Orbit-Reference-Cited by-同舟云学术

Multiple SSO Space Debris Flyby Trajectory Design Based on Cislunar Orbit

Published:2024-03-16 Issue:3 Volume:10 Page:145
ISSN:2218-1997
Container-title:Universe
language:en
Short-container-title:Universe

Author:

Zhang Siyang¹²,Wang Shuquan¹²^ORCID

Affiliation:

1. Technology and Engineering Center for Space Utilization, Chinese Academy of Sciences, Beijing 100094, China

2. University of Chinese Academy of Sciences, Beijing 101408, China

Abstract

This paper investigates the trajectory design problem in the scenario of a multiple Sun-synchronous Orbit (SSO) space debris flyby mission from a DRO space station. At first, the characteristics of non-planar transfer from DRO to SSO in the Earth–Moon system are analyzed. The methods of large-scale ergodicity and pruning are utilized to investigate single-impulse and two-impulse DRO–Earth transfers. Using a powered lunar flyby, the two-impulse DRO–Earth transfer is able to fly by SSO debris while satisfying the requirements of the mission. After the local optimization, the optimal result of two-impulse DRO–Earth transfer and flyby is obtained. A multi-objective evolutionary algorithm is used to design the Pareto-optimal trajectories of multiple flybys. The semi-analytical optimization method is developed to provide the estimations of the transfer parameters in order to reduce the computations caused by the evolutionary algorithm. Simulations show that transferring from the 3:2 resonant DRO to a near-coplanar flyby of a SSO target debris using a powered lunar gravity assist needs a 0.47 km/s velocity increment. The mission’s total velocity increment is 1.39 km/s, and the total transfer time is 2.23 years.

Funder

Strategic Priority Research Program of the Chinese Academy of Sciences

Lab funding of the Key Laboratory of Space Utilization, Chinese Academy of Sciences

Publisher

MDPI AG

Link

https://www.mdpi.com/2218-1997/10/3/145/pdf

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