Back to Search Start Over

Multiple SSO Space Debris Flyby Trajectory Design Based on Cislunar Orbit

Authors :
Siyang Zhang
Shuquan Wang
Source :
Universe, Vol 10, Iss 3, p 145 (2024)
Publication Year :
2024
Publisher :
MDPI AG, 2024.

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.

Details

Language :
English
ISSN :
22181997
Volume :
10
Issue :
3
Database :
Directory of Open Access Journals
Journal :
Universe
Publication Type :
Academic Journal
Accession number :
edsdoj.7c820f416e9f4e58820eced88e3212a4
Document Type :
article
Full Text :
https://doi.org/10.3390/universe10030145