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Multiple SSO Space Debris Flyby Trajectory Design Based on Cislunar Orbit
- 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