The Travelling Space Salesman Problem
- Paper number
IAC-21,A6,IP,19,x65000
- Author
Mr. Deepak Gaur, India, Amity School of Engineering
- Year
2021
- Abstract
Mitigation of orbital debris begins with a sound understanding of relative motion in space. The relative motion of spacecraft in close-proximity is described by the Hill-Clohessy-Wilshire (HCW) equations. Accurately predicting target debris rendezvous trajectories can be quite complex and challenging. The research presented primarily focuses on the close-proximity operations of a proposed spacecraft intended for debris capture. The main objective of this research is to determine the most optimal (minimum $\Delta$V) or fuel-economical trajectory, required for orbital debris mitigation, for such spacecraft present in close-proximity of 5 debris pieces in an orbit. The problem in essence is a traveling salesman problem but in space.
- Abstract document
- Manuscript document
(absent)