The Control Strategy of Soft Landing Trajectory of Lunar Craft

DOI

10.2991/asei-15.2015.261How to use a DOI?

Keywords

Centroid-based Dynamic Model; Numerical Iteration Method; Parameterize Method.

Abstract

The purpose of this paper is study soft landing strategies of the lunar craft during landing on the moon. On the basis of the fixed selenocenter coordinate system, we set up a braking coordinate system in the main reduction stage. Build the centroid-based dynamic differential equation model to describe the relation among different variables and for the target of least fuel consumption. Use the parameterize method to keep complex unknown variables approximate for the power function. Try the numerical iteration method for solving the model. When it comes to an approximate optimal goal, we finally get result that main reduction stage take 585 seconds, and angle of thrust direction show increased over time, and thrust decreases with time, and the rate of reduction increases with time gradually.

Copyright

© 2015, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

Download article (PDF)

TY  - CONF
AU  - Zhiyong Lin
PY  - 2015/05
DA  - 2015/05
TI  - The Control Strategy of Soft Landing Trajectory of Lunar Craft
BT  - Proceedings of the 2015 International conference on Applied Science and Engineering Innovation
PB  - Atlantis Press
SP  - 1327
EP  - 1332
SN  - 2352-5401
UR  - https://doi.org/10.2991/asei-15.2015.261
DO  - 10.2991/asei-15.2015.261
ID  - Lin2015/05
ER  -