Methodology of Autolanding Trajectory Design for Reusable Launch Vehicle

DOI

10.2991/icmmita-15.2015.257How to use a DOI?

Keywords

RLV; autolanding; trajectory design.

Abstract

A trajectory design methodology is developed for autolanding phase of RLV (Reusable Launch Vehicle) based on iterative correction algorithm in this paper. According to the inherent traits in phase of unpowered landing of RLV, geometric structure of trajectory and dynamic characteristics of the aircraft are studied in detail. And mathematical descriptions of the trajectory as well as the selection principle and calculation formula of feature parameters are given. Compared with the traditional design methods of trajectory, this methodology is simple and rapid. The simulation results also demonstrate the feasibility, effectiveness, and superiority of the algorithm.

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/).

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TY  - CONF
AU  - Shuai Huang
AU  - Ran Zhang
AU  - Hong Cai
AU  - Wenming Nie
PY  - 2015/11
DA  - 2015/11
TI  - Methodology of Autolanding Trajectory Design for Reusable Launch Vehicle
BT  - Proceedings of the 2015 3rd International Conference on Machinery, Materials and Information Technology Applications
PB  - Atlantis Press
SP  - 1388
EP  - 1394
SN  - 2352-538X
UR  - https://doi.org/10.2991/icmmita-15.2015.257
DO  - 10.2991/icmmita-15.2015.257
ID  - Huang2015/11
ER  -