| Issue |
MATEC Web Conf.
Volume 179, 2018
2018 2nd International Conference on Mechanical, Material and Aerospace Engineering (2MAE 2018)
|
|
|---|---|---|
| Article Number | 01015 | |
| Number of page(s) | 10 | |
| Section | Mechanical | |
| DOI | https://doi.org/10.1051/matecconf/201817901015 | |
| Published online | 26 July 2018 | |
A Specific Sliding Mode Control for Autopilot Design of Bank-to-Turn Missiles
China Academy of Launch Vehicle Technology Tactical Weapons Division
a Corresponding author: hzphtyy@163.com
This paper studies the BTT missile's sliding mode flight controller. Firstly, the control model is established according to dynamic inverse method and the general dynamic equation of the missile flying in the atmosphere. Then, the sliding mode controller is designed and it adopts the time-varying sliding mode surface, the self-defined reaching law and the adaptive control parameters. Finally, three sets of simulation are carried out to prove the flight controller designed in this paper for BTT missile can follow the guidance instructions and meet operational needs.
© The Authors, published by EDP Sciences 2018
This is an Open Access article distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
Current usage metrics show cumulative count of Article Views (full-text article views including HTML views, PDF and ePub downloads, according to the available data) and Abstracts Views on Vision4Press platform.
Data correspond to usage on the plateform after 2015. The current usage metrics is available 48-96 hours after online publication and is updated daily on week days.
Initial download of the metrics may take a while.