Study on Model and Simulation of the Tilt Rotor Aircraft in Transition Mode

DOI

10.2991/ameii-15.2015.255How to use a DOI?

Keywords

tilt rotor aircraft; transition mode; dynamic model.

Abstract

In recent years, tilt rotor aircraft has been greatly developed because of its excellent performance. However, because of the complicacy in transition mode study on this aircraft is needed. In this paper a six degrees of freedom dynamic model of the tilt rotor aircraft was established, and PID controller was chosen when the aircraft in transition mode. Meanwhile, a defined S-function was used to solve the nonlinearity of the dynamic equations in real time and a simulation model is built in Matlab/Simulink. The results of simulation show the system is stable and provide a reference for analysis of tilt rotor aircraft dynamic and design of its flight control system.

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  - Laohu Yuan
AU  - Wenhao Zhang
AU  - Xin Wen
PY  - 2015/04
DA  - 2015/04
TI  - Study on Model and Simulation of the Tilt Rotor Aircraft in Transition Mode
BT  - Proceedings of the International Conference on Advances in Mechanical Engineering and Industrial Informatics
PB  - Atlantis Press
SP  - 1386
EP  - 1391
SN  - 2352-5401
UR  - https://doi.org/10.2991/ameii-15.2015.255
DO  - 10.2991/ameii-15.2015.255
ID  - Yuan2015/04
ER  -