Affiliation:
1. Henan Polytechnic University
Abstract
In order to design the four rotor aircraft attitude control system, take the hover state or low speed flight state as a benchmark, firstly, divide the aircraft model into linear motion model and the angular motion model and model it separately, the nonlinear mathematical model of aircraft can be obtained. And then use the small disturbance linearization principle to linear mathematical model for a simplified model. After substituting into the previous experimental data, the mathematical model which controller design needs is got.
Publisher
Trans Tech Publications, Ltd.
Reference5 articles.
1. Wang Junsheng, Ma Hongxu Cai Wenlan, tax waves, NieBoWen. Method of unmanned helicopter control small four rotor based on ADRC [J]. Journal of Projectiles Rockets Missiles and Guidance. 2008 (3) : 31 to 40.
2. Hu Yuqun. Study on some dynamic problems of micro air vehicle[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, (2002).
3. HongSenTao Jin Zhihui, li chi keung. Four rotor aircraft modeling and postural stability analysis [J]. Electronic and Electro-optical Systems 2006 (5) : 91-94.
4. J. F. GUERRERO CASTELLANOS, A. HABLY, N. MARCHAND, S. LESECQ. Bounded attitude stabilization: Application on four-rotor helicopter[J]. 2007 IEEE Intemational Conference on Robotics and Automation. 2007: 730-735.
5. L. Derafa, T. MADani, A. Benallegue. Dynamic Modelling and Experimental Identification of Four Rotors Helicopter Permanents[J]. IEEE Intematonal conference on Industrial Technology. 2006: 1834-1839.