微小型傾轉(zhuǎn)旋翼飛行器直升機(jī)模態(tài)辨識(shí)建模研究.pdf

1、南京航空航天大學(xué)碩士學(xué)位論文微小型傾轉(zhuǎn)旋翼飛行器直升機(jī)模態(tài)辨識(shí)建模研究姓名：趙濱申請(qǐng)學(xué)位級(jí)別：碩士專業(yè)：導(dǎo)航、制導(dǎo)與控制指導(dǎo)教師：曹云峰2011-03微小型傾轉(zhuǎn)旋翼飛行器直升機(jī)模態(tài)辨識(shí)建模研究 iiAbstract Aiming at a certain type of micro-small tiltrotor aircraft designed by Nanjing University of Aeronautics, aircra

2、ft modeling method based on system identification is studied in this paper. Work of the paper mainly includes 4 parts: Firstly, the 6 DOF airframe motion equations of micro tiltrotor aircraft in helicopter mode are built

3、, and the angle-velocity transfer function model is determined through the small disturbance line-arization and transverse/longitudinal decoupling, which is a reference for model structure identifica-tion. Secondly, Desi

4、gn the flight bracket for ground simulation and data acquisition device for mi-cro-small tiltrotor aircraft,which are used to collect angle-velocity data of micro-small tiltrotor air-craft. Then, the identification test

5、is designed,including design of identification input signal, choice of Sampling frequency and length of data,identification test data pretreatment. At last,based on test data and the class of angle-velocity model,the opt

6、imization of angle-velocity model is obtained through the method of model structure identification; the model parameters are identified separately by nonlinear and separable least-squar method, the model validation shows

7、 the method gets good angle-velocity model, amend the deficiency of tradition method. Keywords: Tiltrotor aircraft, system identification, least-square method, nonlinear and separable least-squar , identification test,