The Attitude Decoupling Control Of The Flying Wing UAV (IEEE CGNCC)

被引：0

作者：

Li, Jiguang ^{[1
]}

Chen, Xin ^{[1
]}

Li, Zhen ^{[1
]}

机构：

[1] Nanjing Univ Aeronaut & Astronaut, Sch Automat, Nanjing 210016, Jiangsu, Peoples R China

来源：

2016 IEEE CHINESE GUIDANCE, NAVIGATION AND CONTROL CONFERENCE (CGNCC) | 2016年

关键词：

Flying wing UAV; Attitude control; Nonlinear decoupling; Differential geometry method; Trajectory Tracking; NONLINEAR-SYSTEMS; LINEARIZATION; FEEDBACK;

D O I：

暂无

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

Because of the special aerodynamic layout of the flying wing UAV, a strong coupling effect will be generated among its respective channel. However, this thesis, different from the traditional methods, applies the differential geometry method to the decoupling control design of the UAV. Besides, because the difficulty of the differential geometric linearity method's linear condition cannot be solved yet, nominal output function method is put forward in the thesis. And the results of the emulation show that the attitude decoupling control of the flying wing UAV, based on the differential geometry method, can meet the requirements of the program.

引用

页码：357 / 362

页数：6

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