Journal of Projectiles, Rockets, Missiles and Guidance >
The Attitude Decoupling Control of the Flying Wing UAVBased on the Differential Geometry Method
Received date: 2017-07-30
Online published: 2025-05-28
With the special aerodynamic layout, the flying wing has a strong coupling effect between the channels, and decoupling control is a hot issue in its research. Firstly, the decoupling control design of the two common methods in the linear decoupling control of unmanned aerial vehicle is introduced. Secondly, because the system affine model is difficult to satisfy the linearization condition of the differential geometric linearization, the method of constructing nominal output function is put forward. Finally, the simulation results show that the attitude decoupling control of flying wing unmanned aerial vehicle based on the differential geometry method can meet the engineering requirements.
QU Gaomin , LI Jiguang . The Attitude Decoupling Control of the Flying Wing UAVBased on the Differential Geometry Method[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2018 , 38(2) : 116 -122 . DOI: 10.15892/j.cnki.djzdxb.2018.02.026
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