Multi-rotor Attitude Active Disturbance Rejection Control Method and System Based on Axis Angle Vector
A multi-rotor and attitude technology, applied in the general control system, control/regulation system, adaptive control, etc., can solve the problems of loss of control accuracy, and achieve improved adaptability, improved response speed and control accuracy, and strong adaptability Effect
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Embodiment 1
[0104] see figure 1 , figure 1 The flow block diagram of the multi-rotor attitude active disturbance rejection control method based on the axis angle vector provided by Embodiment 1 of the present invention is applied to a multi-rotor UAV, and the multi-rotor UAV includes three axes for flight, The method mainly includes the following steps:
[0105] S10. Based on the pre-obtained target attitude angle of the body and the current attitude angle of the body, acquire the target angular velocity of the three axes;
[0106] What needs to be explained here is that the target attitude angle of the multi-rotor is , , ; Indicates the roll in the target attitude angle, Indicates the pitch in the target attitude angle, Indicates the heading in the target attitude angle;
[0107] The current attitude angle of the body is , , , Indicates the roll in the current attitude angle of the airframe, Indicates the pitch in the current attitude angle of the airframe, Indi...
Embodiment 2
[0165] see figure 2 , this embodiment provides a multi-rotor attitude active disturbance rejection control system based on the axis angle vector, including:
[0166] The acquisition module is used to obtain the target angular velocity of the three axes based on the target attitude angle of the body and the current attitude angle of the body; it is also used for:
[0167] S11. Putting the target attitude angle of the airframe and the current attitude angle of the airframe into the Euler angle conversion quaternion formula to obtain the quaternion of the target attitude angle and the quaternion of the current attitude angle.
[0168] S12. Obtain the quaternion of the target attitude according to the quaternion of the target attitude angle;
[0169] S13. Based on the quaternion of the current attitude angle and the quaternion of the target attitude, the quaternion of the attitude error is obtained, and the vector of the target angular velocity is calculated.
[0170] In step S...
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