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Aircraft rolling channel attitude control method based on sliding mode active disturbance rejection composite control

A composite control and attitude control technology, which is applied in the field of aircraft rolling channel attitude control and aircraft rolling channel attitude control, can solve the problems that PID control cannot meet the control requirements, and achieve strong robustness

Inactive Publication Date: 2020-10-16
SHANGHAI AEROSPACE CONTROL TECH INST
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AI Technical Summary

Problems solved by technology

[0002] Under the premise of continuously improving the technical indicators of aircraft attitude control, the traditional single PID control can no longer meet the control requirements.

Method used

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  • Aircraft rolling channel attitude control method based on sliding mode active disturbance rejection composite control
  • Aircraft rolling channel attitude control method based on sliding mode active disturbance rejection composite control
  • Aircraft rolling channel attitude control method based on sliding mode active disturbance rejection composite control

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Embodiment Construction

[0018] Attached below figure 1 , figure 2 , a specific implementation of the aircraft rolling channel attitude control method based on the sliding mode active disturbance rejection compound control of the method of the present invention is described in detail:

[0019] 1. Using the coefficient freezing method to linearize the mathematical model of the projectile body, the mathematical model of the rolling channel is obtained as:

[0020]

[0021] Among them, γ is the roll angle of the aircraft; w x is the roll angular velocity of the aircraft; c 1 ,c 3 is the aerodynamic parameters of the aircraft, δ x is the aileron deflection angle of the aircraft.

[0022] 2. Use a nonlinear tracking differentiator to reasonably extract the differential signal input by the system:

[0023]

[0024] Among them, the x in the formula 1 Input signal to the vehicle roll channel used for tracking¶ d , x 2 is the approximate differential signal of the input signal of the aircraft r...

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Abstract

The invention discloses an aircraft rolling channel attitude control method based on sliding mode active disturbance rejection composite control, which comprises the following steps of (1) linearizinga projectile mathematical model by using a coefficient freezing method under a small disturbance hypothesis according to an aircraft motion equation to obtain a linearized mathematical model of a rolling channel, (2) arranging a transition process by adopting a nonlinear tracking differentiator, and reasonably extracting a differential signal input by the system, (3) designing a rolling channel attitude control law by adopting a sliding mode variable structure control method according to the linearized mathematical model, and (4) on the basis of the sliding mode variable structure controller,adding an extended state observer to estimate the uncertainty of the system and the sum of external interference in real time, and performing compensation control on the observed external interference. The sliding mode-active disturbance rejection composite control method is adopted to control the attitude of the aircraft rolling channel, has the advantages of being fast in response and high in control precision, and has a good effect in the aspects of attitude instruction tracking, interference resistance and the like.

Description

technical field [0001] The invention belongs to the field of aircraft flight control, and relates to an aircraft rolling channel attitude control method based on sliding mode active disturbance rejection composite control, which is suitable for the aircraft rolling channel attitude control. Background technique [0002] Under the premise that the technical indicators of aircraft attitude control are constantly improving, the traditional single PID control can no longer meet the control requirements. With the development of modern control theory, adopting more effective aircraft attitude control method has become an important topic of aircraft attitude control system. [0003] The essence of sliding mode variable structure control is a special kind of nonlinear control, which is manifested as discontinuity of control. The characteristic of this control strategy is that the feedback control structure continuously changes purposefully in a sudden way during the dynamic process,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCG05D1/0825
Inventor 仲科伟张晓峰叶赛仙彭一洋夏斌郑子元陈亮
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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