Reentry vehicle attitude control method based on self-adaptive gain disturbance compensation

A reentry vehicle, adaptive gain technology, applied in the direction of attitude control, non-electric variable control, control/regulation system, etc.

Pending Publication Date: 2021-02-12
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Abstract
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AI Technical Summary

Problems solved by technology

[0003] The technology of the present invention solves the problem: Aiming at the attitude control problem of the re-entry aircraft in a complex flight environment, fully considering the model uncertainty and the influence of various external disturbances, a re-entry aircraft attitude control based on adaptive gain disturbance compensation is proposed method to improve attitude control accuracy and anti-disturbance ability

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  • Reentry vehicle attitude control method based on self-adaptive gain disturbance compensation
  • Reentry vehicle attitude control method based on self-adaptive gain disturbance compensation
  • Reentry vehicle attitude control method based on self-adaptive gain disturbance compensation

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Embodiment Construction

[0053] like figure 1 As shown, the present invention proposes a reentry vehicle attitude control method based on adaptive gain disturbance compensation, comprising the following steps:

[0054] (1) Reentry kinematics and dynamics modeling

[0055] The reentry kinematics and dynamics of the reentry vehicle are established as follows:

[0056]

[0057] where θ=[α,β,μ] T , α, β, μ denote attack angle, sideslip angle and roll angle respectively; ω=[ω x ,ω y ,ω z ] T , ω x ,ω y ,ω z Represents the three-channel attitude angular velocity; B represents the control matrix, u represents the control input vector; d represents the disturbance torque, ΔJ represents the moment of inertia error matrix; the expressions of the matrices R, J, and Ω are:

[0058]

[0059]

[0060]

[0061] Among them, J x , J y , J z are the principal moments of inertia of the three channels, J xy , J xz , J yz represent the inertial products between the two channels, respectively.

[...

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Abstract

The invention discloses a reentry vehicle attitude control method based on self-adaptive gain disturbance compensation. The reentry vehicle attitude control method comprises the steps: step 1, establishing a control-oriented reentry flight kinematics and dynamics model of a reentry vehicle; step 2, establishing a fixed-time convergence disturbance compensation observer, and observing the state anddisturbance items of the reentry vehicle; and step 3, designing an integral sliding mode controller, introducing an observer disturbance observation item into the integral sliding mode controller, and performing self-adaptive adjustment on the control gain by adopting a double-layer self-adaptive gain strategy. The novel fixed-time convergence disturbance compensation observer disclosed by the invention can ensure that the observation error is quickly converged to zero within the fixed time, has good noise suppression capability, and greatly improves the anti-interference capability of an aircraft.

Description

technical field [0001] The invention relates to an attitude control method of a reentry aircraft based on adaptive gain disturbance compensation, and belongs to the technical field of guidance and control. Background technique [0002] With the development of modern technology, the military value and civilian value of reentry vehicles are becoming increasingly prominent. The reentry vehicle performs various tasks and the flight environment is complex, which makes the reentry attitude control problem have the characteristics of multivariable, fast time-varying, strong coupling, strong nonlinearity and parameter uncertainty, which greatly increases the difficulty of control system design. In recent years, scholars at home and abroad have carried out in-depth research on the problem of reentry attitude control. The commonly used control system design methods mainly include adaptive control, active disturbance rejection control, robust control, and sliding mode control. However,...

Claims

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Application Information

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IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0808G05D1/101Y02T90/00
Inventor 孙光张旭辉李永远陈海鹏黄育秋程奇峰刘焱飞郑雄刘丙利郝宇星郭晶姚星合康磊晶赵大海
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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