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Time-varying feedback finite-time stabilization method of control limited spacecraft rendezvous control system

A control system, time-varying feedback technology, applied in general control systems, control/regulation systems, adaptive control, etc., can solve the problem of inability to achieve limited-time spacecraft rendezvous tasks

Active Publication Date: 2020-01-24
HARBIN INST OF TECH
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0005] The present invention provides a time-varying feedback finite-time stabilization method for a control-limited spacecraft rendezvous control system to solve the limited-time rendezvous task of a spacecraft under control-limited conditions

Method used

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  • Time-varying feedback finite-time stabilization method of control limited spacecraft rendezvous control system
  • Time-varying feedback finite-time stabilization method of control limited spacecraft rendezvous control system
  • Time-varying feedback finite-time stabilization method of control limited spacecraft rendezvous control system

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specific Embodiment approach 1

[0019] Specific implementation mode one: a time-varying feedback finite-time stabilization method for a control-limited spacecraft rendezvous control system, which includes:

[0020] Step 1. Establishing the orbital dynamics model of the control system for the rendezvous control of the limited spacecraft, and obtaining the state space equation;

[0021] Step 2. Establish the parameter Lyapunov equation and analyze its properties. Through the positive definite solution P(γ) of the parameter Lyapunov equation, design an explicit linear time-varying feedback control law under the control-limited situation, that is, design the control-limited spacecraft rendezvous control The state feedback controller of the system;

[0022] Step 3. By constructing an explicit Lyapunov function and using the properties of the solution of the parametric Lyapunov equation to design the controller parameters, it is guaranteed that the tracking spacecraft and the target spacecraft are within a finite ...

specific Embodiment approach 2

[0023] Specific implementation mode two: the difference between this implementation mode and specific implementation mode one is that step one is specifically:

[0024] Establish the mathematical model of the spacecraft rendezvous control system: the nonlinear relative motion equations of the target spacecraft and the catching spacecraft are:

[0025]

[0026] in

[0027] Introduce the orbital coordinate system o-xyz of the target spacecraft, whose origin o is located at the center of mass of the target spacecraft, the x-axis is along the direction of the tangent of the orbit of the target spacecraft, the z-axis is along the direction of the radius of the circular orbit, and the y-axis points out of the orbital plane Form a right-handed coordinate system with the x-axis and z-axis, where, is the normalized acceleration vector on the thruster of the chasing spacecraft, a 1 , a 2 , a 3 is the acceleration generated by the thruster in the directions of x-axis, z-axis an...

specific Embodiment approach 3

[0033] Embodiment 3: The difference between this embodiment and Embodiment 2 is that in the formula (1), μ=GM, μ is a gravitational parameter, M is the mass of a star, and G is a gravitational constant.

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Abstract

The invention relates to a time-varying feedback finite-time stabilization method of a control limited spacecraft rendezvous control system. The stabilization method comprises the steps of: (1), establishing an orbital dynamics model of the control limited spacecraft rendezvous control system, and obtaining a state-space equation; (2), establishing a parametric Lyapunov equation, analyzing the property thereof, according to the positive definite solution P(gamma) of the parametric Lyapunov equation, designing an explicit linear time-varying feedback control law in a control limited condition,namely, designing a state feedback controller of the control limited spacecraft rendezvous control system; and (3), designing controller parameters by constructing an explicit Lyapunov function and utilizing the property of the parametric Lyapunov equation solution, and ensuring that a tracking spacecraft and a target spacecraft complete a rendezvous task in limited time. By means of the time-varying feedback finite-time stabilization method of the control limited spacecraft rendezvous control system in the invention, limited time stabilization of the spacecraft rendezvous control system in the control limited condition can be realized.

Description

technical field [0001] The invention relates to a spacecraft orbit rendezvous space operation control method, in particular to a time-varying feedback finite time stabilization method for a control-limited spacecraft rendezvous control system. Background technique [0002] Spacecraft orbital rendezvous is a space operation in which the chasing spacecraft actively tracks and approaches the target spacecraft so that the two can achieve rendezvous. Orbital control of spacecraft rendezvous is a prerequisite for completing some space operations such as on-orbit assembly, space station replenishment, and space maintenance. [0003] Most of the traditional control algorithms can realize the asymptotic stability of the closed-loop system, that is, the system state tends to infinity and converges to the equilibrium point with time. The finite-time controller realizes the requirement that the closed-loop system can converge to the desired state within a finite time, and in the actual...

Claims

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 周彬张康康张凯段广仁
Owner HARBIN INST OF TECH
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