Time-varying feedback finite time control method for controlling limited satellite formation flight system

A formation flight, limited satellite technology, applied in general control systems, control/regulation systems, aircraft, etc., can solve problems such as large controller input amplitude and chattering

Active Publication Date: 2021-01-29
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, this method will bring disadvantages such as chattering and large controller input amplitude.

Method used

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  • Time-varying feedback finite time control method for controlling limited satellite formation flight system
  • Time-varying feedback finite time control method for controlling limited satellite formation flight system
  • Time-varying feedback finite time control method for controlling limited satellite formation flight system

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specific Embodiment approach 1

[0016] Specific implementation mode one: the time-varying feedback finite-time stabilization method of the control-limited spacecraft rendezvous control system, which is implemented in the following steps:

[0017] Step 1: Establish the orbital dynamics model of the control-constrained satellite formation flight system and obtain the state space equation, establish the signal model to be tracked and obtain the state space equation;

[0018] 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, and then establish the output regulation equation. Through the solution of the output regulation equation, design an explicit The linear time-varying feedforward control law is designed, and finally the time-varying state controller is designed to control the limited satellite formation flight system through the linear time-va...

specific Embodiment approach 2

[0021] Specific embodiment two: the difference between this embodiment and specific embodiment one is: step one is specifically: set up the mathematical model of satellite formation flight system: consider the situation that target satellite moves on the plane circular orbit, wherein R e is the orbital radius of the earth, r ref is the orbital radius of the target satellite, i ref is the initial inclination of the target satellite’s reference orbit, J 2 is the potential constant in the quadratic spherical harmonic function of the earth potential, θ is the phase angle between the target satellite and the pursuing satellite, (x 1 , x 2 ) is the coordinate origin in the right-hand coordinate system on the center of mass of the target satellite, is due to aerodynamic drag in the direction (x 1 , x 2 ), M is the mass of the star, G is the gravitational constant, μ=GM is the gravitational parameter, is the orbital velocity of the target satellite, and the nonlinear relative ...

specific Embodiment approach 3

[0029] Specific embodiment three, what this embodiment is further limited is: the specific process of step 2 is: set up the signal model to be tracked: the task of satellite formation flight is to drive state vector [x 1 ,x 2 ] T to track the given signal where r and w ref is a given constant. A given signal can therefore be described by the following linear equation of state:

[0030]

[0031] in, b=r, the tracking error e(t) can be described by the following equation:

[0032] e(t)=Cx(t)+Dw(t) (4)

[0033] in, Observation (4) shows that when e(t) tends to zero, the satellite formation flight tracking task is completed.

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Abstract

A time-varying feedback finite time control method for controlling a limited satellite formation flight system comprises the steps: step 1, establishing an orbital dynamics model for controlling the limited satellite formation flight system and obtaining a state-space equation, establishing a to-be-tracked signal model and obtaining the state-space equation; step 2, establishing a parameter Lyapunov equation and analyzing the property of the parameter Lyapunov equation, designing an explicit linear time-varying feedback control law through a positive definite solution of the parameter Lyapunovequation, establishing an output adjustment equation, and designing an explicit linear time-varying feedforward control law through a solution of the output adjustment equation; and designing a time-varying state controller for controlling the limited satellite formation flight system through a linear time-varying feedback control law and a linear time-varying feedforward control law; and step 3,constructing an explicit Lyapunov function, and designing controller parameters by utilizing the properties of a parameter Lyapunov equation and an adjustment equation solution to ensure that the accompanying satellite completes a tracking task within finite time. The invention aims to realize finite time control of the satellite formation flight system under the condition of limited control.

Description

technical field [0001] The invention relates to a time-varying feedback finite time control method for controlling a limited satellite formation flight system. Background technique [0002] Satellite formation flight is essentially to use multiple flying satellites to form a system of a certain shape. The satellites communicate with each other through inter-satellite communication, work together, and jointly undertake tasks such as space signal collection and processing. As a main configuration of satellite formation flight, satellite accompanying flight has received extensive attention from many famous aerospace research institutions including NASA, US Air Force and European Space Agency. The satellite accompanying system consists of a target satellite and an accompanying satellite, in which the accompanying satellite moves relative to the target satellite on a specified trajectory. From the current point of view, the main function of the accompanying satellite is to obser...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04B64G1/24B64G1/10
CPCG05B13/042B64G1/24B64G1/1085
Inventor 周彬张凯侯明哲姜怀远段广仁
Owner HARBIN INST OF TECH
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