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Rotational inertia determination method for satellite attitude control system

A technology of satellite attitude control and moment of inertia, applied in the field of satellite control, can solve the problems of lack of theoretical guidance and methods for analyzing the deviation of moment of inertia

Active Publication Date: 2015-04-08
HARBIN INST OF TECH
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  • Summary
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AI Technical Summary

Problems solved by technology

In the satellite attitude control system, a large part of the method is to determine the range of the moment of inertia pull-out through simulation, which lacks theoretical guidance, and there is no method for analyzing the pull-off of the moment of inertia in the prior art

Method used

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  • Rotational inertia determination method for satellite attitude control system
  • Rotational inertia determination method for satellite attitude control system
  • Rotational inertia determination method for satellite attitude control system

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Embodiment Construction

[0073] Step 1. Consider the uncertainty of the satellite's moment of inertia, and treat the uncertainty item as interference. The establishment of the state space of the satellite attitude control system containing the uncertainty is expressed as:

[0074] x · ( t ) = Ax ( t ) + B w w ( t ) + B u u ( t )

[0075] z(t)=C 1 x(t)+D zw w(t)+D zu u(t)

[0076] y(t)=C 2 x(t)

[0077] Where x(t) is the satellite attitude angular velocity and the satellite attitude angle, w(t) is the vector composed of external interference, measurement noise and moment of inertia uncertainty, u(t) is the output control torque of the actuator, z(t) For H ∞ The control index is a vector related to the system output, and y(t) is the system output vector. A,B w ,B w ,C 1 ,D zw ,D zu ,C 2 Is the parameter matrix.

[0078] Step 2. For the state space expression established in step 1, design the state feedback controller as shown below. The specific...

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Abstract

The invention discloses a rotational inertia determination method for a satellite attitude control system and relates to the technical field of satellite control. The method aims to determine the accurate change range of rotational inertia in the satellite attitude control system. The method is technically characterized by comprising the following steps of firstly, building a satellite attitude control system model containing indeterminacy; secondly, making a corresponding constraint index, and acquiring a proper H(u) infinity ( / u) state feedback controller; finally, expressing the indeterminacy in a closed loop system as a form of a polynomial matrix cell, and solving the change range of the indeterminacy of the rotational inertia by using a linear matrix inequality method. According to the method, the change range of the rotational inertia of a satellite under the condition of state feedback is judged by using the stability conditions of the polynomial matrix cell. The indeterminacy is taken into consideration in the design stage of the controller, and the influence on output caused by the indeterminacy serves as a control index, and the indeterminacy in the closed loop system is expressed as the polynomial matrix cell.

Description

Technical field [0001] The invention relates to a method for determining the moment of inertia of a satellite attitude control system, and relates to the technical field of satellite control. Background technique [0002] Satellites operating in orbit inevitably have uncertainties in the moment of inertia. The measurement of the satellite moment of inertia will inevitably produce errors. The influence of the ambient temperature on the sun facing and back sun faces during orbiting will also cause changes in the moment of inertia, so the analysis of the satellite The uncertainty of the moment of inertia is of great significance to the stable operation and maneuvering of satellites in orbit. However, the current analysis of the uncertainty of the satellite moment of inertia mostly stays in the simulation verification stage. For the given moment of inertia deviation range, the uncertainty is not considered in the controller design stage. After the controller design is completed, the ...

Claims

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Application Information

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IPC IPC(8): G05B13/04G05D1/08
Inventor 陈雪芹胡芳芳孙亚辉孙瑞李诚良王爽易涛耿云海
Owner HARBIN INST OF TECH
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