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Method for Determining Moment of Inertia of 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 no method for analyzing the deflection of moment of inertia.

Active Publication Date: 2017-03-01
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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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  • Method for Determining Moment of Inertia of Satellite Attitude Control System
  • Method for Determining Moment of Inertia of Satellite Attitude Control System
  • Method for Determining Moment of Inertia of Satellite Attitude Control System

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Embodiment Construction

[0073] Step 1. Considering the uncertainty of the satellite’s moment of inertia, and treating the uncertainty item as interference, the state space of the satellite attitude control system including uncertainty is established and expressed as:

[0074]

[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 satellite attitude angle, w(t) is a vector composed of external disturbance, 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. Based on the state space expression established in step 1, design the state feedback controller as shown below. The specific structure of the controller is as follows:

[0079] u(t)=K 1 x(t)

[0080] where K 1 is the c...

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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 uncertain moments of inertia, and the measurement of satellite moments of inertia will inevitably produce errors. The influence of ambient temperature on the sunny side and the back side of the orbit will also cause changes in the moment of inertia. Therefore, the analysis of the satellite The uncertainty of moment of inertia is of great significance to the stable operation and maneuvering of satellites in orbit. At present, the analysis of the uncertainty of the satellite's moment of inertia mostly stays in the simulation verification stage. For a given range of moment of inertia, the uncertainty is not considered in the controller design stage. After the controller design is completed, the simulation method T...

Claims

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Application Information

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Patent Type & Authority Patents(China)
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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