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No-gyro satellite gesture determination method based on tensor product multi-cell robust heavy hydrogen (H2) filtering

A multicellular robust, satellite attitude technology, applied in the field of aircraft, can solve problems such as large amount of calculation and complex algorithm

Inactive Publication Date: 2013-03-20
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0003] The purpose of the present invention is to solve the problem of complex non-linear attitude determination algorithm of gyro-free satellites, large amount of calculation, etc., and propose a method for determining the attitude of gyro-free satellites based on tensor product multicellular robust H2 filtering

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  • No-gyro satellite gesture determination method based on tensor product multi-cell robust heavy hydrogen (H2) filtering
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  • No-gyro satellite gesture determination method based on tensor product multi-cell robust heavy hydrogen (H2) filtering

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[0112] In order to better illustrate the purpose and advantages of the present invention, further description will be given below in conjunction with the accompanying drawings and embodiments.

[0113] (1) Establish a state model and measurement model for satellite attitude determination

[0114] The task of determining the attitude of the satellite is to determine the orientation of the satellite's own system relative to the reference coordinate system. Selecting the inertial system as the reference coordinate system, the satellite attitude dynamics equation

[0115] J ω · + ω × Jω = T

[0116] In the formula, ω is the representation of the angular velocity of the satellite system relative to the inertial system in this system, J is the satellite inertial array, T is the rotational torque applied to the satellite, including the control torque and various extern...

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Abstract

The invention relates to a no-gyro satellite gesture determination method based on tensor product multi-cell robust heavy hydrogen (H2) filtering, and belongs to the technical field of aircrafts. As for the nonlinear characteristics of satellite gesture dynamic equations and kinematical equations, the no-gyro satellite gesture determination method based on the tensor product multi-cell robust H2 filtering provides the multi-cell robust H2 filtering based on tensor product conversion to transform a nonlinear filtering problem into a linear filtering problem. The no-gyro satellite gesture determination method based on the tensor product multi-cell robust H2 filtering includes the steps of first establishing a state equation and a star sensor measurement equation of a gesture determination system and transforming a nonlinear system into a linear variable parameter error system by utilizing Jacobian linearization, then establishing linear parameter varying (LPV) system multi-cell model description according to tensor product model transformation and acquiring state estimation correction amount of the gesture determination system through combining with the robust H2 filtering, and last correcting gesture single-step pre-measurement acquired through a extended Kalman filter (EKF) method by utilizing the estimation correction amount to obtain a gesture estimation value. Accordingly, real-time updated filtering gain in the EKF method is avoid, and filtering calculated amount is reduced greatly.

Description

technical field [0001] The invention relates to a method for determining the attitude of a gyroscope-free satellite based on tensor product multicellular robust H2 filtering, and belongs to the technical field of aircraft. Background technique [0002] Star sensor is a kind of high-precision measuring instrument, which has been widely used in satellite attitude measurement system. In the past, due to the limitation of sensitivity and bandwidth, the star sensor could not be used as the main attitude sensor of the satellite in orbit. It needs to be combined with the gyroscope to establish a high-precision attitude reference and ensure the reliability of the satellite attitude information. In recent years, the combined approach of attitude determination based on gyro and attitude sensor has been widely used in engineering. But gyroscopes are expensive and may degrade or fail after long-term operation, and some satellites are limited by power and weight and cannot carry gyro co...

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Application Information

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IPC IPC(8): G01C21/20
Inventor 刘向东杨帆刘冰陈振
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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