Attitude Determination Method for Gyro-less Satellite Based on Tensor Product Multicellular Robust h2 Filter

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 gyro-free satellite based on tensor product multi-cell robust H2 filtering, and belongs to the technical field of aircraft. Background technique [0002] The star sensor is a high-precision measuring instrument, which has been widely used in the 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 combination scheme of attitude determination based on gyroscope and attitude sensor has been widely used in engineering. However, the gyro is expensive, and its performance may be reduced or malfunction after long-term operation, and some satellites cannot be loaded with gyro co...

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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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