An Optimal Gyro Combination Selection Method Based on Residual Generator

Abstract

The invention discloses an optimal gyroscope combination selection method based on residual error generators. The method comprises steps as follows: (1), four gyroscopic instruments of four standby gyroscopic assemblies including three upright gyroscopic assemblies and one oblique gyroscopic assembly are divided into four groups of gyroscope combinations; (2), the three-axis angular speed of each satellite is calculated according to measurement values of the four groups of gyroscopic combinations according to mounting matrixes of the standby gyroscopic assemblies, and three-axis angular speeds of the four satellites are obtained; (3), the three-axis attitude provided by a star sensor and the three-axis angular speeds, calculated by the four groups of gyroscopic combinations, of the satellites are used for forming the residual error generators, and four attitude residual errors are obtained totally; (4), an evaluation function of each attitude residual error is solved, the four evaluation functions are sequenced according to numerical magnitudes, and the smallest group is the optimal gyroscope combination. The gyroscope combination with the optimal performance is dynamically selected in orbit in real time, redundancy of the gyroscopic assemblies on the satellite is effectively used, angular speed information with higher accuracy can be provided for an attitude control system, and the method has certain fault-tolerant capacity for gyroscopic faults.

Description

technical field

[0001] The invention belongs to the technical field of satellite attitude determination, and relates to an online optimization method for gyro instruments, in particular to a method for selecting three gyroscopes with the best performance to participate in angular velocity calculation when alternative gyro components have hardware redundancy. Background technique

[0002] The gyroscope is used to sense the inertial angular velocity of the satellite and is the main inertial measurement component in the satellite attitude determination system. Due to its importance, redundant configurations are often used on satellites. At present, the commonly used high-precision gyroscopes are fiber-optic gyroscope components and hemispherical resonant gyroscope components. Both types of gyroscope components adopt a three-positive and one-inclined redundant configuration, that is, four heads are used to sense the three-axis inertial angular velocity information. Due to the a...

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