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An Optimal Gyro Combination Selection Method Based on Residual Generator

A generator and gyroscope technology, applied in instruments, measuring devices, navigation through speed/acceleration measurement, etc., can solve problems such as inability to select performance gyroscope instruments in real time, and achieve high reliability, easy implementation, and simple algorithms

Active Publication Date: 2018-01-05
HARBIN INST OF TECH
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Problems solved by technology

[0004] In order to solve the problem that the gyro instrument with the best performance cannot be selected in real time to participate in the calculation of the three-axis angular velocity of the satellite when there is redundancy in the existing gyro components, the present invention provides a method for selecting the optimal gyro combination based on the residual generator. The method of a group of residual generators realizes the real-time dynamic selection of the gyro combination with the best performance on the orbit, effectively utilizes the redundancy of the gyro components on the star, and can provide higher-precision angular velocity information for the attitude control system, and for the gyro fault tolerance

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[0016] The technical solutions of the present invention will be further described below in conjunction with the accompanying drawings, but are not limited thereto. Any modification or equivalent replacement of the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention shall be included in the present invention. within the scope of protection.

[0017] The present invention provides a method for selecting an optimal gyro combination based on a residual generator, and the specific implementation steps are as follows:

[0018] 1. Divide the four gyro components into four groups of alternative gyro combinations:

[0019] like figure 1 shown, O n X n Y n Z n It is the instrument coordinate system of the gyro assembly with three positive and one oblique configuration. The gyro assembly has four gyro, which are respectively marked as gyro 1, gyro 2, gyro 3, and gyro 4, wherein the measurement d...

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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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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/20G01C21/18G01C25/00
CPCG01C21/18G01C21/20G01C25/005
Inventor 李利亮王振华沈毅汤文涛
Owner HARBIN INST OF TECH
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