A Calibration Test Method for Inertial Space Gyroscope Based on Three-axis Turntable

Abstract

The invention relates to an inertial space gyro calibration test method based on a three-shaft turntable; while a gyro assembly attitude rotation is provided by the three-shaft turntable, the compensation dosage of the earth autorotation angular velocity is calculated according to the real-time rotating angle output of three rotating shafts of the three-shaft turntable, so that the influence of earth autorotation on the gyro measurement output is eliminated, and the inertial space constant angular velocity required for a gyro calibration algorithm is ensured. At the same time, based on attached rotation characteristics of the three rotation shafts of the three-shaft turntable, the method defines a rotation sequence rule of the three rotation shafts and a three-shaft turntable body coordinate system and a reference inertial coordinate system having the initial zero coinciding with the ground horizontal coordinate system, and provides a reference benchmark for determining the inertial system angle increment according to the gyro output and for determining the inertial system attitude according to the rotation angle output of the three rotation shafts of the three-shaft turntable. The method can significantly improve the precision of a ground gyro calibration test, can guarantee the ground to perform effective calibration and test result calibration on a gyro assembly, can establish a good foundation for performing relevant calibration tests of satellites in orbit, and improves the determination precision of the gyro attitude.

Description

technical field [0001] The invention belongs to the technical field of spacecraft control system simulation, and relates to a ground test method for the error calibration technology of a spacecraft inertia attitude sensor measurement model. Background technique [0002] With the development of spacecraft control technology, the spacecraft puts forward higher attitude maneuver requirements for the control subsystem. For example, the typical point-to-point attitude maneuver and stability index is 20 seconds to maneuver and stabilize at 25 degrees. At the same time, the satellite is also required to have in-motion imaging. In the process of imaging in motion, the satellite has a certain attitude angular velocity and changes continuously with time. [0003] Due to the maneuverability of the satellite attitude and the imaging process in motion, the gyroscope is mainly used to determine the attitude. In order to reduce the attitude determination error after the spacecraft attitud...

AI Technical Summary

Problems solved by technology

Since the gyro is used for sensitive inertial angular velocity, when the gyro calibration test is performed on the ground, the measurement output of the gyro will be affected by the rotation of the earth, which will affect the calibration accuracy

In the traditional static test, in order to eliminate the influence of the earth's rotation, the characteristic that the angular velocity of the earth's rotation is distributed in the true north and the surface normal, that is, the sky, is often used to place a measurement axis of the gyro component on the earth's horizontal coordinate system due east or positive. In the west direction, this method cannot be used because it cannot meet the attitude rotation requirements of gyro calibration

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