Gyroscope angular rate random walk and rate slope coefficient calculation method

Abstract

The invention provides a gyroscope angular rate random walk and rate slope coefficient calculation method, which comprises the following steps of: S1, calculating a reference system triaxial angular velocity of a spacecraft body relative to a reference system on a satellite; S2, generating a triaxial gyroscope angular velocity integral value based on the reference system triaxial angular velocity, and remotely measuring and downloading the triaxial gyroscope angular velocity integral value to the ground; and S3, calculating a triaxial Allan variance of the spacecraft based on the triaxial gyroscope angular velocity integral value, and fitting thetriaxial Allan variance to obtain a triaxial angular velocity random walk coefficient and a velocity slope coefficient of the spacecraft. According to the gyroscope angular rate random walk and rate slope coefficient calculation method, the triaxial gyroscope angular velocity integral value of the last beat of each integral period is calculated on a satellite and is downloaded to the ground, so that the data processing amount of the ground is greatly reduced, and the calculated triaxial angular velocity random walk coefficient and the velocity slope coefficient of the spacecraft meet the high-precision requirement.

Description

technical field [0001] The invention relates to the technical field of spacecraft attitude and orbit control systems, in particular to a calculation method for gyroscope angular rate random walk and rate slope coefficient. Background technique [0002] High-precision optical gyroscopes (fiber-optic gyroscopes, laser gyroscopes, etc.), as the key measurement components of spacecraft attitude-orbit control systems, are used in combination with high-precision attitude references (such as star sensors), which can increase the accuracy of spacecraft attitude determination by more than an order of magnitude; Since the gyroscope is not disturbed by the field of view, the dynamic range is large, and the response time is short, it can also greatly improve the validity of the attitude data of the spacecraft and enhance the responsiveness of the spacecraft to high dynamics. [0003] The working principle of the fiber optic gyro is to sense the rotational angular velocity through the sa...

AI Technical Summary

Problems solved by technology

Considering the on-orbit application of FOG, affected by the thermal deformation between gyroscope and attitude reference and the change of spacecraft working mode, the data of FOG shows non-white noise characteristics, and the relevant influence needs to be eliminated when processing ground data of FOG. The ground treatment process is complex and the engineering operability is poor

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