A MEMS gyroscope on-orbit constant drift calibration method and system for microsatellites

Abstract

The invention discloses a MEMS gyroscope on-orbit constant value drift calibration method and system for microsatellites. The method includes: determining the calibration mode of the gyroscope in the attitude determination system; determining the calibration time interval and the calibration time interval according to the task situation The number k of star sensors and MEMS gyroscope data sets is required; obtain the attitude quaternion and gyroscope data of the star body relative to the inertial system output by the star sensor at the current moment, and judge the validity of the data. If valid, increase the number of data sets 1; if invalid, discard the set of data and wait for the next set of data until the amount of qualified data reaches k sets; perform calibration calculations based on the k sets of data to obtain the angular velocity measured by the gyroscope under the relative inertial system of the satellite body The constant value drift is used to judge the calculation result, and if the calibration is successful, the calibration result is returned to the attitude determination system for zero compensation of the gyro data.

Description

technical field [0001] The invention relates to the field of spacecraft attitude determination and control. More specifically, it relates to a MEMS gyroscope on-orbit constant drift calibration method and system for micro-satellites. Background technique [0002] Due to the advantages of small size, light weight, good performance, short development cycle, low cost, and flexible launch methods, microsatellites have been widely used in communication, remote sensing, navigation, scientific exploration and other fields, and have become an important development in the current aerospace development. One of the directions, and shows good economic and social benefits. All countries in the world attach great importance to the development of the Wiener satellite industry. Since 2015, China's small industry has begun to develop "blowout". It is estimated that in five to ten years, China's Weiner satellite industry, driven by the construction and operation of micro-satellite constella...

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Problems solved by technology

Although UKF solves the filter divergence problem caused by severe nonlinearity, because it uses a Gaussian distribution to approximate the posterior probability density of the system, if the probability density is not Gaussian, it will bring a huge error and the calculation speed is slow

[0005] Aiming at the problems that the existing MEMS gyroscope constant drift on-orbit calibration method is complicated, the calculation amount is large, and the algorithm is prone to divergence and instability, the solution provided by the invention can be used for the constant drift calibration of MEMS gyroscopes during the on-orbit phase of micro-satellites

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