A calibration method of gyroscope constant current source for satellite

Abstract

The invention belongs to the technical field of spacecraft testing, and discloses a method for calibration of a satellite gyro constant current source. The method comprises the steps as follows: 1, setting D code values input to a constant current source board card, and measuring the output currents so as to obtain a plurality of currents in one-to-one correspondence with the D code values; adopting a certain method to perform linear fitting on the D code values and the currents which are in one-to-one correspondence to obtain a transformational relation between the D code values and the currents ; 2, setting currents input to a gyro for many times, and measuring output angular velocities of the gyro so as to obtain a plurality of angular velocities in one-to-one correspondence with the currents; adopting a certain method to perform linear fitting on the currents and the angular velocities which are in one-to-one correspondence to obtain a transformational relation between the currents and the angular velocities; 3, indirectly obtaining a transformational relation between the D code values and the angular velocities via the transformational relation between the D code values and the currents, which is obtained in the step 1, and the transformational relation between the currents and the angular velocities, which is obtained in the step 2. The method is suitable for calibration of the satellite gyro constant current source.

Description

Technical field [0001] The invention relates to the technical field of spacecraft testing, in particular to a calibration method of a gyro constant current source for satellites. Background technique [0002] The gyroscope device with various functions made according to the mechanical properties of the gyroscope is called the gyroscope. The gyroscope can be used to indicate the flight status of each spacecraft. When the satellite is flying in orbit, the gyroscope can also be used to perform the attitude of the satellite. Instructions. [0003] During the ground test, since the spacecraft does not actually rotate, the angular velocity that the gyroscope is sensitive to is fixed. Therefore, in order to make the output of the gyroscope the ideal angular velocity value when the spacecraft is in motion during the test, the ground must be added to the gyroscope. For suitable excitation, a constant current source for testing is usually used. The constant current source is provided by th...

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Problems solved by technology

However, there is not a complete linear relationship between the D value of the constant current source board and the angular velocity of the gyroscope.

[0006] Therefore, the existing method requires repeated measurements in the calibration process to find the boundary points of different segments, and when the position of the gyroscope is changed, the entire calibration process needs to be repeated. There are many segments, low precision, complex calibration process, and heavy workload. ,low efficiency

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