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A gyroscope installation matrix calibration method based on satellite inertial space rotation attitude

A technology for installing matrix and inertial space, applied in the field of aerospace, can solve problems such as low efficiency, complex parameter adjustment, and many state quantities

Active Publication Date: 2020-06-19
CHANGGUANG SATELLITE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, in order to overcome the influence of noise, the method of filtering is used for processing, there are many state quantities, the matrix dimension is high, the parameter adjustment is complicated, the efficiency is low, and the installation matrix needs a period of time to converge.

Method used

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  • A gyroscope installation matrix calibration method based on satellite inertial space rotation attitude
  • A gyroscope installation matrix calibration method based on satellite inertial space rotation attitude
  • A gyroscope installation matrix calibration method based on satellite inertial space rotation attitude

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Experimental program
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Effect test

Embodiment

[0158] Set the initial installation matrix and the actual installation matrix of the gyro, through three maneuvers around the X, Y, and Z axis, the star sensitive data, gyro data and time are derived and calculated, and the method of the present invention is verified (the feasibility of the algorithm is not verified , Gyro and Star Min are all noise-free data).

[0159] Set the initial installation matrix as:

[0160]

[0161] Assuming that the gyro changes 0.1° around the X axis, 0.2° around the Y axis, and 0.3° around the Z axis after being in orbit, the actual installation matrix is:

[0162]

[0163] Before calculation, suppose the installation matrix of the gyro is as follows:

[0164]

[0165] a) The star rotates around the X axis

[0166] Let the star rotate around the X axis at an angular velocity of 0.5° / s, export the star sensitive data, gyro data and time data for calculation, and select the star sensitive initial attitude as:

[0167] q xstart =[0.09598 0.799913 -0.18954 -0...

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Abstract

The invention relates to a gyro installation matrix calibration method based on satellite inertial space rotation attitude. In order to calculate the actual installation matrix of the gyro in orbit, it is necessary for the satellite to orbit X, Y, The Z axis rotates on a single axis at a fixed angular velocity, and downloads the data of the star sensor and the gyroscope, converts the angular velocity of the gyroscope into the star coordinate system, and then calculates the attitude through the fourth-order Runge-Kutta integral solution, and solves it with the star sensor The calculated attitude can be solved simultaneously to calculate the attitude matrix. The method of the invention can complete the calculation of the installation matrix through three specific attitude maneuvering processes, the calculation process is simple, the calculation result is accurate, and it is suitable for the calibration of the satellite on-orbit gyroscope installation matrix.

Description

Technical field [0001] The invention relates to the field of aerospace technology, in particular to a method for calibrating a gyroscope installation matrix based on a satellite inertial space rotation attitude. Background technique [0002] With the development of satellite technology, the aerospace industry will occupy an increasingly important position in the human industry, and the attitude determination of satellites is one of the most basic and critical links in satellite technology. As the satellite's attitude measurement sensor, the gyroscope can determine the satellite's attitude relative to the three-axis in the inertial coordinate system through measurement data. Factors such as gyroscope installation error and ground calibration error, vibration and impact on the satellite launch section, harsh space working environment and other factors will cause the gyroscope measurement value to deviate from the true value due to the installation position error, thereby affecting ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C25/00
CPCG01C25/00
Inventor 童鑫戴路徐开李峰刘萌萌
Owner CHANGGUANG SATELLITE TECH CO LTD