Satellite relative attitude reference error analysis method, system and device

Abstract

The invention provides a satellite relative attitude reference error analysis method which comprises the following steps: S1, establishing a gyroscope relative attitude reference error model suitable for rapid maneuvering according to different requirements of tasks; s2, carrying out gyroscope zero offset estimation in combination with an optical sensor before a maneuvering task, and analyzing the influence on attitude reference precision; s3, carrying out quantitative analysis on attitude reference errors caused by gyro scale factor errors and uncalibrated deviation; s4, after quantitative analysis is carried out on the attitude reference error, a gyroscope random measurement model is established; s5, performing attitude estimation by using the gyroscope random measurement model, and establishing a gyroscope random error statistical model through a gyroscope state estimation equation; and S6, in the rapid maneuvering process, carrying out quantitative analysis on the gyroscope attitude angle reference total error by utilizing the gyroscope random error statistical model. The method solves the problem that the random error affects the quantitative analysis of the attitude reference error, and can be applied to the rapid maneuvering process of various spacecrafts.

Description

technical field [0001] The present invention relates to the technical field of attitude maneuvering, and in particular, to a method, system and device for analyzing satellite relative attitude reference error. Background technique [0002] With the continuous development of remote sensing satellites, remote sensing satellites continue to enrich their own functions and improve their performance. Among them, agile maneuvering imaging capability is the technology that is more concerned at present. Agile maneuvering mainly means that the satellite platform has the capability of large-scale rapid attitude maneuvering, and can implement flexible ground observation within the limits of the maximum attitude angle and attitude maneuvering speed. In practical applications, inertial measurement attitude determination and external reference vector attitude determination are often combined. Inertial measurement is used in each sampling interval, and external reference vector (sun vector,...

AI Technical Summary

Problems solved by technology

Its disadvantages are: 1) the initial attitude needs to be known; 2) if the integration time is long, the attitude determination error caused by gyro drift will increase; 3) if the reference coordinate system is a non-inertial reference system, it is also necessary to calculate the relative Attitude motion of inertial system, etc.

Although this prior art utilizes the rate turntable to calibrate the gyro zero bias, scale factor, installation error coefficient, etc., it does not test the various random error coefficients, and cannot quantify the impact of random errors on attitude reference errors.

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