Mars navigation sensor installation error in-orbit calibration method

Abstract

The invention discloses a Mars navigation sensor installation error in-orbit calibration method, which comprises that 1, before autonomous optical navigation is performed, moon or asteroid celestial body is screened as a calibration celestial body according to a Mars exploration orbit design result, and attitude maneuver is performed at an appropriate moment, such that a Mars navigation sensor isaligned with the calibration celestial body; 2, a sequence star map containing the target celestial body is subjected to in-orbit shooting by using the Mars navigation sensor, the mass center of the calibration celestial body is extracted by using a star map recognition algorithm and a mass center algorithm, and the mass center coordinate of the star map is subjected to multi-frame average in-orbit processing so as to reduce random error; and 3, calculation is performed according to a reference ephemeris, ground station navigation data and the current attitude of the Mars detector to obtain the expected mass center parameter and the like of the calibration celestial body. According to the present invention, with the Mars navigation sensor installation error in-orbit calibration method, theparameter error of the navigation sensor can be determined, and the reliability, the stability and the precision of the optical autonomous navigation can be improved.

Description

Technical field [0001] The invention relates to a spacecraft autonomous management method, in particular to an on-orbit calibration method for the installation error of a Mars navigation sensor. Background technique [0002] The Mars navigation sensor is the main measurement equipment in the Mars exploration autonomous navigation. Its measurement accuracy directly affects the accuracy of the navigation. Although the navigation sensor has been rigorously calibrated on the ground, it is subject to the release of stress during the launch process. The complex and changeable space environment and the aging of long-term flight components will cause changes in the installation parameters of the navigation sensor. The installation parameters of the navigation sensor directly affect the accuracy of the line of sight and the navigation accuracy. Research on the Mars navigation sensor Installation error in orbit autonomous calibration method can obtain high-precision pointing information ba...

AI Technical Summary

Problems solved by technology

[0002] The Mars navigation sensor is the main measurement equipment in the autonomous navigation of Mars exploration. Its measurement accuracy directly affects the accuracy of navigation. The complex and changeable space environment, the aging of long-term flight devices and other factors will change the installation parameters of the navigation sensor. The installation parameters of the navigation sensor directly affect the line-of-sight pointing accuracy, thereby affecting the navigation accuracy. The installation error on-orbit autonomous calibration method can obtain high-precision pointing information according to the measurement of the calibration celestial body, provide high-precision geometric calibration information for the navigation sensor, and greatly improve the reliability, stability and accuracy of optical autonomous navigation

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