Aerospace vehicle star sensor installation error online calibration method

Abstract

The invention discloses an aerospace vehicle star sensor installation error online calibration method. The method comprises the following steps: S1, establishing a dynamic calibration star sensor installation error angle model; S2, deriving a star sensor installation error calibration method; and S3, verifying the effectiveness of the star sensor installation error calibration method, and correcting the star sensor installation error. Simulation results show that the designed dynamic identification method can be used for accurately and rapidly carrying out online calibration and compensation correction on the star sensor installation error angle, and the precision of an inertia / astronomical integrated navigation system is effectively improved.

Description

technical field [0001] The invention relates to aerospace vehicle technology, in particular to an on-line calibration method for installation errors of star sensors of aerospace vehicles. Background technique [0002] Aerospace vehicle refers to a new type of aircraft with two functions of aircraft and spacecraft. It is launched from the ground to orbital space through a booster, completes the mission and operates in orbit for a long time, and finally reaches the re-entry point to return to the earth. The key technology of aerospace vehicle navigation is the core technology to realize its intelligent autonomous control. Star sensor is one of the navigation sensors of aerospace vehicles. autonomous navigation plays an important role. The accuracy of the star sensor itself can reach the arc-second level, and the installation error of the star sensor is the main factor determining the accuracy of astronomical navigation, which limits the attitude determination and positioning ...

AI Technical Summary

Problems solved by technology

The accuracy of the star sensor itself can reach the arc-second level. The installation error of the star sensor is the main factor determining the accuracy of astronomical navigation, which limits the attitude determination and positioning performance of the integrated inertial / astronomical integrated navigation system.

[0003] At present, the calibration and correction of the installation error of the star sensor is mainly completed on the ground before take-off. The method of calibrating the installation error of the star sensor using the star simulator and the azimuth reference, and the three-position ground calibration method of the installation error of the star sensor, the above methods Both can accurately calibrate the installation error of the star sensor, but the aerospace vehicle often performs a mission for hundreds of days, after three mission stages of launch, in-orbit and re-entry, the integrated inertial / celestial navigation system has a star sensor The device is fixedly connected to the carrier, due to vibration, shock and other factors during the launch process, as well as the accumulated installation angle drift over a long period of time, the installation error may reach the angular classification

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