On-line calibration method of star sensor based on sins assistance of aerospace aircraft

Abstract

The invention discloses an on-line calibration method for a star sensor based on the SINS assistance of an aerospace aircraft, comprising the following process: obtaining the attitude matrix output by the star sensor relative to the inertial coordinate system; obtaining the attitude matrix output by the SINS, and converting the The attitude matrix output by SINS is constructed as a measurement that can match the attitude matrix output by the star sensor; construct the state vector of the SINS / star sensor integrated navigation system; utilize the star sensor attitude matrix obtained and the SINS attitude matrix to construct Construct the Kalman filter measurement equation of the SINS / star sensor integrated navigation system; then use the aerospace plane to perform angular maneuvers in at least two axes to estimate the installation error angles of the star sensors in the three axes, so that all The star sensor is calibrated online. The invention can calibrate the installation error angle of the star sensor on-line in real time only by performing a simple swinging action of the aerospace plane during the flight, and effectively guarantee the attitude determination accuracy of the star sensor in the actual use process.

Description

technical field [0001] The invention relates to the technical field of star sensors, in particular to an on-line calibration method for star sensors based on aerospace aircraft SINS assistance. Background technique [0002] The aerospace plane has the functions of both aviation and aerospace platforms. It can not only fly hypersonic in the atmosphere like an ordinary plane, but also enter space like a rocket or a satellite, and can flexibly conduct orbital maneuvers. The entire flight mission of the aerospace plane spans two different fields of aviation and aerospace, and the navigation control information used will be very different. It is necessary to use a variety of integrated navigation technologies to solve this problem. The star sensor (CNS) can be fully utilized. ) long-term high-precision attitude determination information and short-term high-precision navigation information of strapdown inertial navigation (SINS), they are organically combined through Kalman filter...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to disclose a star sensor online calibration method based on the SINS assistance of the aerospace aircraft, to solve the problem that the navigation accuracy is affected due to the installation error of the star sensor in practical applications, and it is suitable for space On-line calibration of star sensors during all phases of aircraft flight

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