Spacecraft combination navigation method

Abstract

The invention relates to a spacecraft combination navigation method. The problem that as drifting exists on the earth surface, the orbital parameter cannot be calculated based on the positions / speeds output based on inertial navigation for a long time is solved through satellite sensor / horizon sensor / inertia automatic astronomy combination navigation based on PI filtering. The positions and the speeds output by inertial navigation are corrected based on the earth core pointing error determined by a satellite sensor and a horizon sensor, the inertial navigation accumulative error can be restrained through the inertia / astronomy combination navigation. According to the spacecraft combination navigation method, under the abnormal situations that a satellite GNSS compatible machine becomes abnormal and ground orbital parameters are not transmitted in real time, corresponding orbital parameters are calculated through the positions / speeds output by the satellite sensor and horizon sensor inertia-astronomy combination navigation, and the posture, determined based on a satellite sensor, of a body relative orbit system can be ensured. Compared with the prior art, the spacecraft combination navigation method has the advantages that the algorithm is simple and effective and engineering achievement is easy.

Description

technical field [0001] The invention relates to a spacecraft integrated navigation method, in particular to a PI filter-based star-sensing / horizon / inertial autonomous astronomical integrated navigation method. Background technique [0002] Orbital parameters are required to determine the attitude of the body relative to the orbital system based on the star sensitivity, and there is drift in the added table, and the inertial navigation integration leads to cumulative navigation errors, and the orbital parameters cannot be calculated based on the position / velocity output by the inertial navigation for a long time. [0003] The ground is generally based on the WGS-84 non-inertial system for inertial navigation calculation, which is not applicable in high latitude areas; the orbit is generally based on the orbit flat root noted on the ground for orbit calculation, which cannot be used for a long time and is not suitable for orbit changes . [0004] Correct the position and velo...

AI Technical Summary

Problems solved by technology

[0002] Orbital parameters are required to determine the attitude of the body relative to the orbital system based on the star sensitivity, and there is drift in the added table, and the inertial navigation integration leads to navigation accumulation errors, and the orbital parameters cannot be calculated based on the position / velocity output by the inertial navigation for a long time

[0003] The ground is generally based on the WGS-84 non-inertial system for inertial navigation calculation, which is not applicable in high latitude areas; the orbit is generally based on the orbit flat root noted on the ground for orbit calculation, which cannot be used for a long time and is not suitable for orbit changes

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