Autonomous navigation method for heo satellite formation flight based on star sensor and inter-satellite link

Abstract

The invention discloses an HEO satellite-formation-flying automatic navigation method based on a star sensor and an inter-satellite link. The HEO satellite-formation-flying automatic navigation method includes the steps that two satellite-formation-flying structures and rail parameters are designed with HEO satellite earth observation as the task requirement, and according to a rail dynamic model of a primary satellite relative to a secondary satellite under a geocentric inertial coordinate system, an automatic navigation system state model is established; the theoretical light condition and the imaging condition which are required to be met when the secondary satellite is observed through the primary-satellite star sensor are proposed; the theoretical azimuth angle and the pitch angle of the secondary satellite relative to the primary satellite are calculated, the direction of the real optical axis of the primary-satellite star sensor and the theoretical direction are adjusted to be coincident, the secondary satellite is really observed, and an observation equation with the relative unit direction vector and the distance as observation quantities is established; the position and the speed of the satellite are estimated with Unscented Kalman filtering. By means of the HEO satellite-formation-flying automatic navigation method, errors of the relative positions of satellites can be effectively corrected, the relative navigation accuracy is improved, and the HEO satellite-formation-flying automatic navigation method is quite suitable for satellite-formation-flying automatic navigation.

Description

technical field [0001] The invention belongs to the field of spacecraft formation flight space measurement, in particular to an autonomous navigation method for HEO satellite formation flight based on a star sensor and an inter-satellite link. Background technique [0002] The orbital eccentricity of the High Elliptical Orbit (HEO) satellite is greater than 0.6, the perigee height is between 300 km and 1000 km, and the height at the apogee is higher than that of the geostationary orbit satellite (36000 km). HEO satellites have the characteristics of wide coverage area and long coverage time, so they have been applied in many fields, such as missile early warning, weather detection, navigation and positioning, space science exploration, etc. Early HEO satellites were mainly used in the military field, typical representatives of which include Russia's "Lightning" series of satellites; the United States' "Folding Chair" and "Bullion" satellites. It can be said that although th...

AI Technical Summary

Problems solved by technology

[0005] Purpose of the invention: The present invention aims at the problem of low navigation accuracy due to insufficient observation information of HEO satellite formation flight, and proposes an autonomous navigation method for HEO satellite formation flight based on star sensors and inter-satellite links, providing high-speed navigation for HEO satellite formation flight. Accuracy Relative Observation Information

Images