Spacecraft autonomous navigation method based on fixed star sight relativistic effect

Abstract

The invention relates to a spacecraft autonomous navigation method based on a fixed star sight relativistic effect, which is characterized in that a fixed star angular distance is measured by using a space optical interferometer on a spacecraft, and the value of the fixed star angular distance reflects fixed star aberration caused by the movement of the spacecraft and the light gravity deflection effect caused by a celestial body gravitational field. The fixed star aberration reflects the movement speed of the spacecraft perpendicular to the fixed star sight line direction, the light gravity deflection effect reflects the relative position relation between the spacecraft and a gravitational body, and the fixed star aberration and the light gravity deflection effect both comprise information needed by autonomous navigation of the spacecraft. Furthermore, in combination with a spacecraft orbit kinetic equation, a fixed star angular distance observed quantity on a time sequence is processed through a navigation filtering algorithm, and estimated values of a spacecraft position vector and a speed vector are obtained. The method does not depend on ground measurement and control and inter-satellite links, is not prone to electromagnetic interference, can easily achieve high positioning precision through the technical level of a measurement sensor at the present stage, can be used for earth orbit spacecrafts and can also be used for autonomous navigation of deep space probes.

Description

technical field [0001] The invention relates to an autonomous navigation method for a spacecraft based on the relativistic effect of star line of sight, and belongs to the technical field of aerospace control. Background technique [0002] Traditional autonomous celestial navigation methods for spacecraft include navigation methods based on optical sensors to measure geocentric vectors, and X-ray pulsar navigation methods. Among them, the navigation system based on optical sensors to measure geocentric vectors is limited by the accuracy of geocentric direction extraction. The positioning accuracy is usually on the order of km, which is difficult to meet the requirements of high-precision autonomous navigation of spacecraft; the measurement accuracy of the X-ray pulsar navigation system depends on the effective area of ​​the X-ray detector, and the X-ray detector often has a large mass and volume, which limit the scope of application of this method. In 2018, in the "Space St...

AI Technical Summary

Problems solved by technology

[0003] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, aiming at the problem of the limited accuracy of the existing autonomous astronomical navigation methods, propose a spacecraft autonomous navigation method based on the relativistic effect of star line of sight, which does not rely on ground measurement and control and inter-satellite navigation. Link, to achieve high positioning accuracy at the current level of measurement sensor technology

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