Method for correcting rotation errors of a constellation of distributed autonomous navigators

By calculating the orbital plane orientation error using satellites and fitting the local constellation rotation, a virtual observation condition constraint equation was constructed, which solved the rotation error problem of the distributed autonomous navigation constellation and achieved high-precision autonomous orbit determination and a stable constellation configuration.

CN117029875BActive Publication Date: 2026-06-26SHANGHAI ASTRONOMICAL OBSERVATORY CHINESE ACAD OF SCI +1
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Patent Information

Application Number
CN202310885737.5
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2023-07-18
Publication Date
2026-06-26
Estimated Expiration
2043-07-18

AI Technical Summary

Technical Problem

In existing distributed autonomous navigation constellations, the unobservable rotation of the constellation's inertial space leads to changes in orbital orientation parameters, causing the constellation's reference to rotate as a whole. Existing correction methods increase inter-satellite communication pressure or disrupt the constellation's autonomous operation capabilities.

Method used

Each satellite calculates its own orbital plane orientation error and distributes it to visible satellites. The local constellation rotation is fitted, virtual observation condition constraint equations are constructed, and satellite orbits are solved by filtering to suppress the overall constellation rotation effect.

Benefits of technology

Without increasing the pressure on inter-satellite data exchange and communication, improve the accuracy of satellite distributed autonomous orbit determination and maintain the constellation configuration stably in the long term.

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Abstract

The application relates to a rotation error correction method of a distributed autonomous navigation constellation, and comprises the following steps: S1, each satellite calculates the orbit plane orientation error of the satellite in orbit and distributes the result to all visible satellites in the constellation in real time; S2, each satellite fits a local constellation rotation quantity according to the orbit plane orientation error of the satellite and the collected orbit plane orientation error; S3, each satellite determines a virtual satellite orbit observation quantity according to the local constellation rotation quantity of the satellite; S4, each satellite constructs a conditional constraint equation of virtual observation according to the virtual satellite orbit observation quantity and the second type of non-singularity orbit root number; and S5, each satellite solves the satellite orbit through filtering according to the conditional constraint equation of virtual observation, so that the overall rotation effect of the constellation is inhibited and corrected. The application can inhibit the rotation effect of the constellation, improve the distributed autonomous orbit determination precision of the satellite, does not increase the inter-satellite data interaction communication pressure, and can stably maintain the constellation configuration for a long time.
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