Spacecraft relative position correction method based on single-satellite angle measurement information

By performing projection transformations and Jacobian matrix operations between different coordinate systems and utilizing the geometric relationship between the spacecraft and the space target, the distance ambiguity problem of relative position correction under single-satellite angle measurement information was solved, achieving efficient relative position correction and avoiding non-convergence of state estimation and fuel consumption.

CN122149524APending Publication Date: 2026-06-05SHANGHAI AEROSPACE CONTROL TECH INST
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Patent Information

Application Number
CN202610152764.5
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2026-02-03
Publication Date
2026-06-05

AI Technical Summary

Technical Problem

Existing technologies cannot accurately calculate the relative positional relationship between a spacecraft and a space target using single-satellite angle measurement information, resulting in the inability to obtain accurate relative position correction results. Furthermore, traditional methods suffer from high fuel consumption, orbital deviation, and non-convergence of state estimation.

Method used

By performing projection transformation between different coordinate systems, utilizing the geometric relationship between the spacecraft and the orbit of the space target, and combining the Moore-Penrose inverse and inverse operation of the Jacobian matrix, the error correction of the relative position of the spacecraft is performed, thus solving the distance ambiguity problem under single-star angle measurement information.

Benefits of technology

It achieves a unique relative position correction result, avoids the problem of non-convergence in state estimation, reduces computational steps, and improves computational efficiency.

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Abstract

A spacecraft relative position correction method based on single-satellite angle measurement information comprises the following steps: (1) recurring a target position of a space target in a J2000 system based on initial orbit determination information; (2) calculating an estimated value of a relative position of two satellites under a target VVLH coordinate system; (3) judging whether a relative position full-component error correction condition is met or not; if the correction condition is met, executing the step (4); otherwise, executing the step (5); (4) based on the estimated value of the relative position and the measured value of the sight angle of the spacecraft, calculating a Moore-Penrose inverse matrix of the observed quantity relative to a first Jacobian matrix of the relative position, and calculating a correction value of the relative position of the spacecraft and the space target to complete correction of the relative position of the spacecraft; and (5) calculating an inverse matrix of the observed quantity relative to the second jacobian matrix of the relative position based on the estimated value of the relative position and the measured value of the sight angle of the spacecraft, and calculating X-axis and Z-axis correction values of the relative position of the spacecraft and the space target to complete the correction of the relative position of the spacecraft.
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