Real-time orbit determination method for low-orbit satellite based on particle filtering

By adopting particle filtering based on satellite orbit technology, the observation and overpowering model is constructed and particle filter updates are performed, the problem of insufficient non-Gaussian noise processing capabilities in the existing technology is solved, and higher positioning accuracy and faster convergence speed are achieved.

CN119738848AInactive Publication Date: 2025-04-01TIANJIN YUNYAO AEROSPACE TECH CO LTD +2
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Patent Information

Application Number
CN202510251707.8
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-03-05
Publication Date
2025-04-01
Estimated Expiration
Not applicable · inactive patent

AI Technical Summary

Technical Problem

The existing satellite real-time orbit fixed-orbit technology has deteriorated performance when facing non-Gaussian noise, insufficient positioning accuracy and slow convergence speed. Especially on the computing platform of ARM architecture, the calculation rate is insufficient, and the expansion Kalman filtering lacks description of the nonlinear part, resulting in large tracking errors.

Method used

The real-time orbit fixed-orbit method of low-orbit satellites based on particle filtering is adopted. By constructing an observation model and an overpowering model, geometric single-point orbit fixed-orbit and filter initialization are carried out, relative dynamic orbit integrals are calculated, carrier phase double-difference relative positioning is performed, and particle filters are updated to dynamically adjust the particle swarm distribution to ensure the continuous stability of state estimation.

Benefits of technology

It improves positioning accuracy and convergence speed, can effectively deal with non-Gaussian noise, dynamically adjusts the particle swarm distribution to ensure the continuous stability of state estimation, and significantly improves the accuracy and real-time performance of satellite orbiting.

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Abstract

The present invention provides a real-time orbit determination method for low-orbit satellites based on particle filtering, comprising the following steps: data acquisition and preprocessing; constructing an observation model; constructing a perturbation force model; geometric single-point orbit determination and filter initialization; relative dynamic orbit integration; carrier phase double-difference relative positioning; particle filter update; orbit interpolation and release. Beneficial effects of the present invention: The present invention achieves technical breakthroughs in the two dimensions of positioning accuracy and convergence speed. Its core advantage comes from the natural adaptability of particle filtering to nonlinear systems and non-Gaussian noise. Through the discretization characterization of probability density functions, it effectively overcomes the problem of decreased calculation accuracy of the Kalman filter series methods in non-Gaussian noise environments. In particular, when the satellite is subject to sudden changes in atmospheric perturbations or intermittent interference in onboard observation equipment, the constructed hybrid suggestion distribution function can dynamically adjust the distribution of the particle swarm to ensure the continuous stability of state estimation.
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