A process noise adaptive satellite autonomous continuous maneuver orbit determination method

CN122110165BActive Publication Date: 2026-10-16HUANTIAN SMART TECH CO LTD +1
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Patent Information

Application Number
CN202610183074.6
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2026-02-09
Publication Date
2026-10-16
Estimated Expiration
2046-02-09

AI Technical Summary

Technical Problem

[0008]针对现有卫星机动定轨方法中动态场景下噪声协方差固定的问题，本发明提出了一种过程噪声自适应的卫星自主连续机动定轨方法，以无迹粒子滤波为基础框架，引入一种基于新息的自适应过程噪声协方差调整策略，使滤波器能够实时感知系统动态变化，动态调整模型参数，从而在非机动和连续机动阶段实现高精度、高鲁棒性的轨道确定

Benefits of technology

[0044] (1) This invention addresses the model mismatch problem in satellite maneuvering scenarios, achieving rapid and accurate adaptive correction. Unlike traditional adaptive methods targeting measurement noise, this invention innovatively identifies the process noise covariance matrix as the core object of adaptive adjustment, directly addressing the abrupt changes in the system dynamics model caused by thruster operation during satellite maneuvers. By introducing a forgetting factor to calculate the weighted innovation norm and setting upper and lower thresholds for segmented adjustment, a step-like rapid response to sudden maneuvers is achieved. This allows the filter to rapidly increase process noise to match the model's uncertainty, preventing divergence caused by the accumulation of estimation bias. During non-maneuvering phases, it maintains relatively low process noise, thereby ensuring high-precision orbit determination. This targeted design overcomes the shortcomings of traditional methods, such as slow response or misjudgment during maneuvers.

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Abstract

The application provides a satellite autonomous continuous maneuvering orbit determination method with adaptive process noise, and aims at the problem of orbit determination accuracy reduction of a satellite in a maneuvering process.The method is based on innovation, and adaptively adjusts process noise in a non-maneuvering stage and a maneuvering stage, so that the estimation accuracy reduction problem caused by fixed noise parameters is solved, and the filter can more accurately represent the dynamic state of the system.In a Gaussian noise, compared with a traditional unscented particle filter, the APNUPF exhibits better orbit determination accuracy during the maneuvering, and even if the state mutates, the APNUPF can still maintain high-precision orbit determination.In addition, in order to meet the actual engineering requirements, the robustness and reliability of the method for satellite autonomous continuous maneuvering orbit determination are comprehensively verified under non-Gaussian noise conditions.
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