Multi-information-based engine fault fusion discrimination method

By adopting a multi-information-based fault fusion discrimination method in rocket engines, using angular velocity, apparent acceleration and other characteristic information for thrust identification, the problem of online diagnosis of rocket engine faults outside the atmosphere is solved, and high-reliability fault diagnosis is achieved.

CN119935556APending Publication Date: 2025-05-06BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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Patent Information

Application Number
CN202411928284.0
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-12-25
Publication Date
2025-05-06

AI Technical Summary

Technical Problem

There are challenges in online diagnosis of rocket engine faults outside the atmosphere, and the prior art is difficult to effectively solve this problem.

Method used

The engine fault fusion judgment method based on multiple information is adopted, and the angular velocity and apparent acceleration information are obtained through the control system, combined with the engine installation angle, swing angle and mass characteristic information, the engine thrust is identified online, and the thrust information provided by the power system is verified to verify the fault fusion judgment.

Benefits of technology

It realizes effective online diagnosis of rocket engine faults, improves the reliability and accuracy of fault diagnosis, and can detect and diagnose engine faults in real time after flying out of the atmosphere.

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Abstract

The invention discloses an engine fault fusion discrimination method based on multi-information, and the method comprises the steps: a control system obtains the centroid and centroid motion parameters of a rocket through a strapdown inertial measurement unit, and obtains the angular velocity and apparent acceleration of three axes through the collection, conversion and calculation of signals; and obtaining angular acceleration information by using the angular velocity based on an extended state observer. Meanwhile, thrust is identified on line through engine installation angle information, real-time swing angle information and quality characteristic information of the rocket, and engine faults are diagnosed in real time in combination with thrust information provided by an engine power system.
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