An engine fuel rate model correction method under overload conditions and related equipment

By constructing a fluid-structure interaction overload combustion rate calculation model, the problem of insufficient combustion rate prediction under complex overload conditions in existing models is solved, achieving high-precision combustion rate correction and improved model applicability, supporting engine performance analysis and safety assessment under high overload environments.

CN122174589APending Publication Date: 2026-06-09BEIJING INST OF TECH
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
BEIJING INST OF TECH
Filing Date
2026-02-10
Publication Date
2026-06-09

AI Technical Summary

Technical Problem

Existing overload combustion rate models lack applicability and prediction accuracy under different propellant formulations and complex overload conditions, making it difficult to efficiently address the strong coupling effects of multiple physics fields during combustion through engine testing.

Method used

A fluid-structure interaction (FSI) overload combustion rate calculation model is constructed, including gas phase flow control equations, a fluid-structure interaction heat transfer model, a discrete phase particle motion model, and a particle impact heat transfer model. Overload acceleration is introduced as a source term, and numerical simulation calculations are performed to correct the traditional combustion rate model to reflect the actual gas density and particle collision heat feedback.

Benefits of technology

It improves the accuracy and reliability of burning rate prediction under high overload conditions, reduces the number of tests and costs, enhances the applicability and generalization ability of the model under different operating conditions, and supports internal ballistic performance analysis and structural safety assessment of engines.

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Abstract

This invention discloses a method and related equipment for correcting an engine combustion rate model under overload conditions, relating to the field of rocket engines. The method first constructs a fluid-structure interaction (FSI) overload combustion rate calculation model incorporating an overload inertial force source term, comprehensively considering gas flow, fluid-structure interaction heat transfer, discrete phase particle motion, and particle impact heat transfer effects. Subsequently, numerical simulations are conducted within a preset overload range to obtain gas density, propellant burner surface temperature, and particle collision heat transfer parameters. Based on this, propellant combustion rate data is calculated using burner surface temperature, particle thermal feedback, and gas density. This combustion rate data is then used to correct the parameters of the traditional combustion rate model, establishing an overload combustion rate correction model that considers the influence of actual gas density. This method can significantly reduce combustion rate prediction errors under high overload conditions, improving the accuracy and engineering applicability of predicting engine internal ballistic performance under overload conditions.
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