A solid rocket engine erosion combustion rapid parameter identification method

Abstract

The invention discloses a solid rocket engine erosion combustion rapid parameter identification method, and the method comprises the steps of carrying out an ignition test on a designed standard erosion engine and a standard erosion propellant grain, and obtaining a test pressure intensity curve with erosion pressure intensity peak characteristics; and giving a group of erosion parameters, and substituting the group of erosion parameters into the one-dimensional erosion internal ballistic calculation model to obtain a theoretical pressure intensity curve, and making a curve residual between the test pressure intensity curve and the theoretical pressure intensity curve, and judging whether the curve residual meets the residual requirement or not. And if the requirement is met, outputting the erosion parameter in the erosion inner ballistic calculation as an identification result, and ending the identification calculation; if the curve residual does not meet the requirement, updating anerosion parameter given by iteration through an algorithm, performing inner ballistic calculation again, calculating the curve residual, and judging whether the curve residual meets the requirement ornot; and completing the rapid parameter identification of the erosion combustion after the iteration is ended. The identification method is wide in application, and the erosion parameters of different propellants can be identified.

Description

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AI Technical Summary

Benefits of technology

This patented technology allows researchers to quickly identify which type or model of fuel used in their experiments on an engine's performance. It does this without requiring expensive equipment that requires complicated testing systems.

Problems solved by technology

This patented technical problem addressed in the patents describes how to accurately identify eroded or combusted materials during flight operations without causing damage from excess heat generated due to their own weight. Current techniques involve analyzing static electricity behavior under specific conditions but they require expensive equipment that cannot be easily adapted into different types of aircraft models. There is an urgent demand for improved analysis tools to help predict failures caused by these processes while reducing costs associated with testing them.

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