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Method for identifying combustion end of solid-propellant rocket engine in real time

A technology of solid rockets after combustion is completed, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc., and can solve problems such as misjudgments that are prone to occur

Inactive Publication Date: 2011-01-05
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

This method is simple and easy to implement, but when the equilibrium pressure of the combustion chamber deviates from the design value, it is easy to misjudgment

Method used

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  • Method for identifying combustion end of solid-propellant rocket engine in real time
  • Method for identifying combustion end of solid-propellant rocket engine in real time
  • Method for identifying combustion end of solid-propellant rocket engine in real time

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Abstract

The invention relates to a method for identifying the combustion end of a solid-propellant rocket engine in real time, which is characterized by collecting the pressure of a combustor in the experiment process of the solid-propellant rocket engine, performing low pass filtering to P0 (delta t) by using a second-order Butterworth method, calculating first-order difference and second-order difference to obtain a first-order derivative processing result and a second-order derivative processing result, and determining the combustion end of the engine together. The method for identifying the combustion end of solid-propellant rocket engine in real time is simple and easy to realize and is not easy to lead to misjudgment.

Description

A real-time method for identifying the end of solid rocket motor combustion technical field The invention relates to a solid rocket motor experimental data processing, in particular to a method for real-time identification of the combustion end of the solid rocket motor. Background technique The combustion end time of solid rocket motor is an important moment in the working process of the solid rocket motor. It is of great significance whether it is used for the calculation of engine performance parameters or for the control of the working process of the engine. Therefore, it is an important task in data processing of engine experiments to correctly identify the combustion end time of solid rocket motors. The solid rocket motor test data processing specification QJ1047-92 gives a method of using double tangents to judge the combustion end time of the rocket motor, but this method can only be applied to the data readback analysis after the end of the engine experiment, and ...

Claims

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Application Information

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IPC IPC(8): F02K9/96
Inventor 吕翔李江魏祥庚刘洋秦飞徐开民
Owner NORTHWESTERN POLYTECHNICAL UNIV
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