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Liquid rocket engine data curve analysis method

A liquid rocket, data curve technology, applied in the direction of engine testing, complex mathematical operations, machine/structural component testing, etc., can solve the problems of deviation of test data, unable to reflect the working conditions of the engine, etc., to achieve the effect of improving accuracy

Pending Publication Date: 2022-04-29
XIAN AEROSPACE PROPULSION TESTING TECHN INST
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to solve the technical problem that the test data deviates greatly or cannot reflect the real working conditions of the engine due to environmental factors in the existing liquid rocket engine test process, the invention provides a liquid rocket engine data curve analysis method

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  • Liquid rocket engine data curve analysis method
  • Liquid rocket engine data curve analysis method
  • Liquid rocket engine data curve analysis method

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Embodiment Construction

[0051] The content of the present invention will be further described in detail below in conjunction with specific embodiments.

[0052] The liquid rocket engine test evaluates the state of the test system and product performance through real-time and effective processing, analysis and display of data. During the process, the test curve is drawn in real time, which can provide reliable basis for the test personnel to make real-time judgments and forecasts . The invention compares the measured data of the key parameters with the preset standard theoretical curve, directly reflects the deviation between the measured data and the theoretical design data of the liquid rocket engine test, and can accurately evaluate the state and performance of the test system.

[0053] A kind of liquid rocket engine data curve analysis method of the present invention comprises the following steps:

[0054] 1) Obtain preset data

[0055] 1.1) The key to the preset of the standard curve is to dete...

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Abstract

The invention provides a liquid-propellant rocket engine data curve analysis method, and solves the problem that test data are greatly deviated or the real working condition of an engine cannot be reflected due to the influence of environmental factors in a liquid-propellant rocket engine test process. The method comprises the following steps: 1) acquiring preset data; 2) obtaining a linear regression equation; 3) in a liquid rocket engine test process, non-random factors X1 ', X2',..., Xp-1 'and dependent variables Y' are measured in real time; drawing corresponding curves of different time t and Y ', and recording measured data curves; according to real-time measurement of X1 ', X2',..., Xp-1 'and a linear regression equation, corresponding dependent variables Y ''are obtained; drawing a corresponding curve of different time t and Y '', and recording the curve as a standard theoretical data curve; and comparing the measured data curve with the standard theoretical data curve, and analyzing the deviation between the measured data and the theoretical data of the liquid rocket engine test.

Description

technical field [0001] The invention relates to liquid rocket engine test technology, in particular to a liquid rocket engine data curve analysis method. Background technique [0002] The liquid rocket engine test is to evaluate the state and performance of the test system through real-time and effective processing, analysis and display of data. The real-time curve interpretation of the test system is the direct basis for judging the engine test performance, and the real-time curve is drawn through the test data. Due to the harsh test environment of the liquid rocket engine, the test process will be accompanied by various factors such as high pressure, vacuum, high temperature, ultra-low temperature, large vibration, strong corrosion, electromagnetic interference, etc. Multi-field coupling is the main factor affecting the accuracy of the on-site test of the main parameters of the engine. Under harsh environmental conditions, the test data may deviate greatly or cannot refle...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/00G06F17/16G06F17/18
CPCG01M15/00G06F17/16G06F17/18
Inventor 徐峰唐云龙胡瑛史雪梅刘晓朱成亮陈海峰刘英元
Owner XIAN AEROSPACE PROPULSION TESTING TECHN INST