Method for testing combustion speed of NEPE (nitrate ester plasticized polyether) solid propellant

A solid propellant, burning rate technology, applied in the direction of measuring devices, material analysis through optical means, instruments, etc., can solve the problems of long curing process, solid propellant slurry to judge the burning rate of solid propellant, etc., to save samples Test time, overcoming the long time-consuming curing molding, the effect of convenient and quick detection method

Inactive Publication Date: 2017-09-01
XIAN AEROSPACE CHEM PROPULTION PLANT
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AI Technical Summary

Problems solved by technology

[0005] In order to overcome the long curing process in the prior art and the inability to judge the burning rate of solid propellan

Method used

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  • Method for testing combustion speed of NEPE (nitrate ester plasticized polyether) solid propellant
  • Method for testing combustion speed of NEPE (nitrate ester plasticized polyether) solid propellant

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Experimental program
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Embodiment Construction

[0049]The invention is a method for testing the burning rate of NEPE solid propellant

[0050] Step 1, determine the near-infrared spectroscopy data acquisition parameters.

[0051] The near-infrared spectroscopy data acquisition parameters are determined by testing NEPE solid propellant slurry. The specific process is:

[0052] Take 5-10 parts of NEPE solid propellant slurry; carry out near-infrared spectrum test on said 5-10 parts of NEPE solid propellant slurry one by one, and obtain a set of near-infrared spectrum test curves. In the test, each NEPE solid propellant slurry was scanned in the full band in turn; the number of scans for each NEPE solid propellant slurry was selected as 50 times, 100 times, 120 times, 160 times, and 200 times. The resolution of one scan is 2cm -1 、4cm -1 、8cm -1 ; The number of scans is orthogonally matched with the resolutions.

[0053] A group of near-infrared spectrum test curves obtained is compared, and the parameters of the near-in...

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Abstract

The invention relates to a method for testing combustion speed of an NEPE (nitrate ester plasticized polyether) solid propellant. The method comprises the following steps of testing the data of a near-infrared spectrum map of a standard product; after processing by a spectrum pre-processing method, determining the relationship between the data of the near-infrared spectrum of the standard product and the combustion speed of the NEPE solid propellant. The method has the advantages that the sample curing process is reduced in the testing process, and the sample testing time is effectively shortened; when the combustion speed of the NEPE solid propellant is detected, the high-efficiency and non-destructive analyzing purpose is realized, the defect of long curing and forming time in the traditional testing process is thoroughly overcome, and a convenient and rapid detection method is provided for the production quality and safety manufacturing of the NEPE solid propellant.

Description

technical field [0001] The invention relates to the field of solid propellants, in particular to a near-infrared spectrum analysis method for the burning rate of NEPE solid propellants. Background technique [0002] The NEPE solid propellant is a nitrate plasticized polyether propellant. [0003] The NEPE solid propellant combustion is characterized by the retreat of its surface after the initiation of combustion. The burning rate is defined as the normal distance that the flame front moves on the burning surface per unit time. The burning rate of solid propellant is the main index to characterize solid propellant, and its burning rate directly affects the performance of the product. The burning rate test methods are divided into the rod burner method, the liquid filled rod burner method and the ultrasonic method. The stick burner method is to burn a small propellant sample of standard size (hereinafter referred to as the stick) in a constant pressure burner, and wrap the...

Claims

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Application Information

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IPC IPC(8): G01N21/359G01N21/3563
CPCG01N21/3563G01N21/359
Inventor 郭培培杨英郭琪阎京文
Owner XIAN AEROSPACE CHEM PROPULTION PLANT
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