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Method for determining reaction kinetic parameters of lining and interface of solid propellant

A kinetic parameter, solid propellant technology, applied in measurement devices, scientific instruments, material analysis by optical means, etc., can solve problems such as no application technology and published literature reports, and achieve the elimination of specific sample defects and easy operation. , the effect of the simple method

Inactive Publication Date: 2015-01-14
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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AI Technical Summary

Problems solved by technology

[0003] In the prior art, there are no mature application technologies and published literature reports on the chemical reaction kinetics of the liner / propellant interface, liner or insulation layer related components to the adhesive and curing agent system

Method used

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Embodiment Construction

[0010] The present invention will be further described in two groups below in conjunction with the embodiments.

[0011] The first group is the detection of kinetic parameters of the interfacial curing reaction between the butyl hydroxyl liner and the nitrate plasticized polyether (NEPE) propellant.

[0012] Step 1, sample preparation: curing reaction of hydroxybutylene lining layer Sample preparation: according to the curing parameter R=1.0, R is the ratio of isocyanate group to hydroxyl group, weigh 50g of hydroxyl-terminated polybutadiene adhesive (HTPB) and toluene diisocyanate curing agent (TDI), after rapid stirring, divide them into 5 parts, each weighing 10g, add 0.5% by weight of curing catalyst and 1-5% by weight of other formulation components in the liner or heat insulation layer , continue to mix and place in a constant temperature oven at a certain temperature for curing reaction.

[0013] Step 2, condition selection: use an infrared spectrometer, the detection ...

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Abstract

The invention relates to a method for determining reaction kinetic parameters of a lining and an interface of a solid propellant, belonging to technology for evaluating reliability of a lining of a rocket motor and an interface of a propellant. The method comprises the detection steps of sample preparation, condition selection, detection, data processing and evaluation analysis; a detection object is a tested sample of the lining or a propellant binder, an isocyanate group and a methylene group; the detection condition is a curing reaction of a binder system and a curing agent; and the detection process comprises the steps of detecting a measuring peak, a reference peak, absorbance, an absorbance ratio, an absorbance ratio in a starting period, and an absorbance ratio in a t period. According to the invention, a smear infrared spectroscopic transmission analytical method is adopted to detect bonding chemical reaction kinetics of the lining / propellant interface, and the impact degree of components of the propellant on the interface main reaction kinetics is qualitatively and quantitatively judged based on a curing reaction rate constant through data processing and evaluation analysis. The method also has the advantages of simplicity, convenience in operation, expense saving and accurate data.

Description

technical field [0001] The invention relates to a solid rocket motor liner and propellant interface reliability evaluation technology, in particular to a solid propellant liner and interface reaction kinetic parameter determination method. Background technique [0002] Among the bonding interfaces of shell-bonded charges, the liner / propellant interface is the weakest bonding interface, and it is also the bonding interface most likely to cause interface debonding failure in solid rocket motors. In the bonding interface area, the cross-reaction between the hydroxyl group of the adhesive phase in the liner and the propellant and the isocyanate group of the curing agent is the main chemical reaction of the interface bonding, such as the hydroxyl-terminated polybutadiene in the butylated hydroxyl liner ( HTPB) with toluene diisocyanate (TDI). The reaction between other hydroxyl and amino group-containing components in the lining or thermal insulation layer and the curing agent i...

Claims

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Application Information

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IPC IPC(8): G01N21/3563
Inventor 庞爱民徐胜良胡伟马新刚黄志萍章园园蔡如琳赵志刚吴倩
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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