Combustion speed testing method for gel propellant

A technology of gel propellant and test method, which is applied in the direction of chemical analysis by combustion, etc., can solve the problems of long test period, large number of samples required for test, cumbersome operation steps, etc., and achieve the effect of easy promotion and simple preparation

Inactive Publication Date: 2014-02-26
XIAN MODERN CHEM RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The purpose of the present invention is to provide an efficient and fast test method for the burning rate of gel propellant, which can solve the problems of long test period, cumbersome operation steps and the need for a large number of samples in the traditional test method for the burning rate of gel propellant. question

Method used

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  • Combustion speed testing method for gel propellant
  • Combustion speed testing method for gel propellant
  • Combustion speed testing method for gel propellant

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0062] For a certain formulation of nano aluminum powder gel propellant at room temperature, the burning rate measured at 7MPa is as follows:

[0063]

[0064] After selection by Grubbs method, 4 valid data are obtained. The average burning speed is 12.559mm / s calculated by formula (2), and the standard deviation S is calculated by formula (3) u =0.0864, ​​the relative standard deviation (coefficient of variation) C is calculated by formula (4) v =0.69%, the combustion speed at this pressure can be expressed as 12.559±0.137mm / s from the formula (5).

Embodiment 2

[0066] For a certain hand-mixed gel propellant, the initial pressure was tested at room temperature at 4MPa, 7MPa, 10MPa, and 13MPa. The average burning rate was calculated from equation (2). The specific values ​​are shown in the following table:

[0067]

[0068] Substituting the values ​​in the table into equation (7), the burning rate pressure index is calculated to be 0.560, and the constant term is calculated as 3.621 when substituting into equation (8). According to formula (6), the burning rate-pressure relationship of this formulation gel propellant in the range of 4~13MPa can be expressed as U=3.621P 0.560 .

Embodiment 3

[0070] For a certain high-energy gel propellant, the initial pressure is constant at 7MPa, and the initial temperature of the test sample is the burning rate of -40℃, 20℃ and 50℃ respectively. The average burning speed is calculated by formula (2). The specific values ​​are as follows Shown:

[0071]

[0072] Substituting the values ​​in the table into equation (10), the temperature sensitivity coefficient of the burning rate of the gel propellant when the pressure is 7MPa is calculated to be 9.551×10 -4 / ℃. Reference temperature T 0 Take it as 20°C and substitute it into formula (8) to calculate the corresponding constant term as 1.289. According to formula (9), the gel propellant of this formula is at 7MPa, the reference temperature T 0 Is the burning rate at 20℃—the initial temperature relationship can be expressed as u=1.289e 0.000955(T-20) .

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Abstract

The invention discloses a combustion performance testing method for a gel propellant. The method comprises the following steps: directly taking a prepared gel propellant as a sample to be tested and injecting the sample into a thin-wall straight plastic pipe of which the inner diameter is 8mm-10mm and one end is closed to prepare a powder pipe to be detected; fixing the powder pipe to be detected on a powder rack of a combustion room; placing ignition powder on one unclosed end and fixing by using a nickel-chrome wire; coating an end face by using a coating agent; and putting the powder rack of the combustion room, which carries the fixed powder pipe to be detected, into an underwater acoustic emission combustion speed meter to test a combustion speed and finally calculating an average combustion speed, a combustion speed pressure index and a combustion speed temperature sensitivity coefficient. The method is simple and easy to operate and short in testing period, and can rapidly and accurately test the combustion performance of the gel propellant.

Description

Technical field [0001] The invention relates to a method for testing the burning rate of gel propellant. Background technique [0002] The burning rate of the propellant refers to the distance of the disappearance of the solid phase in the normal direction of the solid propellant surface per unit time, referred to as the burning rate of the solid propellant. It determines the energy release rate of the solid propellant and is also the core parameter for calculating other combustion properties of the solid propellant (burning rate pressure index, burning rate temperature sensitivity coefficient, erosion ratio, etc.). Regardless of the changes in pressure, initial temperature, airflow velocity and other influencing factors during combustion, they will eventually be reflected in the changes in burning rate. In addition, it also directly affects the ballistic performance, flight speed and working stability of the rocket engine. Therefore, the burning rate of solid propellant is one...

Claims

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Application Information

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IPC IPC(8): G01N31/12
Inventor 裴庆赵凤起徐司雨仪建华姚二岗郝海霞高红旭安亭肖立柏
Owner XIAN MODERN CHEM RES INST
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