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Impulse method solid propellant burning rate test original experiment data validity determination method

A technology of solid propellants and experimental data, applied to jet propulsion devices, rocket engine devices, machines/engines, etc., to achieve the effect of ensuring consistency and effectiveness

Active Publication Date: 2021-06-29
NORTHWESTERN POLYTECHNICAL UNIV +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

But how to determine the ignition synchronization and whether there is erosion combustion is not mentioned in the above two papers

Method used

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  • Impulse method solid propellant burning rate test original experiment data validity determination method
  • Impulse method solid propellant burning rate test original experiment data validity determination method
  • Impulse method solid propellant burning rate test original experiment data validity determination method

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specific Embodiment

[0041] The method of the invention is used to analyze and judge the test data of different solid propellants, and select the solid propellant with excellent performance.

[0042] 1. Measure the shape of the solid propellant to be tested. Since the shape of the propellant used is a tubular grain, it is necessary to record the inner and outer diameters, length, and diameter of the nozzle, as shown in Table 1, which are the size parameters of different propellants.

[0043] Table 1 Size parameters of triple-engine double-base propellant

[0044]

[0045] 2. Cover the outer surface and end surface of the solid propellant grain to be tested according to the requirements, leaving only the inner surface as the initial burning surface.

[0046] 3. Freely fill the solid propellant coated as required in the combustion chamber of the rocket engine. Connect the ignition circuit and confirm that the circuit connection is correct, start the ignition button, and observe the real-time cha...

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Abstract

The invention discloses an impulse method solid propellant burning rate test original experiment data validity determination method. The boundary dimension of a tubular grain of a solid propellant is recorded, the outer surface and the end surface of the tubular grain are coated, and only the inner surface is reserved as an initial burning surface; then the tubular grain is filled in a combustion chamber of a solid rocket engine; and the solid rocket engine is ignited, the combustion pressure intensity and the generated thrust in the working process of the solid rocket engine are recorded, a pressure intensity and thrust time curve is drawn on a same graph, the pressure intensity and thrust time curve are analyzed, and the effectiveness of a thrust curve is judged, namely judging whether the ignition is synchronous and erosive combustion exists or not. Technical guarantee is provided for specific implementation of the impulse method and mass flow rate method burning rate testing technology, and consistency and effectiveness of testing results are guaranteed.

Description

technical field [0001] The invention belongs to the technical field of rocket engines, and in particular relates to a method for judging the validity of experimental data. Background technique [0002] The burning rate of solid propellant is a basic parameter in rocket engine design and an important parameter to predict the ballistic performance of the engine. The definition of burning rate is the distance that the propellant charge burning surface recedes along its normal direction per unit time, referred to as the burning rate of solid propellant. It not only directly determines the energy release rate of solid propellants, but also calculates other combustion properties of solid propellants, such as burning rate coefficient, burning rate pressure index, burning rate temperature sensitivity coefficient, erosion ratio and other core parameters. [0003] In March 2019, the "Journal of Propellant and Explosives" paper "Impulse method to test the high-pressure dynamic burning...

Claims

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Application Information

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IPC IPC(8): F02K9/96F02K9/95F02K9/08F02K9/24
CPCF02K9/96F02K9/95F02K9/08F02K9/24
Inventor 王英红张鑫鹏唐红梅吴世曦杨虹
Owner NORTHWESTERN POLYTECHNICAL UNIV
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