Burning surface identification-based solid propellant burning rate identifying method

Abstract

The invention relates to a burning surface identification-based solid propellant burning rate identifying method. The method comprises the following steps: designing a propellant with three different diameters, and carrying out combustion test; knowing the current burning surface area according to the time and the pressure of three different burning propellant web propellant s in recorded pressure-time curves and the remaining shape; and solving the instantaneous burning rates of four characteristic points by combining the pressure-time curves obtained through the test with an engine balance pressure expression to obtain the burning rate expression of three segments AB, BC and CD in different pressure ranges, and carrying out burning rate identification. The method has the following advantages: the tree curves are obtained by one-shot test in to carry out identification in order to obtain three burning rates, so the efficiency is increased, and the cost is reduced; the burning rates are solved through combining the identification of the burning surface with the test pressure-time curves, so the method is simple, can be easily known; and the method has wide applicability, and can realize the measurement of the burning rates under different test pressures by changing the sizes of a propellant grain and a jet tube.

Description

technical field [0001] The invention belongs to the research category of aerospace propulsion technology, and relates to a method for identifying the burning rate of solid propellant based on a burning surface mark. Background technique [0002] The burning rate of solid propellants is an important parameter in the design and performance analysis of solid rocket motors, and it is also one of the main indicators that need to be strictly controlled in the propellant formulation design and production process. The measurement of burning rate plays an important guiding role in the design improvement of the whole engine. Generally speaking, the burning rate refers to the linear burning rate, that is, the distance that the solid phase disappears along the normal direction of the propellant burning surface per unit time. (thickness of meat burnt per unit time) indicates that the empirical formula of burning rate commonly used in the industry is r=ap n (a, n are constants measured...

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Problems solved by technology

[0009] In order to avoid the deficiencies of the prior art, the present invention proposes a solid propellant burning rate identification method based on the burning surface mark to solve the shortcomings of the current solid propellant burning rate measurement method (the target line method cannot truly simulate the engine working process Practical environmental issues for medium propellants

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