Combustion rate calculation method for tubular propellant powder in permeation process

Abstract

The invention discloses a combustion rate calculation method for tubular propellant powder in a permeation process. The combustion rate calculation method is suitable for calculation of the combustion rate of the tubular propellant powder in the permeation process. According to the invention, different process methods of permeating liquid components into solid are adopted, and a permeation distribution function is adopted for representation, so that the influence of process parameters is removed, and combustion characteristic representation of propellant powder with any multiple permeation components can be realized; energy calculation is directly carried out by adopting a mode of combining inner and outer layer osmotic distribution functions with a new formula formed by grouping homogeneous propellant powder components, so that gunpowder forces at different distribution positions of the tubular propellant powder can be accurately obtained; a calculation method for dividing a permeable layer and a homogeneous layer into two charge shape functions is adopted, and the physical process of combustion of the non-completely parallel layer can be well described. The invention solves the problem of accurate calculation of the burning rate of the tubular propellant powder in the permeation process, and provides a technical means for calculating the burning rate of the tubular propellant powder in the permeation process.

Description

Technical field [0001] The present invention relates to the field of launching drugs, and more particularly to the calculation of the combustion rate of the emission, and it is specifically involved in a tubular emission drug prepared by the permeation process, and it is possible to implement the calculation of its combustion. Background technique [0002] Tubular launcosts are mainly used in small diameter weapons or weapons that require low pressure velocked drugs, as well as the central air-fired drug bundle. In order to reduce the initial combustion pressure of the tubular launcher, increase its energy or combustion increasing increase, usually need to post treatment of tubular emission drugs, generally using deep blunt or impregnated high-energy components, the common characteristics of these methods are adopted Liquid function reagent is permeated by the molded tubular emitter, and then subsequent processes such as drying, the tubular emission drug using such a penetration ...

AI Technical Summary

Problems solved by technology

The current calculation methods for the burning rate of tubular propellants in the infiltration process mainly include: (1) average the characteristics of the different components of the propellant, and treat the tubular propellant in the infiltration process as a macroscopically uniform substance, which is obviously different from the composition of the actual substance (2) Each component is represented by an approximate function related to the penetration depth, and the parameters of the total component are considered to be the sum of the parameters of each component. Although this method takes into account The distribution of permeable substances, but the method of parameter summation cannot obtain more reliable results. For example, the oxygen balance of different components is different, and the gunpowder power is also different. After mixing two components with one positive and one negative oxygen balance, use gunpowder The gunpowder power obtained by calculating the two separate components by the force addition method is smaller than the actual gunpowder power, because in the actual combustion process, the two substances will participate in the combustion at the same time, the oxygen will be effectively used, and there will be no combination The combustion product of one component is in positive oxygen balance, and the combustion product of another component is in negative oxygen balance; (3) The powder shape parameter of the propellant is regarded as a constant parameter, which conforms to the average material from the beginning of combustion to the completion of combustion. The law of parallel layers of combustion is obviously different from the actual situation. The composition and burning rate of tubular propellants vary with the arc thickness of the infiltration process.

Therefore, the existing calculation method cannot obtain the burning rate of the tubular propellant of the infiltration process well.

[0003] From the technical information retrieved so far, there is no calculation method for the burning rate of tubular propellant in the infiltration process that can consider the distribution of penetration depth of components, the performance of propellant parameters and the change of drug shape.

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