Combustion rate calculation method of permeation process girdling rod-shaped propellant powder

Abstract

The invention discloses a combustion rate calculation method for a permeation process girdling rod-shaped propellant powder, which is suitable for calculation of the combustion rate of the permeation process girdling rod-shaped propellant powder. According to the method, 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 permeation distribution functions with a new formula formed by grouping homogeneous propellant powder components, so that gunpowder forces at different distribution positions of the girdling rod-shaped 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. According to the method, the problem of accurate calculation of the burning rate of the permeation process girdling rod-shaped propellant powder is solved, and a technical means for calculating the girdling rate of the permeation process girdling rod-shaped propellant powder is provided.

Description

technical field [0001] The present invention relates to the technical field of propellants, in particular to the calculation of the burning rate of propellants, and in particular to a method capable of realizing the calculation of the burning rate of circumscribed rod-shaped propellants prepared by an infiltration process. Background technique [0002] Circumferential rod-shaped propellants are mainly used in weapons with large caliber and high chamber pressure charges, and have the characteristics of high filling density. In order to reduce the initial combustion pressure of the circumscribed rod-shaped propellant, increase its energy or combustion gradual increase, it is usually necessary to post-treat the circumscribed rod-shaped propellant, and generally adopt the method of deep insensitivity or impregnation of high-energy components. The methods of these methods The common feature is the use of liquid functional reagents to infiltrate the formed circular-cut rod-shaped ...

AI Technical Summary

Problems solved by technology

The current methods for calculating the burning rate of circumscribed rod propellants by infiltration process mainly include: (1) average the characteristics of the different components of the propellant, and treat the circumscribed propellant propellant by infiltration process as a macroscopically uniform substance, which is obviously different from that of The composition of the actual substance does not match, and more accurate parameters of the combustion process cannot be obtained; (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 the method considers the distribution of penetrating substances, 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. Mixing two components with one positive and one negative oxygen balance Finally, the gunpowder power obtained by using the summation method of the gunpowder power to calculate the two separate components 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, and the oxygen will be effectively used and will not There is a situation where the combustion product of one component is in positive oxygen balance and the combustion product of the other is in negative oxygen balance; (3) The shape parameter of the propellant is regarded as a constant parameter, from the beginning of combustion to the completion of combustion All conform to the parallel layer law of average material combustion, which is obviously different from the actual situation. The composition and burning rate of the penetrating process ring-cut rod-shaped propellant vary with the arc thickness.

Therefore, the existing calculation method cannot obtain the burning rate of circumscribed rod-shaped propellant well in the infiltration process

[0003] From the technical information retrieved so far, there is no method for calculating the burning rate of circumscribed rod-shaped propellant by the infiltration process that can consider the penetration depth distribution of components, propellant parameter performance and drug shape change.

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