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Method for calculating characteristic parameters of trajectory in flaky multilayer propellant charge

A technology of characteristic parameters and calculation methods, applied in the field of propellant, can solve the problems of inability to quantitatively characterize and calculate the calculation of propellant, and achieve the effect of fast and efficient calculation

Active Publication Date: 2020-02-07
ZHONGBEI UNIV
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Problems solved by technology

[0005] The present invention mainly aims to solve the calculation problem that the prior art cannot be quantitatively characterized and cannot be applied to propellants with arbitrary multi-layer complex structures, and provides a method for calculating the internal ballistic characteristic parameters of sheet-like multi-layer propellant charges

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  • Method for calculating characteristic parameters of trajectory in flaky multilayer propellant charge
  • Method for calculating characteristic parameters of trajectory in flaky multilayer propellant charge
  • Method for calculating characteristic parameters of trajectory in flaky multilayer propellant charge

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Embodiment Construction

[0053] The specific implementation manners of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0054] The calculation method of the internal ballistic characteristic parameters of the flake multi-layer propellant charge of the present invention specifically comprises the following steps:

[0055] (1) Determine the number of layers of sheet propellant

[0056]A sheet-like multi-layer propellant is composed of three layers of base powder. The upper and lower layers are the same base material with a thickness of 0.5mm, and the middle is other base material with a thickness of 1mm. The total thickness after physical compaction is 2mm, showing Disc shape with an outer diameter of 45mm and an inner diameter of 8mm.

[0057] (2) The characteristic parameters under the corresponding coordinates of the given propellant

[0058] Combined with specific test data to illustrate, according to figure 2 The p-t curve and Fi...

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Abstract

The invention relates to the technical field of propellant powder, in particular to a method for calculating trajectory characteristic parameters in flaky multilayer propellant powder. The combustiongradual increasing property of the multilayer propellant powder is represented by adopting a combustion speed ratio method, so that the problem that the combustion gradual increasing property of the multilayer propellant powder can only be qualitatively represented and cannot be quantitatively represented is solved. A transition layer gradient function method is adopted, calculation of the inner trajectory of the multi-layer propellant powder is optimized, and the inner trajectory characteristic parameters of the flaky multi-layer propellant powder can be obtained through one-time inner trajectory circulation. The same coordinate mode in the direction from the outer layer to the inner layer is adopted, so that all characteristic parameters of the propellant in the combustion process are converted into a single relation with the coordinate as a variable, the combustion increasability of the multi-layer propellant can be quantitatively represented, and the method is suitable for any propellant of a multi-layer complex structure.

Description

technical field [0001] The invention relates to the technical field of propellants, in particular to a method for calculating internal ballistic characteristic parameters of sheet-like multi-layer propellant charges. Background technique [0002] Sheet-shaped multi-layer propellant is composed of at least three layers of propellant combustion layers with different components, each layer has a different burning speed, combined by physical extrusion, and has a certain strength and geometric shape. medicine. This type of propellant has a high combustion gradual increase, and at the same time, the propellant has a high packing density. Compared with granular bulk propellant, the packing density can be increased by more than 25%, and the highest can reach 1.25g / cm 3 above. Applying the characteristics of high combustion and gradual increase of multi-layer propellants can increase the muzzle kinetic energy by 15%-50% while maintaining the maximum chamber pressure. Therefore, the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/11
CPCG06F17/11Y02T90/00
Inventor 马中亮齐乐何利明贺增弟赵树森
Owner ZHONGBEI UNIV
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