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Method for calculating combustion performance of flaky multilayer propellant powder based on permeation and diffusion

A calculation method and permeation and diffusion technology, applied in the field of propellants, can solve the problems of not being able to better characterize the combustion gradual increase and combustion characteristics of sheet-like multi-layer propellants, and achieve a wide application range, expand the calculation range, and smooth transition representational effect

Active Publication Date: 2020-01-14
ZHONGBEI UNIV
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Problems solved by technology

[0005] In order to solve the problem that the existing technology cannot better characterize the combustion accretion and combustion characteristics of the sheet-like multi-layer propellant, the present invention provides a method for calculating the combustion performance of the sheet-like multi-layer propellant based on permeation and diffusion

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  • Method for calculating combustion performance of flaky multilayer propellant powder based on permeation and diffusion
  • Method for calculating combustion performance of flaky multilayer propellant powder based on permeation and diffusion
  • Method for calculating combustion performance of flaky multilayer propellant powder based on permeation and diffusion

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Embodiment Construction

[0041] The specific implementation manners of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0042] In this embodiment, a method for calculating the combustion performance of sheet-like multi-layer propellants based on permeation and diffusion includes the following steps:

[0043] (1) Determine the number of layers of sheet-like multi-layer propellant

[0044] 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 45 mm, and a transition layer thickness of 0.2 mm.

[0045] (2) Give the relationship between the characteristics of different layers of the propellant and x

[0046] The direction from the outer layer to the inner layer of the sheet mu...

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Abstract

The invention relates to the technical field of propellant powder, in particular to a method for calculating the combustion performance of flaky multilayer propellant powder based on permeation and diffusion. The characterization method for the combustion characteristics of the flaky multilayer propellant powder is achieved, and a technical means for evaluating the combustion increasability is provided. By adopting the same coordinate mode from the outer layer to the inner layer, the parameter representation of any multi-layer propellant powder can be realized, and the calculation complexity is not increased along with the increase of the number of layers. The transition layer of the flaky multi-layer propellant adopts a gradient function processing method, so that the physical process canbe better met, and the combustion gradual increasing property of the flaky multi-layer propellant can be better represented. The established method does not need to specify a slow-burning layer and aquick-burning layer, so that the method can be suitable for propellant powder with various complex structures.

Description

technical field [0001] The invention relates to the technical field of propellants, in particular to a method for calculating the combustion performance of sheet-like multi-layer propellants based on permeation and diffusion. 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 highly progressive combustion characteristics 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): G06F30/20
Inventor 马中亮何利明贺增弟代淑兰梁泰鑫
Owner ZHONGBEI UNIV