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Propellant powder combustion speed calculation method

A calculation method and propellant technology, applied in chemical process analysis/design, etc., can solve problems such as calculating the burning rate of propellant, and achieve a wide range of effects

Active Publication Date: 2019-12-03
XIAN MODERN CHEM RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] This invention proposes a method for calculating the burning rate of propellant to solve the technical problem of how to accurately calculate the burning rate of propellant

Method used

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  • Propellant powder combustion speed calculation method
  • Propellant powder combustion speed calculation method
  • Propellant powder combustion speed calculation method

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Embodiment

[0054] Taking a certain three-base propellant as an example, the specific description of its burning rate calculation method is given below. The three-base propellant formula consists of:

[0055] code name NC(12.8) NG RDX NGU C 2

BYZGR 39 20 25.5 14.2 1.3

[0056] According to the established calculation method, the main component of the propellant is RDX.

[0057] (1) Combustion product H 2 O.CO 2 、H 2 , N 2 The number of moles of CO and CO are expressed as a, b, c, d, e respectively, and the combustion products are obtained by using the energy calculation method as follows:

[0058] Component a b c d e Mole number 10.37 4.40 3.53 9.29 12.34

[0059] (2) ξ(P)=1-exp(-P / P*), P * Take 9.81MPa.

[0060] (3)

[0061]

[0062]

[0063] ψ is 0.93, α is 26%, β is 11.1%, q is 8.8%, γ is 23.2%, and δ is 30.9%.

[0064] (4) Burning rate of propellant: u=1.817×P×Q 0 (P) 2 × h H / ρ P

[0065] Among them,...

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Abstract

The invention belongs to the technical field of propellant powder combustion speed calculation, and particularly relates to a method suitable for calculating the combustion speed of propellant powdercomposed of a given formula within a certain pressure range. The method comprises the following steps: determining the mole molecular number of each combustion product of propellant powder; calculating the mole molecular number of the combustion products of the propellant by adopting an energy calculation algorithm of an internal energy method; calculating the proportion of each combustion productby adopting a percentage method; determining the change rule of the oxidability of the oxidation product in the propellant powder combustion product along with the pressure; calculating the molar fraction of an oxidizing gas product in the propellant powder combustion product; and calculating the combustion speed of the propellant and calculating a combustion speed coefficient and a combustion speed pressure index. Compared with the prior art, the method can comprehensively consider the influence of formula composition and combustion products on the combustion speed, employs the influence factors of main components in a propellant formula for achieving the calculation of the burning rates of different types of propellants, and can achieve the estimation calculation of the burning rates ofmultiple types of propellants.

Description

technical field [0001] The invention belongs to the technical field of calculating the burning rate of propellant, and in particular relates to a method suitable for calculating the burning rate of propellant composed of a given formula within a certain pressure range. Background technique [0002] The burning rate of propellant is one of the important characteristic parameters of propellant. It must be used in the calculation of closed explosive device and internal ballistic. In the development of propellant and propellant charge, if the burning rate of propellant is too fast or too slow , will cause the product not to be used normally, causing waste or accidents. The existing calculation method of propellant burning rate is mainly for nitramine propellants, single-base propellant and double-base propellant mainly rely on empirical data, and it is believed that the thermal decomposition process of nitramine propellant combustion is multi-stage under certain conditions. Und...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G16C20/10
CPCG16C20/10
Inventor 张江波赵煜华梁磊严文荣周媛丽肖霞闫光虎刘毅韦丁赵晓梅
Owner XIAN MODERN CHEM RES INST
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