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Numerical simulation method for solid-liquid phase transition of aluminium oxide in solid rocket exhaust

A solid rocket, numerical simulation technology, used in electrical digital data processing, design optimization/simulation, special data processing applications, etc.

Active Publication Date: 2017-08-25
BEIJING INST OF ENVIRONMENTAL FEATURES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Al currently 2 o 3 The simulation method of particle phase transition focuses on the combustion chamber, which involves the oxidation process of metal aluminum. However, in the tail jet flow section, most of the existing phase transition processes are ignored. 2 o 3 The numerical simulation method of solid-liquid phase transition is also a blank

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  • Numerical simulation method for solid-liquid phase transition of aluminium oxide in solid rocket exhaust
  • Numerical simulation method for solid-liquid phase transition of aluminium oxide in solid rocket exhaust
  • Numerical simulation method for solid-liquid phase transition of aluminium oxide in solid rocket exhaust

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Embodiment Construction

[0027] Exemplary embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The description of the exemplary embodiments is for the purpose of illustration only, and in no way limits the invention and its application or usage.

[0028] The numerical simulation method of the solid-liquid phase transition of solid rocket jet flame alumina of the present invention comprises:

[0029] Obtain the solid specific calorific value and liquid specific calorific value of alumina at the current flame height and flame temperature;

[0030] Determine the content of solid phase alumina and liquid phase alumina in the paste phase alumina;

[0031] According to the content of solid phase alumina and liquid phase alumina, as well as the solid specific heat value and liquid specific heat value of alumina, determine the effective specific heat value of alumina in the spray flame;

[0032] The effective specific heat value of alumina is us...

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Abstract

The invention discloses a numerical simulation method for solid-liquid phase transition of aluminium oxide in solid rocket exhaust. The method comprises the steps that a solid-phase specific heat value and a liquid-phase specific heat value of aluminium oxide under current exhaust height and exhaust temperature are acquired; the content of solid-phase aluminium oxide and liquid-phase aluminium oxide in pasty-phase aluminium oxide is determined; an effective specific heat value of aluminium oxide in the exhaust is determined according to the content of solid-phase aluminium oxide and liquid-phase aluminium oxide and the solid-phase specific heat value and the liquid-phase specific heat value of aluminium oxide; and the effective specific heat value of aluminium oxide is utilized to simulate the solid-liquid phase transition process of aluminium oxide in the solid rocket exhaust. Through the method, thermodynamic changes caused in the solid-liquid phase transition process of aluminium oxide particles in the solid rocket exhaust can be effectively simulated, and the numerical simulation precision of an exhaust flow field and the precision of exhaust-targeted infrared property simulation can be improved.

Description

technical field [0001] The invention relates to the modeling of the jet flame flow field of the solid rocket tail and the infrared characteristics of the target, in particular to a numerical simulation method for the solid-liquid phase transition of the solid rocket jet flame alumina. Background technique [0002] The technical background related to the present invention will be described below, but these descriptions do not necessarily constitute the prior art of the present invention. [0003] Aluminum oxide (Al 2 o 3 ) particles, formed by the oxidation of metallic aluminum (Al) powder in the propellant, Al 2 o 3 The shape of the particles is similar to a sphere, and its particle size is related to the size and working state of the engine. Due to the Al in the plume 2 o 3 Particles are an important source of radiation and have a strong scattering effect, and their existence will have a greater impact on the gas flow field, so the inclusion of Al must be considered w...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 段然朱希娟马静吴杰
Owner BEIJING INST OF ENVIRONMENTAL FEATURES