A Numerical Simulation Method for Solid-liquid Phase Transition of Solid Rocket Flame Aluminum Oxide

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 modeling of a solid rocket tail jet flow field and target infrared characteristics, in particular to a numerical simulation method for solid-liquid phase transition of solid rocket jet flame alumina. Background technique [0002] The related technical background of the present invention is described below, but these descriptions do not necessarily constitute the prior art of the present invention. [0003] Solid rocket tail flames contain aluminum oxide (Al 2 O 3 ) particles, formed by the oxidation of metallic aluminum (Al) powder in the propellant, Al 2 O 3 The particles are shaped like spheres, and their size is related to the size and working state of the engine. Due to the Al in the tail plume 2 O 3 Particles are important radiation sources and have a strong scattering effect, and their existence will have a greater impact on the gas flow field, so it must be considered when simulating solid rocket tail flames contai...

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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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