Numerical analysis of 3-D inner flow field for ladder-shaped multiple propellant rocket motor. Issue 1 (1st August 2022)

• Record Type: Journal Article
• Authors: Zhou, Baihang; Wang, Hao; Ruan, Wenjun
• Is Part Of: Journal of physics. Volume 2336:Issue 1(2022)
• Publication Date: 2022-08-01
• Subjects: Solid rocket motor -- 3-D inner flow field -- Ladder-shaped multiple propellant -- Dynamic boundary condition; Physics -- Congresses; 530.5
• DOI: 10.1088/1742-6596/2336/1/012025
• Languages: English
• ISSNs: 1742-6588

Abstract

Abstract: In order to study the characteristics of ladder-shaped multiple propellant rocket motor, it was conducted that the numerical simulation of the full 3-D inner flow field for ladder-shaped multiple propellant rocket motor working process using FLUENT calculation software. The secondary development was carried out through UDF interface programming, and the changing rules of the added mass in propellant burning surface and dynamic boundary with the burning rate were set, so that the dynamic process of propellant combustion is accurately simulated. The numerical simulation results demonstrated the spatial distribution information of parameters, such as pressure and flow rate at each moment in the inner flow field, and the pressure-time curves of three monitoring points in front, center and rear of the combustion chamber. Then, several key characteristic moments were selected for specific analysis, and the pressure-time curve of the monitoring point was compared with the experimental data to show that the calculated results were basically accurate. The pressure, flow rate and the pressure difference between the internal and external surfaces of the propellant in the rocket motor inner flow field were analyzed. At present, the dynamic boundary treatment method that the burning rate of the propellant varies regularly with the surface pressure has not been applied in the 3-D calculation model. The research results of this paper can provide reference for the numerical simulation of similar structure of solid rocket motors.