Two-phase flow simulation method of solid rocket engine under flight overload

Abstract

The invention discloses a two-phase flow simulation method for a solid rocket engine under flight overload, and the method comprises the steps: (1) selecting a target time point and an overload value for research according to the time and overload conditions in a flight trajectory; (2) constructing a physical model of a three-dimensional flow field of the solid rocket engine; (3) discretizing the simulation area by adopting a hexahedral structured grid; (4) regarding a combustion product of the propellant as a combustion gas-phase particle and a combustion condensed-phase particle, and setting simulation boundary conditions; (5) calculating and solving the flow field of the two-phase flow by adopting an Euler-Lagrange method; (6) designing a condensed phase particle collection test experiment device, and obtaining a particle size distribution rule of condensed phase particles; and (7) carrying out simulation calculation on the flow field of the two-phase flow of the solid rocket engine again to obtain the movement and distribution rule of the particles in the flow field. The method is high in simulation calculation accuracy, wide in application range, low in technical difficulty, high in engineering feasibility and capable of being conveniently applied to model development.

Description

technical field [0001] The invention belongs to the technical field of solid rocket motors, and relates to a flow field simulation calculation method of a solid rocket motor, in particular to a two-phase flow simulation method of a flow field in a combustion chamber of an engine under flight overload conditions. Background technique [0002] During the flight process of the booster phase of the near-space vehicle, the ballistic trajectory needs to be depressed to meet the requirements of the handover point. As the propulsion force of the vehicle, the solid rocket motor needs to face a long-term continuous lateral overload environment during the working process. The condensed phase particles in the propellant combustion products are affected by the overload condition and converge into a particle flow in the flow field of the combustion chamber, which impacts on the heat insulation layer, resulting in a strong erosion and ablation effect, increasing the load capacity of the hea...

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