关键词: 固液火箭发动机;退移速率+;耦合;传热

Abstract: In order to understand the complex combustion and heat transfer in hybrid rocket motor,temperature field and gas component distribution were calculated in a two-dimensional experimental burner by using the flow/structure coupled heat transfer method based on the FLUENT software.The irregular regression rate of the burning surface was simulated by using dynamic grid.Results indicate that both the distance between diffusion flame and the solid surface and velocity of gas play important role for the regression rate.This method can be used to simulate the complex process of unsteady heat transfer and fuel regression in the hybrid rocket motor.Also,it can predict the inner ballistic performance of hybrid rocket motor.

Key words: Hybrid rocket motor;Regression rate+;Coupling;Heat transfer