Optimization Design of Rocket Deflector Channel Surface Based on Kriging Surrogate Model

Abstract

This study aims to optimize the gas flow environment of a rocket’s deflector channel. Numerical calculations and analysis were conducted on the influencing factors of a certain type of single-sided deflector channel, with the injection coefficient used as the evaluation index for the flow clearance. The study identified the deflector channel’s impact angle, curvature diameter of the bending section, and distance from the top of the deflector surface to the bottom as important structural parameters. There exists a complex nonlinear relationship between these parameters and the gas flow guiding effect of the deflector channel. The kriging surrogate model was employed for the optimization of the deflector channel’s surface. The results showed that, while meeting the basic requirements of the deflector channel, the optimized design improved the gas flow guiding effect by 27.58%, significantly enhancing the gas flow environment. The optimization error was within 1%, confirming the effectiveness and accuracy of the optimization. This study provides a reference for the future design and optimization of gas flow deflector channels, with the potential to improve the performance and efficiency of rocket deflector channels.