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Journal of Projectiles, Rockets, Missiles and Guidance >

2025 , Vol. 45 >Issue 2: 251 - 259

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.02.016

Prediction and Optimization of the Surface Parameters of the Flame Guide Groove at the Space Launch Site

  • WANG Xinyu ,
  • JIANG Yi ,
  • SHEN Bohan
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  • School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

Received date: 2025-02-27

  Online published: 2025-05-16

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Abstract

Based on the study of the mechanism of high-temperature gas ablation on the surface of the flame guide groove during rocket launch, this paper proposes an innovative algorithm for predicting the maximum temperature of the guide groove surface. The algorithm uses Latin hypercube sampling technology to obtain sample data, and uses the Kriging fitting algorithm to construct a proxy model based on the sample data to predict the maximum temperature value of the guide groove surface under different profile parameters. Combining sample data analysis with optimized configuration calculation, the influence law of the structural size parameters of the guide groove on its surface temperature distribution is further analyzed. On the basis of the established proxy model, the genetic algorithm is used to calculate that the guide groove surface temperature reaches the lowest value when the basic straight section length is 2 084.2 mm, the guide surface curvature radius is 2 276.0 mm, and the guide surface inclination angle is 62.2°. By numerically simulating the gas flow field under different combinations of guide groove size parameters, the distribution characteristics of the high-temperature and high-pressure areas on the guide groove surface are studied, and the optimized configuration is compared with the original optimal working condition in terms of pressure gradient and other aspects. The results show that in the outer area of the guide groove, the high temperature and high pressure areas formed by the direct impact of the gas are more concentrated; compared with the optimized configuration, the pressure gradient distribution near the outer side of the original optimal working condition is more significant, which has a certain hindering effect on the gas flow.This causes the gas temperature to rise after compression, thereby maintains the surface temperature of the guide groove at a higher level. The research conclusion provides a theoretical basis and reference value for the optimization design of the guide groove of the rocket launcher.

Key words： gas jet; flow guide slot; Latin hypercube sampling; Kriging model; genetic algorithm

Cite this article

WANG Xinyu , JIANG Yi , SHEN Bohan . Prediction and Optimization of the Surface Parameters of the Flame Guide Groove at the Space Launch Site[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2025 , 45(2) : 251 -259 . DOI: 10.15892/j.cnki.djzdxb.2025.02.016

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