基于对火箭发射过程中高温燃气对导流槽表面烧蚀机理的研究, 提出了一种用于预测导流槽表面最高温度的创新算法。该算法采用拉丁超立方采样技术获取样本数据, 拟合样本计算结果由Kriging拟合算法构建代理模型, 以预测不同型面参数下导流槽表面的最高温度值。结合样本数据分析与优化构型计算, 进一步分析了导流槽结构尺寸参数对其表面温度分布的影响规律。在建立代理模型的基础上, 以遗传算法计算获得基本段直段长度为2 084.2 mm、导流面曲率半径为2 276.0 mm、导流面倾角为62.2°时, 导流槽表面温度达到最低值。通过对不同导流槽尺寸参数组合下的燃气流场进行数值模拟, 研究了导流槽表面的高温区和高压区分布特征, 并对优化构型与原最优工况在压力梯度等方面进行了对比分析。结果表明, 在导流槽外侧区域, 由于燃气直接冲击形成的高温区和高压区较为集中;与优化构型相比, 原最优工况在外侧附近的压力梯度分布更为显著, 对燃气流动起到了一定的阻碍作用, 导致燃气经过压缩后温度升高, 从而使得导流槽表面温度维持在一个较高的水平。文中研究结论为火箭发射装置导流槽的优化设计提供了理论依据。

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.