Performance Prediction and Optimization of Ramjet for Projectiles Using Support Vector Regression Model

Ning ZHANG; Jinguang SHI; Zhongyuan WANG; Xinxin ZHAO

doi:10.12382/bgxb.2022.0493

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Performance Prediction and Optimization of Ramjet for Projectiles Using Support Vector Regression Model

更新时间：2025-08-18

- Performance Prediction and Optimization of Ramjet for Projectiles Using Support Vector Regression Model
- Acta Armamentarii Vol. 44, Issue 10, Pages: 2944-2953(2023)
- 作者机构：
  
  南京理工大学能源与动力工程学院, 江苏南京 210094
- 作者简介：
- 基金信息：
- DOI：10.12382/bgxb.2022.0493
  CLC：
- Received：07 June 2022，
  
  Online First：15 December 2023，
  
  Published：30 October 2023
- 稿件说明：
移动端阅览
Ning ZHANG, Jinguang SHI, Zhongyuan WANG, et al. Performance Prediction and Optimization of Ramjet for Projectiles Using Support Vector Regression Model[J]. Acta Armamentarii, 2023, 44(10): 2944-2953.
DOI：

Ning ZHANG, Jinguang SHI, Zhongyuan WANG, et al. Performance Prediction and Optimization of Ramjet for Projectiles Using Support Vector Regression Model[J]. Acta Armamentarii, 2023, 44(10): 2944-2953. DOI： 10.12382/bgxb.2022.0493.

摘要

为提高弹用固体燃料冲压发动机的工作性能和优化设计效率

提出一种与弹内有限空间适配的发动机性能预测及优化方法。采用带转捩的剪切应力输运和涡概念耗散方程

建立其内弹道计算模型

获得流场结构与性能参数;在此基础上

基于支持向量回归方法构建了发动机性能参数的预测模型

并结合改进非支配排序遗传算法对发动机结构进行优化。研究结果表明:新建立的内弹道计算模型

可较好地模拟发动机内燃烧与流动过程;构建的预测模型可靠性较高

与高可信度模型相比

最大相对误差小于3%;发动机结构优化后

燃烧室缩短了13.88%

补燃室增长了13.50%

燃烧效率、推力和比冲分别提高12.02%、24.22%、20.28%。

Abstract

To improve the working performance of solid fuel ramjet for projectiles and shorten the optimization period

the transitionshear stress transfer and vortex concept dissipation equations are used to establish an internal ballistic calculation model

and the flow field and performance parameters are obtained. Then

based on the support vector regression method

a prediction model of the performance parameters is built

and the ramjet structure is optimized using the NSGA-Ⅱ algorithm. The results show that the internal ballistic calculation model can simulate the combustion and flow process in the ramjet well. At the same time

the constructed prediction model has high reliability

and the maximum relative error is less than 3% compared with that of the high-confidence model. After the ramjet is optimized

the combustion chamber is shortened by 13.88%

the aft mixing chamber is increased by 13.50%

and the combustion efficiency

thrust and specific impulse are increased by 12.02%

24.22% and 20.28%

respectively.

关键词

Keywords

references

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张宁 , 史金光 , 王中原 , 等 . 带有钝体的弹用固体燃料冲压发动机工作性能 [J ] . 兵工学报 , 2022 , 43 ( 7 ): 1519 - 1526 . DOI: 10.12382/bgxb.2021.0428 http://doi.org/10.12382/bgxb.2021.0428 为发展一种弹用高性能冲压发动机，提出了在补燃室带有钝体的发动机设计方案，并数值计算对比分析了补燃室有无钝体方案下的内流场、燃烧效率、推力、比冲与总压损失。结果表明：钝体后部孔隙外侧有两个漩涡，孔隙内的高速气流与下部漩涡在一定程度维持了尾迹的稳定性，能够保证冲压发动机工作的平稳性；与参考固体燃料冲压发动机（不带钝体结构方案）相比，在补燃室中增加钝体能提高补燃室下游燃料与空气的掺混效果与温度，当进气质量流率为0.3 kg/s时，可使发动机推力和比冲提高约16.21%、燃烧效率提高约20.50%，但此增益效果会随着空燃比的增大而减小；当燃烧效率相同时，在补燃室中增设钝体，可以有效地缩减冲压发动机长度，为其他部件提供安装空间。

ZHANG N , SHI J G , WANG Z Y , et al . Performance of solid fuel ramjet with central bluff body for projectile [J ] . Acta Armamentarii , 2022 , 43 ( 7 ): 1519 - 1526 . (in Chinese) DOI: 10.12382/bgxb.2021.0428 http://doi.org/10.12382/bgxb.2021.0428 To develop a high-performance ramjet for projectiles, a scheme of using bluff bodies in the combustion chamber of the solid fuel ramjet is proposed. The turbulent combustion model is established based on equations for Reynolds transition and eddy dissipation, and the internal flow field, combustion efficiency, thrust, specific impulse and total pressure loss of the combustion chamber with or without the bluff body are compared and analyzed by numerical calculation. The findings show that there are two vortices outside the pore behind the central bluff body. The high-speed airflow in the pore and small-scale vortices below has maintained some wake stability, which can ensure the smooth operation of the ramjet. Compared with the reference solid fuel ramjet (without bluff body structure), adding a bluff body in the afterburning chamber can improve the mixing effect and temperature of fuel and air at the downstream of this chamber, which can increase the combustion efficiency. When the intake air mass flow rate was 0.3 kg/s, the ramjet thrust and specific impulse was increased by about 16.21%, and the combustion efficiency improved by about 20.50%, but the enhancement effects would decrease with the increase of air-fuel ratio. Under the same combustion efficiency, adding a bluff body in the combustion chamber can effectively reduce the length of the ramjet and thus leaving installation space for other parts.

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