基于支持向量回归模型的弹用冲压发动机性能预测及优化  

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

作　　者：张宁 史金光[1] 王中原[1] 赵新新 ZHANG Ning;SHI Jinguang;WANG Zhongyuan;ZHAO Xinxin(School of Energy and Power Engineering,Nanjing University of Science and Technology,Nanjing 210094,Jiangsu,China)

机构地区：[1]南京理工大学能源与动力工程学院,江苏南京210094

出　　处：《兵工学报》2023年第10期2944-2953,共10页Acta Armamentarii

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%。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-Ⅱalgorithm.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：固体燃料冲压发动机 代理模型 多目标优化模型 性能预测 

分 类 号：TJ413.6[兵器科学与技术—火炮、自动武器与弹药工程] V435[航空宇航科学与技术—航空宇航推进理论与工程]