多工况下变推力固体发动机喉栓喷管型面一体化优化设计  

Optimization design for contour of pintle nozzle for variable thrust solid rocket motor under multiple working conditions

作　　者：王鹏宇 王政涛 武泽平 张锡 张为华 WANG Pengyu;WANG Zhengtao;WU Zeping;ZHANG Xi;ZHANG Weihua(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073

出　　处：《固体火箭技术》2022年第3期337-342,共6页Journal of Solid Rocket Technology

基　　金：国家自然科学基金资助项目(52005502);湖南省科技创新计划资助(2020RC2035);国防科技大学科研计划项目(ZK19-11)。

摘　　要：喉栓式变推力固体火箭发动机在保留传统固体发动机优点的基础上,实现了推力实时、大范围地主动调节,极大地提高了固体火箭发动机性能。在实现推力调节的同时,喉栓的运动势必会对流场结构造成影响,增大流动损失。为减小喉栓式喷管流动过程中的比冲损失,综合考虑喉栓不同位置条件下的流场结构,以多工况下的平均实际平均比冲为目标函数,基于代理模型对已有喉栓喷管型面进行一体化优化设计。最优拉丁超立方实验设计方法生成初始样本点用于构建Kriging模型,通过非精确采样准则进行序列采样逐步更新代理模型。结果表明,优化后的型面能够有效减弱喉栓头部下游的激波强度,平均实际比冲提高2.13%,验证了多工况下喉栓喷管型面一体化优化设计方法的有效性。Having the advantages of traditional solid rocket motor,the pintle controlled thrust solid rocket motor realizes real-time and large-scale active adjustment of thrust,which greatly improves the performance of solid rocket motor.While the thrust is adjusted,the movement of the pintle is bound to affect the flow field structure and increase the flow loss.In order to reduce the spe-cific impulses loss of the pintle nozzle,the integrated optimization design for the current pintle nozzle contour was carried out based on the surrogate model in this paper.In the optimization,taking the average specific impulses under multiple working conditions as the objective function,the flow field structure for the pintle in different positions were simultaneously considered.The initial sample points generated by Optimal Latin Hypercube Sampling(OLHS)were utilized to build a Kriging model,and the surrogate model was updated step by step through sequential sampling based on imprecise sampling criteria.The results show that the optimized con-tour can effectively reduce the intensity of the shock wave downstream of the pintle head.The average actual specific impulses under multiple working conditions increases by 2.13%,which verifies the effectiveness of the optimization method of pintle nozzle under multiple working conditions.

关 键 词：喉栓式喷管 型面优化 KRIGING模型 实际比冲 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]