基于响应面法的喉栓式喷管型面优化设计  

Optimization design for contour of pintle nozzle based on response surface method

作　　者：成沉 鲍福廷[1] 刘旸[1] 许昊[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2014年第1期47-51,共5页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(51005179)

摘　　要：为减小喉栓式喷管的气动损失,综合考虑了喉栓的型面与喷管型面的相互作用,基于响应面法结合CFD数值计算,对喉栓式喷管进行了优化设计。采用中心复合实验设计(CCD)生成响应面采样点。分别采用多项式模型和Kriging模型生成响应面,并比较了2种方法对本问题的拟合程度。结果表明,Kriging模型拟合效果较好。优化算法采用序列二次规划法。优化后,喷管的比冲损失从9.01%降到了3.63%,气动损失有所减小。对影响比冲效率的关键参数进行了单独优化,得到了关键参数对比冲效率的影响规律。结果表明,影响比冲效率的因素主要为喷管的设计参数,在进行喉栓式喷管的优化设计时,喷管部分完全可采用传统喷管的优化设计方法,再针对喉栓进行匹配性优化。基于响应面法进行喉栓式喷管的型面优化设计,计算量相对较小,计算结果的精度和可靠度相对较高,可快速进行型面优化设计,具有一定的工程实用价值。In order to reduce the loss of fluid dynamic of the pintle nozzle, considering the interaction of the nozzle contour and the pintle contour, CFD method combined with the response surface method was used to optimize the contour of the pintle nozzle.The central composite design（CCD） was used to create sampling points on response surface.The full 2nd order polynomials algorithm and the Kriging algorithm were used to create the response surface.The result shows that the Kriging model is more suitable for the case in this paper. Nonlinear Programming by Quadratic Lagrangian was used for optimizing. After the optimization, the loss of specif ic impulse decreases from 9.01% to 3.63% ,so the loss of fluid dynamic is reduced.To study the influence of the key parameters on the loss of specific impulse, the key parameters were optimized independently.The results show that the main factor influencing the loss of specific impulse is the parameters of the nozzle.When optimizing the pintle nozzle, the optimization method of the traditional nozzle can be used for the nozzle part ,then the designer optimizes the pintle part of the pintle nozzle.The optimization design for con tour of pintle nozzle based on the response surface method has a relatively small calculation work with high accuracy and reliability. It can be used to select the optimal shape parameters of the pintle nozzle quickly,which is valuable in engineering application.

关 键 词：喉栓式喷管 响应面法 固体火箭发动机 优化设计 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]