基于响应面法的火箭发动机喷管型面优化设计

王英鹏; 徐义华; 孙海俊; 冯喜平

doi:10.13224/j.cnki.jasp.20210004

基于响应面法的火箭发动机喷管型面优化设计

doi: 10.13224/j.cnki.jasp.20210004

1.
南昌航空大学飞行器工程学院江西省微小航空发动机重点实验室，南昌 330063
2.
西北工业大学燃烧、热结构与内流场重点实验室，西安 710072

基金项目: 国家自然科学基金（51666012）

详细信息

作者简介:
王英鹏（1995-），男，硕士生，主要从事航空宇航推进理论与工程研究。

通讯作者:
徐义华（1971-），男，教授，博士，研究领域为发动机工作过程仿真。E-mail：xuyihua2003@163.com

中图分类号: V238
计量
- 文章访问数: 623
- HTML浏览量: 292
- PDF量: 124
- 被引次数: 0
出版历程
- 收稿日期: 2021-01-05
- 刊出日期: 2022-01-28

Optimization design for nozzle contour of rocket engine based on response surface method

1.
Jiangxi Key Laboratory of Micro Aeroengine，School of Aircraft Engineering， Nanchang Hangkong University，Nanchang 330063，China
2.
Science and Technology on Combustion，Internal Flow and Thermo-Structure Laboratory，Northwestern Polytechnical University，Xi'an 710072，China

摘要

摘要: 针对已知某型火箭发动机的燃气参数，对比了维托辛斯基、双三次、五次曲线及基于维托辛斯基的移轴法设计的收缩段型面喷管性能，其中移轴法得到喷管性能较优；采用单一变量法计算分析了喷管型面参数（初始扩张段圆弧半径、扩张段出口半角、扩张段长径比、扩张段扩张角以及收缩段长径比）对喷管性能影响规律，喷管出口推力随着初始扩张段圆弧半径以及出口半角的增大而减小；随着收缩段长径比、扩张段长径比以及扩张角的增大，喷管出口推力先增大后减小。由于各型面参数的影响关系存在着耦合现象，为了综合考虑各参数对喷管性能影响，采用响应面法（RSM）对喷管型面各参数进行优化设计，结果表明：RSM所得到的型面喷管在推力增加的基础上，长度减小了3.40%。
- 推进系统 /
- 推力喷管 /
- 响应面法 /
- 型面参数 /
- 优化设计
Abstract: Based on the known gas parameters of a certain rocket engine，the performance of nozzle with convergent section designed by Witoszynski，bicubic curve，quintic curve and axis shifting method based on Witoszynski was analyzed on a comparative basis.Better performance of nozzle was obtained by axis shifting method.The nozzle contour parameters （initial arc radius of arc segment，outlet half angle，length diameter ratio of expansion section） were calculated and analyzed by single variable method.The results showed that the nozzle outlet thrust decreased with the increase of the initial expansion arc radius and outlet half angle； with the increase of the length diameter ratio of the convergent section，the length diameter ratio of the expansion section and the expansion angle，the nozzle outlet thrust first increased and then decreased.Due to the interact phenomenon of the influence of the parameters of each contour，the response surface method （RSM） was used to optimize the parameters of nozzle contour in order to comprehensively consider the influence of various parameters on nozzle performance.The results showed that the length of the performance of nozzle contour obtained by RSM was reduced by 3.40% with the increase of thrust.
- propulsion system /
- thrust nozzle /
- response surface method /
- contour parameters /
- optimization design

HTML

参考文献(25)

[1]	BERTIN J J,CUMMINGS R M.Critical hypersonic aerothermodynamic phenomena[J].Annual Review of Fluid Mechanics,2006,38（1）:129-157.
[2]	吴杰.Ludwieg管向超声速流域拓展的设计技术[J].空气动力学学报,2018,36（3）:480-492.
[3]	ALLAN A.Design of maximum thrust nozzles for nonequilibrium chemically reacting flow[J].AIAA Journal,1974,12（10）:1299-1300.
[4]	BIANCHI D,NERI A.Numerical simulation of chemical erosion in VEGA launcher solid-propellant rocket motor nozzles[J].Journal of Propulsion and Power,2015,34（2）:1-17.
[5]	杨飞,李振海,李建昌.固体火箭发动机喷管型面的研究进展[J].真空,2020,57（1）:45-52.
[6]	刘文芝,张乃仁,张春林,等.某型号固体火箭发动机喷管型面设计与数值计算[J].工程设计学报,2006,13（2）:99-103.
[7]	季宗德,周长省,丘广申.火箭弹设计理论[M].北京:兵器工业出版社,1995:219-220.
[8]	王成轩.固体发动机喷管内部型面最佳设计[J].宇航学报,1996,17（3）:64-67.
[9]	孙得川,于泽游.一种考虑燃气性质变化的喷管型面优化方法[J].兵工学报,2018,39（11）:2145-2152.
[10]	YUMU?AK M,EYI S.Design optimization of rocket nozzles in chemically reacting flows[J].Computers and Fluids,2012,65:25-34.
[11]	王筱蓉,周长省,鞠玉涛,等.固体火箭发动机特型喷管的型面设计[J].弹道学报,2008,20（4）:77-80.
[12]	陈威男,徐林.高超声速风洞喷管型线设计[J].应用能源技术,2018,36（7）:1-4.
[13]	赵一龙,赵玉新,王振国,等.超声速型面可控喷管设计方法[J].国防科技大学学报,2012,34（5）:1-4.
[14]	马国宝.二次抛物线型面喷管参数的优化选择[J].固体火箭技术,1995,18（3）:8-12.
[15]	揭国平,方丁酉.喷管型面对固体火箭发动机性能的影响[J].推进技术,1988,9（4）:7-13,75.
[16]	陈林泉,李岩芳,王建儒,等.喷管扩散段型面对固体发动机性能的影响[J].固体火箭技术,2004,27（1）:9-11.
[17]	易仕和.超声速与高超声速喷管设计[M].北京：国防工业出版社,2013.
[18]	张连河,范洁川.三元收缩段优化设计研究[J].空气动力学学报,2003,21（4）:417-423.
[19]	SU Yaoxi.Flow analysis and design of three-dimensional wind tunnel contractions[J].AIAA Journal,1992,29（11）:1912-1920.
[20]	SHOPE F,ABOULMOUNA M.On the importance of convergent design for supersonic wind tunnel nozzles[R].AIAA 2008-3940,2008.
[21]	李志刚,周珊,王华.某型运载火箭单喷管轴对称模型数值模拟[J].兵工自动化,2018,37（6）:96-99.
[22]	BOX G E P,WILSON K B J R.On the experimental attainment of optimum conditions[J].Journal of the Royal Statistical Society,1951,13（1）:1-45.
[23]	成沉,鲍福廷,刘旸,等.基于响应面法的喉栓式喷管型面优化设计[J].固体火箭技术,2014,37（1）:47-51.
[24]	MASON R L,GUNST R F,HESS J L.Statistical design and analysis of experiments: with applications to engineering and science,second edition[M].New Jersey: John Wiley & Sons Publication,2003.
[25]	LIU Yahui,WANG Jun,WANG Donghong.Numerical optimization on hot forging process of connecting rods based on RSA with experimental verification[J].International Journal of Advanced Manufacturing Technology,2017,90（7）:3129-3135.