含硼推进剂固冲发动机补燃室响应面优化设计

胡建新; 夏智勋; 赵建民; 郭健; 张炜; 罗振兵; 缪万波

含硼推进剂固冲发动机补燃室响应面优化设计

国防科学技术大学航天与材料工程学院, 长沙 410073

基金项目: 自然科学基金(50376072)

计量
- 文章访问数: 1697
- HTML浏览量: 0
- PDF量: 486
- 被引次数: 0
出版历程
- 收稿日期: 2006-11-21
- 修回日期: 2007-04-18
- 刊出日期: 2007-12-28

Design optimization of secondary chamber response surface of boron-based propellant ducted rocket motor

College of Aerospace and Material Engineering, National University of Defense Technology, Changsha 410073, China

摘要

摘要: 影响含硼推进剂固体火箭冲压发动机补燃室燃烧效率的因素很多,且各因素对燃烧效率的影响很难用精确的解析函数式来表示.首先建立了发动机补燃室内两相湍流燃烧数值模拟模型,然后提出了选用基于正交多项式的响应面方法来解决含硼推进剂固体火箭冲压发动机补燃室结构优化问题.这种方法可以减少为得到近似函数式而对补燃室流场进行计算的次数,能比较方便地对固体火箭冲压发动机补燃室各个参数进行优化与分析.
- 航空、航天推进系统 /
- 固体火箭冲压发动机 /
- 含硼推进剂 /
- 响应面法 /
- 优化设计 /
- 数值模拟 /
- 燃烧过程 /
- 两相流
Abstract: There are a variety of influential factors to the combustion efficiency of secondary chamber of boron-based propellant ducted rocket motor,which are difficult to be expressed accurately by analytical functions.Atwo-phase turbulent flow combustion value simulation model was firstly established within the secondary chamber of the rocket motor.Then,the structural optimization of secondary chamber of Boron-based propellant ducted rocket motor was achieved through the response surface based on orthogonal polynomial.This method allows to compute less frequently the flow field of secondary chamber in obtaining the approximate functions,and makes it easier to optimize and analyze the parameters of secondary chamber of boron-based propellant ducted rocket motor.
- aerospace propulsion system /
- ducted rocket motor /
- boron-based propellant /
- response surface methodology /
- optimization design /
- numerical analysis /
- combustion process /
- two phase flow

HTML

参考文献(9)

[1]	Mayer A E H J,Stowe R A.Experimental study into mixing in a solid fuel ducted rocket combustion chamber[R].AIAA Paper 2000-3346.
[2]	Stowe R A,Champlain A De,Mayer A E H J.Modeling combustor performance of a ducted rocket[R].AIAA Paper 2000-3728.
[3]	Onn S C,Chiang H J,Hwang H C,et al.Optimization of operation conditions and configurations for solid-propellant ducted rocket combustors[R].AIAA Paper 93-1885.
[4]	罗世彬.高超声速飞行器机体/发动机一体化及总体多学科设计优化方法研究[D].长沙:国防科学技术大学,2004.
[5]	Steffen C Jr.Response surface modeling of combined-cycle propulsion components using computational fluid dynamics[R].AIAA 2002-0542.
[6]	胡建新,夏智勋,赵建民,等.固体火箭冲压发动机补燃室的响应面法优化设计[J].推进技术,2004,25(6):491-497.HU Jianxin,XIA Zhixun,ZHAO Jianmin,et al.Ducted rocket secondary chamber optimization with response surface methodology[J].Journal of Propulsion Technology,2004,25(6):491-497.
[7]	庄逢辰编著.液体火箭发动机喷雾燃烧的理论、模型及应用[M].长沙:国防科学技术大学出版社,1995.
[8]	胡建新,夏智勋,方丁酉,等.固冲发动机补燃室内硼颗粒点火和燃烧数值研究[J].弹道学报.2006,18(1):68-71.HU Jianxin,XIA Zhixun,FANG Dingyou,et al.A numerical study on ignition and combustion of boron particles in the flowfield of a ducted rocket secondary combustor[J].Journal of Ballistics,2006,18(1):68-71.
[9]	陈小前.飞行器总体优化设计理论与应用研究[D].长沙:国防科学技术大学,2002.