ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Multidisciplinary integrated design optimization for an airbreathing air-to-air missile shape
Received date: 2015-03-31
Revised date: 2015-07-18
Online published: 2015-08-28
It is challenging for aerodynamic configuration design of an airbreathing air-to-air missile using integrated solid ramjet rocket motor,which is difficult to solve aerodynamic and propellant interaction.In this paper,multidisciplinary integrated design optimization method is introduced to solve the problem.The disciplines include aerodynamics/propulsion/weight/trajectory.Aerodynamic forces are carried through the surrogate models,which are created from aerodynamic database constructed automatically by the techniques of parametric geometric modeling,unstructured grid and CFD.Propulsion characteristics are evaluated by an engineering method,which is developed according to solid ramjet rocket propulsion theory.The accuracy of aerodynamic surrogate model and propulsion engineering method are validated before being used,and both of them are acceptable.The trajectory path is gained from 3-DOF point mass simulation.After the integration of above disciplines,inlet and wing shape of an airbreathing air-to-air missile are designed by multidisciplinary integrated design optimization method.The objective of missile dynamic range is improved by 10% after design optimization,which shows good thrust-drag match.The proposed method is useful to solve aerodynamic and propellant interaction for similar airbreathing missile shape design.
WANG Rong , ZHANG Hongjun , WANG Guidong , CHEN Guangqiang , BAI Peng , ZHANG Zhenming , LI Xiaodong , FU Jianming . Multidisciplinary integrated design optimization for an airbreathing air-to-air missile shape[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016 , 37(1) : 207 -215 . DOI: 10.7527/S1000-6893.2015.0206
[1] 樊会涛,王起飞.远程空空导弹的发展及其关键技术[J].航空兵器,2006(1):3-7.FAN H T,WANG Q F.Development and key technology of long-range air-to-air missile[J].Aero Weaponry,2006(1):3-7(in Chinese).
[2] 李国雄.吸气式远程超声速防空导弹一体化外形设计的几个重大技术问题[J].现代防御技术,2002,30(2):29-34.LI G X.Several important technical questions in integrated configuration design of air-breathing long-range supersonic surface-to-air missiles[J].Modern Defence Technology,2002,30(2):29-34(in Chinese).
[3] 王明鉴.整体式固冲发动机与导弹一体化优化设计[J].固体火箭技术,1997,20(2):7-13.WANG M J.The integrated design optimization of solid rocket ramjet and missile[J].Journal of Solid Rocket Technology,1997,20(2):7-13(in Chinese).
[4] 赵建民,夏智勋,郭健,等.基于全模式遗传算法的导弹/固体冲压发动机一体化优化[J].固体火箭技术,2005 28(1):1-4.ZHAO J M,XIA Z X,GUO J,et al.Integral design optimization for missile/solid rocket ramjet based on all schema genetic algorithm[J].Journal of Solid Rocket Technology,2005,28(1):1-4(in Chinese).
[5] 谷良贤,李文华.整体式固冲发动机空空导弹一体化设计[J].战术导弹技术,1997(4):1-4.GU L X,LI W H.Integral design of air-to-air missile with integrate rocket ramjet[J].Tactical Missile Technology,1997(4):1-4(in Chinese).
[6] BESSER H L.History of ducted rocket development at Bayern-Chemie:AIAA-2008-5261[R].Reston:AIAA,2008.
[7] SOBIESKI J,HAFTKA R T.Multidisciplinary aerospace design optimization:survey of recent developments:AIAA-1996-0711[R].Reston:AIAA,1996.
[8] THOMAS A Z,LAWRENCE L G.Multidisciplinary design optimization techniques:implications and opportunities for fluid dynamics research:AIAA-1999-3798[R].Reston:AIAA,1999.
[9] 熊俊涛,乔志德,韩忠华.基于响应面法的跨声速机翼气动优化设计[J].航空学报,2006,27(3):399-402.XIONG J T,QIAO Z D,HAN Z H.Optimum aerodynamic design of transonic wing based on response surface methodology[J].Acta Aeronautica et Astronautica Sinica,2006,27(3):399-402(in Chinese).
[10] 蒙文巩,马东立,楚亮.基于神经网络响应面的机翼气动稳健性优化设计[J].航空学报,2010,31(6):1134-1140.MENG W G,MA D L,CHU L.Wing aerodynamic robustness optimization based on neural network response surface[J].Acta Aeronautica et Astronautica Sinica,2010,31(6):1134-1140(in Chinese).
[11] MYERS R H,MONTGOMERY D C.Response surface methodology:process and product optimization using designed experiments[M].New York:John Wiley & Sons,1995:28-31,79-133.
[12] KIM H.Statistical modeling of simulation errors and their reduction via response surface techniques[D].Blacksburg,Virginia:Virginia Polytechnic Institute and State University,2001:22-32.
[13] GIUNTA A A.Aircraft multidisciplinary design optimization using design of experiments theory and response surface modeling methods[D].Blacksburg,Virginia:Virginia Polytechnic Institute and State University,1997:36-42.
[14] 鲍福廷,黄熙君,张振鹏,等.固体火箭冲压组合发动机[M].北京:中国宇航出版社,2006:292-312.BAO F T,HUANG X J,ZHANG Z P,et al.Integral solid propellant ramjet rocket motor[M].Beijing:China Astronautic Publishing House,2006:292-312(in Chinese).
/
| 〈 |
|
〉 |
CJA