一体化高超声速飞行器攻角特性的数值研究

黄伟; 王振国

doi:10.3879/j.issn.1000-0887.2009.06.012

一体化高超声速飞行器攻角特性的数值研究

doi: 10.3879/j.issn.1000-0887.2009.06.012

黄伟,
王振国

国防科技大学航天与材料工程学院,长沙 410073

基金项目: 国防科技大学优秀研究生创新资助项目(B070101);湖南省研究生科研创新资助项目(3206)

详细信息

作者简介:
黄伟(1982- ),男,湖北天门人,博士生(联系人.Email:gladrain2001@yahoo.com.cn).

中图分类号: V211
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- 文章访问数: 1806
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- 被引次数: 0
出版历程
- 收稿日期: 2008-06-27
- 修回日期: 2009-04-10
- 刊出日期: 2009-06-15

Numerical Study of Attack Angle Characteristics for Integrated Hypersonic Vehicle

Institute of Aerospace & Material Engineering, National University of Defense Technology, Changsha 410073, P. R. China

摘要

摘要: 采用二维耦合隐式NS方程和标准k-ε湍流模型，对采用Hark形头部的一体化高超声速飞行器在进气道关闭、发动机通流和发动机点火工况下的攻角特性进行了数值仿真研究．探索了可变攻角情况下，飞行器各部件对飞行器整体气动-推进性能的贡献程度A·D2结果表明，在3种不同的工作状态下，飞行器都是纵向静稳定的，足够大的升阻比可以满足飞行器飞行要求，同时，对发动机型面及机身上壁面的改进有利于进一步满足飞行器对气动-推进性能的要求．
- 一体化高超声速飞行器 /
- 攻角特性 /
- 部件分析 /
- 数值仿真 /
- Hark形头部 /
- 气动-推进性能
Abstract: Two dimension coupled implicit NS equations and standard k epsilon viscous models were used to simulate the angle of attack characteristics of integrated hypersonic vehicle with hark head configuration under three kinds of working conditions,i.e.inlet cut off,engine through flow,engine ignition.The influence of each component on the aero propulsive performance of vehicle was dis cussed.It is concluded that the longitudinal static stability of vehicle is good;it has enough lift to drag ratio to satisfy the flying requirement of the vehicle.At the same time,it is very important to change the configurations of engine and upper surface of airframe to improve the aero propulsion of the vehicle.
- integrated hypersonic vehicle /
- properties of attack angle /
- component analysis /
- computer simulation /
- Hark head configuration /
- aero propulsive performance

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参考文献(16)

[1]	刘嘉，姚文秀，雷麦芳，等. 高超声速飞行器前体压缩性能研究[J]. 应用数学和力学,2004,25(1):85-92.
[2]	Bissinger N C, Blagoveshchensky N A, Gubanov A A,et al.Improvement of forebody/inlet integration for hypersonic vehicle[J].Aerospace Science and Technology,1998,2(8):505-514. doi: 10.1016/S1270-9638(99)80009-1
[3]	LIU Zhen-xia, XIAO Hong, WU Ding-yi,et al. Aerodynamic performance of waverider forebody integrated with inlet and isolator[R]. AIAA Paper, 2007-5413,2007.
[4]	LIN Sheam-chyun, LUO Yu-shan. Integrated inlets for cone-derived waveriders with combined transverse and longitudinal curvature[J].Journal of Spacecraft and Rockets, 1994,31(4):609-614. doi: 10.2514/3.26485
[5]	俞刚，张新宇. 燃烧室构型对超燃冲压发动机性能影响研究[J]. 流体力学实验与测量, 2000,14(1):72-80.
[6]	WU Xian-yu, LI Xiao-shan, DING Meng,et al. Effects of the configuration and fuel injection on scramjet combustor performance[R]. AIAA Paper,2007-5421,2007.
[7]	陈兵，徐旭，蔡国飙. 二维超燃冲压发动机尾喷管优化设计[J]. 推进技术, 2002, 23(5): 433-437.
[8]	Bradford J E. A technique for rapid prediction of aftbody nozzle performance for hypersonic launch vehicle design[D].Atlanta:Georgia Institute of Technology,2001.
[9]	LIN Sheam-chyun , LUO Yu-shan. Integrated design of hypersonic waveriders including inlets and tailfins[J].Journal of Spacecraft and Rockets,1995,32(1):48-54. doi: 10.2514/3.26573
[10]	O’Neill Mary Kae L, Lewis Mark J. Optimized scramjet integration on a waverider[J].Journal of Aircraft,1992,29(6):1114-1121. doi: 10.2514/3.56866
[11]	O’Neill Mary Kae L, Lewis Mark J. Design tradeoffs on scramjet engine integrated hypersonic waverider vehicles[J].Journal of Aircraft,1993,30(6):943-952. doi: 10.2514/3.46438
[12]	贺元元，乐嘉陵，倪鸿礼. 吸气式高超声速机体/推进一体化飞行器数值和试验研究[J]. 实验流体力学,2007,21(2):29-34.
[13]	贺元元，倪鸿礼，乐嘉陵. 一体化高超声速飞行器气动-推进性能评估[J]. 实验流体力学,2007,21(2):63-67.
[14]	罗金玲，徐敏，刘杰. 一体化外形的高超声速飞行器升阻特性研究[J]. 宇航学报, 2007, 28(6):1478-1481.
[15]	Bolender M A, Doman D B. Nonlinear longitudinal dynamical model of an air-breathing hypersonic vehicle[J].Journal of Spacecraft and Rockets,2007,44(2):374-387. doi: 10.2514/1.23370
[16]	严恒元. 飞行器气动特性分析与工程计算[M].西安：西北工业大学出版社,1990.