一种两侧布局的亚声速无人机进气道流场特性

蒋武根; 彭云晖; 李博

一种两侧布局的亚声速无人机进气道流场特性

计量
- 文章访问数: 1414
- HTML浏览量: 0
- PDF量: 44
- 被引次数: 0
出版历程
- 收稿日期: 2011-07-21
- 修回日期: 2011-09-14
- 刊出日期: 2011-11-28

Flow field characteristics of a side-mounted subsonic inlet of unmanned aerial vehicle

摘要

摘要: 对一种两侧布局的亚声速无人机进气道进行了气动设计和数值模拟研究,得到了该进气道的工作特性.结果表明,进气道唇口、两侧管道的汇合段、以及发动机轮毂对进气道流场和性能影响较大,发动机轮毂能改善进气道出口流场品质,降低流场畸变.在所有状态下,该进气道的总压恢复系数大于0.97,畸变指数小于0.15,满足发动机的工作要求.
- 亚声速进气道 /
- 无人机 /
- 数值模拟 /
- 总压恢复系数 /
- 畸变指数
Abstract: A side-mounted subsonic inlet of unmanned aerial vehicle (UAV) was designed and the flow field was simulated.The characteristics of the inlet were obtained.The results show that, the inlet lip,the junction of the duct and the engine hub have great influence on the flow filed and characteristics of the inlet.The engine hub can improve the quality of the flow field at the exit of the inlet and reduce the distortion index.The total pressure recovery coefficient of the inlet is more than 0.97 and the distortion index is less than 0.15.The inlet meets the requirements of the engine at all states.
- subsonic inlet /
- unmanned aerial vehicle(UAV) /
- numerical simulation /

HTML

参考文献(15)

[1]	李光超,马晓平.无人机伞降回收运动分析[J].飞行力学,2007,25(4):25-28. LI Guangchao,MA Xiaoping.Parachute landing recovery motion analysis for unmanned aerial vehicle[J].Flight Dynamics,2007,25(4):25-28.(in Chinese)
[2]	马高建,郭荣伟.无人机两侧式布局的S弯进气道设计与实验[J].南京航空航天大学学报,2008,40(2):146-150. MA Gaojian,GUO Rongwei.Design and experiment of bilateral type S-shaped inlet of UAV[J].Journal of Nanjing University of Aeronautics and Astronautics,2008,40(2):146-150.(in Chinese)
[3]	李其弢,郭荣伟,付强.一种高亚声速弹用S 弯进气道设计及其特性[J]. 南京航空航天大学学报,2002,34(2):108- 113. LI Qitao,GUO Rongwei,FU Qiang.Design and performance of S-shaped inlet for high subsonic missiles[J].Journal of Nanjing University of Aeronautics and Astronautics,2002,34(2):108-113.(in Chinese)
[4]	万大为,郭荣伟,艾清,等.一种S弯进气道的设计与实验研究[J].南京航空航天大学学报,2004,36(2):150-154. WAN Dawei,GUO Rongwei,AI Qing,et al.Design and experimental study of an S-shaped Inlet[J].Journal of Nanjing University of Aeronautics and Astronautics,2004,36(2):150-154.(in Chinese)
[5]	谢旅荣,郭荣伟.一种受总体限制的弹用S弯进气道的设计和实验验证[J].空气动力学学报,2006,24(1):95-101. XIE Lürong,GUO Rongwei.Design and experimental study of an S-shaped inlet restricted by missile[J].Acta Aerodynamica Sinica,2006,24(1):95-101.(in Chinese)
[6]	靖建朋,郭荣伟.弹用S弯进气道气动性能试验[J].航空动力学报,2009,24(9):2085-2090. JING Jianpeng,GUO Rongwei.Experimental investigation of pneumatic characteristics for S-shaped inlet in missiles[J].Journal of Aerospace Power,2009,24(9):2085-2090.(in Chinese)
[7]	李博,梁德旺.Y形进气道流场数值研究[J].南京航空航天大学学报,2004,36(2):6-10. LI Bo,LIANG Dewang.Numerical computation for a bifurcated Y-inlet[J].Journal of Nanjing University of Aeronautics and Astronautics,2004,36(2):6-10.(in Chinese)
[8]	Uthup B,Deshpande S M.Viscous computational for a bifurcated Y-duct of a fighter aircraft .AIAA 97-2207,1997.
[9]	黄国平,梁德旺.一种改进的MUSCL格式[J].南京航空航天大学学报,1997,29(3):277-282. HUANG Guoping,LIANG Dewang.Improvement on MUSCL scheme[J].Journal of Nanjing University of Aeronautics and Astronautics,1997,29(3):277-282.(in Chinese)
[10]	黄国平,梁德旺.块结构的MUSCL算法求解三维进气道流场[J].空气动力学学报,2000,18(2):194-199. HUANG Guoping,LIANG Dewang.The numerical simulation of 3-D flows of a inlet using a multi-block MUSCL algorithm[J].Acta Aerodynamica Sinica,2000,18(2):194-199.(in Chinese)
[11]	梁德旺,黄国平,赵海峰.B/L湍流模型在强压力梯度流场计算中的应用[J] .南京航空航天大学学报,1999,31(1):37-42. LIANG Dewang,HUANG Guoping,ZHAO Haifeng.Application of B/L turbulence model for calculating flow with strong adverse pressure gradient[J]. Journal of Nanjing University of Aeronautics and Astronautics,1999,31(1):37-42. (in Chinese)
[12]	李博,梁德旺.混压式进气道与弹体一体化流场数值模拟[J].推进技术,2002,23(4):307-310. LI Bo,LIANG Dewang.Computation of the integrated flow field around missile and mixed compression intake[J]. Journal of Propulsion Technology,2002,23(4):307-310.(in Chinese)
[13]	梁德旺,李博.无隔道进气道反设计及附面层排除机理分析[J].航空学报,2005,26(3):286-289. LIANG Dewang,LI Bo.Reverse design of diverterless inlet and mechanism of diversion of boundary layer[J].Acta Aeronautica et Astronautica Sinica,2005,26(3):286-289.(in Chinese)
[14]	李博,梁德旺.无隔道超声速进气道/前机身一体化计算与试验[J].航空学报,2009,30(9):1597-1604. LI Bo,LIANG Dewang.Numerical simulation and experiment of integral flow field of diverterless supersonic inlet/forebody[J]. Acta Aeronautica et Astronautica Sinica,2009, 30(9):1597-1604.(in Chinese)
[15]	朱自强,吴子牛,李津,等.应用计算流体力学[M].北京:北京航空航天大学出版社,1998:127-131. ZHU Ziqiang,WU Ziniu,LI Jin,et al.Applied computational fluid dynamics[M].Beijing:Beijing University of Aeronautics and Astronautics Press,1998:127-131.(in Chinese)