二元引射喷管高空性能及对无人机红外抑制的数值研究

斯仁; 吉洪湖; 刘福城; 林兰之

doi:10.13224/j.cnki.jasp.2014.01.006

二元引射喷管高空性能及对无人机红外抑制的数值研究

doi: 10.13224/j.cnki.jasp.2014.01.006

南京航空航天大学能源与动力学院, 南京 210016

计量
- 文章访问数: 1520
- HTML浏览量: 5
- PDF量: 1103
- 被引次数: 0
出版历程
- 收稿日期: 2012-12-04
- 刊出日期: 2014-01-28

Numerical investigation of high altitude performance of 2-D ejector nozzle and infrared supperssion of unmanned aerial vehicle

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 研究了长/短套管两种结构的二元引射喷管在高空飞行的无人机上的推力特性，以及对无人机3~5μm波段红外辐射特征分布的影响，同时还对比了高空和地面状态下二元引射喷管推力和红外辐射特征.排气系统和无人机的流场、温度场采用商用软件Fluent计算，红外辐射特征采用自主开发的软件（NUAA-IR）进行计算.结果表明：高空状态下二元引射喷管仍可以提高推力特性，但其效果略弱于地面状态；无人机采用二元引射喷管后在大部分探测方向上的红外抑制效果明显，最大降幅为90%；机尾探测方向上长/短套管两种结构的二元引射喷管的红外抑制规律与地面状态不同，短套管二元引射喷管的红外辐射强度大于长套管二元引射喷管，最大增幅为7%.
- 二元引射喷管 /
- 推力特性 /
- 无人机 /
- 红外辐射 /
- 红外抑制
Abstract: The thrust characteristics and infrared radiation characteristics in the waveband of 3-5μm of 2-D ejector nozzle with long/short shrouds in the high-flying unmanned aerial vehicle(UAV) were studied.The thrust characteristics and infrared radiation characteristics of 2-D ejector nozzle under the conditions of high-altitude and ground state were compared.The system of the exhaust jet, UAV flow field and temperature field were calculated with commercial software Fluent, and the infrared radiation characteristics were calculated with an infrared analysis software(NUAA-IR) developed independently.The results show that the 2-D ejector nozzle can still improve thrust characteristic under the condition of high-altitude,but the thrust characteristic is a little weaker than that under ground condition.The effect of infrared radiation suppression of 2-D ejector nozzle used by UAV is obvious in most of the detection directions,with the largest decreasing amplitude of 90%.The trend of infrared radiation suppression of these two types of 2-D ejector nozzles in the direction of UAV's tail is different from that under ground condition;the infrared radiation of the 2-D ejector nozzle with short shroud is greater than that with long shroud,and the largest increasing amplitude is 7%.
- 2-D ejector nozzle /
- thrust characteristics /
- unmanned aerial vehicle(UAV) /
- infrared radiation /
- infrared suppression

HTML

参考文献(15)

[1]	李晋岭, 汪卫华.无人机红外辐射特性数值模拟研究综述[J].舰船电子工程, 2010, 30(8):21-24. LI Jinling, WANG Weihua.Review of infrared radiation characteristics numerical simulation study on unmanned aerial vehicle[J].Ship Electronic Engineering, 2010, 30(8):21-24.(in Chinese)
[2]	张勃, 吉洪湖.大宽高比矩形喷管的射流与外流掺混特性的数值研究[J].航空动力学报, 2005, 20(1):104-110. ZHANG Bo, JI Honghu.Numerical study of internal and external flow mixing for rectangular nozzles with large aspect ratio[J].Journal of Aerospace Power, 2005, 20(1):104-110.(in Chinese)
[3]	《航空发动机设计手册》总编委会.航空发动机设计手册:第七册进排气装置[M].北京:航空工业出版社, 2002.
[4]	Greathouse W K, Hollister D P.Preliminary air-flow and thrust calibrations of several conical cooling-air ejectors with a primary to secondary temperature ratio of 1.0:I diameter ratios of 1.21 and 1.10[R].NACA RM E52E21, 1952.
[5]	Choi Y H, Soh W Y.Computational analysis of the flowfield of a two-dimensional ejector nozzle[R].AIAA 90-190, 1990.
[6]	额日其太, 王志杰, 吴寿生.高速热喷流条件下二元收扩喷管扩张段壁面冷却的初步试验研究[J].航空动力学报, 2002, 17(1):40-44. Eriqitai, WANG Zhijie, WU Shousheng.Preliminary experimental investigation on the divergent wall cooling of two dimensional C-D nozzles at high speed and hot jet conditions[J].Journal of Aerospace Power, 2002, 17(1):40-44.(in Chinese)
[7]	李黎.排气引射系统主喷管选型试验研究[J].航空动力学报, 1998, 13(1):85-88. LI Li.An experimental study on primary nozzle types of exhaust ejector systems[J].Journal of Aerospace Power, 1998, 13(1):85-88.(in Chinese)
[8]	刘福城, 吉洪湖, 林兰之, 等.二元引射喷管几何特征参数对推力及红外特性的影响[J].航空动力学报, 2011, 26(6):1244-1250. LIU Fucheng, JI Honghu, LIN Lanzhi, et al.Impact of geometry parameters on the thrust and infrared radiation characteristics of two-dimensional ejector nozzle[J].Journal of Aerospace Power, 2011, 26(6):1244-1250.(in Chinese)
[9]	刘福城, 吉洪湖, 斯仁, 等.短套管二元引射喷管设计及气动与红外特性数值研究[J].红外技术, 2013, 35(10):607-610. LIU Fucheng, JI Honghu, SI Ren, et al.Numerical simulation of two-dimensional ejector nozzle with short shroud[J].Infrared Technology, 2013, 35(10):607-610.(in Chinese)
[10]	李娜, 吉洪湖, 黄伟, 等.混合排气二元收敛喷管气动与红外隐身综合设计方法[J].航空动力学报, 2011, 26(11):2563-2570. LI Na, JI Honghu, HUANG Wei, et al.Comprehensive design of aerodynamic and infrared stealth of 2-D convergent nozzle with mixed flow[J].Journal of Aerospace Power, 2011, 26(11):2563-2570.(in Chinese)
[11]	罗明东, 吉洪湖, 黄伟.非加力涡轮发动机排气系统红外辐射强度的数值计算研究[J].航空动力学报, 2007, 22(10):1609-1616. LUO Mingdong, JI Honghu, HUANG Wei.Numerical evaluation on infrared radiant intensity of exhaust system of turbine engine without afterburning[J].Journal of Aerospace Power, 2007, 22(10):1609-1616.(in Chinese)
[12]	徐南荣, 朱谷君.热空腔-喷气流的组合辐射[J].航空动力学报, 1995, 10(3):295-298. XU Nanrong, ZHU Gujun.Thermal cavity-plume combination radiation[J].Journal of Aerospace Power, 1995, 10(3):295-298.(in Chinese)
[13]	王琴芳.航空燃气涡轮发动机原理[M].南京:南京航空航天大学出版社, 2005.
[14]	Presz W Jr, Reynolds G, Hunter C.Thrust augmentation with mixer/ejector systems[R].AIAA-2002-0230, 2002.
[15]	李立国, 张靖周.航空用引射混合器[M].北京:国防工业出版社, 2007.