超燃冲压发动机喷管下唇板可调方案

庞丽娜; 徐惊雷; 葛建辉

doi:10.13224/j.cnki.jasp.2015.07.021

超燃冲压发动机喷管下唇板可调方案

doi: 10.13224/j.cnki.jasp.2015.07.021

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室, 南京 210016

基金项目:

国家自然科学基金(90916023)

详细信息

作者简介:
庞丽娜(1988-),女,黑龙江哈尔滨人,硕士生,主要从事高超声速排气系统气动力学研究.

中图分类号: V231.3
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- 被引次数: 0
出版历程
- 收稿日期: 2014-02-26
- 刊出日期: 2015-07-28

Scramjet nozzle with adjustable cowl scheme

Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 高超声速飞行器在飞行接力点和巡航结束点受喷管冷、热态膨胀状态不同的影响,会产生较大的冷、热态俯仰力矩差,从而对飞行器姿态控制带来较大困难.针对该问题,研究了下唇板可调方案对降低冷、热态俯仰力矩差的有效性,对不同下唇板角度进行数值模拟,得到了喷管性能参数.结果表明:下唇板旋转6°时,设计马赫数Ma=4.5下冷、热态俯仰力矩差下降29.57%,推力系数减小0.42%.并且进行了下唇板角度可调方案的风洞试验和对应的数值模拟,对比发现数值模拟结果与试验结果吻合较好,验证了所提出的可调方案及数值模拟结果的正确性.
- 超燃冲压发动机 /
- 单膨胀斜面喷管 /
- 几何调节 /
- 俯仰力矩差 /
- 风洞试验
Abstract: The difference of cold/hot pitch moment will result in difficulty of vehicle attitude control when the hypersonic vehicle works at the relay point and cruising end point under the influence of cold and hot expansion conditions. To solve this problem, an adjustable cowl scheme was adopted and investigated, and also proven in effectively decreasing the difference of cold/hot pitch moment. The flow-field with different cowl angles was numerically simulated to obtain the performance parameters of nozzle. The results showed that, when the cowl angle was adjusted to 6°, the difference of cold/hot pitch moment was reduced by 29.57% and the thrust coefficient decreased only 0.42% in design Mach number 4.5. Finally, a wind tunnel experiment was carried out, and numerical simulation was performed based on the conditions of the wind tunnel experiment. The results of the simulation were in good agreement with experiment data, validating the effectiveness and correctness of the adjustment scheme and the results of numerical simulation.
- scramjet /
- single expansion ramp nozzle /
- geometry adjustment /
- difference of pitch moment /
- wind tunnel experiment

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参考文献(16)

[1]	Perrier P,Rapuc M,Rostand P.Nozzle and afterbody design for hypersonic airbreathing vehicles[R].AIAA 96-4548,1996.
[2]	Edwards C L Q,Small W J,Weidner J P,et al.Studies of scramjet/airframe integration techniques for hypersonic aircraft[R].AIAA 75-58,1975.
[3]	张留欢,徐惊雷,莫建伟.二元非对称喷管可调方案试验研究[J].航空学报,2013,34(4):772-778. ZHANG Liuhuan,XU Jinglei,MO Jianwei.Experimental study of 2D adjustable asymmetric nozzles[J].Acta Aeronoutica et Astronautica Sinica,2013,34(4):772-778.(in Chinese)
[4]	徐惊雷,张艳慧,张堃元.超燃冲压发动机非对称喷管非设计状态性能计算[J].推进技术,2007,28(3):287-290. XU Jinglei,ZHANG Yanhui,ZHANG Kunyuan.Numerical simulation of single expansion ramp nozzle for scramjet on the off-design point[J].Journal of Propulsion Technology,2007,28(3):287-290.(in Chinese)
[5]	XU Jinglei, SHA Jiang,MO Jianwei,et al.The numerical study of improving the performance of the over expanded SERN by using SJA[R].AIAA-2010-6790,2010.
[6]	张堃元,张荣学,徐辉.非对称大膨胀比喷管研究[J].推进技术,2001,22(5):380-382. ZHANG Kunyuan,ZHANG Rongxue,XU Hui.Investigation of single expansion ramp nozzle[J].Journal of Propulsion Technology,2001,22(5):380-382.(in Chinese)
[7]	汪维娜,王占学,乔渭阳.单斜面膨胀喷管几何参数对流场和性能的影响[J].航空动力学报,2006,21(2):280-284. WANG Weina,WANG Zhanxue,QIAO Weiyang.Investigation of the influence of single expansion ramp nozzle ge ometric parameters on the flow field and performance[J].Journal of Aerospace Power,2006,21(2):280-284.(in Chinese)
[8]	晏至辉.超燃冲压发动机尾喷管仿真和试验研究[D].长沙:国防科学技术大学,2005. YAN Zhihui.Simulation and experimental research on scramjet nozzle[D].Changsha:National University of Defense Technology,2005.(in Chinese)
[9]	Deere K A,Asbury S C.An experimental and compu-tational investigation of a translating throat single expansion ramp nozzle[R].AIAA 96-2540,1996.
[10]	Chevalier A,Bouchez M,Levine V,et al.French-Russian partnership on hypersonic wide range ramjets[R].AIAA 96-4554-CP,1996.
[11]	Baranovsky S I,Gilevith D D.A program of the scramjet design and optimization[R].AIAA 91-5073,1991.
[12]	Baranovsky S I,Levin V M,Avrashkov V N.Gas dynamic features of supersonic kerosene combustion in a model combustion chamber[R]. AIAA 90-5268,1990.
[13]	葛建辉,徐惊雷,庞丽娜.Scramjet尾喷管几何调节方案的计算与实验研究[J].推进技术,2013,34(9):1158-1164. GE Jianhui,XU Jinglei,PANG Lina,et al.CFD and experimental investigation for an adjustable scramjet nozzle[J].Journal of Propulsion Technology,2013,34(9):1158-1164.(in Chinese)
[14]	Goeing M.Nozzle design optimization by method-of-characteristics[R].AIAA 90-2024,1990.
[15]	张艳慧,徐惊雷,张堃元.超燃冲压发动机非对称喷管设计状态性能[J].推进技术,2007,28(3):282-286. ZHANG Yanhui,XU Jinglei,ZHANG Kunyuan.Numerical simulation of single expansion ramp nozzle for scramjet on the designing point[J].Journal of Propulsion Technology,2007,28(3):282-286.(in Chinese)
[16]	MO Jianwei,XU Jinglei,ZHANG Liuhuan,et al.The experimental and numerical study of the over-under TBCC exhaust system[R].AIAA-2011-2234,2011.