流体推力矢量技术研究综述

肖中云; 江雄; 牟斌; 陈作斌

doi:10.11729/syltlx20160207

流体推力矢量技术研究综述

doi: 10.11729/syltlx20160207

中国空气动力研究与发展中心计算空气动力研究所, 四川绵阳 621000

基金项目:

国家自然科学基金项目 11572341

详细信息

作者简介:
肖中云(1977-), 男, 四川大竹人, 副研究员。研究方向:流动控制。通信地址:四川省绵阳市二环路南段6号13信箱08分箱(621000)。E-mail:scxiaozy@sina.cn

通讯作者:
肖中云, E-mail:scxiaozy@sina.cn

中图分类号: V211.3
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- 文章访问数: 553
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- 被引次数: 0
出版历程
- 收稿日期: 2016-12-22
- 修回日期: 2017-04-20
- 刊出日期: 2017-08-25

Advances influidic thrust vectoring technique research

Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

摘要

摘要: 流体推力矢量技术不采用机械偏转，以流动控制方式实现推力转向，有望成为一种更加高效的推力矢量控制方法。目前实现流体推力矢量的主要方法有激波矢量法、双喉道方法、逆流控制方法和同向流方法等，对以上方法选择具有共性的计算与试验数据，对喷管的推力矢量效率、推力损失和流量系数进行了对比分析。结果表明激波矢量方法、双喉道方法和逆流方法能够在大落压比范围内（NPR=1.89~10）实现推力矢量控制，并且具有俯仰/偏航耦合甚至多轴控制的潜力。相比激波矢量法和逆流方法，双喉道和同向流方法在减少推力损失和提高矢量效率上占有优势，不足之处是双喉道方法对喉道进行控制限制了流量系数，而同向流方法的适用落压比范围受到严重限制。为寻求更加高效的矢量喷管技术，国内外相继发展了多种新概念流体推力矢量方法，对每种方法的控制原理、潜在优势和存在的问题挑战进行了探讨，新方法着眼于从喷流出口下游进行控制，对主流的干扰很小，值得深入研究，同时也为流体推力矢量的下一步研究方向提供了借鉴参考。
- 喷管 /
- 推力矢量 /
- 控制 /
- 效率 /
- 二次流
Abstract: In contrast to the mechanical deflecting nozzle, the fluidic thrust vectoring control hires flow control methods to realize the jet vectoring, which is expected to be a more efficient way to manipulate the thrust direction. Among the main fluidic vectoring control methods, including shock vectoring control(SVC), dual throat nozzle(DTN), counter-flow(CC) and co-flow control, performance parameters such as the thrust vectoring efficiency, the thrust ratio and the discharge coefficient are compared based on published experimental and computational data. It shows that SVC, DTN and CC methods produce thrust vectoring in a wide range of Nozzle Pressure Ratio(NPR) from 1.8 to 10, and are extendable to pitch/yaw control or multi-axis control. Comparatively, DTN and co-flow control are superior to SVC and CC in the thrust loss and thrust vectoring efficiency, yet DTN is disadvantageous in the discharge coefficient as a consequence of throat injection, and the working range of co-flow method is highly limited. In pursuit of highly efficient control, some new methods of jet vectoring are introduced, and the principles, potential advantages and challenges of each method are discussed. These methods adopt after-deck-flow control and introduce little disturbance to the main jet, which are desirable for the thrust vectoring control. Such methods show promising prospects and the related experience should be drawn on for further studies.
- nozzle /
- thrust vectoring /
- control /
- efficiency /
- secondary flow

HTML全文

图 1 几种主要流体推力矢量方法的控制原理

Figure 1. Principles of several fluidic thrust vectoring methods

下载: 全尺寸图片幻灯片

图 2 3种控制方法的推力系数比较

Figure 2. Comparison of thrust coefficients for three control methods

下载: 全尺寸图片幻灯片

图 3 双喉道方法与激波矢量法的推力矢量效率比较

Figure 3. Comparison of thrust vectoring efficiencies between DTN and SVC

下载: 全尺寸图片幻灯片

图 4 双喉道方法与激波矢量法的流量系数比较

Figure 4. Comparison of discharge coefficients between DTN and SVC

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图 5 合成射流控制的涡量云图

Figure 5. Vorticity contour of synthetic jet flow control

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图 6 合成射流控制射流偏转

Figure 6. Jet vectoring caused by synthetic jet

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图 7 双主流合成作用的Coanda效应喷管^[39]

Figure 7. Coanda effect nozzle with two streams synthetic jet^[39]

下载: 全尺寸图片幻灯片

图 8 引射效应导致射流摇摆

Figure 8. Jet swing caused by pumping effect

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表 1 3种流体推力矢量控制方法的比较

Table 1. Comparison of three fluidic thrust vectoring methods

控制方法	矢量效率	推力系数	流量系数	缺点
激波法	＜3.3°/1%	0.86~0.94	＞0.95	推力损失大
双喉道法	(3.4~5.2)°/1%	0.92~0.96	0.78~0.88	流量系数低
逆流方法	＞5°/1%	0.92~0.97	＞0.95	系统复杂

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参考文献(44)

[1]	Bowers A H, Pahle J W. Thrust vectoring on the NASA F-18 high alpha research vehicle[R]. NASA Technical Memorandum 4771, 1996.
[2]	Kowal H J. Advances in thrust vectoring and the application of flow-control technology[J]. Canadian Aeronautics and Space Journal, 2002, 48(2):145-151. doi: 10.5589/q02-020
[3]	Deere K A. Summary of fluidic thrust vectoring research conducted at NASA langley research center[R]. AIAA-2003-3800, 2003.
[4]	连永久.射流推力矢量控制技术研究[J].飞机设计, 2008, 28(2):19-24. http://cpfd.cnki.com.cn/Article/CPFDTOTAL-AGLU201512001157.htm Lian Y J. Fluidic thrust vectoring techniques research[J]. Aircraft Design, 2008, 28(2):19-24. http://cpfd.cnki.com.cn/Article/CPFDTOTAL-AGLU201512001157.htm
[5]	宋亚飞, 高峰, 何至林.流体推力矢量技术[J].飞航导弹, 2010, (11):72-75. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201211004.htm
[6]	Wing D J. Static investigation of two fluidic thrust-vectoring concepts on a two dimensional convergent-divergent nozzle[R]. NASA Technical Memorandum 4574, 1995.
[7]	Deere K A. Computational investigation of the aerodynamic effects on fluidic thrust vectoring[R]. AIAA-2000-3598, 2000.
[8]	Giuliano V J, Wing D J. Static investigation of a fixed-aperture nozzle employing fluidic injection for multiaxis thrust vector control[R]. AIAA-1997-3149, 1997.
[9]	Wing D J, Giuliano V J. Fluidic thrust vectoring of an axisymmetric exhaust nozzle at static conditions[R]. FEDSM97-3228, 1997.
[10]	Shi J W, Wang Z X, Zhang X B, et al. Performance estimation for fluidic thrust vectoring nozzle coupled with aero-engine[R]. AIAA-2014-3771, 2014.
[11]	Miller D N, Yagle P J, Hamstra J W. Fluidic throat skewing for thrust vectoring in fixed geometry nozzles[R]. AIAA-99-16262, 1999.
[12]	Deere K A, Berrier B L, Flamm J D, et al. Computational study of fluidic thrust vectoring using separation control in a nozzle[R]. AIAA-2003-3803, 2003.
[13]	Deere K A, Flamm J D, Berrier B L, et al. Computational study of an axisymmetric dual throat fluidic thrust vectoring nozzle for a supersonic aircraft application[R]. AIAA-2007-5085, 2007.
[14]	Flamm J D, Deere K A, Berrier B L, et al. Experimental study of a dual-throat fluidic thrust-vectoring nozzle concept[R]. AIAA-2005-3503, 2005.
[15]	Flamm J D, Deere K A, Mason M L, et al. Design enhancements of the two-dimensional, dual throat fluidic thrust vectoring nozzle concept[R]. AIAA-2006-3701, 2006.
[16]	Flamm J D, Deere K A, Mason M L, et al. Experimental study of an axisymmetric dual throat fluidic thrust vectoring nozzle for supersonic aircraft application[R]. AIAA-2007-5084, 2007.
[17]	谭慧俊, 陈智.二元双喉道射流推力矢量喷管的数值模拟研究[J].航空动力学报, 2007, 22(10):1678-1684. doi: 10.3969/j.issn.1000-8055.2007.10.016 Tan H J, Chen Z. A computational study of 2-D dual-throat fluidic thrust-vectoring nozzles[J]. Journal of Aerospace Power, 2007, 22(10):1678-1684. doi: 10.3969/j.issn.1000-8055.2007.10.016
[18]	吴正科, 杨青真, 施永强, 等.基于RBF和PSO的双喉道气动矢量喷管优化设计[J].推进技术, 2013, 34(4):451-456. http://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201304005.htm Wu Z K, Yang Q Z, Shi Y Q, et al. Optimization design of the dual throat fluidic thrust vectoring nozzle based on RBF and PSO[J]. Journal of Propulsion Technology, 2013, 34(4):451-456. http://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201304005.htm
[19]	Hunter C A, Deere K A. Computational investigation of fluidic counterflow thrust vectoring[R]. AIAA-99-2669, 1999.
[20]	Flamm J D. Experimental study of a nozzle using fluidic counterflow for thrust vectoring[R]. AIAA-1998-3255, 1998.
[21]	Strykowski P J, Krothapalli A, Forliti D J. Counterflow thrust vectoring of supersonic jets[J]. AIAA Journal, 1996, 34(11):2306-2314. doi: 10.2514/3.13395
[22]	Alvi F S, Strykowski P J. Forward flight effects on counterflow thrust vector control of a supersonic jet[J]. AIAA Journal, 2015, 37(2):279-281.
[23]	Strykowski P J. An experimentallmodeling study of jet attachment during counterflow thrust vectoring[R]. NASA-CR-204436, 1996.
[24]	Hunter C A. Experimental, theoretical, and computqational investigation of separated nozzle flows[R]. AIAA-98-3107, 1998.
[25]	Mason M S, Crowther W J. Fluidic thrust vectoring for low observable air vehicles[R]. AIAA-2004-2210, 2004.
[26]	Banazadeh A, Saghafi F, Ghoreyshi M, et al. Multi-directional co-flow fluidic thrust vectoring intended for a small gas turbine[R]. AIAA-2007-2940, 2007.
[27]	Fielding J P, Smith H. FLAVⅡR, an innovative university/industry research program for collaborative research and demonstration of UAV technologies[C]. 25th International Congress of the Aeronautical Sciences, 2006.
[28]	Abbasi A Y, Clarke A, Lawson C P, et al. Design and development of the eclipse and demon demonstrator UAVs[C]. 26th International Congress of The Aeronautical Sciences, 2008.
[29]	Fielding J P, Lawson C P, Pires R, et al. Development of the demon technology demonstrator UAV[C]. 27th International Congress of The Aeronautical Sciences, 2010.
[30]	Gill K, Wilde P, Gueroult R, et al. Development of an integrated propulsion and pneumatic power supply system for flapless UAVs[R]. AIAA-2007-7726, 2007.
[31]	Heo J Y, Yoo K H, Lee Y, et al. Fluidic thrust vector control of supersonic jet using co-flow injection[R]. AIAA-2009-5174, 2009.
[32]	Lamb M, Taylor J G, Frassinelli M C. Static internal performance of a two dimensional convergent divergent nozzle with external shelf[R]. NASA Technical Memorandum 4719, 1996.
[33]	Smith B L, Glezer A. Vectoring and small-scale motions effected in free shear flows usin synthetic jet actuators[R]. AIAA-97-0213, 1997.
[34]	夏智勋, 罗振兵.合成射流激励器射流矢量控制的物理因素[J].应用数学和力学, 2007, 28(7):811-823. http://www.cnki.com.cn/Article/CJFDTOTAL-YYSX200707010.htm Xia Z X, Luo Z B. Physical factors of a primary jet vectoring control using synthetic jet actuators[J]. Applied Mathematics and Mechanics, 2007, 28(7):811-823. http://www.cnki.com.cn/Article/CJFDTOTAL-YYSX200707010.htm
[35]	罗振兵, 夏智勋.合成射流技术及其在流动控制中应用的进展[J].力学进展, 2005, 35(2):221-234. doi: 10.6052/1000-0992-2005-2-J2004-044 Luo Z B, Xia Z X. Advances in synthetic jet technology and applications in flow control[J]. Advances in Mechanics, 2005, 35(2):221-234. doi: 10.6052/1000-0992-2005-2-J2004-044
[36]	Park L G, Seifert A. Periodic excitation for jet vectoring and enhanced spreading[J]. Journal of Aircraft, 2001, 38(3):486-495. doi: 10.2514/2.2788
[37]	Trancossi M, Dumas A, Vucinic D. Mathematical modeling of coanda effect[R]. SAE Technical Paper 2013-01-2195, 2013.
[38]	Trancossi M, Dumas A, Das S S, et al. Design methods of Coanda effect nozzle with two streams[J]. INCAS Bulletin, 2014, 6(1):83-95. doi: 10.13111/2066-8201
[39]	Sunol A, Vucinic D. Numerical analysis and UAV application of the ACHEON thrust vectoring nozzle[R]. AIAA-2014-2046, 2014.
[40]	吴云, 李应红.等离子体流动控制研究进展与展望[J].航空学报, 2015, 36(2):381-405. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201502001.htm Wu Y, Li Y H. Progress and outlook of plasma flow control[J]. Acta Aeronautica Et Astronautica Sinica, 2015, 36(2):381-405. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201502001.htm
[41]	Sinha A, Alkandry H, Fischer M K, et al. The impulse response of a high-speed jet forced with localized arc filament plasma actuators[J]. Physics of Fluids, 2012, 24(12):1-20. http://authors.library.caltech.edu/36737/
[42]	肖中云, 顾蕴松, 江雄, 等.一种基于引射效应的流体推力矢量新技术[J].航空学报, 2012, 33(11):1967-1974. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201211004.htm Xiao Z Y, Gu Y S, Jiang X, et al. A new fluidic thrust vectoring technique based on ejecting mixing effects[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(11):1967-1974. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201211004.htm
[43]	Ozgu M R, Stenning A H. Switching dynamics of bistable fluid amplifiers[R]. AD72383, 1971.
[44]	曹永飞, 顾蕴松, 程克明, 等.基于被动二次流的射流偏转比例控制[J].航空学报, 2015, 36(3):757-762. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201503006.htm Cao Y F, Gu Y S, Cheng K M, et al. Proportional control of jet deflection with passive secondary flow[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(3):757-762. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201503006.htm