尾梁边条对直升机气动性能影响试验研究
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摘要
为克服旋翼产生的反扭矩,目前直升机上主要采用单旋翼带尾桨、双旋翼等布局方案,同时发展了尾梁环量控制及尾梁边条技术。本文应用旋翼/机身组合模型风洞试验方法,探究了尾梁边条对直升机悬停及前飞性能的影响。重点研究了悬停及不同前飞速度下,不同长度和不同安装角度尾梁边条对直升机气动性能的影响。试验结果表明,悬停状态尾梁边条可通过提供侧向力来增加机身扭矩,能够帮助尾桨卸载从而减少尾桨功率消耗。而前飞状态尾梁边条对直升机气动性能基本没有影响。
In order to overcome the counter-torque caused by the rotor, the helicopter mainly adopts the single-rotor with tail rotor and double-rotor. At the same time, the technology of tail boom circulation control and tail boom strake has been developed. Rotor/fuselage model wind tunnel test was conducted to investigate the effect of the tail boom strake on the performance of helicopter hovering and forward flight. Particularly, focus on the influence of tail boom strakes with different length and installation angles on aerodynamic performance of the helicopter in hover and forward flight. The test results show that the tail boom strake can provide lateral force and increasing the fuselage torque in hovering, which can help tail rotor offload and reduce the power consumption of the tail rotor. In the forward flight, the tail boom strake has no effect on the aerodynamic performance of helicopter.
In order to overcome the counter-torque caused by the rotor, the helicopter mainly adopts the single-rotor with tail rotor and double-rotor. At the same time, the technology of tail boom circulation control and tail boom strake has been developed. Rotor/fuselage model wind tunnel test was conducted to investigate the effect of the tail boom strake on the performance of helicopter hovering and forward flight. Particularly, focus on the influence of tail boom strakes with different length and installation angles on aerodynamic performance of the helicopter in hover and forward flight. The test results show that the tail boom strake can provide lateral force and increasing the fuselage torque in hovering, which can help tail rotor offload and reduce the power consumption of the tail rotor. In the forward flight, the tail boom strake has no effect on the aerodynamic performance of helicopter.
引文
[1]王适存.直升机空气动力学[M].南京:南京航空航天大学出版社,1998.Wang Shicun. Helicopter aerodynamic[M]. Nanjing:Nanjing University of Aeronautics and Astronautics Press, 1998.(in Chinese)
[2]倪先平.直升机手册[M].北京:航空工业出版社,2003.Ni Xianping. Helicopter manual[M].Beijing:Aviation Industry Press, 2003.(in Chinese)
[3] Kelley H L,Crowell C A,Yenni K R, et al. Flight investigation of the effect of tail boom strakes on helicopter directional control[C]//AHS 46th Annual Forum and Technology Display.Washington D.C.,1990.
[4] Wilson J C,Kelley H L,Donahue C C, et al. Developments in helicopter tail boom strakes applications in the United States[R]. 88-B-014, America:NASA Technical Memorandum, 1988.
[5] Banks D W,Kelley H L. Exploratory investigation of aerodynamic characteristics of helicopter tail boom crosssection models with passive venting[R]. NASA Langley Research Center Hampton,2000.
[6]李家春.直升机环量控制尾梁发扭矩系统研究[D].南京:南京航空航天大学,2014.Li Jiachun. Research on helicopter circulation control tail boom anti-torque system[D]. Nanjing:Nanjing University of Aeronautics and Astronautics, 2014.(in Chinese)
[7]张雅铭,张玮.直升机基本原理[M].郑州:河南科学技术出版社,2008.Zhang Yaming, Zhang Wei. Helicopter basic principle[M].Zhengzhou:Henan Science and Technology Press, 2008.(in Chinese)
[8]艾伯特.G.布兰德,吉米.纳拉莫尔,詹姆斯.H.黑尔塞,等.翼型尾梁:中国,CN 103569359 A[P]. 2013.Brand A G, Narramore J, Hessel J H, et al. Airfoil tail boom:China, CN103569359 A[P]. 2013.(in Chinese)
[9] Wilson J C, Kelley H L. Helicopter low-speed yaw control. U.S., NASA CASE NO. LAR 14219-1[P].1992.
[10]Lockwood R A, Kelly W A, Carson R W. Flight characteristics test of the UH-60A with tail boom mounted strake[R]. NASA Technical Memorandum, ADA1807916XSP, 1986.
[11]李家春,杨卫东.直升机环量控制尾梁截面形状分析[J].空气动力学报, 2015, 33(2):239-245.Li Jiachun, Yang Weidong. An analysis of cross section of helicopter tail boom for NOTAR system[J]. Acta Aerodynamica Sinica, 2015,33(2):239-245.(in Chinese)
[12]董振兴,高亚东,王华明.环量控制尾梁参数对直升机尾梁侧向推力的影响[J].直升机技术, 2011(4):12-15.Dong Zhenxing, Gao Yadong, Wang Huaming. Influence of circulation control parameters on lateral thrust of helicopter tail boom in rotor downwash[J]. Helicopter Technique, 2011(4):12-15.(in Chinese)
[13]牟晓伟.环量控制尾梁系统设计与分析[D].南京:南京航空航天大学,2010.Mou Xiaowei. Design and analysis on NOTAR system[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2010.(in Chinese)
[14]黄明其.直升机风洞试验[M].北京:国防工业出版社,2014.Huang Mingqi. Helicopter wind tunnel experiment[M]. Beijing:National Defense Industry Press, 2014.(in Chinese)
[2]倪先平.直升机手册[M].北京:航空工业出版社,2003.Ni Xianping. Helicopter manual[M].Beijing:Aviation Industry Press, 2003.(in Chinese)
[3] Kelley H L,Crowell C A,Yenni K R, et al. Flight investigation of the effect of tail boom strakes on helicopter directional control[C]//AHS 46th Annual Forum and Technology Display.Washington D.C.,1990.
[4] Wilson J C,Kelley H L,Donahue C C, et al. Developments in helicopter tail boom strakes applications in the United States[R]. 88-B-014, America:NASA Technical Memorandum, 1988.
[5] Banks D W,Kelley H L. Exploratory investigation of aerodynamic characteristics of helicopter tail boom crosssection models with passive venting[R]. NASA Langley Research Center Hampton,2000.
[6]李家春.直升机环量控制尾梁发扭矩系统研究[D].南京:南京航空航天大学,2014.Li Jiachun. Research on helicopter circulation control tail boom anti-torque system[D]. Nanjing:Nanjing University of Aeronautics and Astronautics, 2014.(in Chinese)
[7]张雅铭,张玮.直升机基本原理[M].郑州:河南科学技术出版社,2008.Zhang Yaming, Zhang Wei. Helicopter basic principle[M].Zhengzhou:Henan Science and Technology Press, 2008.(in Chinese)
[8]艾伯特.G.布兰德,吉米.纳拉莫尔,詹姆斯.H.黑尔塞,等.翼型尾梁:中国,CN 103569359 A[P]. 2013.Brand A G, Narramore J, Hessel J H, et al. Airfoil tail boom:China, CN103569359 A[P]. 2013.(in Chinese)
[9] Wilson J C, Kelley H L. Helicopter low-speed yaw control. U.S., NASA CASE NO. LAR 14219-1[P].1992.
[10]Lockwood R A, Kelly W A, Carson R W. Flight characteristics test of the UH-60A with tail boom mounted strake[R]. NASA Technical Memorandum, ADA1807916XSP, 1986.
[11]李家春,杨卫东.直升机环量控制尾梁截面形状分析[J].空气动力学报, 2015, 33(2):239-245.Li Jiachun, Yang Weidong. An analysis of cross section of helicopter tail boom for NOTAR system[J]. Acta Aerodynamica Sinica, 2015,33(2):239-245.(in Chinese)
[12]董振兴,高亚东,王华明.环量控制尾梁参数对直升机尾梁侧向推力的影响[J].直升机技术, 2011(4):12-15.Dong Zhenxing, Gao Yadong, Wang Huaming. Influence of circulation control parameters on lateral thrust of helicopter tail boom in rotor downwash[J]. Helicopter Technique, 2011(4):12-15.(in Chinese)
[13]牟晓伟.环量控制尾梁系统设计与分析[D].南京:南京航空航天大学,2010.Mou Xiaowei. Design and analysis on NOTAR system[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2010.(in Chinese)
[14]黄明其.直升机风洞试验[M].北京:国防工业出版社,2014.Huang Mingqi. Helicopter wind tunnel experiment[M]. Beijing:National Defense Industry Press, 2014.(in Chinese)