圆柱体尾梁环量控制参数研究
|
摘要
无尾桨概念(NOTAR)改变了传统的尾桨设计概念,利用环量控制尾梁产生平衡旋翼反扭矩所需的力,从而取消尾桨,从根本上消除尾桨给直升机带来的各种不利影响。环量控制尾梁结构简单,安全性好,改善了可靠性和维护性,减少了直升机的振动和噪声,使操纵性能提高,特别适用于轻型直升机的飞行要求。
本文对用壁面射流控制圆柱绕流的环量控制参数进行了研究,利用FLUENT软件计算并分析了缝隙位置、几何尺寸和数目等参数对环量控制尾梁气动特性的影响。其中,动量系数和缝隙几何参数对圆柱尾梁上气动力的影响是研究重点。本文具体工作包括:
1.利用CATIA软件建立尾梁模型,采用了适用于尾梁流场计算的网格生成方法和网格生成软件GAMBIT进行对网格进行了划分;
2.采用动量源方法模拟旋翼下洗流,编制动量源程序并导入FLUENT软件进行环量控制尾梁的气动特性研究,分别对风洞和旋翼下洗流的流场进行仿真分析,根据所得数据分析缝隙位置、尺寸和数目等参数对尾梁气动特性的影响,获得了圆柱体尾梁气动力随环量控制参数变化的规律,确定最优参数的选取。
3.通过仿真数据与实验数据的对比分析,修正了环量控制尾梁理论模型,得到具有工程实用价值的分析模型,为后续实验研究工作提供理论指导。
研究结果表明,缝隙位置和动量系数对圆柱体尾梁的气动性能影响明显;采用双缝喷气和合适的动量系数可提高圆柱体尾梁的最大升力系数,也可降低喷气能量消耗。
NOTAR changed the conventional concept of helicopter tail rotor. This technology adopts a tail boom with circulation control to balance the rotor anti-torque for cancelling the tail rotor, which eliminates adverse effects of tail rotor on helicopters. The circulation control tail boom has a simple structure and good safety, which improves the reliability and maintainability and reduces vibrations and noises of helicopter. What’s more, it improves the manipulation of helicopter, so it is especially suitable for light helicopters.
This paper studied the parameters of circulation control cylinder, which was controlled by the wall jet flowing around it. The influence of the slots’geometric parameters such as position, size and number on aerodynamic characteristics of a circulation control tail boom was analyzed by using the FLUENT software, which focused on effects of momentum coefficient’s and slots’geometric parameters on aerodynamic characteristics of the tail boom. The detailed work in this paper includes:
First, a model of circulation control tail boom was established by using CATIA, and pre-treatment software of FLUENT, GAMBIT, was employed for meshing. A method for grid generation of flow field around the tail boom was presented.
Second, the momentum source model was used to analyze the rotor downwash and its code was programmed in FLUENT. Aerodynamic characteristic of the circulation control tail boom was studied. Wind tunnel and rotor downwash flow field were simulated and analyzed respectively. Influence of the slots’geometric parameters such as position, size and number on aerodynamic characteristics of the tail boom was analyzed according to the flow field data. The law that aerodynamic characteristics of the tail boom changing with the momentum coefficient and the slots’geometric parameters was obtained and the best parameters were chosen.
Third, the above CFD analysis results were compared with experimental data and the theoretical model of circulation control tail boom was revised. In the end, an analysis model for engineering practice was established to provide theoretical guidance for a following experimental study.
The results show that the slots position and momentum coefficient have marked influences on aerodynamic performance of the tail boom. Using double-slit jets and a proper momentum coefficient can help to increases the maximum lift coefficient of circulation control tail boom, and also can reduce the jet energy consumption.
本文对用壁面射流控制圆柱绕流的环量控制参数进行了研究,利用FLUENT软件计算并分析了缝隙位置、几何尺寸和数目等参数对环量控制尾梁气动特性的影响。其中,动量系数和缝隙几何参数对圆柱尾梁上气动力的影响是研究重点。本文具体工作包括:
1.利用CATIA软件建立尾梁模型,采用了适用于尾梁流场计算的网格生成方法和网格生成软件GAMBIT进行对网格进行了划分;
2.采用动量源方法模拟旋翼下洗流,编制动量源程序并导入FLUENT软件进行环量控制尾梁的气动特性研究,分别对风洞和旋翼下洗流的流场进行仿真分析,根据所得数据分析缝隙位置、尺寸和数目等参数对尾梁气动特性的影响,获得了圆柱体尾梁气动力随环量控制参数变化的规律,确定最优参数的选取。
3.通过仿真数据与实验数据的对比分析,修正了环量控制尾梁理论模型,得到具有工程实用价值的分析模型,为后续实验研究工作提供理论指导。
研究结果表明,缝隙位置和动量系数对圆柱体尾梁的气动性能影响明显;采用双缝喷气和合适的动量系数可提高圆柱体尾梁的最大升力系数,也可降低喷气能量消耗。
NOTAR changed the conventional concept of helicopter tail rotor. This technology adopts a tail boom with circulation control to balance the rotor anti-torque for cancelling the tail rotor, which eliminates adverse effects of tail rotor on helicopters. The circulation control tail boom has a simple structure and good safety, which improves the reliability and maintainability and reduces vibrations and noises of helicopter. What’s more, it improves the manipulation of helicopter, so it is especially suitable for light helicopters.
This paper studied the parameters of circulation control cylinder, which was controlled by the wall jet flowing around it. The influence of the slots’geometric parameters such as position, size and number on aerodynamic characteristics of a circulation control tail boom was analyzed by using the FLUENT software, which focused on effects of momentum coefficient’s and slots’geometric parameters on aerodynamic characteristics of the tail boom. The detailed work in this paper includes:
First, a model of circulation control tail boom was established by using CATIA, and pre-treatment software of FLUENT, GAMBIT, was employed for meshing. A method for grid generation of flow field around the tail boom was presented.
Second, the momentum source model was used to analyze the rotor downwash and its code was programmed in FLUENT. Aerodynamic characteristic of the circulation control tail boom was studied. Wind tunnel and rotor downwash flow field were simulated and analyzed respectively. Influence of the slots’geometric parameters such as position, size and number on aerodynamic characteristics of the tail boom was analyzed according to the flow field data. The law that aerodynamic characteristics of the tail boom changing with the momentum coefficient and the slots’geometric parameters was obtained and the best parameters were chosen.
Third, the above CFD analysis results were compared with experimental data and the theoretical model of circulation control tail boom was revised. In the end, an analysis model for engineering practice was established to provide theoretical guidance for a following experimental study.
The results show that the slots position and momentum coefficient have marked influences on aerodynamic performance of the tail boom. Using double-slit jets and a proper momentum coefficient can help to increases the maximum lift coefficient of circulation control tail boom, and also can reduce the jet energy consumption.
引文
[1]张呈林,郭才根.直升机总体设计.北京:国防工业出版社,2006.
[2]张呈林.直升机无尾桨技术的发展.第八届全国直升机年会论文,1992.
[3]罗晓平,张呈林,沈梦山.环量控制尾梁实验研究[J].空气动力学学报,1996年04期:387~393.
[4] Nielson N J,Biggers J C. Resent Progress in Circulation Control Aerodynamics. AIAA-87-0001,1987.
[5] Liu Jing-chang,Sun Mao,Wu Liyi. Navier-Stokes Analysis of a Circulation Control Airfoil.力学学报(英) ,1995,11(2):137～143.
[6] Gregory McGowan,Christopher Rumsey,R. Charles Swanson,et al. A Three-Dimensional Computational Study of a Circulation Control Wing. 3rd AIAA Flow Control Conference 5-8 June 2006,San Francisco, California. AIAA Paper 2006-3677.
[7] Geoffrey M. Lilley. Circulation Control for Quiet Commercial Aircraft. 3rd AIAA Flow Control Conference 5-8 June 2006,San Francisco,California. AIAA Paper 2006-2842.
[8] Warren J. Baker,Eric G. Paterson. RANS CFD Simulation of a Circulation-Control Foil:Validation of Performance,Flow Field,and Wall Jet. 3rd AIAA Flow Control Conference 5-8 June 2006,San Francisco,California.
[9] Kai Christoph Pfingsten,Rolf Radespie. Experimental and numerical investigation of a circulation control airfoil. 47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition 5 - 8 January 2009,Orlando,Florida
[10] Peter A. Chang, III,Joseph Slomski,Thomas Marino,et al. Numerical Simulation of Two-and Three-Dimensional Circulation Control Problems[C].43rd AIAA Aerospace Sciences Meeting and Exhibit 10-13 January 2005,Reno,Nevada.
[11] Dunham,J. A Theory of Circulation Control by Slot Blowing,Applied to a Circular Cylinder,Journal of Fluid Mechanics,Vol.33,Part 3,September 1968.
[12] David T.Fisher. Wind Tunnel Performance Comparative Test Results of A Circular Cylinder And 50% Ellipse Tailboom for Circulation Control Ant-torque Application. Thesis of Naval Postraduate School. March,1994.
[13]陶文栓.数值传热学(第二版).西安:西安交通大学出版社,2001.
[14]苏铭德,黄素逸著.计算流体力学基础.清华大学出版社,1997.1.
[15] Paul,Ralph and William L. Dynamics and control of tailless aircraft. AIAA Atmospheric Flight Mechanics Conference,AIAA 97-3776.
[16]金贺.直升机旋翼/机身/尾面的气动干扰分析. [硕士学位论文].南京:南京航空航天大学,2008.
[17] Landgrebe A J,Taylor R B,Bennett J C,Egolf T A. Helicopter Airflow and Wake Characteristics for Low Speed Flight. Proceedings of the 37th annual forum of American Helicopter Society,1981.
[18]王适存主编.直升机空气动力学.航空专业教材编审组出版,1985.
[19]徐国华,王适存.前飞状态直升机旋翼的自由尾迹计算.南京航空航天大学学报,Vol.29,No.6,1997.
[20]赵景根.直升机旋翼/机身气动干扰的计算. [硕士学位论文].南京:南京航空航天大学,1999.
[21]王福军编.计算流体动力学分析.清华大学出版社,2004.9.
[22] Mathur S R. and Rajagopalan. R Ganesh. Three dimensional analysis of a rotor in forward flight. Journal of the American Helicopter Society,V38,Jul.1993: p14-25.
[23] Chaffin M S. and Berry J D. Navier-Stokes simulation of a rotor using a distributed pressure disk method. Proceedings of 51st Annual Forum of AHS, 1995.
[24]王博.基于CFD方法的直升机旋翼/机身流场模拟及分析. [硕士学位论文].南京:南京航空航天大学,2007.
[25]钱翼稷编著.空气动力学.北京航空航天大学出版社,2005.2.
[26] W.约翰逊著.孙如林译.直升机理论.航空工业出版社,1991.
[27]王瑞金,张凯,王刚编著. Fluent技术基础与应用实例.清华大学出版社,2006.10.
[28]罗晓平.环量控制尾梁实验研究. [硕士学位论文].南京:南京航空航天大学,1995.3.
[29]徐有恒,穆晟.基础流体实验[M].上海:复旦大学出版社,1990.
[30] McKee J.W, R L. Naeseth. Experimental investigation of the drag of flat plates and cylinders in the slipstream of a hovering rotor. NASA Document ID: 19930085197,1958.
[31] Logan,A.h. Evaluation of a Circulation Control Tail Boom for Yaw Control. Hughes Helicopters,Inc. ,USARTL-TR-79-10,April 1978.
[32]韩占忠,王敬,兰小平编. FLUENT流体工程仿真计算实例与应用.北京理工大学出版社,2004.3.
[33]王瑞金,张凯,王刚编著. Fluent技术基础与应用实例.清华大学出版社,2006.10.
[34]徐恺.倾转旋翼飞行器旋翼/机翼/机身气动干扰计算. [硕士学位论文].南京:南京航空航天大学,2007.
[35]航空气动力手册编写组编.航空气动力手册(第二册).国防工业出版社,1983.6.
[36]王立群,乔志德,钟伯文.直升机旋翼悬停流场的欧拉方程计算,空气动力学学报,Vol. 16,No.3,1998.
[37]李人宪编.有限体积法基础.国防工业出版社,2005.7.
[38] Esteban,Sergio (Missouri, Univ, Rolla). Static and dynamic analysis of an unconventional plane - Flying wing. AIAA Atmospheric Flight Mechanics Conference and Exhibit. AIAA Paper 2001-4010.
[39] Rao,C.S. Tailboom Design of the American Helicopter,Presented at the 46th Forum of the American Helicopter Society.
[40]董振兴,高亚东,王华明.圆柱体尾梁环量控制技术研究[J].航空科学技术,2009年06期:17—21.
[2]张呈林.直升机无尾桨技术的发展.第八届全国直升机年会论文,1992.
[3]罗晓平,张呈林,沈梦山.环量控制尾梁实验研究[J].空气动力学学报,1996年04期:387~393.
[4] Nielson N J,Biggers J C. Resent Progress in Circulation Control Aerodynamics. AIAA-87-0001,1987.
[5] Liu Jing-chang,Sun Mao,Wu Liyi. Navier-Stokes Analysis of a Circulation Control Airfoil.力学学报(英) ,1995,11(2):137～143.
[6] Gregory McGowan,Christopher Rumsey,R. Charles Swanson,et al. A Three-Dimensional Computational Study of a Circulation Control Wing. 3rd AIAA Flow Control Conference 5-8 June 2006,San Francisco, California. AIAA Paper 2006-3677.
[7] Geoffrey M. Lilley. Circulation Control for Quiet Commercial Aircraft. 3rd AIAA Flow Control Conference 5-8 June 2006,San Francisco,California. AIAA Paper 2006-2842.
[8] Warren J. Baker,Eric G. Paterson. RANS CFD Simulation of a Circulation-Control Foil:Validation of Performance,Flow Field,and Wall Jet. 3rd AIAA Flow Control Conference 5-8 June 2006,San Francisco,California.
[9] Kai Christoph Pfingsten,Rolf Radespie. Experimental and numerical investigation of a circulation control airfoil. 47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition 5 - 8 January 2009,Orlando,Florida
[10] Peter A. Chang, III,Joseph Slomski,Thomas Marino,et al. Numerical Simulation of Two-and Three-Dimensional Circulation Control Problems[C].43rd AIAA Aerospace Sciences Meeting and Exhibit 10-13 January 2005,Reno,Nevada.
[11] Dunham,J. A Theory of Circulation Control by Slot Blowing,Applied to a Circular Cylinder,Journal of Fluid Mechanics,Vol.33,Part 3,September 1968.
[12] David T.Fisher. Wind Tunnel Performance Comparative Test Results of A Circular Cylinder And 50% Ellipse Tailboom for Circulation Control Ant-torque Application. Thesis of Naval Postraduate School. March,1994.
[13]陶文栓.数值传热学(第二版).西安:西安交通大学出版社,2001.
[14]苏铭德,黄素逸著.计算流体力学基础.清华大学出版社,1997.1.
[15] Paul,Ralph and William L. Dynamics and control of tailless aircraft. AIAA Atmospheric Flight Mechanics Conference,AIAA 97-3776.
[16]金贺.直升机旋翼/机身/尾面的气动干扰分析. [硕士学位论文].南京:南京航空航天大学,2008.
[17] Landgrebe A J,Taylor R B,Bennett J C,Egolf T A. Helicopter Airflow and Wake Characteristics for Low Speed Flight. Proceedings of the 37th annual forum of American Helicopter Society,1981.
[18]王适存主编.直升机空气动力学.航空专业教材编审组出版,1985.
[19]徐国华,王适存.前飞状态直升机旋翼的自由尾迹计算.南京航空航天大学学报,Vol.29,No.6,1997.
[20]赵景根.直升机旋翼/机身气动干扰的计算. [硕士学位论文].南京:南京航空航天大学,1999.
[21]王福军编.计算流体动力学分析.清华大学出版社,2004.9.
[22] Mathur S R. and Rajagopalan. R Ganesh. Three dimensional analysis of a rotor in forward flight. Journal of the American Helicopter Society,V38,Jul.1993: p14-25.
[23] Chaffin M S. and Berry J D. Navier-Stokes simulation of a rotor using a distributed pressure disk method. Proceedings of 51st Annual Forum of AHS, 1995.
[24]王博.基于CFD方法的直升机旋翼/机身流场模拟及分析. [硕士学位论文].南京:南京航空航天大学,2007.
[25]钱翼稷编著.空气动力学.北京航空航天大学出版社,2005.2.
[26] W.约翰逊著.孙如林译.直升机理论.航空工业出版社,1991.
[27]王瑞金,张凯,王刚编著. Fluent技术基础与应用实例.清华大学出版社,2006.10.
[28]罗晓平.环量控制尾梁实验研究. [硕士学位论文].南京:南京航空航天大学,1995.3.
[29]徐有恒,穆晟.基础流体实验[M].上海:复旦大学出版社,1990.
[30] McKee J.W, R L. Naeseth. Experimental investigation of the drag of flat plates and cylinders in the slipstream of a hovering rotor. NASA Document ID: 19930085197,1958.
[31] Logan,A.h. Evaluation of a Circulation Control Tail Boom for Yaw Control. Hughes Helicopters,Inc. ,USARTL-TR-79-10,April 1978.
[32]韩占忠,王敬,兰小平编. FLUENT流体工程仿真计算实例与应用.北京理工大学出版社,2004.3.
[33]王瑞金,张凯,王刚编著. Fluent技术基础与应用实例.清华大学出版社,2006.10.
[34]徐恺.倾转旋翼飞行器旋翼/机翼/机身气动干扰计算. [硕士学位论文].南京:南京航空航天大学,2007.
[35]航空气动力手册编写组编.航空气动力手册(第二册).国防工业出版社,1983.6.
[36]王立群,乔志德,钟伯文.直升机旋翼悬停流场的欧拉方程计算,空气动力学学报,Vol. 16,No.3,1998.
[37]李人宪编.有限体积法基础.国防工业出版社,2005.7.
[38] Esteban,Sergio (Missouri, Univ, Rolla). Static and dynamic analysis of an unconventional plane - Flying wing. AIAA Atmospheric Flight Mechanics Conference and Exhibit. AIAA Paper 2001-4010.
[39] Rao,C.S. Tailboom Design of the American Helicopter,Presented at the 46th Forum of the American Helicopter Society.
[40]董振兴,高亚东,王华明.圆柱体尾梁环量控制技术研究[J].航空科学技术,2009年06期:17—21.