后缘小翼智能旋翼减振效果影响因素分析
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摘要
建立了带后缘小翼智能旋翼气动弹性载荷计算模型及减振优化分析方法。模型考虑刚体后缘小翼的气动力与惯性力对弹性桨叶系统的影响,使用粘性涡粒子法结合翼型查表法计算旋翼气动载荷,采用力积分法计算桨叶与桨毂载荷,构造了包含桨叶根部扭转及桨毂振动载荷为目标函数的优化问题,基于最速下降-黄金分割组合优化算法寻找最佳小翼偏转规律。研究发现,建立的后缘小翼载荷控制方法有效,可降低振动目标函数70%。桨叶的弹性扭转使后缘小翼能有效实施减振,但弹性扭转对小翼气动力矩的放大作用使减振时通常伴随着桨叶扭转载荷增大的现象。
An aeroelastic load computation model and the optimization method of vibration control for a smart rotor wing with trailing edge flags were developed. The influences of aerodynamic forces and inertial forces of rigid body trailing edge flaps on its elastic blades system were considered. The viscous vortex particle method with the airfoil look-up table was used to compute the aerodynamic load of the rotor wing. The vibratory blade and hub loads were predicted with the force integration method. An optimal algorithm combining the steepest decent method and the golden section algorithm was derived for the defined objective function including the blade torsion and hub vibration loads. It was demonstrated that the proposed model can effectively control the vibratory loads,and the objective function can be reduced by about 70%; the torsion of elastic blades ensures the trailing edge flaps can effectively reduce vibration,while it amplifies the aerodynamic pitch moment of the trailing edge flaps,the latter brings additional blade torsional moment.
An aeroelastic load computation model and the optimization method of vibration control for a smart rotor wing with trailing edge flags were developed. The influences of aerodynamic forces and inertial forces of rigid body trailing edge flaps on its elastic blades system were considered. The viscous vortex particle method with the airfoil look-up table was used to compute the aerodynamic load of the rotor wing. The vibratory blade and hub loads were predicted with the force integration method. An optimal algorithm combining the steepest decent method and the golden section algorithm was derived for the defined objective function including the blade torsion and hub vibration loads. It was demonstrated that the proposed model can effectively control the vibratory loads,and the objective function can be reduced by about 70%; the torsion of elastic blades ensures the trailing edge flaps can effectively reduce vibration,while it amplifies the aerodynamic pitch moment of the trailing edge flaps,the latter brings additional blade torsional moment.
引文
[1]FRIEDMANN P P.On-blade control of rotor vibration,noise,and performance:Just around the corner?The 33rd Alexander Nikolsky Honorary Lecture[J].Journal of the American Helicopter Society,2014,59(4):1-37.
[2]FALLS J,DATTA A,CHOPRA I.Integrated trailing-edge flaps and servotabs for helicopter primary control[J].Journal of the American Helicopter Society,2010,55(3):1-15.
[3]PATT D,LIU L,FRIEDMANN P P.Rotorcraft vibration reduction and noise prediction using a unified aeroelastic response simulation[J].Journal of the American Helicopter Society,2005,50(1):95-106.
[4]DATTA A.Fundamental understanding,prediction and validation of rotor vibratory loads in steady-level flight[D].College Park:University of Maryland,2004.
[5]DATTA A,CHOPRA I.Validation and understanding of UH-60A vibratory loads in steady level flight[J].Journal of the American Helicopter Society,2004,49(3):271-287.
[6]KIM J S,SMITH E C,WANG K W.Helicopter blade loads control via multiple trailing-edge flaps[C]//AHS 62nd Annual Forum.Phoenix AZ:AHS International,2006:1000-1010.
[7]虞志浩,杨卫东,张呈林.基于Broyden法的旋翼多体系统气动弹性分析[J].航空学报,2012,33(12):2171-2182.YU Zhihao,YANG Weidong,ZHANG Chenglin.Aeroelasticity analysis of rotor multibody system based on Broyden method[J].Acta Aeronautica et Astronautica Sinica,2012,33(12):2171-2182.
[8]THEODORSEN T,GARRICK I E.Nonstationary flow about a wing-aileron-tab combination including aerodynamic balance[R].NACA Report 736,1942.
[9]谭剑锋,王浩文,吴超,等.基于非定常面元/黏性涡粒子混合法的旋翼/平尾非定常气动干扰[J].航空学报,2014,35(3):643-656.TAN Jianfeng,WANG Haowen,WU Chao,et al.Rotor/empennage un-steady aerodynamic interaction with unsteady pan-el/viscous vortex particle hybrid method[J].Acta Aeronautica et Astronautica Sinica,2014,35(3):643-656.
[10]吴杰,杨卫东,虞志浩.旋翼桨叶结构载荷计算方法比较研究[J].振动与冲击,2014,33(7):210-214.WU Jie,YANG Weidong,YU Zhihao.Comparison among rotor blade structural load calculation methods[J].Journal of Vibration and Shock,2014,33(7):210-214.
[11]KORATKAR N A,CHOPRA I.Analysis and testing of machscaled rotor with trailing edge flaps[J].AIAA Journal,2000,38(7):1113-1124.
[12]张柱,黄文俊,杨卫东.后缘小翼型智能旋翼桨叶模型设计分析与试验研究[J].南京航空航天大学学报,2011,43(3):296-301.ZHANG Zhu,HUANG Wenjun,YANG Weidong.Design analysis and test of smart rotor blades model with trailing edge flaps[J].Journal of Nanjing University of Aeronautics&Astronautics,2011,43(3):296-301.
[13]STALEY J A.Validation of rotorcraft flight simulation program through correlation with flight data for soft-in-plane hingeless rotors[R].AMRDL-TR-75-50,1976.
[14]HARRIS T A,LOWRY J G.Pressure distribution over an NACA 23012 airfoil with a fixed slot and a slotted flap[R].NACA-TR-633,1942.
[15]PETERSON R L,MAIER T.Correlation of wind tunnel and flight test results of a full-scale hingeless rotor[C]//AHS Aeromechanics Specialists Conference.Washington DC:AHS International,1994.
[16]张晓谷.直升机动力学设计[M].北京:航空工业出版社,1995.
[2]FALLS J,DATTA A,CHOPRA I.Integrated trailing-edge flaps and servotabs for helicopter primary control[J].Journal of the American Helicopter Society,2010,55(3):1-15.
[3]PATT D,LIU L,FRIEDMANN P P.Rotorcraft vibration reduction and noise prediction using a unified aeroelastic response simulation[J].Journal of the American Helicopter Society,2005,50(1):95-106.
[4]DATTA A.Fundamental understanding,prediction and validation of rotor vibratory loads in steady-level flight[D].College Park:University of Maryland,2004.
[5]DATTA A,CHOPRA I.Validation and understanding of UH-60A vibratory loads in steady level flight[J].Journal of the American Helicopter Society,2004,49(3):271-287.
[6]KIM J S,SMITH E C,WANG K W.Helicopter blade loads control via multiple trailing-edge flaps[C]//AHS 62nd Annual Forum.Phoenix AZ:AHS International,2006:1000-1010.
[7]虞志浩,杨卫东,张呈林.基于Broyden法的旋翼多体系统气动弹性分析[J].航空学报,2012,33(12):2171-2182.YU Zhihao,YANG Weidong,ZHANG Chenglin.Aeroelasticity analysis of rotor multibody system based on Broyden method[J].Acta Aeronautica et Astronautica Sinica,2012,33(12):2171-2182.
[8]THEODORSEN T,GARRICK I E.Nonstationary flow about a wing-aileron-tab combination including aerodynamic balance[R].NACA Report 736,1942.
[9]谭剑锋,王浩文,吴超,等.基于非定常面元/黏性涡粒子混合法的旋翼/平尾非定常气动干扰[J].航空学报,2014,35(3):643-656.TAN Jianfeng,WANG Haowen,WU Chao,et al.Rotor/empennage un-steady aerodynamic interaction with unsteady pan-el/viscous vortex particle hybrid method[J].Acta Aeronautica et Astronautica Sinica,2014,35(3):643-656.
[10]吴杰,杨卫东,虞志浩.旋翼桨叶结构载荷计算方法比较研究[J].振动与冲击,2014,33(7):210-214.WU Jie,YANG Weidong,YU Zhihao.Comparison among rotor blade structural load calculation methods[J].Journal of Vibration and Shock,2014,33(7):210-214.
[11]KORATKAR N A,CHOPRA I.Analysis and testing of machscaled rotor with trailing edge flaps[J].AIAA Journal,2000,38(7):1113-1124.
[12]张柱,黄文俊,杨卫东.后缘小翼型智能旋翼桨叶模型设计分析与试验研究[J].南京航空航天大学学报,2011,43(3):296-301.ZHANG Zhu,HUANG Wenjun,YANG Weidong.Design analysis and test of smart rotor blades model with trailing edge flaps[J].Journal of Nanjing University of Aeronautics&Astronautics,2011,43(3):296-301.
[13]STALEY J A.Validation of rotorcraft flight simulation program through correlation with flight data for soft-in-plane hingeless rotors[R].AMRDL-TR-75-50,1976.
[14]HARRIS T A,LOWRY J G.Pressure distribution over an NACA 23012 airfoil with a fixed slot and a slotted flap[R].NACA-TR-633,1942.
[15]PETERSON R L,MAIER T.Correlation of wind tunnel and flight test results of a full-scale hingeless rotor[C]//AHS Aeromechanics Specialists Conference.Washington DC:AHS International,1994.
[16]张晓谷.直升机动力学设计[M].北京:航空工业出版社,1995.