带后缘小翼的旋翼振动载荷计算
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摘要
建立了考虑弹性桨叶、刚性小翼的旋翼气动弹性分析模型和旋翼载荷计算方法.以广义质量和广义力的形式描述小翼惯性力和气动力对系统的影响,以非定常/动态失速模型计算剖面气动力,结合基于实验数据修正的组合气动模型计算带小翼部分的剖面气动力,集成大变形桨叶模型考虑弹性变形的非线性,以力积分法计算桨叶剖面振动载荷.通过计算分析与实验结果相比较,验证了建立的气动弹性模型和载荷计算方法.结果表明:建立的桨叶结构模型精度很高,气弹模型能够准确预测旋翼的振动载荷,挥舞弯矩平均误差控制在9.1%,使用修正的小翼气动模型能有效提高小翼运动时桨叶振动载荷的计算精度.
A rotor aeroelastic model with elastic blade and rigid trailing edge flap and its load calculation method were developed.The inertial forces and aerodynamic forces of flap were described as generalized mass and generalized forces.The aerodynamic forces of the common airfoil were calculated with the unsteady/dynamic stall model,and those of the flapped airfoil were got from a coupled aerodynamic model corrected with experimental data.The nonlinear elastic deformation was considered by a large deformation blade model.The force integration method was used to predict the vibratory structural loads.The predicted results and the test results were compared to verify the aeroelastic model and the load calculation method.The results show the accuracy of the blade structure model is quite high.Vibratory loads of rotor can be calculated well with the aeroelastic model,the average error of flapwise moment is 9.1%.Prediction in the vibratory loads of blade with flap motion is implemented with corrected flapped airfoil aerodynamic model.
A rotor aeroelastic model with elastic blade and rigid trailing edge flap and its load calculation method were developed.The inertial forces and aerodynamic forces of flap were described as generalized mass and generalized forces.The aerodynamic forces of the common airfoil were calculated with the unsteady/dynamic stall model,and those of the flapped airfoil were got from a coupled aerodynamic model corrected with experimental data.The nonlinear elastic deformation was considered by a large deformation blade model.The force integration method was used to predict the vibratory structural loads.The predicted results and the test results were compared to verify the aeroelastic model and the load calculation method.The results show the accuracy of the blade structure model is quite high.Vibratory loads of rotor can be calculated well with the aeroelastic model,the average error of flapwise moment is 9.1%.Prediction in the vibratory loads of blade with flap motion is implemented with corrected flapped airfoil aerodynamic model.
引文
[1]Gagliardi A,Barakos G N.Analysis and design of a flap-equipped low-twist rotor for hover[J].Journal of Aircraft,2009,46(1):74-84.
[2]Dalli U,Yüksel爦.Identification of flap motion parameters for vibration reduction in helicopter rotors with multiple active trailing edge flaps[J].Shock and Vibration,2011,18(5):727-745.
[3]Maurice J B,King F A,Fichter W.Derivation and validation of a helicopter rotor model with trailing-edge flaps[J].Journal of Guidance,Control,and Dynamics.2013,36(5):1375-1387.
[4]Lee T,Chopra I.Development of a smart trailing-edge flap actuator with multistage stroke amplifier for a rotor blade[C]∥SPIE's 7th Annual International Symposium on Smart Structures and Materials.Bellingham:International Society for Optics and Photonics,2000:11-25.
[5]Szefi J T,Mockensturm E,Smith E C,et al.Development of a novel high authority piezoelectric actuator for rotor blades with trailing edge flaps[C]∥Proceedings of the AHS 62th Annual Forum.Phoenix,Arizona,USA:Curran Associates Incorporated,2006:839-849.
[6]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 and Astronautics,2011,43(3):296-301.(in Chinese)
[7]Dieterich O,Enenkl B,Roth D.Trailing edge flaps for active rotor control aeroelastic characteristics of the ADASYS rotor system[C]∥Proceedings of the AHS 62th Annual Forum.Phoenix,Arizona,USA:Curran Associates Incorporated,2006:964-985.
[8]Brandon H,Sesi K.Boeing SMART rotor full-scale wind tunnel test[R].NASA TM 2012-216048,2012.
[9]Potsdam M,Fulton M V,Dimanlig A.Multidisciplinary CFD/CSD analysis of the SMART active flap rotor[C]∥Proceedings of the AHS 66th Annual Forum.Washington DC:AHS International,2010:1991-2012.
[10]Gennaretti M,Molica Colella M,Bernardini G.Analysis of helicopter vibratory hub loads alleviation by cyclic trailingedge blade flap actuation[J].Aeronautical Journal,2009,113(1146):549-556.
[11]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.
[12]王荣,夏品奇.多片后缘小翼对直升机旋翼桨叶动态失速及桨毂振动载荷的控制[J].航空学报,2013,34(5):1083-1091.WANG Rong,XIA Pinqi.Control of helicopter rotor blade dynamic stall and hub vibration loads by multiple trailing edge flaps[J].Acta Aeronautica et Astronautica Sinica,2013,34(5):1083-1091.(in Chinese)
[13]Green R B,Gillies E A,Wang Y.Trailing-edge flap flow control for dynamic stall[J].Aeronautical Journal,2011,115(1170):493-503.
[14]杨卫东,张呈林,王适存,等.带受控振荡附翼的新概念旋翼气动弹性分析[J].航空学报,1999,20(2):161-163.YANG Weidong,ZHANG Chenglin,WANG Shicun,et al.Aeroelastic analysis of new concept rotor blade with controlled oscillating trailing edge flap[J].Chinese Journal of Aeronautics,1999,20(2):161-163.(in Chinese)
[15]虞志浩,杨卫东,邓景辉,等.基于多体动力学的旋翼模型与气弹稳定性[J].航空动力学报,2012,27(5):1122-1130.YU Zhihao,YANG Weidong,DENG Jinghui,et al.Model of rotor aeroelastic stability using dynamics of flexible multibody systems[J].Journal of Aerospace Power,2012,27(5):1122-1130.(in Chinese)
[16]陆洋,王浩文,高正.电控旋翼气弹动力学建模研究[J].航空动力学报,2006,21(6):1021-1026.LU Yang,WANG Haowen,GAO Zheng.Aeroelastic dynamic modeling of the electrically controlled rotor[J].Journal of Aerospace Power,2006,21(6):1021-1026.(in Chinese)
[17]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.(in Chinese)
[18]Leishman J G,Beddoes T S.A semi-empirical model for dynamic stall[J].Journal of the American Helicopter Society,1989,34(3):3-17.
[19]Bagai A,Leishman J G.Rotor free-wake modeling using a preudo-implicit algorithm[J].Journal of Aircraft,1995,32(6):1276-1285.
[20]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.(in Chinese)
[21]Peterson R L,Maier T,Langer H J,et al.Correlation of wind tunnel and flight test results of a full-scale hingeless rotor[R].San Francisco,California,USA:AHS Aeromechanics Specialists Conference,1994.
[22]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.
[23]Fulton M V,Ormiston R A.Hover testing of a small-scale rotor with on-blade elevons[J].Journal of the American Helicopter Society,2001,46(2):96-106.
[24]Fulton M V,Ormiston R A.Small-scale rotor experiments with on-blade elevons to reduce blade vibratory loads in forward flight[C]∥Proceedings of the AHS 54th Annual Forum.Washington DC:AHS International,1998:433-451.
[25]Terlizzi M D.Blade vortex interaction and its alleviation using passive and active control approaches[D].Los Angeles:University of California,1999.
[2]Dalli U,Yüksel爦.Identification of flap motion parameters for vibration reduction in helicopter rotors with multiple active trailing edge flaps[J].Shock and Vibration,2011,18(5):727-745.
[3]Maurice J B,King F A,Fichter W.Derivation and validation of a helicopter rotor model with trailing-edge flaps[J].Journal of Guidance,Control,and Dynamics.2013,36(5):1375-1387.
[4]Lee T,Chopra I.Development of a smart trailing-edge flap actuator with multistage stroke amplifier for a rotor blade[C]∥SPIE's 7th Annual International Symposium on Smart Structures and Materials.Bellingham:International Society for Optics and Photonics,2000:11-25.
[5]Szefi J T,Mockensturm E,Smith E C,et al.Development of a novel high authority piezoelectric actuator for rotor blades with trailing edge flaps[C]∥Proceedings of the AHS 62th Annual Forum.Phoenix,Arizona,USA:Curran Associates Incorporated,2006:839-849.
[6]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 and Astronautics,2011,43(3):296-301.(in Chinese)
[7]Dieterich O,Enenkl B,Roth D.Trailing edge flaps for active rotor control aeroelastic characteristics of the ADASYS rotor system[C]∥Proceedings of the AHS 62th Annual Forum.Phoenix,Arizona,USA:Curran Associates Incorporated,2006:964-985.
[8]Brandon H,Sesi K.Boeing SMART rotor full-scale wind tunnel test[R].NASA TM 2012-216048,2012.
[9]Potsdam M,Fulton M V,Dimanlig A.Multidisciplinary CFD/CSD analysis of the SMART active flap rotor[C]∥Proceedings of the AHS 66th Annual Forum.Washington DC:AHS International,2010:1991-2012.
[10]Gennaretti M,Molica Colella M,Bernardini G.Analysis of helicopter vibratory hub loads alleviation by cyclic trailingedge blade flap actuation[J].Aeronautical Journal,2009,113(1146):549-556.
[11]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.
[12]王荣,夏品奇.多片后缘小翼对直升机旋翼桨叶动态失速及桨毂振动载荷的控制[J].航空学报,2013,34(5):1083-1091.WANG Rong,XIA Pinqi.Control of helicopter rotor blade dynamic stall and hub vibration loads by multiple trailing edge flaps[J].Acta Aeronautica et Astronautica Sinica,2013,34(5):1083-1091.(in Chinese)
[13]Green R B,Gillies E A,Wang Y.Trailing-edge flap flow control for dynamic stall[J].Aeronautical Journal,2011,115(1170):493-503.
[14]杨卫东,张呈林,王适存,等.带受控振荡附翼的新概念旋翼气动弹性分析[J].航空学报,1999,20(2):161-163.YANG Weidong,ZHANG Chenglin,WANG Shicun,et al.Aeroelastic analysis of new concept rotor blade with controlled oscillating trailing edge flap[J].Chinese Journal of Aeronautics,1999,20(2):161-163.(in Chinese)
[15]虞志浩,杨卫东,邓景辉,等.基于多体动力学的旋翼模型与气弹稳定性[J].航空动力学报,2012,27(5):1122-1130.YU Zhihao,YANG Weidong,DENG Jinghui,et al.Model of rotor aeroelastic stability using dynamics of flexible multibody systems[J].Journal of Aerospace Power,2012,27(5):1122-1130.(in Chinese)
[16]陆洋,王浩文,高正.电控旋翼气弹动力学建模研究[J].航空动力学报,2006,21(6):1021-1026.LU Yang,WANG Haowen,GAO Zheng.Aeroelastic dynamic modeling of the electrically controlled rotor[J].Journal of Aerospace Power,2006,21(6):1021-1026.(in Chinese)
[17]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.(in Chinese)
[18]Leishman J G,Beddoes T S.A semi-empirical model for dynamic stall[J].Journal of the American Helicopter Society,1989,34(3):3-17.
[19]Bagai A,Leishman J G.Rotor free-wake modeling using a preudo-implicit algorithm[J].Journal of Aircraft,1995,32(6):1276-1285.
[20]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.(in Chinese)
[21]Peterson R L,Maier T,Langer H J,et al.Correlation of wind tunnel and flight test results of a full-scale hingeless rotor[R].San Francisco,California,USA:AHS Aeromechanics Specialists Conference,1994.
[22]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.
[23]Fulton M V,Ormiston R A.Hover testing of a small-scale rotor with on-blade elevons[J].Journal of the American Helicopter Society,2001,46(2):96-106.
[24]Fulton M V,Ormiston R A.Small-scale rotor experiments with on-blade elevons to reduce blade vibratory loads in forward flight[C]∥Proceedings of the AHS 54th Annual Forum.Washington DC:AHS International,1998:433-451.
[25]Terlizzi M D.Blade vortex interaction and its alleviation using passive and active control approaches[D].Los Angeles:University of California,1999.
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