受控后缘小翼智能旋翼气动弹性分析
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摘要
建立了一种考虑刚体小翼-弹性桨叶耦合的后缘小翼智能旋翼动力学分析模型,分析小翼受控后的旋翼气动弹性响应及动载荷变化。通过与SA349/2直升机的飞行实测数据比较,证实模型的计算结果可靠,精度与CAMRAD II软件相当。悬停状态基准旋翼的后缘小翼受控后,桨尖的挥舞/摆振/扭转响应都明显增加,且响应幅值基本随小翼的偏转角线性增加。对0.197前进比的前飞状态,以针对桨毂载荷的优化控制规律操纵后缘小翼偏转,挥舞与摆振响应变化不明显,震荡扭转响应的幅值明显增大。对于两个计算状态,挥舞响应与扭转响应收敛速度均比摆振响应快。
A dynamic analysis model for smart rotor was built to investigate the aeroelastic response and dynamic loads with controlled trailing edge flaps. The predicted results were compared to the flight test data of the SA349 /2 helicopter to verify the reliability of the aeroelastic model,and the model was verified to have the similar precision as the CAMRAD II. For the baseline rotor in hover,controlled trailing edge flaps can obviously increase the responses at blade tip in flap,lag and torsion directions. The amplitudes of responses linearly increase with the controlled deflection angle. In forward flight condition of 0. 197 advance ratio,control the flaps with an optimized control law for hub load reduction. The variation of flap and lag responses are not obvious,while the vibratory torsional response is significantly increased. For the discussed two conditions,the convergence rates of flap and torsion directions are faster than the lag direction.
A dynamic analysis model for smart rotor was built to investigate the aeroelastic response and dynamic loads with controlled trailing edge flaps. The predicted results were compared to the flight test data of the SA349 /2 helicopter to verify the reliability of the aeroelastic model,and the model was verified to have the similar precision as the CAMRAD II. For the baseline rotor in hover,controlled trailing edge flaps can obviously increase the responses at blade tip in flap,lag and torsion directions. The amplitudes of responses linearly increase with the controlled deflection angle. In forward flight condition of 0. 197 advance ratio,control the flaps with an optimized control law for hub load reduction. The variation of flap and lag responses are not obvious,while the vibratory torsional response is significantly increased. For the discussed two conditions,the convergence rates of flap and torsion directions are faster than the lag direction.
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.Journal of the American Helicopter Society,2014;59(4):1—37
2 Hagerty B,Kottapalli S.Boeing SMART rotor full-scale wind tunnel test data report.California:NASA Ames Research Center,2012
3 Sim B,Potsdam M,Kitaplioglu C,et al.Localized,nonharmonic active flap motions for low frequency in-plane rotor noise reduction.AHS 68th Annual Forum.Fort Worth,TX:AHS International,2012:8—23
4 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.南京航空航天大学学报,2011;43(3):296 —301Zhang Z,Huang W J,Yang W D.Design analysis and test of smart rotor blades model with trailing edge flaps.Journal of Nanjing University of Aeronautics&Astronautics,2011;43(3):296—301
5 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.航空学报,2013;34(5):1083—1091Wang R,Xia P Q.Control of dynamic stall of helicopter rotor blades.Acta Aeronautica et Astronautica Sinica,2013;34(5):1083—1091
6 刘洋,向锦武.后缘襟翼对直升机旋翼翼型动态失速特性的影响.航空学报,2013;34(5):1028—1035Liu Y,Xiang J W.Effect of the trailing edge flap on dynamic stall performance of helicopter rotor airfoil.Acta Aeronautica et Astronautica Sinica,2013;34(5):1028—1035
7 尚丽娜,夏品奇.可变翼型动态失速气动模型研究.中国科学:技术科学,2015;45(9):975—983Shang L N,Xia P Q.Study of aerodynamic model for morphing airfoils in dynamic stall.Scientia Sinica Technologica,2015;45(9):975 —983
8 吴杰,杨卫东,虞志浩.基于几何精确桨叶模型的旋翼刚柔耦合建模.科学技术与工程,2014;14(31):119—123Wu J,Yang W D,Yu Z H.Rotor rigid-flexible coupling modeling based on geometrically exact beam model.Science Technology and Engineering,2014;14(31):119—123
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.航空学报,2014;35(3):643 —656Tan J F,Wang H W,Wu C,et al.Rotor/empennage unsteady aerodynamic interaction with unsteady panel/viscous vortex particle hybrid method.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.振动与冲击,2014;33(7):210—214Wu J,Yang W D,Yu Z H.Comparison among rotor blade structural load calculation methods.Journal of Vibration and Shock,2014;33 (7):210—214
11 Heffernan R,Gaubert M.Structural and aerodynamic loads and performance measurements of an SA349/2 helicopter with an advanced geometry rotor.Washingon DC:NASA,1986
12 Yeo H,Johnson W.Assessment of comprehensive analysis calculation of airloads on helicopter rotors.Journal of Aircraft,2005;42(5):1218—1228
2 Hagerty B,Kottapalli S.Boeing SMART rotor full-scale wind tunnel test data report.California:NASA Ames Research Center,2012
3 Sim B,Potsdam M,Kitaplioglu C,et al.Localized,nonharmonic active flap motions for low frequency in-plane rotor noise reduction.AHS 68th Annual Forum.Fort Worth,TX:AHS International,2012:8—23
4 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.南京航空航天大学学报,2011;43(3):296 —301Zhang Z,Huang W J,Yang W D.Design analysis and test of smart rotor blades model with trailing edge flaps.Journal of Nanjing University of Aeronautics&Astronautics,2011;43(3):296—301
5 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.航空学报,2013;34(5):1083—1091Wang R,Xia P Q.Control of dynamic stall of helicopter rotor blades.Acta Aeronautica et Astronautica Sinica,2013;34(5):1083—1091
6 刘洋,向锦武.后缘襟翼对直升机旋翼翼型动态失速特性的影响.航空学报,2013;34(5):1028—1035Liu Y,Xiang J W.Effect of the trailing edge flap on dynamic stall performance of helicopter rotor airfoil.Acta Aeronautica et Astronautica Sinica,2013;34(5):1028—1035
7 尚丽娜,夏品奇.可变翼型动态失速气动模型研究.中国科学:技术科学,2015;45(9):975—983Shang L N,Xia P Q.Study of aerodynamic model for morphing airfoils in dynamic stall.Scientia Sinica Technologica,2015;45(9):975 —983
8 吴杰,杨卫东,虞志浩.基于几何精确桨叶模型的旋翼刚柔耦合建模.科学技术与工程,2014;14(31):119—123Wu J,Yang W D,Yu Z H.Rotor rigid-flexible coupling modeling based on geometrically exact beam model.Science Technology and Engineering,2014;14(31):119—123
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.航空学报,2014;35(3):643 —656Tan J F,Wang H W,Wu C,et al.Rotor/empennage unsteady aerodynamic interaction with unsteady panel/viscous vortex particle hybrid method.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.振动与冲击,2014;33(7):210—214Wu J,Yang W D,Yu Z H.Comparison among rotor blade structural load calculation methods.Journal of Vibration and Shock,2014;33 (7):210—214
11 Heffernan R,Gaubert M.Structural and aerodynamic loads and performance measurements of an SA349/2 helicopter with an advanced geometry rotor.Washingon DC:NASA,1986
12 Yeo H,Johnson W.Assessment of comprehensive analysis calculation of airloads on helicopter rotors.Journal of Aircraft,2005;42(5):1218—1228