ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Aeroelastic loads of rotor during collective pitch ramp increase in hovering state based on VVPM/GEBT coupling method
Received date: 2024-12-09
Revised date: 2025-01-02
Accepted date: 2025-02-11
Online published: 2025-02-18
Supported by
National Natural Science Foundation of China(12102186);Aeronautical Science Foundation of China(2024Z010052002);Young Elite Scientists Sponsorship Program by CAST(2022QNRC001);The Priority Academic Program Development of Jiangsu Higher Education Institutions
To balance the computational accuracy and efficiency of rotor aeroelastic coupling analysis， the Viscous Vortex Particle Method （VVPM） and the Geometrically Exact Beam Theory （GEBT） tight-coupling method are developed. In aerodynamic aspect， the VVPM method and the Leishman-Beddoes （L-B） dynamic stall model which consider the influence of the elastic deformation are used to simulate the wake viscous flow of the rotor and the unsteady aerodynamic characteristics of blades. In structural aspect， the nonlinear dynamic equations which consider the collective pitch ramp increase have been developed based on the GEBT method. The high efficiency and accuracy characteristics of the coupling method are verified by comparative analyses of the steady/unsteady aerodynamic characteristics in the hovering state. Taking the BO105 rotor as a reference， the elastic responses of the blade and its influence on the aerodynamic characteristics are analyzed during collective pitch ramp increase in the hovering state. The results show that the dynamic stall phenomenon tends to occur when the initial collective pitch is large， leading to a rapid increase of the negative moment， a decrease of the section airfoil normal force coefficient， and a weakening of the thrust overshoot. At the end of the collective pitch ramp increase， the elastic blade has a larger range of thrust overshoot area compared to the rigid blade， resulting in a more serious thrust overshoot phenomenon. The delayed shedding of the rotor wake is captured through rotor vortex field simulation， revealing that the induced velocity of rotor disc is responsible for the thrust overshoot phenomenon of the rotor.
Xin WANG , Xiayang ZHANG , Qijun ZHAO , Jinwu XIANG . Aeroelastic loads of rotor during collective pitch ramp increase in hovering state based on VVPM/GEBT coupling method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2025 , 46(16) : 231628 -231628 . DOI: 10.7527/S1000-6893.2025.31628
| [1] | PITT D M， PETERS D A. Theoretical prediction of dynamic-inflow derivatives： ERF-1980-047［R］. 1980. |
| [2] | ZHOU X， ZHANG X Y， WANG B， et al. Aerodynamic and structural characteristics of helicopter rotor in circling flight?［J］. Chinese Journal of Aeronautics， 2023， 36（12）： 282-296. |
| [3] | 王俊超， 谭剑锋， 李建波， 等. 基于自由尾迹方法的自转旋翼气动特性研究［J］. 航空学报， 2015， 36（11）： 3540-3548. |
| WANG J C， TAN J F， LI J B， et al. Investigation of autorotating rotor aerodynamic characteristics based on free wake method［J］. Acta Aeronautica et Astronautica Sinica， 2015， 36（11）： 3540-3548 （in Chinese）. | |
| [4] | BHAGWAT M J， LEISHMAN J G. Generalized viscous vortex model for application to free-vortex wake algorithms?［C］?∥Proceedings of the Annual Forum of the American Helicopter Society. American Helicopter Society， 2002： 2042-2057. |
| [5] | KOMERATH N M， SMITH M J， TUNG C. A review of rotor wake physics and modeling［J］. Journal of the American Helicopter Society， 2011， 56（2）： 22006. |
| [6] | NARDUCCI R. Hover performance assessment of several tip shapes using OVERFLOW： AIAA-2015-1243［R］. Reston： AIAA， 2015. |
| [7] | JAIN R. Hover predictions for the S-76 rotor with tip shape variation using CREATE-AV Helios： AIAA-2015-1244［R］. Reston： AIAA， 2015. |
| [8] | GHARAKHANI A， GHONIEM A F. Three-dimensional vortex simulation of time dependent incompressible internal viscous flows［J］. Journal of Computational Physics， 1997， 134（1）： 75-95. |
| [9] | PLOUMHANS P， WINCKELMANS G S， SALMON J K， et al. Vortex methods for direct numerical simulation of three-dimensional bluff body flows： Application to the sphere at Re=300， 500， and 1 000［J］. Journal of Computational Physics， 2002， 178（2）： 427-463. |
| [10] | HE C J， ZHAO J G. Modeling rotor wake dynamics with viscous vortex particle method［J］. AIAA Journal， 2009， 47（4）： 902-915. |
| [11] | LAKKIS I， GHONIEM A. A high resolution spatially adaptive vortex method for separating flows. Part I： Two-dimensional domains［J］. Journal of Computational Physics， 2009， 228（2）： 491-515. |
| [12] | STOCK M J， GHARAKHANI A. Solution-responsive particle size adaptivity in Lagrangian vortex particle methods［C］?∥ASME 2021 Fluids Engineering Division Summer Meeting. New York： ASME， 2021. |
| [13] | ALVAREZ E J， NING A. Development of a vortex particle code for the modeling of wake interaction in distributed propulsion： AIAA-2018-3646［R］. Reston： AIAA， 2018. |
| [14] | CHENG H， GREENGARD L， ROKHLIN V. A fast adaptive multipole algorithm in three dimensions?［J］. Journal of Computational Physics， 1999， 155（2）： 468-498. |
| [15] | SINGH P， FRIEDMANN P P. Application of vortex methods to coaxial rotor wake and load calculations in hover［J］. Journal of Aircraft， 2018， 55（1）： 373-381. |
| [16] | TAN J， SUN Y， BARAKOS G N. Unsteady loads for coaxial rotors in forward flight computed using a vortex particle method［J］. The Aeronautical Journal， 2018， 122（1251）： 693-714. |
| [17] | ALVAREZ E J， NING A. High-fidelity modeling of multirotor aerodynamic interactions for aircraft design［J］. AIAA Journal， 2020， 58（10）： 4385-4400. |
| [18] | HE C J， RAJMOHAN N. Modeling the aerodynamic interaction of multiple rotor vehicles and compound rotorcraft with viscous vortex particle method［C］?∥American Helicopter Society 72nd Annual Forum. American Helicopter Society International， Inc.， 2016. |
| [19] | 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 J F， WANG H W， WU C， et al. Rotor/empennage unsteady aerodynamic interaction with unsteady panel/viscous vortex particle hybrid method［J］. Acta Aeronautica et Astronautica Sinica， 2014， 35（3）： 643-656 （in Chinese）. | |
| [20] | HODGES D H. Nonlinear composite beam theory［M］. Reston： AIAA， 2006. |
| [21] | YU W B， BLAIR M. GEBT： A general-purpose nonlinear analysis tool for composite beams?［J］. Composite Structures， 2012， 94（9）： 2677-2689. |
| [22] | WU J， MA Y J， WANG Z D， et al. Structurally coupled characteristics of rotor blade using new rigid-flexible dynamic model based on geometrically exact formulation［J］. Chinese Journal of Aeronautics， 2022， 35（6）： 186-197. |
| [23] | CHEN J G， SHEN X， LIU P Y， et al. Design tool for aeroelastic analysis of wind turbine blades based on geometrically exact beam theory and lifting surface method： AIAA-2017-0450［R］. Reston： AIAA， 2017. |
| [24] | FACCIO C J， CARDOZO Jr， ， MONTEIRO V， Jr， et al. Modeling wind turbine blades by geometrically-exact beam and shell elements： A comparative approach［J］. Engineering Structures， 2019， 180： 357-378. |
| [25] | WANG L， LIU X W， RENEVIER N， et al. Nonlinear aeroelastic modelling for wind turbine blades based on blade element momentum theory and geometrically exact beam theory［J］. Energy， 2014， 76： 487-501. |
| [26] | SHANG L N， XIA P Q， HODGES D H. Aeroelastic response analysis of composite blades based on geometrically exact beam theory［J］. Journal of the American Helicopter Society， 2019， 64（2）： 1-14. |
| [27] | CHANDRASEKARAN R， HODGES D H. Performance advantages and resonance analysis of a variable speed rotor using geometrically exact beam formulations［J］. Journal of the American Helicopter Society， 2022， 67（4）： 1-21. |
| [28] | 王华龙， 张夏阳， 赵国庆， 等. 基于CFD/CSD耦合的TEF旋翼气弹特性高精度模拟［J］. 航空学报， 2024， 45（18）： 229904. |
| WANG H L， ZHANG X Y， ZHAO G Q， et al. High-precision simulation of aeroelastic characteristics of TEF rotor based on CFD/CSD coupling［J］. Acta Aeronautica et Astronautica Sinica， 2024， 45（18）： 229904 （in Chinese）. | |
| [29] | 张凯， 招启军， 马砾， 等. 基于CFD/CSD耦合方法的旋翼降转速气动特性［J］. 航空动力学报， 2024， 39（12）： 20230074. |
| ZHANG K， ZHAO Q J， MA L， et al. Slowed rotor aerodynamic characteristics using CFD/CSD coupling method［J］. Journal of Aerospace Power， 2024， 39（12）： 20230074 （in Chinese）. | |
| [30] | ABHISHEK A， CHOPRA I. Prediction and validation of UTTAS pull-up maneuver using CFD/CSD coupling： AIAA-2011-1774［R］. Reston： AIAA， 2011. |
| [31] | 王博. 基于全本征方程的无铰式旋翼气动弹性分析方法［D］. 南京： 南京航空航天大学， 2015. |
| WANG B. Analytical method on aeroelasticity of hingeless rotor using fully intrinsic equations［D］. Nanjing： Nanjing University of Aeronautics and Astronautics， 2015 （in Chinese）. | |
| [32] | 李攀. 旋翼非定常自由尾迹及高置信度直升机飞行力学建模研究［D］. 南京： 南京航空航天大学， 2010. |
| LI P. Rotor unsteady free-vortex wake model and investigation on high-fidelity modeling of helicopter flight dynamics［D］. Nanjing： Nanjing University of Aeronautics and Astronautics， 2010 （in Chinese）. | |
| [33] | SINGH P， FRIEDMANN P P. A computational fluid dynamics-based viscous vortex particle method for coaxial rotor interaction calculations in hover［J］. Journal of the American Helicopter Society， 2018， 63（4）： 1-13. |
| [34] | WILLIAMSON J H. Low-storage Runge-Kutta schemes［J］. Journal of Computational Physics， 1980， 35（1）： 48-56. |
| [35] | WANG Q， YU W B. Geometrically nonlinear analysis of composite beams using Wiener-Milenkovi? parameters［J］. Journal of Renewable and Sustainable Energy， 2017， 9（3）： 033306. |
| [36] | 朱秋娴. 基于非定常动量源方法的倾转旋翼机气动分析及性能优化［D］. 南京： 南京航空航天大学， 2016. |
| ZHU Q X. Aerodynamic analysis and optimal design of tilt-rotor aircraft based on an unsteady momentum source method［D］. Nanjing： Nanjing University of Aeronautics and Astronautics， 2016 （in Chinese）. | |
| [37] | KOMP D， KUMAR S， HAJEK M， et al. Effect of active camber morphing on rotor performance and control loads［J］. Aerospace Science and Technology， 2021， 108： 106311. |
| [38] | LI P， CHEN R L. Rotor unsteady aerodynamics model using an efficient free-vortex method［J］. Aircraft Engineering and Aerospace Technology， 2012， 84（5）： 311-320. |
| [39] | WOODGATE M A， SHI Y J， FITZGIBBON T A， et al. Simulation of step input in collective pitch for hovering rotor［J］. Aerospace Science and Technology， 2021， 110： 106425. |
| [40] | CARPENTER P J， FRIDOVICH B. Effect of a rapid blade-pitch increase on the thrust and induced-velocity response of a full-scale helicopter rotor： NACA-TN-3044［R］. Washington， D.C.： NACA， 1953. |
| [41] | 邓景辉， 谭剑锋， 张呈林. 基于时间步进自由尾迹的旋翼总距突增气动响应分析［J］. 空气动力学学报， 2011， 29（2）： 217-221. |
| DENG J H， TAN J F， ZHANG C L. Analysis of rotor dynamic response during ramp increased collective pitch by time-step free wake［J］. Acta Aerodynamica Sinica， 2011， 29（2）： 217-221 （in Chinese）. |
/
| 〈 |
|
〉 |
CJA