旋翼高效/高精度气弹全耦合分析方法
收稿日期: 2025-02-25
修回日期: 2025-03-31
录用日期: 2025-04-29
网络出版日期: 2025-05-06
基金资助
国家自然科学基金(12472237);国家自然科学基金(12032012);航空科学基金(2024Z010052002);中国科协青年人才托举工程(2022QNRC001);国家重点实验室基金(61422202201);江苏高校优势学科建设工程
High-efficiency and high-precision aeroelastic full coupling method of rotor
Received date: 2025-02-25
Revised date: 2025-03-31
Accepted date: 2025-04-29
Online published: 2025-05-06
Supported by
National Natural Science Foundation of China(12472237);Aeronautical Science Foundation of China(2024Z010052002);Young Elite Scientists Sponsorship Program by CAST(2022QNRC001);National Laboratory Foundation of China(61422202201);Priority Academic Program Development of Jiangsu Higher Education Institutions
兼顾旋翼气弹耦合的计算精度及效率，建立了一套基于GEBT/VVPM/L-B全耦合旋翼气弹分析方法。结构上采用可有效考虑大变形的几何精确梁理论（GEBT）建立桨叶动力学模型，并耦合黏性涡粒子方法（VVPM）以及L-B动态失速模型，有效捕捉尾迹黏性流动和畸变以及桨叶的非定常气动特性。在动力学模型迭代求解过程中，将响应以参数化形式写入气动求解模块，实现旋翼气弹全耦合求解。以UH-60A的c8534高速前飞状态为例，通过与试验值和CFD/CSD紧耦合计算结果对比，验证了气弹全耦合方法的有效性。结果表明：相比于刚性旋翼，气弹全耦合求解模型可显著提高旋翼非定常气弹载荷的分析精度；相比于CFD/CSD耦合方法，在不影响计算精度的前提下，计算效率可提升54倍以上；前飞过程中桨叶的挥舞和扭转响应具有强非线性特性，在此状态下仍可有效预测旋翼气弹载荷，进一步验证了模型的鲁棒性。
王鑫 , 张夏阳 , 郑礼雄 , 向锦武 . 旋翼高效/高精度气弹全耦合分析方法[J]. 航空学报, 2025 , 46(S1) : 732161 -732161 . DOI: 10.7527/S1000-6893.2025.32161
To balance calculation accuracy and efficiency of rotor aeroelastic coupling analysis， a fully coupling aeroelastic method based on GEBT/VVPM/L-B is established. Structurally， the dynamic model of blade is established by using the Geometrically Exact Beam Theory （GEBT）， which effectively consider the large deformation. The Viscous Vortex Particle Method （VVPM） and the L-B dynamic stall model are coupled to consider the viscous flow， the distortion of the wake and the unsteady aerodynamics of the airfoil. In each iterative step， the aeroelastic response is inserted into the aerodynamic computation module in a parametric form to realize the full coupling strategy. The c8534 flight of UH-60A is introduced for verification， and the effectiveness of the aeroelastic coupling method is verified by comparing with the experiment and the CFD/CSD tight coupling result. The results show that the proposed method can improve the computational accuracy significantly relative to the rigid rotor model. Compared with the CFD/CSD coupling method， the calculation efficiency can be improved by more than 54 times without apparently affecting the calculation accuracy. The rotor aeroelastic loads can be effectively predicted in solving the strong nonlinear aeroelastic responses， which verifies the robustness of the model.
| [1] | ROSEN A， ISSER A. A new model of rotor dynamics during pitch and roll of a hovering helicopter［J］. Journal of the American Helicopter Society， 1995， 40（3）： 17-28. |
| [2] | PITT D M， PETERS D A. Theoretical prediction of dynamic-inflow derivatives［C］∥9th European Rotorcraft Forum. 1980. |
| [3] | 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. |
| [4] | 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）. | |
| [5] | BHAGWAT M J， LEISHMAN J G. Generalized viscous vortex model for application to free-vortex wake and aeroacoustic calculations［C］∥Proceedings of the Annual Forum Proceedings-American Helicopter Society. 2002. |
| [6] | 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. |
| [7] | JAIN R. Hover predictions for the S-76 rotor with tip shape variation using CREATE-AV helios［C］∥53rd AIAA Aerospace Sciences Meeting. Reston： AIAA， 2015. |
| [8] | NARDUCCI R. Hover performance assessment of several tip shapes using OVERFLOW［C］∥53rd AIAA Aerospace Sciences Meeting. Reston： AIAA， 2015. |
| [9] | 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. |
| [10] | 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. |
| [11] | HE C J， ZHAO J G. Modeling rotor wake dynamics with viscous vortex particle method［J］. AIAA Journal， 2009， 47（4）： 902-915. |
| [12] | 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. |
| [13] | STOCK M J， GHARAKHANI A. Solution-responsive particle size adaptivity in Lagrangian vortex particle methods［C］∥ASME 2021 Fluids Engineering Division Summer Meeting. 2021. |
| [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] | ALVAREZ E J， NING A. Development of a vortex particle code for the modeling of wake interaction in distributed propulsion［C］∥2018 Applied Aerodynamics Conference. Reston： AIAA， 2018. |
| [16] | SINGH P， FRIEDMANN P P. Application of vortex methods to coaxial rotor wake and load calculations in hover［J］. Journal of Aircraft， 2017， 55（1）： 373-381. |
| [17] | 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. |
| [18] | ALVAREZ E J， NING A. Modeling multirotor aerodynamic interactions through the vortex particle method［C］∥AIAA Aviation 2019 Forum. Reston： AIAA， 2019. |
| [19] | ALVAREZ E J， NING A. High-fidelity modeling of multirotor aerodynamic interactions for aircraft design［J］. AIAA Journal， 2020， 58（10）： 4385-4400. |
| [20] | 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）. | |
| [21] | 王清， 招启军， 赵国庆. 旋翼翼型动态失速流场特性PIV试验研究及L-B模型修正［J］. 力学学报， 2014， 46（4）： 631-635. |
| WANG Q， ZHAO Q J， ZHAO G Q. PIV experiments on flowfield characteristics of rotor airfoil dynamic stall and modifications of L-B model［J］. Chinese Journal of Theoretical and Applied Mechanics， 2014， 46（4）： 631-635 （in Chinese）. | |
| [22] | HODGES D H. Nonlinear composite beam theory［M］. Reston： AIAA， 2006. |
| [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［C］∥35th Wind Energy Symposium. Reston： AIAA， 2017. |
| [24] | FACCIO C J JR， CARDOZO A C P， 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 H， 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] | 王鑫， 张夏阳， 招启军， 等. 基于VVPM/GEBT耦合方法的旋翼悬停状态总距突增气弹载荷分析［J］. 航空学报， 2025， 46（16）： 231628. |
| WANG X， ZHANG X Y， ZHAO Q J， et al. Analysis of the aeroelastic loads of rotor during collective pitch ramp increase in hovering state based on VVPM/GEBT coupling method［J］. Acta Aeronautica et Astronautica Sinica， 2025， 46（16）： 231628 （in Chinese）. | |
| [29] | 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. |
| [30] | WILLIAMSON J H. Low-storage Runge-Kutta schemes［J］. Journal of Computational Physics， 1980， 35（1）： 48-56. |
| [31] | 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. |
| [32] | 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）. | |
| [33] | SITARAMAN J， BAEDER J， CHOPRA I. Validation of UH-60 rotor blade aerodynamic characteristics using CFD［C］∥Proceedings of the Annual Forum Proceedings-American Helicopter Society. 2003. |
| [34] | REVELES N. Advanced methods for dynamic aeroelastic analysis of rotors［D］. Atlanta： Georgia Institute of Technology， 2014. |
/
| 〈 |
|
〉 |
CJA