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static aeroelasticity of the propulsion system of ion propulsion unmanned aerial vehicles

Propulsion and Power Research 2023年第3期12卷 336-355页

作者： Shuai Hao Tielin Ma She Chen Hongzhong Ma Jinwu Xiang Fangxiang Ouyang School of Aeronautic Science and Engineering Beihang UniversityBeijing 100191China Research Institute of Unmanned Systems Beihang UniversityBeijing 100191China Hiwing General Aviation Equipment Co. Ltd.Beijing 100074China College of Electrical and Information Engineering Hunan UniversityChangsha 410082China

“Ionic wind”generators are used as the main propulsion system in ion propulsion unmanned aerial vehicles(UAVs).Owing to the large size and poor stiffness of the electrode array in the propulsion system,the electrode array is prone to deformation under the flight *** this work,the thrust characteristics and static aeroelastic properties of“ionic wind”propulsion systems were analyzed in *** simulation model for an“ionic wind”propulsion system was established by coupling a two-dimensional gas discharge model with a gas dynamics *** influences of electrode voltage,spacing,size,and shape on the performance of the propulsion system were *** fluid-solid interaction method was used to solve static aeroelastic characteristics under *** aerodynamic and thrust performances of the elastic state and the rigid state were *** was found that the operating voltage,the distance between two electrodes,and the emitter radius had greater impacts on the thrust of the propulsion *** propulsion system had a small contribution to the lift but a large contribution to the *** the elastic state,the lift coefficient accounted for 12.2%,and the drag coefficient accounted for 25.8%.Under the action of the downwash airflow from the wing,the propulsion system formed an upward moment around the center of mass,which contributed greatly to the pitching moment derivative of the whole *** the elastic state,the pitching moment derivative accounted for 29.7%.After elastic deformation,the thrust action point moved upward by 28.7 ***,the no lift pitching moment is reduced by 0.104 N$m,and the pitching moment coefficient is reduced by 0.014,causing a great impact on the longitudinal trimming of the whole aircraft.

关键词： Ion propulsion unmanned aerial vehicle(UAV) Propulsion system Electro-aerodynamics static aeroelasticity Fluid-solid interaction

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static aeroelasticity analysis of a rotor blade using a Gauss-Seidel fluid-structure interaction method

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Advances in Aerodynamics 2023年第1期5卷 478-496页

作者： Jiaxing Li Jiaqi Luo Yaolong Liu Zhonghua Han School of Aeronautics and Astronautics Zhejiang UniversityHangzhou 310027China School of Aeronautics Northwestern Polytechnical UniversityXi’an 710072China

The present study introduces a Gauss-Seidel fluid-structure interaction(FSI)method including the flow solver,structural statics solver and a fast data transfer technique,for the research of structural deformation and flow field variation of rotor blades under the combined influence of steady aerodynamic and centrifugal *** FSI method is illustrated and validated by the static aeroelasticity analysis of a transonic compressor rotor blade,NASA Rotor *** improved local interpolation with data reduction(LIWDR)algorithm is introduced for fast data transfer on the fluid-solid interface of *** results of FSI calculation of NASA Rotor 37 show that when compared with the radial basis function(RBF)based interpolation algorithm,LIWDR meets the interpolation accuracy requirements,while the calculation cost can be greatly *** data transmission time is only about 1%of that of ***,the iteration step of steady flow computation within one single FSI has little impact on the converged aerodynamic and structural *** aerodynamic load-caused deformation accounts for nearly 50%of the *** effects of blade deformation on the variations of aerodynamic performance are given,demonstrating that when static aeroelasticity is taken into account,the choke mass flow rate increases and the peak adiabatic efficiency slightly *** impact mechanisms on performance variations are presented in detail.

关键词： Fluid-structure interaction Rotor blade static aeroelasticity Data transfer aerodynamic performance

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DIRECT SOLUTION OF 2-DIMENSIONAL NAVIER-STOKES EQUATIONS FOR static aeroelasticity PROBLEMS

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AIAA JOURNAL 1993年第1期31卷 148-153页

作者： FELKER, FF NASA Ames Research Center Moffett Field California 94035

A new method has been developed to calculate the steady flow and structural deformations for fluid/structure interaction problems. The discretized fluid dynamic and structural equations are regarded as a single set of coupled, nonlinear, algebraic equations. The equilibrium solution is directly obtained using Newton's method. The governing equations used for the fluid flow are the two-dimensional Navier-Stokes equations, and a finite element model is used to represent the structure. This paper describes the analytical method and presents sample calculations demonstrating the technique. The results show rapid convergence and good agreement with experimental data.

关键词： static aeroelasticity Navier Stokes Equations Newton Raphson Method Finite Element Modeling Convergent Divergent Nozzles CFD Data Structures Aerodynamic Force Finite Volume Method Structural Modeling

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Fast Nonlinear static aeroelasticity Method for High-Aspect-Ratio Wings at Different Mach Regimes

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JOURNAL OF AIRCRAFT 2023年第4期60卷 1017-1037页

作者： Chandre-Vila, Oriol Boin, Jean-Philippe Barriety, Bernard Nivet, Yann Morlier, Joseph Gourdain, Nicolas Airbus Operat SAS Dept Loads & Aeroelast 316 Route Bayonne F-31060 Toulouse France Univ Toulouse Dept Mech Struct & Mat ICA ISAE SUPAEROMINES ALBIUPSINSACNRS 3 Rue Caroline Aigle F-31400 Toulouse France ISAE SUPAERO Dept Aerodynam Energet & Prop 10 Ave Edouard Belin F-31055 Toulouse France

A low-computational-cost method is proposed in this paper to predict steady-state nonlinear aeroelastic response for high-aspect-ratio wings. This fast nonlinear static aeroelasticity method relies on a simple but robust mathematical approach. The work presented in this paper evaluates the accuracy of a nonlinear aerodynamic method on a large range of Mach numbers for a geometry representative of a typical industrial high-aspect-ratio-wing aircraft. The robustness of the method relies on the accurate estimation of the local pressure field based on an aerodynamic database using a local incidence estimated with a vortex lattice method. The database can be filled with flight test, wind tunnel test, or high-fidelity numerical simulation. The structural deformation is provided by a coupled aeroelastic high-fidelity numerical simulation, and so this paper focuses mainly on the development and validation of the aerodynamic model. Then, the flexible coefficients of the wing are compared to the high-fidelity aeroelastic numerical simulations for a set of Mach numbers ranging from subsonic to transonic conditions. The results presented in this paper show that the present method is very accurate for low-Mach-number regimes (error is lower than 1% on lift), and it is also adapted to transonic flow regimes because the error on lift is lower than 5%. For high Mach numbers, the current solution commits larger errors on drag and pitching moment coefficients.

关键词： Aerodynamic Coefficients Incompressible Flow static aeroelasticity Transonic Flow Compressible Flow

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Effects of static aeroelasticity on composite wing characteristics under different flight attitudes

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Journal of Central South University 2013年第2期20卷 312-317页

作者：霍世慧袁喆王富生岳珠峰 Advanced Materials Test Center School of Mechanics and Civil Engineering & ArchitectureNorthwestern Polytechnical University

Composite wing static aeroelasticity was analyzed through a loosely coupled method and the effects on composite wing characteristics under different flight attitudes were presented. Structural analysis and aerodynamic analysis were carried out through finite element method (FEM) software NASTRAN and computational fluid dynamics (CFD) software FLUENT, respectively. Correlative data transfer and mesh regenerate procedure were applied to couple the results of computational structure dynamics (CSD) and CFD. After static aeroelasticity analysis under different flight attitudes, it can be seen that lift increases with the increase of flight speed and the incremental value enlarges gradually in both rigid and elastic wings. Lift presents a linear increment relationship with the increase of attack angle when the flight speed is 0.4Ma or 0.6Ma, but nonlinear increment in elastic wing when flight speed is 0.8Ma. On the effect of aeroelasticity, the maximum of deformation increases with the increase of flight speed and attack angle, and the incremental value decreases with the increase of flight speed while uniform with different attack angles. The results provide a reference for engineering applications.

关键词： static aeroelasticity elastic deformation aerodynamic characteristics structural characteristics flight attitudes

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Accelerated loosely-coupled CFD/CSD method for nonlinear static aeroelasticity analysis

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AEROSPACE SCIENCE AND TECHNOLOGY 2010年第4期14卷 250-258页

作者： Dang Huixue Yang Zhichun Li Yi Northwestern Polytech Univ Sch Aeronaut Xian 710072 Peoples R China

The flexible high-aspect-ratio wings of high-altitude long-endurance unmanned aerial vehicles experience large geometrical deformations. The nonlinear aeroelastic analysis for such a wing is carried out by using a loosely-coupled CFD/CSD method, which treats the fluid and structure as two separate modules and updates the CFD and CSD variables separately with a transfer of variables at the fluid-structure interface. In the loosely-coupled method employed here, an unsteady Euler solver and a nonlinear CSD solver are joined together by a fully three-dimensional integral constant volume tetrahedron (CVT) interfacing technique. The computation process is very time-consuming when the computed incremental displacements of every aerodynamic node on the wing surface are fully added to the previously computed deformed wing configuration. For a maximum deflection of approximately 8.7 mm (0.54% of semi-span length), the coupled computation scheme takes 20 coupling iteration steps with about 72 hours to converge on an HP XW6400 workstation with a 3 GHz Xeon5160 CPU. To reduce the computational expense of this loosely-coupled method, the golden section technique with an empirical parameter is introduced to speed up convergence. The deflections relaxed by using this technique are assimilated, and the wing bends up monotonically to its static equilibrium position with a maximum deflection 44.9 mm. The convergence history shows that, this accelerated algorithm takes just 6 coupling iteration steps with about 24 hours to monotonically converge to its static equilibrium position, although the maximum deflection 44.9 mm is 5 times larger than the maximum deflection 8.7 mm of the above test case with aeroelastic deflections fully assimilated. So, it is employed in the following nonlinear fluid-structure interaction (FSI) computations. After this nonlinear aeroelastic system has reached its static equilibrium position, the aerodynamic loads on wing surface are extracted and then applied

关键词： static aeroelasticity Loosely-coupled CFD/CSD method Structural geometric nonlinearity Acceleration technique Golden section

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static aeroelasticity Analysis of High Aspect Ratio Wing and the Jig-Shape Design based on Multi-block Structural Grid

Static Aeroelasticity Analysis of High Aspect Ratio Wing and...

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2013 International Conference on Mechanical Engineering and Materials(ICMEM 2013)

作者： LIU Yan BAI Jun-qiang HUA Jun School of Aeronautics Northwest Polytechnical University

The influence of structural elastic deformation on the aerodynamic characterisitcs of large transport aircraft has been researchedA method of static aeroelasticity based on multi-block structural grid of high aspect ratio wing has been established, and then a design method of jig-shape is developedThe technology of RBF interpolation is used to exchange the data of CFD/CSDBased on RBF&Delaunay technology, a mesh motion method is developed to make the design process less time-consuming, which can be applied to large deformation of multi-block structural gridThe static aeroelastic deformation of a wing-body of large transport aircraft is analyzedThen the wing-body's jig-shape is designedCompared the aerodynamic characteristics between design cruise shape and target cruise shape, it shows that the aerodynamic characteristics of design cruise shape is almost equal to target cruise shape and the design process of jig-shape is feasible.

关键词： static aeroelasticity Jig shape RBF interpolation method Mesh motion method Data exchange

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High-fidelity fluid-structure interaction applied to static aeroelasticity in transonic flows

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AEROSPACE SCIENCE AND TECHNOLOGY 2024年 153卷

作者： Lyrio, J. Allan A. Rade, Domingos A. Azevedo, Joao Luiz F. Inst Tecnol Aeronaut BR-12228900 Sao Jose Dos Campos SP Brazil Inst Aeronaut & Espaco BR-12228904 Sao Jose Dos Campos SP Brazil

Transonic flows at high Reynolds numbers can lead to high dynamic pressures and, consequently, to aerostructural deflections of aircraft structures. This study aims to develop and validate a high-fidelity static aeroelastic analysis environment that is efficient and that can be used in an industrial setting. The aerodynamics is represented by numerical solutions of the Reynolds-averaged Navier-Stokes equations with appropriate turbulence closures. The load transfer process uses finite element shape functions in order to distribute the aerodynamic loads into the structural discretization. The structural analysis employs a modal basis approach, and a wingtip deflection convergence study is performed to find an adequate modal basis size. Radial basis functions are used for the fluid mesh displacement, and the influence of the support radius is evaluated to determine the optimal values relative to the wing mean aerodynamic chord. The capability is tested using the static aeroelastic benchmarks of the High Reynolds Aerostructural Dynamics Project (HIRENASD) and NASA's Common Research Model (CRM). The static aeroelastic results demonstrate robustness and consistency for the aerodynamic coefficients, pressure distributions, and structural deflection predictions at different normalized dynamic pressure values and grid refinement levels.

关键词： static aeroelasticity CFD RANS equations HIRENASD NASA CRM Radial basis functions

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Modelling and analysis of two-dimensional static and dynamic aeroelasticity of Fish Bone Active Camber morphing aerofoils

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JOURNAL OF FLUIDS AND STRUCTURES 2024年 129卷

作者： Wu, Jun Woods, Benjamin K. S. Univ Bristol Dept Aerosp Engn Bristol BS8 1TR England Univ Oxford Dept Biol Oxford England

As a continuous and smooth morphing concept for aerofoils, the Fish Bone Active Camber (FishBAC) concept has demonstrated significant aerodynamic efficiency improvements over traditional hinged flaps. In this paper, to investigate the static and dynamic aeroelasticity of FishBAC aerofoils, an unsteady two dimensional coupled fluid-structure interaction model is developed, which includes the structural response of the FishBAC spine, skin, stringers, tendons and actuator, coupled to an unsteady aerodynamics model. The structural dynamic model is Timoshenko beam-theory-based, while the aerodynamic model is based on Peters' unsteady model. The static and dynamic aeroelasticity is studied after the model is validated. Results show that the increase in pulley rotational angle reduces the zero-lift angle of attack, while keeping the slope between the lift coefficient and angle of attack the same. A shorter morphing region closer to the trailing edge is beneficial for generating larger lift coefficient with the same tendon moment and angle of attack. Flutter occurs with the increase of the air speed. When the morphing end position is fixed at 0.9 chord, increasing the morphing length reduces the critical flutter speed significantly, with the second bending mode tending to drive instability. With the same morphing length, moving the morphing region closer to the leading edge increases the critical flutter speed, and the unstable mode changes from the second mode into the first mode.

关键词： static aeroelasticity Dynamic aeroelasticity Aerofoil morphing FishBAC concept Flutter

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Effects of aeroelastic coupling accuracy and geometrical nonlinearity performances of optimized composite wings

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AEROSPACE SCIENCE AND TECHNOLOGY 2025年 158卷

作者： Liu, Yajun Date, Shugo Nagashima, Toshio Okabe, Tomonaga Abe, Yoshiaki Tohoku Univ Inst Fluid Sci 2-1-1 Katahira Sendai Miyagi 9808577 Japan Tohoku Univ Dept Aerosp Engn 6-6-01 Aramaki Aza Aoba Sendai 9808579 Japan Sophia Univ Fac Sci & Technol Dept Engn & Appl Sci 7-1 KioichoChiyoda Ku Tokyo 1028554 Japan Univ Washington Dept Mat Sci & Engn Box 352120 Seattle WA 98195 USA

The design of next-generation aircraft utilizing carbon fiber-reinforced plastic (CFRP) has garnered significant attention due to its enhanced efficiency, driving the demand for simulation-based design approaches. This study presents a numerical investigation into the impact of aeroelastic coupling accuracy and geometrical nonlinearity on the aerodynamic performance and structural sizing of CFRP wings with optimized planforms and varying aspect ratios. The optimization process employed the NSGA-II genetic algorithm, integrated with a two-way aeroelastic analysis framework and structural sizing for CFRP wings. A trade-off between minimizing aerodynamic drag and structural weight was successfully identified. A comprehensive analysis of the optimal wing designs on the Pareto front was conducted, focusing on the effects of aeroelastic coupling accuracy, geometrical nonlinearity, and wingspan variations to evaluate their impacts on each objective function. The results revealed that optimal wing designs with higher aspect ratios demonstrated increased structural weight and reduced drag, and were more sensitive to the effects of coupling methods and geometrical nonlinearity due to their higher structural flexibility and resultant follower forces.

关键词： static aeroelasticity Multi-objective optimization Geometrical nonlinearity Aircraft wing Carbon fiber-reinforced plastic

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