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Chinese Journal of Aeronautics 2021年第1期34卷 380-396页

作者： Yang MENG zhiqiang wan Changchuan XIE Chao AN School of Aeronautic Science and Engineering Beihang UniversityBeijing 100083China

A theoretical formulation for time-domain nonlinear aeroelastic analysis of a flexible wing model is presented and validated by wind tunnel tests. A strain-based beam model for nonlinear structural analysis is combined with the Unsteady Vortex Lattice Method(UVLM) to form the complete framework for aeroelastic analysis. The nonlinear second-order differential equations are solved by an implicit time integration scheme that incorporates a Newton-Raphson sub-iteration technique. An advanced fiber optic sensing technique is firstly used in a wind tunnel for measuring large structural deformations. In the theoretical study, the nonlinear flutter boundary is determined by analyzing the transient response about the nonlinear static equilibrium with a series of flow velocities. The gust responses of the wing model at various gust frequencies are also studied. Comparisons of the theoretical and experimental results show that the proposed method is suitable for determining the nonlinear flutter boundary and simulating the gust response of flexible wings in the time domain.

关键词： Flexible wings Flutter Geometric nonlinearity Gust response Wind tunnel test

Integrated optimization on aerodynamics-structure coupling and flight stability of a large airplane in preliminary design

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Chinese Journal of Aeronautics 2018年第6期31卷 1258-1272页

作者： Xiaozhe wanG zhiqiang wan Zhu LIU Chao YANG School of Aeronautic Science and Engineering Beihang University Key Laboratory of Aircraft Advanced Design Technology Ministry of Industry and Information

The preliminary phase is significant during the whole design process of a large airplane because of its enormous potential in enhancing the overall performance. However, classical sequential designs can hardly adapt to modern airplanes, due to their repeated iterations, long periods, and massive computational burdens. Multidisciplinary analysis and optimization demonstrates the capability to tackle such complex design issues. In this paper, an integrated optimization method for the preliminary design of a large airplane is proposed, accounting for aerodynamics, structure, and stability. Aeroelastic responses are computed by a rapid three-dimensional flight load analysis method combining the high-order panel method and the structural elasticity correction. The flow field is determined by the viscous/inviscid iteration method, and the cruise stability is evaluated by the linear small-disturbance theory. Parametric optimization is carried out using genetic algorithm to seek the minimal weight of a simplified plate-beam wing structure in the cruise trim condition subject to aeroelastic, aerodynamic, and stability constraints, and the optimal wing geometry shape, front/rear spar positions, and structural sizes are obtained simultaneously. To reduce the computational burden of the static aeroelasticity analysis in the optimization process, the Kriging method is employed to predict aerodynamic influence coefficient matrices of different aerodynamic shapes. The multidisciplinary analyses guarantee computational accuracy and efficiency, and the integrated optimization considers the coupling effect sufficiently between different disciplines to improve the overall performance, avoiding the limitations of sequential approaches utilized currently.

关键词： Aeroelasticity Integrated optimization Multidisciptinary analysis Large airplane Preliminary design

Aeroelastic two-level optimization for preliminary design of wing structures considering robust constraints

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Chinese Journal of Aeronautics 2014年第2期27卷 259-265页

作者： wan zhiqiang Zhang Bocheng Du Ziliang Yang Chao School of Aeronautic Science and Engineering Beihang University Beijing Aeronautical Science & Technology Research Institute of COMAC

An aeroelastic two-level optimization methodology for preliminary design of wing struc- tures is presented, in which the parameters for structural layout and sizes are taken as design vari- ables in the first-level optimization, and robust constraints in conjunction with conventional aeroelastic constraints are considered in the second-level optimization. A low-order panel method is used for aerodynamic analysis in the first-level optimization, and a high-order panel method is employed in the second-level optimization. It is concluded that the design of the abovementioned structural parameters of a wing can be improved using the present method with high efficiency. An improvement is seen in aeroelastic performance of the wing obtained with the present method when compared to the initial wing. Since these optimized structures are obtained after consideration of aerodynamic and structural uncertainties, they are well suited to encounter these uncertainties when they occur in reality.

关键词： Aeroelasticity Preliminary design Robust optimization Structure optimization Uncertainty

Stiffness Distribution and Aeroelastic Performance Optimization of High-Aspect-Ratio Wings

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Transactions of Nanjing University of Aeronautics and Astronautics 2016年第3期33卷 243-251页

作者： wan zhiqiang Du Ziliang Wu Qiang Yang Chao School of Aeronautic Science and Engineering Beihang University Beijing 100191 P. R. China Shanghai Aircraft Design and Research Institute Shanghai 201210 P. R. China

The relationship between stiffness distribution and aeroelastic performance for a beam-frame model and a3-D model is investigated based on aeroelastic optimization of global stiffness design for high-aspect-ratio *** sensitivity information of wing spanwise stiffness distribution with respect to the twist angle at wing tip,the vertical displacement at wing tip,and the flutter speed are obtained using a sensitivity method for both *** the relationship between stiffness distribution and aeroelastic performance is summarized to guide the design *** using the genetic/sensitivity-based hybrid algorithm,an optimal solution satisfying the strength,aeroelastic and manufacturing constraints is *** is found that the summarized guidance is well consistent with the optimal solution,thus providing a valuable design advice with *** study also shows that the aeroelastic-optimization-based global stiffness design procedure can obtain the optimal solution under multiple constraints with high efficiency and precision,thereby having a strong application value in engineering.

关键词： aeroelastic high-aspect-ratio wing stiffness design structural optimization sensitivity analysis

A method for static aeroelastic analysis based on the high-order panel method and modal method

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Science China(Technological Sciences) 2011年第3期54卷 741-748页

作者： YANG Chao ZHANG BoCheng wan zhiqiang wanG YaoKun School of Aeronautic Science and Engineering Beijing University of Aeronautics & Astronautics Beijing 100191 China

A method for static aeroelastic analysis based on the high-order panel method and modal method is presented. The static aeroelastic characteristics of flexible wings are investigated using this method. Three-dimensional aerodynamic models of flexible wings are constructed based on the geometry of wing configuration, and the modal method is adopted to achieve the fluid-structure coupling. The static aeroelastic characteristics of the AGARD445.6 wing and a low-aspect-ratio wing are investigated in this study. The influences of elastic structural deformation on aerodynamic forces are studied with an emphasis analyzing the aerodynamic coefficients, wing root loads, structural deformation and pressure distribution of different sections, and results are compared with the results from wind-tunnel tests and the elastic results based on experimental aerodynamic forces. It is concluded that aerodynamic forces can be accurately calculated with the high-order panel method. The method presented in this study is feasible, credible and efficient. Comprehensive static aeroelastic characteristics can be provided by the method for early phases of aircraft design.

关键词： aeroelasticity flight loads high-order panel method modal method experimental aerodynamic forces

Studies on the influence of spar position on aeroelastic optimization of a large aircraft wing

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Science China(Technological Sciences) 2012年第1期55卷 117-124页

作者： wan zhiqiang LIU DongYue TANG ChangHong YANG Chao School of Aeronautic Science and Engineering Beihang University Beijing 100191 China

Aeroelastic problems are encountered at the preliminary design stage of flexible wings for large aircraft. A three-dimensional finite element model of a high-aspect-ratio wing was built, and the influence of the front and rear spar positions on the results of the aeroelastic analysis and optimization was studied to improve the wing structure desgin. The most feasible and optimal solutions were effectively obtained by aeroelastic optimization. In particular, the position parameter of the front spar has a greater influence on the aeroelastic analysis and optimization than the rear spar. In addition, some key constraints became re- strictive leading to a rapid increase in the structural weight. Therefore, reasonable constraints were necessary for the optimization of results.

关键词： large aircraft aeroelasticity optimization design high-aspect-ratio wing spar

Two-Way-Coupling Method for Rapid Aerothermoelastic Analyses of Hypersonic Wings

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Transactions of Nanjing University of Aeronautics and Astronautics 2018年第1期35卷 135-145页

作者： wan zhiqiang Yi Nan Li Guoshu Yang Chao School of Aeronautics Science and Engineering Beihang UniversityBeijing 100191P.R.China Key Laboratory of Aircraft Advanced Design Technology(Behang University) Ministry of Industry and Information TechnologyBeijing 100191P.R.China Beijing Institute of Nearspace Vehicle′s Systems Engineer Beijing 100076P.R.China

Several types of coupling methods for resolving aerothermoelastic problems associated with hypersonic wings are summarized,and the appropriate coupling methods for engineering calculations are ***,the calculation and analysis methods for the subdisciplines in this field are introduced,and the time step issue is discussed.A two-way-coupling rapid static aerothermoelastic method for analyzing hypersonic wings is *** method considers thermal effects and is used to conduct an aerothermoelastic response analysis for a hypersonic *** addition,the aerodynamic force,heat flux,structural deformation and temperature field are *** following three conclusions are ***,the heating effect has a significant impact on the static aeroelastic response of hypersonic wings;therefore,thermal protection shields are ***,the application of thermal protection shields reduces the differences in the calculation results between the one-and two-way-coupling ***,hypersonic wings exhibit large thermal deformation under high-temperature environments,and in certain cases,the thermal deformation is even larger than the deformation caused by aerodynamic force.

关键词： hypersonic aerothermoelastic two-way-coupling aerodynamic heating thermal deformation

Static aeroelastic analysis of a high-aspect-ratio wing based on wind-tunnel experimental aerodynamic forces

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Science China(Technological Sciences) 2011年第10期54卷 2716-2722页

作者： wan zhiqiang ZHANG BoCheng YANG Chao XU Yan School of Aeronautic Science and Engineering Beijing University of Aeronautics & Astronautics Beijing 100191 China Research and Development Center Chengdu Aircraft and Industrial Group Crop. Ltd. Chengdu 610092 China

The aeroelastic responses of a high-aspect-ratio wing are investigated based on nonlinear experimental aerodynamic forces. The influences of nonlinear experimental aerodynamic forces and dynamic pressures on the wing loads are studied in the longitudinal and lateral maneuver states. The flight loads of the wing fixed at the root are calculated at different angles of attack. The aileron efficiency with respect to the dynamic pressures and aileron deflections are also studied. The results indicate that the flight loads of the wings vary nonlinearly with the angle of attack and dynamic pressure. Due to the high-lift aerofoil, elastic components are a large portion of the wing loads, especially for small angles of attack and high dynamic pressure condi-tions. The aileron efficiency is significantly affected by aileron deflections, dynamic pressures and angles of attack when the nonlinear experimental aerodynamic forces are used for calculation. In states with high dynamic pressures and large aileron deflections, aileron reversal can occur. The aileron deflection and angle of attack have a nonlinear effect on the aileron efficiency. An efficient method for analyzing the flight loads and structural design of high-aspect-ratio wings is derived in this study, and the analysis can provide insight into the distribution of flight loads for high-aspect-ratio wings.

关键词： high-aspect-ratio wing aeroelasticity flight loads aileron efficiency aileron reversal experimental aerodynamic forces

A high-efficiency aerothermoelastic analysis method

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Science China(Physics,Mechanics & Astronomy) 2014年第6期57卷 1111-1118页

作者： wan zhiqiang wanG YaoKun LIU YunZhen YANG Chao School of Aeronautic Science and Engineering Beihang University

In this paper,a high-efficiency aerothermoelastic analysis method based on unified hypersonic lifting surface theory is *** method adopts a two-way coupling form that couples the structure,aerodynamic force,and aerodynamic thermo and heat *** aerodynamic force is first calculated based on unified hypersonic lifting surface theory,and then the Eckert reference temperature method is used to solve the temperature field,where the transient heat conduction is solved using Fourier’s law,and the modal method is used for the aeroelastic ***,flutter is analyzed based on the p-k *** aerothermoelastic behavior of a typical hypersonic low-aspect ratio wing is then analyzed,and the results indicate the following:(1)the combined effects of the aerodynamic load and thermal load both deform the wing,which would increase if the flexibility,size,and flight time of the hypersonic aircraft increase;(2)the effect of heat accumulation should be noted,and therefore,the trajectory parameters should be considered in the design of hypersonic flight vehicles to avoid hazardous conditions,such as flutter.

关键词： aerothermoelastic two-way coupling unified hypersonic lifting surface theory piston theory flutter

Aeroelastic optimization on composite skins of large aircraft wings

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Science China(Technological Sciences) 2012年第6期55卷 1078-1085页

作者： LIANG Lu wan zhiqiang YANG Chao School of Aeronautic Science and Engineering Beijing University of Aeronautics and AstronauticsBeijing 100191China

This paper presents studies of aeroelastic optimization on composite skins of large aircraft wings subject to aeroelastic constraints and strength/strain constraints. The design variable for optimization was the ply thickness of the wing skin panels, and the structural weight was the objective function to be minimised. The impacts of three strength/strain constraints and the ply proportion of the wing skin panels on the optimization results are discussed. The results indicate that the optimal composite wings that satisfy different constraints have remarkable weight advantages over metal wing. High levels of stiffness can be achieved while satisfying the constraints regarding allowable design strains and failure criteria. The optimization results with variable-proportions indicate that wing skins with higher proportions of 0° plies from the root to the middle segment and ±45° plies outboard have a more efficient and reasonable stiffness distribution.

关键词： aeroelastic optimization large aircraft composite wing strength constraints ply proportion

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