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

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....     

Reliability-based design optimization of aeroelastic structures

Aeroelastic phenomena are most often either ignored or roughly approximated when uncertainties are considered in the design optimization process of structures subject to aerodynamic loading, affecting the quality of the optimization results. Therefore, a design methodology is proposed that combines reliability-based design optimization and high-fidelity aeroelastic simulations for the analysis and design of aeroelastic structures. To account for uncertainties in design and operating conditions, a first-order reliability method (FORM) is employed to approximate the system reliability. To limit model uncertainties while accounting for the effects of given uncertainties, a high-fidelity nonlinear aeroelastic simulation method is used. The structure is modelled by a finite element method, and the aerodynamic loads are predicted by a finite volume discretization of a nonlinear Euler flow. The usefulness of the employed reliability analysis in both describing the effects of uncertainties on a particular design and as a design tool in the optimization process is illustrated. Though computationally more expensive than a deterministic optimum, due to the necessity of solving additional optimization problems for reliability analysis within each step of the broader design optimization procedure, a reliability-based optimum is shown to be an improved design. Conventional deterministic aeroelastic tailoring, which exploits the aeroelastic nature of the structure to enhance performance, is shown to often produce designs that are sensitive to variations in system or operational parameters.     

基于H无穷范数的颤振分析方法

颤振是一种典型的气动弹性动不稳定现象, 求解颤振临界点是气动弹性稳定性分析的重要任务之一.从H_∞控制理论观点出发, 将气动弹性系统视为多输入多输出系统, 并导出其传递函数矩阵. 在颤振临界点附近, 根据系统传递函数矩阵的H_∞–范数趋于无穷大的特点, 发展了相应的颤振临界点搜索方法. 与传统的颤振分析方法相比, 该方法属于完全频域方法, 算法更为简洁, 且具有更高的自动化程度. 数值算例表明, 该方法可以获得正确的颤振临界点.     

Integrated aerodynamic-structural-control wing design

The aerodynamic-structural-control design of a forward-swept composite wing for a high subsonic transport aircraft is considered. The structural analysis is based on a finite-element method. The aerodynamic calculations are based on a vortex-lattice method, and the control calculations are based on an output feed-back control law. The wing is designed for minimum weight subject to structural, performance/aerodynamic and control constraints. Efficient techniques are developed to calculate the control-deflection and control-effectiveness sensitivities which appear as second-order derivatives in the control constraint equations. To suppress the aeroelastic divergence of the forward-swept wing, and to minimize the take-off gross weight of the design aircraft, two separate cases are studied: (1) combined application of aeroelastic tailoring and active controls; and (2) aeroelastic tailoring alone. For the particular example problem considered in this study, the aeroelastic tailoring was found to have a substantially greater influence than active controls on weight minimization and divergence suppression.     

Frequency- and time-domain methods for the numerical modeling of full-bridge aeroelasticity

A numerical framework for full-bridge aeroelasticity is presented, based on unsteady cross-sectional load models and on the finite-element modeling of the structure. A frequency-domain approach based on aeroelastic derivatives and nonlinear complex eigenvalue analysis is compared to its equivalent time-domain counterpart based on indicial functions and direct integration of the equations of motion. A version of the time-domain load model consistent with the quasi-steady limit behavior is developed and a procedure for the numerical identification of the indicial functions from measured aeroelastic derivatives is presented. The aeroelastic stability analysis is chosen as benchmark. A numerical example is offered where the equivalency of the two approaches is proved for a full-bridge model. Advantages and disadvantages of the two techniques are discussed.     

基于CFD/CSD方法的亚音速平板结构气动弹性分析

采用CFD/CSD双向流固耦合算法研究平板结构的气动弹性耦合特性.首先,采用CFD/CSD算法计算平板结构的颤振临界速度,并与已有文献中的实验结果进行比较验证.然后,分别对简支和固支边界条件的三维平板结构进行气动弹性特性分析,计算不同约束情况下流场分布的变化和平板结构的位移响应.同时还考虑加肋和结构材质对平板结构气动弹性特性的影响.     

Efficient nonlinear static aeroelastic wing analysis

The objective of this work is to demonstrate a computationally efficient, high-fidelity, integrated static aeroelastic analysis procedure. The aerodynamic analysis consists of solving the nonlinear Euler equations by using an upwind cell-centered finite-volume scheme on unstructured tetrahedral meshes. The use of unstructured grids enhances the discretization of irregularly shaped domains and the interaction compatibility with the wing structure. The structural analysis utilizes finite elements to model the wing so that accurate structural deflections are obtained and allows the capability for computing detailed stress information for the configuration. Parameters are introduced to control the interaction of the computational fluid dynamics and structural analyses; these control parameters permit extremely efficient static aeroelastic computations. To demonstrate and evaluate this procedure, static aeroelastic analysis results for a flexible wing in low subsonic, high subsonic (subcritical), transonic (supercritical), and supersonic flow conditions are presented.     

Identification and robust limit-cycle-oscillation analysis of uncertain aeroelastic system

Model uncertainty directly affects the accuracy of robust flutter and limit-cycle-oscillation (LCO) analysis. Using a data-based method, the bounds of an uncertain block-oriented aeroelastic system with nonlinearity are obtained in the time domain. Then robust LCO analysis of the identified model set is performed. First, the proper orthonormal basis is constructed based on the on-line dynamic poles of the aeroelastic system. Accordingly, the identification problem of uncertain model is converted to a nonlin...     

Adaptive Control of a Nonlinear Prototypical Wing Section with Reduced Order Observer

This paper treats the question of control of an aeroelastic system with unknown parameters using output feedback. The equations of motion of the chosen aeroelastic system describe the plunge and pitch motion of a wing. A single trailing edge flap is used for the purpose of control, and plunge displacement and pitch angle are measured for feedback. Using a canonical representation of the aeroelastic system, reduced order filters are designed to obtain the unmeasured state variables. Then based on a backstepping design technique, adaptive control laws for the trajectory control of the pitch angle and the plunge displacement are derived. In the closed-loop system, the state vector is shown to converge asymptotically to zero. Simulation results are presented which show that regulation and trajectory following are accomplished in the closed-loop system in spite of large uncertainties in the structural and aerodynamic parameters of the model.     

Computational-fluid-dynamics-based aeroelastic analysis and structural design optimization—a researcher’s perspective

The paper discusses current approaches for the use of computational fluid dynamics in aeroelastic analyses and structural design optimization applications. Current methods for computational fluid dynamics-based static maneuver load analysis and flutter analysis are reviewed, including related issues such as fluid-structure interface, and moving mesh. Present state-of-the-art examples from the literature are presented along with research studies by the author. The paper highlights the challenges of computational fluid dynamics-based aeroelastic methods and their incorporation into aircraft structural design.     

Sliding mode robust control of supersonic three degrees-of-freedom airfoils

The robust aeroelastic control of a three-degrees-of-freedom (3DOF) linear and non-linear wing-flap system under sliding mode control (SMC) and operation in supersonic flight speeds is presented. Open- and closed-loop aeroelastic responses to blast and sonic-boom excitation in the wing-flap system with uncertainty, as well as flutter analysis, are investigated along with the implementation of a Sliding Mode Observer (SMO). The effectiveness of control in reducing the amplitude of oscillation and preventing flutter instability is demonstrated.     

带控制截面机翼结构基于非线性能量阱的颤振抑制

二元刚性机翼结构简化为三自由度结构,在浮沉位移和俯仰位移方向的非线性刚度简化为立方非线性,对于控制截面存在间隙采用双线性刚度代替.基于靶能量转移的原理在机翼结构耦合非线性能量阱,实现对机翼颤振的抑制.考虑准定常气流,建立机翼减振前后的运动方程,通过数值模拟构造减振前后峰值-峰值图,初步反应其整体的减振效果.通过弧长数值连续法和结合Floquet算子构造减振前后的分岔图,并研究其稳定性.通过分岔图结合数值模拟的峰值图,讨论在不同风速下的减振效果,结果表明机翼结构颤振可以部分甚至全部抑制.     

Aeroelastic tailoring considering uncertainties in material properties

The robustness of aeroelastic design optimization with respect to uncertainties in material and structural properties is studied both numerically and experimentally. The model consists of thin orthotropic composite wings virtually without fuselage. Three different configurations with consistent geometry but varying orientation of the main stiffness axis of the material are investigated. The onset of aeroelastic instability, flutter, is predicted using finite element analysis and the doublet-lattice method for the unsteady aerodynamic forces. The numerical results are experimentally verified in a low-speed wind tunnel. The optimization problem is stated as to increase the critical air speed, above that of the bare wing by massbalancing. It is seen that the design goals are not met in the experiments due to uncertainties in the structural performance of the wings. The uncertainty in structural performance is quantified through numerous dynamic material tests. Once accounting for the uncertainties through a suggested reformulation of the optimization problem, the design goals are met also in practice. The investigation indicates that robust and reliable aeroelastic design optimization is achievable, but careful formulation of the optimization problem is essential.     

Multidisciplinary approach to aeroelastic studies of long-span bridges

This paper focuses on the design of long-span suspension bridges under aeroelastic constraints. Such challenging structures need to be protected against wind-induced instabilities as flutter. The authors envision that a set of scientific disciplines not currently used in bridge engineering may help along the design process and constitute a useful tool. First, the formulation of sensitivity analysis of flutter speed is described, indicating how this technique can be a guide for engineers making changes in the prototype; two examples of important bridges, as the Great Belt and Messina Strait, are used to demonstrate the capability of this approach. Then, the idea of producing computer animations to represent the aeroelastic deformation of bridges simulating virtual boundary layer wind tunnel testing is presented showing pictures of the Tacoma Narrows and Messina Bridges. Finally, the advantages of introducing distributed computing to make easier to implement the previously mentioned techniques are demonstrated. The authors have previously published papers related with sensitivity analysis in bridges or computer animations of the aeroelastic behaviour of suspension bridges. However, this is the first time that their comprehensive multidisciplinary approach is presented.     

大展弦比机翼μ控制

利用大展弦比机翼后缘不同位置上的操纵面进行颤振主动控制,通过将大展弦比机翼简化为包含弯曲和扭转两种模态的悬臂梁结构,根据片条理论,建立包含操纵面运动规律的大展弦比机翼气动弹性方程.由于简化的数值模型与实际模型之间存在一定的误差,通常模型的运动方程包含有不确定参量用来表示建模误差.鲁棒控制方法能够得到一个有效控制器,控制这种带有模型不确定参量的运动方程.文中论述利用鲁棒μ控制方法,研究有两个操纵面大展弦比机翼的鲁棒控制问题.仿真结果表明鲁棒μ控制可以有效地抑制大展弦比机翼的受扰振动,提高颤振临界速度,且两个操纵面共同控制效果比单操纵面显著.     

Aerodynamic and aeroelastic analyses on the CAARC standard tall building model using numerical simulation

The simulation of the wind action over the CAARC (Commonwealth Advisory Aeronautical Council) standard tall building model is performed in the present work. Aerodynamic and aeroelastic analyses are reproduced numerically in order to demonstrate the applicability of CFD techniques in the field of wind engineering. A major topic in this paper is referred to one of the first attempts to simulate the aeroelastic behavior of a tall building employing complex CFD techniques. Numerical results obtained in this work are compared with numerical and wind tunnel measurements and some important concluding remarks about the present simulation are also reported.     

Composite stacking sequence optimization for aeroelastically tailored forward-swept wings

A method for stacking sequence optimization and aeroelastic tailoring of forward-swept composite wings is presented. It exploits bend-twist coupling to mitigate aeroelastic divergence. The method proposed here is intended for estimating potential weight savings during the preliminary aircraft design stages. A structural beam model of the composite wingbox is derived from anisotropic shell theory and the governing aeroelastic equations are presented for a spanwise discretized forward swept wing. Optimization of the system to reduce wing mass is undertaken for sweep angles of ?35° to 0° and Mach numbers from 0.7 to 0.9. A subset of lamination parameters (LPs) and the number of laminate plies in each pre-defined direction (restricted to {0°,±45°, 90°}) serve as design variables. A bi-level hybrid optimization approach is employed, making use of a genetic algorithm (GA) and a subsequent gradient-based optimizer. Constraints are implemented to match lift requirements and prevent aeroelastic divergence, excessive deformations, airfoil stalling and structural failure. A permutation GA is then used to match specific composite ply stacking sequences to the optimum design variables with a limited number of manufacturing constraints considered for demonstration purposes. The optimization results in positive bend-twist coupling and a reduced structural mass. Results are compared to an uncoupled reference wing with quasi-isotropic layups and with panel thickness alone the design variables. For a typical geometry and a forward sweep of ?25° at Mach 0.7, a wingbox mass reduction of 13 % was achieved.     

GLOBAL ASYMPTOTIC STABILIZATION OF THE PROTOTYPICAL AEROELASTIC WING SECTION VIA TP MODEL TRANSFORMATION

A comprehensive analysis of aeroelastic systems has shown that these systems exhibit a broad class of pathological response regimes when certain types of non‐linearities are included. In this paper, we propose a design method of a state‐dependent non‐linear controller for aeroelastic systems that includes polynomial structural non‐linearities. The proposed method is based on recent numerical techniques such as the Tensor Product (TP) model transformation and the Linear Matrix Inequality (LMI) control design methods within the Parallel Distributed Compensation (PDC) frameworks. In order to link the TP model transformation and the LMI's in the proposed design method, we extend the TP model transformation with a further transformation. As an example, a controller is derived that ensures the global asymptotic stability of the prototypical aeroelastic wing section via one control surface, in contrast with previous approaches which have achieved local stability or applied additional control actuator on the purpose of achieving global stability. Numerical simulations are used to provide empirical validation of the control results. The effectiveness of the controller design is compared with a former approach.     

Dynamic modeling of swept wing with PTFE method

A numerical approach for the solution of structural problems, based on the concept of parameter transfer finite elements, is here adopted to study the dynamic behaviour of composite wings.The purpose of this paper is to extend the methodology to a wing-like swept composite plate, which can be used, for example, for aeroelastic analysis, multidisciplinary optimization, structural control etc. The dynamics of composite swept wing is here analyzed and numerical results are compared with FEM solution. The effect of sweep angles and material anisotropicity on the aeroelastic behaviour of the wing is studied both from static divergency and dynamic flutter point of view. Several numerical results are presented.