基于当地流活塞理论的气动弹性稳定性分析方法研究

基于改进的当地流活塞理论,推导了用模态坐标表示的弹性振动翼面的非定常广义气动力表达式。通过与非定常Euler方程的比较,证明该气动力模型具有较高的数值精度,放宽了原始活塞理论对翼型厚度、迎角、马赫数的限制。再耦合两自由度结构运动方程,在时域和频域内实现了超音速、高超音速气动弹性的稳定性分析。应用算例计算了一系列二元机翼和三维舵面的气动弹性特性。通过与耦合非定常Euler方法或实验结果的比较,证明该方法在保证精度的同时大大提高了超音速气动弹性的计算效率,在颤振分析中有较高的工程实用价值。     

大展弦比机翼气动弹性的几何非线性效应

随着飞行器性能和需求的提高,大展弦比机翼逐渐成为新型飞行器的主要结构形式。这类机翼具有高升阻比、大变形、重量轻等特性,几何非线性效应明显。该文采用本征梁结构模型和有限状态入流气动模型,对典型大展弦比机翼的几何非线性效应开展结构的静、动态特性和气动弹性研究。分析结果发现:考虑几何非线性效应后,机翼的变形减小;颤振临界速度降低,并且与攻角相关;机翼的时域响应则表现为衰减振动、单频极限环和多频极限环振荡,不出现振动发散状态;与传统的线性气动弹性现象显著不同。该文的方法能够有效预示大展弦比机翼的气动弹性现象。     

连翼布局飞行器飞行载荷与颤振分析

对相同总体设计条件下的传统布局飞行器的机翼和连翼布局飞行器的机翼进行了静气动弹性特性和颤振特性的对比分析。重点开展了考虑弹性变形的情况下,两种机翼在提供相同升力的条件下,结构所承受的气动载荷的对比分析及气动导数随动压变化趋势的对比分析。分析结果表明:与传统布局机翼相比,连翼布局机翼具有更高的设计灵活性;在相同的结构重量条件下,连翼布局机翼较之传统布局弯曲和扭转刚度特性更好,并具有较高的颤振速度;弹性情况下连翼布局机翼升力线斜率随动压增大而增大,且这种增加梯度受到后翼弯曲刚度的影响。     

带间隙非线性的机翼操纵面颤振特性研究EI北大核心CSCD

针对大型民用飞机复杂机翼-副翼系统,利用双协调动态子结构法建立了缩比三维机翼-副翼带间隙操纵面颤振分析模型,得到非线性气动弹性方程,并分别在频域及时域内建立了求解方法:在频域内,利用谐波平衡法进行求解,通过引入间隙刚度的描述函数及相对舵偏振幅,建立了可利用V-g法进行颤振计算的方案;在时域内,利用有理函数拟合和时域推进法进行数值仿真,得到了与频域法结果相吻合的操纵面颤振极限环振荡特性规律。对三维矩形机翼模型开展风洞试验,揭示了间隙对操纵面颤振特性间的影响:间隙非线性使系统出现极限环振荡并使系统振荡发散风速明显降低。     

一种针对含非线性子结构多点耦合运输包装系统的解耦方法

目的 考虑到运输包装系统耦合形式复杂,包装材料及包装结构具有非线性特性,不容易测量局部物理参数,需要对传统逆向子结构方法进行优化,使之能够求解非线性多点耦合系统中子结构的动态响应特性。方法 使用描述函数法将非线性的运输包装系统线性化,测量其在若干特定振动幅值下的频率响应函数;之后,应用逆向子结构方法和参数识别方法,计算包装件的模态参数;最后,拟合包装件模态参数与振动幅值之间的关系,构建函数来描述包装件的动态响应特性。结果 在集总参数模型中,解耦预测值与实际值吻合;在有限元模型中,对响应峰值的预测误差小于5%,对响应跳跃现象所在频率的预测误差小于3%。结论 该研究将传统逆向子结构方法的应用范围拓展到了非线性多点耦合系统,对复杂运输包装系统动力学模型的构建和防振包装的设计具有指导意义。     

考虑发动机推力影响的机翼颤振分析

发动机安装在机翼上时,其推力具有典型的随动特征,并对机翼颤振产生重要影响.基于有限元分析软件MSC/Nastran的DMAP开发,提出了一种考虑发动机推力和几何非线性影响的机翼颤振分析方法.作为验证,分析了推力对某高空长航时飞行器机翼颤振速度的影响,与已有结果吻合良好.对一带有两个发动机的复杂机翼结构进行了结构建模和颤振分析,重点分析了推力大小及作用位置对颤振速度的影响.结果表明,发动机的推力效应在颤振分析中是不应忽略的.     

考虑几何非线性效应的大展弦比机翼气动弹性分析

针对飞机飞行过程中因受气动载荷作用、机翼几何非线性效应影响气动弹性稳定性,提出考虑结构大变形几何非线性效应的大展弦比机翼气动弹性特性分析方法。通过对MSC.Nastran软件二次开发实现该方法的计算流程。考虑大展弦比机翼几何大变形对气动面网格构型影响,在每个迭代步对气动面网格进行更新,求出大展弦比机翼在给定飞行状态下的静气动弹性变形,获得考虑机翼结构几何非线性效应的刚度矩阵,并进行机翼颤振特性分析。对大展弦比机翼模型进行气动弹性特性分析计算表明,与线性气动弹性分析结果相比,考虑机翼结构大变形几何非线性效应,机翼静气动弹性变形会影响机翼动力学特性,使机翼扭转频率明显下降,导致机翼几何非线性颤振速度低于线性颤振速度。     

热环境下某飞行器振动特性分析与模型修正

基于结构热振动理论,针对某型复合材料结构飞行器建立其热环境下结构动力学计算的有限元模型。对该结构进行结构动态特性分析,并结合地面常温的模态实验数据对该有限元模型进行优化。得到该结构常温下的振动特性及其受给定温度场影响的变化情况。针对该类复合材料结构建模及模型修正的方法,给出较为合理的优化方法及优化结果,对工程实际有一定的指导意义。     

二元机翼极限环颤振复杂分岔

机翼颤振是飞机飞行中最常见的、可能带来灾难性后果的气动弹性现象,属于自激振动。揭示其机理和规律,对机翼和飞行器设计有重要意义。以二元机翼模型为例,通过数值计算Poincare映射分岔的方法,讨论了极限环颤振随气流速度变化引起的复杂分岔行为。对自治非线性系统,还没有公认的方法选取合适的Poincare截面,特选俯仰角加速度为零的点作为广义Poincare截面上的点。通过考察广义Poincare截面上点的数目随参数的变化来考察系统的分岔。计算出了参数气流激振力变化导致的分岔图,并给出了8种不同的具有代表性的典型的相图和谱图,对应8种闭轨曲线的拓扑形状各不相同,发现系统中存在正向和反向的超谐分岔是产生这种闭轨分岔的根源。     

发动机振动模态的实验研究与计算

为了研究发动机整机结构的动力学特性,在各子结构--机体、曲轴、缸盖和曲轴箱正确的三维实体模型的基础上,组装成整机模型.采用实验研究和理论计算相结合的方法,对此整机的振动模态进行了研究.由于部件间结合面的刚度与阻尼特性难于理论分析和实验提取,采用了虚拟材料来模拟结合面特性,通过反复修正虚拟材料的特性常数,使得整机有限元振动模态分析结果与实验结果相吻合.从而说明所建立的整机的有限元模型是正确可靠的,为整机结构进一步的动态仿真研究奠定了基础.     

Design optimization framework for tiltrotor composite wings considering whirl flutter stability

This paper constructs the design optimization framework for the composite wing of a tiltrotor aircraft based on the Korea Aerospace Research Institute (KARI) Smart Unmanned Aerial Vehicle (SUAV) TRS4 model. The present optimal design attempts to find the cross-section layout that minimizes the structural weight of a composite wing, while satisfying a series of design constraints. The framework consists of various analysis and design tools that include a 2-D beam cross-section analysis, a whirl flutter analysis, and a 3-D strain/stress analysis under the worst wing-loading case. The variation of wing sectional properties of tiltrotor aircrafts in the course of design optimization greatly affects the whirl flutter stability and shows considerable influence on the structural integrity of the wing. In the design framework, the whirl flutter stability is analysed by the nonlinear flexible multibody analysis code DYMORE and the structural integrity is investigated using a MATLAB-based 3-D strain analysis module along with the previous load analysis result. The MATLAB is used to conduct the optimization with a gradient-based optimizer and integrate all of the design and analysis tools. The nonlinear constraints associated with the aeroelastic stability and the structural integrity are also considered. For optimal design examples using the developed framework, a simplified cross-section model based on the KARI SUAV TRS4 composite wing is considered as an initial model. Design optimization examples are investigated to show the validity of the proposed framework and to illustrate the reduction of the structural weight of the composite wing. It is observed that weight reductions of wing structures by 26% and 40% are achieved, while maintaining the whirl flutter stability margins.     

Materials selection in design of structures and engines of supersonic aircrafts: A review

This article reviews the advances in the materials selection for applications in structures and engines of current and future supersonic aircrafts. A brief overview of configuration design of the supersonic aircrafts is first given; which also includes techniques to improve configuration design for future supersonic aircrafts. The operating and ambient environmental conditions during supersonic flight and the resulting material requirements have been discussed; and consequently various aerospace aluminum alloys, titanium alloys, superalloys, and composites have been recommended. Finally, a new materials-selection chart is presented that would enable aerospace designers to select appropriate materials for application in high-performance current and future supersonic/hypersonic aircrafts.     

Multidisciplinary characterization of new shield with metallic nanoparticles for composite aircrafts

Because of major advantages (e.g. weight saving, maintenance advantages), the airframe manufacturers use more and more Polymer Matrix Composites (PMCs) in different parts of aircraft structures. But PMCs have a substantial disadvantage of low conductivity and therefore low Electromagnetic (EM) Shielding. Electromagnetic Interference (EMI) sources are all around and inside aircraft and can potentially threat the immunity of aircraft. Metallic meshes have been used to overcome this shortage. However in high frequencies most of the mentioned methods loose their performances. Regrettably on one side most of the present and upcoming systems onboard of aircraft are functional in mentioned range of frequencies. On the other side, passengers use more and more Personal Electronic Devices (PEDs) onboard of aircraft. Interferences caused by PEDs are also in the same range of frequencies. Measured susceptibility caused by PEDs is higher in composite aircrafts comparing to metallic ones. To overcome this back door lack of composite aircrafts, design of a new light weight shield particularly for aeronautic application is needed. Metallic nanoparticles have a great potential to be used as new EM shields for aerospace applications, particularly in high frequencies. Without multidisciplinary characterization of new shield, the application onboard would be suspended. Here the encouraging results of EM characterization are presented. Thermal, microscopy and mechanical tests are also performed. Based on acquired results in this work, thermal and mechanical behaviors as well as distribution of particles are all acceptable. The promising results obtained in this work can assure the designers on using metallic nanoparticles as a new shield for protection of composite aircrafts.     

桥梁颤振概率性评价的随机有限元法

在桥梁的各种风振形式当中,颤振对桥梁的安全威胁最大,而在各种随机因素作用下的桥梁颤振概率性评价也受到了人们的重视。为了计算大跨度桥梁的颤振失效概率,推出了一种结合有限元分析和可靠度计算理论的随机有限元方法,考虑了质量、刚度、阻尼和颤振导数等随机因素对颤振临界风速的影响,并对我国第一座真正意义上的大跨度海上桥梁——东海大桥颗珠山斜拉桥进行了颤振可靠性分析。     

Flutter analysis using transversality theory

Summary A new method of calculating the flutter boundaries of undamped aeroelastic typical section models is presented. The method is an application of the weak transversality theorem used in catastrophe theory. In the first instance, the flutter problem is cast in matrix form using a frequency domain method, leading to an eigenvalue matrix. The characteristic polynomial resulting from this matrix usually has a smooth dependence on the system's parameters. As these parameters change with operating conditions, certain critical values are reached at which flutter sets in. Our approach is to use the transversality theorem in locating such flutter boundaries using this criterion:at a flutter boundary, the characteristic polynomial does not intersect the axis of the abscissa transversally. Formulas for computing the flutter boundaries of structures with two degrees of freedom are presented, and extension to multi degree of freedom systems is indicated. The formulas have obvious applications in, for instance, problems of panel flutter at supersonic Mach numbers. Substantial savings in computation resources are possible when this non-iterative method is used, compared to existing frequency domain methods which are essentially iterative.     

苏通大桥三维颤振分析

基于结构有限元模型,给出了大跨度缆索承重桥梁三维颤振分析方法。该方法能够考虑静风作用、主梁附加攻角、拉索自激力和振型参与影响,同时迭代搜索侧弯、竖弯和扭转三种振动频率。采用该方法对苏通大桥进行了三维颤振分析,该方法的可靠性和实用性得到证实。结果表明:对于苏通大桥而言,不考虑静风作用和主梁附加攻角影响会高估颤振临界风速;不考虑拉索自激力作用和拉索振型参与,相当于忽略了系统气动正阻尼,会低估颤振临界风速;颤振临界风速颤振分析计算结果与风洞试验结果之间存在差异。     

Active aeroelastic flutter suppression of a supersonic plate with piezoelectric material

The active aeroelastic flutter properties of supersonic plates are investigated by using the piezoelectric material. The piezoelectric material has been extensively used for the active vibration control of engineering structures. In this paper, the piezoelectric material is further used to improve the flutter characteristics of the supersonic plates. The equation of motion of the plate and piezoelectric material system is obtained by Hamilton’s principle with the assumed mode method. The supersonic piston theory is used to evaluate the aerodynamic load. By applying an appropriate external control voltage to activate the piezoelectric material, a displacement and acceleration feedback control strategy is used to obtain the active stiffness and active mass. Solving the eigenvalue problem of the equation of motion, the natural frequencies and damping ratios of the structural system are obtained. Furthermore, the aeroelastic flutter bounds are calculated, and the effects of feedback control gains on the active aeroelastic flutter characteristics of the structure are analyzed in detail. From the numerical results it is seen that the active stiffness and active mass have prominent effects on the flutter characteristics of the supersonic plates. The aeroelastic flutter properties can be greatly improved by introducing the active stiffness and active mass into the supersonic plate with the piezoelectric patch. With the increase of the feedback control gains, the active aeroelastic flutter properties for the lower order modes of the supersonic plate are gradually improved.     

Active aeroelastic flutter analysis and vibration control of supersonic composite laminated plate

The active aeroelastic flutter analysis and vibration control at the flutter bounds of the supersonic composite laminated plates with the piezoelectric patches are studied. The piezoelectric patches are bonded on the top and bottom surfaces of the composite laminated plate to act as the sensor and actuator so that the active aeroelastic flutter suppression and vibration control for the supersonic laminated plate can be conducted. The unsteady aerodynamic pressure in supersonic flow is computed by using the supersonic piston theory. Hamilton’s principle with the assumed mode method is used to develop the governing equation of the structural system. The controller is designed by the velocity feedback and proportional feedback control algorithm, and the active damping and stiffness are obtained. The solutions for the complex eigenvalue problem are obtained by using the generalized eigenvalue methodology. The natural frequencies and damping ratios are also gotten. The aeroelastic flutter bounds of the supersonic composite laminated plate are calculated to investigate the characteristics of the aeroelastic flutter. The impulse responses of the structural system are calculated by using the Houbolt numerical algorithm to study the active aeroelastic vibration control. The influences of ply angle of the laminated plate and the control method on the characteristic of flutter and active vibration control are analyzed. From the numerical results it is observed that the aeroelastic flutter characteristics of the supersonic composite laminated plate can be improved and that the aeroelastic vibration response amplitudes can be reduced, especially at the flutter points, by the proportional feedback or the velocity feedback control algorithm using the piezoelectric actuator/sensor pairs. The effectiveness of the flutter control by the two control algorithms is also compared. The results of this study are of great significance to the flutter analysis and aeroelastic design of the aircraft.     

复合材料机翼结构相似颤振模型的设计与实验验证

为了进行颤振实验, 依据原始金属模型, 根据结构相似方法和刚度相等的原则, 提出了基于设计元素的复合材料结构设计方法, 建立了结构缩比和复合材料结构设计软件, 并分别设计了复合材料机翼盒段和机翼模型。采用低模量复合材料制造, 进行了模态实验和风洞实验。实验结果与理论值吻合较好。设计的梁架2蒙皮复合材料机翼模型实现了结构和动力学相似, 相对于传统的蒙皮不传递载荷的梁架-维形颤振模型有了质的飞跃。      

机翼外挂系统极限环颤振的次谐响应研究

本文从理论分析及模型风洞实验两个方面对机翼带外挂系统极限环颤振的次谐响应进行研究。在非线性气动弹性系统处于稳定极限环颤振条件下,借助于单自由度非对称分段线性振子的次谐分叉条件,本文建立了一种预估极限环颤振次谐响应存在区域的相对简单的分析方法。数值积分及模型风洞实验结果表明这种预估是正确的。