Aeroelastic response of a coupled rotor/fuselage system in hovering and forward flight

Summary The aeroelastic response analysis of a coupled rotor/fuselage system is approached by iterative solution of the blade aeroelastic response in the non-inertial reference frame fixed on the hub, and the periodic response of the fuselage in the inertial reference frame. A model of the coupled system hinged with the flap and lag hinges, the pitching bearing which may not coincide with the hinges, and the sweeping-blade configuration is established. The moderate-deflection beam theory and the two-dimensional quasi-steady aerodynamic model are employed to model the aeroelastic blade, all the kinetic and inertial factors are taken into account in a unified manner. A five-nodes, 15-DOFs pre-twisted nonuniform beam element is developed for the discretization of the blade, three rigid-body-motion DOFs are introduced for the motion of the hinges and the bearing. The Hamilton's principle is employed to evaluate the equation of motion of the blade. The derived nonlinear ordinary differential equations with time-dependent periodic coefficients are solved by a modified quasi-linearization method, which is developed for the higher DOF periodic system. The resulting periodic forces and moments exerted on the fuselage by all the blades are evaluated every time, when the converged nonlinear periodic response of the blade is obtained under the consideration of the equilibrium of the blades. The fuselage structure is simplified to be a beam structure, the governing equation is established in the inertial reference frame and a two-nodes beam element is used to discretize the flexible fuselage. The periodic response of the fuselage is solved by a simple shooting method. The iteration of the rotor/fuselage response is continued, until the aeroelastic responses of the blade and the fuselage converge simultaneously. Both the hovering and the forward flight states can be considered. The results of a computed numerical example by the developed program are presented to verify in practice the economy of the modeling as well as the reliability and efficiency of the corresponding solving methods. Received 4 May 1998; accepted 11 August 1998     

直升机旋翼与机身耦合固有频率分析

在分析直升机旋翼挥舞，扭摆，变距运动基础上，应用多体系统动力学建模法建立直升机旋翼与机身耦合的动力学方程。在直升机稳定飞行状态下，对其动力学方程中描述直升机机身刚体运动的参数和旋翼刚体运动的参数进行泰勒展开，做线性化处理，导出直升机旋翼与机身耦合线性化动力学方程，然后计算系统的固有频率。分析计算了一个直升机样机的固有频率，算例表明机身的弹性变形对系统的固有特性有一定的影响。     

THE STRENGTHENING OF AERO-TRANSPORT WITH LARGE OPENING

为了对运输类飞机机身大开口结构进行加强,满足刚度连续变形协调的设计要求,本文对机身大开口结构和完整机身结构的刚度进行了深入研究,首先简化了计算模型,对刚度进行了计算,提出了刚度比的定义,得出刚度比与大开口角度、机身半径、蒙皮厚度以及边梁面积之间的关系表达式,得到运输类飞机机身大开口结构加强的原则和方法,在型号上成功得到了应用,用于指导初期的结构设计.     

飞机槽型大开口结构刚度加强研究

为了飞机典型的方舱型机身大开口结构能够满足刚度设计要求,设计了一种对槽型大开口结构增加4个边梁进行刚度加强的设计方案,并构建了工程分析模型,与无开口槽型结构的弯曲刚度及扭转刚度进行了对比研究,得到了两种构型的刚度比,进一步得到了满足一定刚度指标下的边梁面积计算公式,提出了方舱型机身大开口结构刚度设计流程,可以用于方案阶段的飞机大开口结构加强设计。     

民机中央翼舱段适坠性仿真

建立了带中央翼的民机舱段的有限元模型,应用MSC.Dytran分析软件对民机中央翼舱段模型进行坠撞仿真,得到加速度响应和客舱舱体结构变形结果.结果表明,带中央翼舱段发生坠撞后,乘客的生存空间基本没有变化,撞击能量主要靠舱段下部的龙骨梁、框及蒙皮和中央翼壁板的破坏来吸收,地板导轨的峰值加速度比不带中央翼的典型舱段的峰值加速度要大许多.     

无轴承旋翼柔性梁载荷特性研究

应用Hamilton原理建立了双路传力的无轴承旋翼运动方程。采用均匀入流模型,基于直升机飞行平衡条件,建立了无轴承旋翼柔性梁载荷的计算模型,并通过算例验证了模型的精度。利用该模型,研究了全机重心位置、机身气动阻力以及平尾安装角对柔性梁载荷特性的影响,给出了各因素对柔性梁载荷的影响趋势,得出了降低柔性梁载荷的方法。数值结果表明:2cm左右重心位置的变化能够引起9%~11%的柔性梁载荷变化量,15%气动阻力的增加会导致约9%的柔性梁载荷的增大;2°平尾安装角的变化引起约10%柔性梁载荷的变化量,3°平尾安装角的变化引起约26%柔性梁载荷的变化。     

确定性载荷作用下Timoshenko薄壁梁的弯扭耦合动力响应

建立了一种普遍的解析理论用于求解确定性载荷作用下Timoshenko薄壁梁的弯扭耦合动力响应。首先通过直接求解单对称均匀Timoshenko薄壁梁单元弯扭耦合振动的运动偏微分方程，给出了计算其自由振动的精确方法，并导出了Timoshenko弯扭耦合薄壁梁自由振动主模态的正交条件。然后利用简正模态法研究了确定性载荷作用下单对称Timoshenko薄壁梁的弯扭耦合动力响应，该弯扭耦合梁所受到的荷载可以是集中载荷或沿着梁长度分布的分布载荷。最后假定确定性载荷是谐波变化的，得到了各种激励下封闭形式的解，并对动力弯曲位移和扭转位移的数值结果进行了讨论。     

直升机气动弹性力学发展现状(续)

Ⅲ.单片桨叶气动弹性问题的求解1.桨叶离散化方法求解旋翼桨叶气动弹性力学问题的第一步是将连续桨叶离散化,即把一个具有无限多个自由度的连续参数系统离散化为具有有限个自由度的离散系统。常用方法有三种: 1)整体模态方法在直升机旋翼气动弹性力学中,以往用得多的离散方法是整体模态法,或称为整体伽辽金方法。此方法的实质是利用桨叶自由振动振型是线性独立      

The influence of shape changes on structural dynamics of a round-cornered thin-walled beam with warping

The objective of this study is to investigate the influence of shape changes on the natural frequencies of a channel beam. To achieve this objective, the solutions of differential equations of motion for a beam experiencing coupled bending and torsion are derived using the Ritz approach. The functional of the corresponding system frequency equation is formulated. A set of polynomial that satisfies the fixed-free boundary condition is generated. The Ritz method leads the formulation to an eigen value problem for frequency calculations. A numerical examples is presented to validate the approach and to study the influence of shape changes on the dynamics of the beam structure.     

压电层合梁静动力学分析的高精度梁单元

给出了一个对复合材料压电层合梁进行数值分析的高精度压电层合梁单元。基于Shi三阶剪切变形板理论的位移场和Layer-wise理论的电势场,用力-电耦合的变分原理及Hamilton原理推导了压电层合梁单元列式。采用拟协调元方法推导了一个可显式给出单元刚度矩阵的两节点压电层合梁单元,并应用于压电层合梁的力-电耦合弯曲和自由振动分析。计算结果表明,该梁单元给出的梁挠度和固有频率与解析解吻合良好,并优于其它梁单元的计算结果,说明了本文所给压电层合梁单元的可靠性和准确性。研究结果可为力-电耦合作用下压电层合梁的力学分析提供一个简单、精确且高效的压电层合梁单元。     

温度-随机载荷下CFL加固RC梁疲劳性能的实验研究

考虑亚热带地区公路桥梁的服役环境温度与车辆载荷的作用效应,本文以碳纤维薄板(CFL)加固钢筋混凝土(RC)桥梁结构为研究对象,利用本课题组构建的实验平台,提出了温度与车辆随机载荷耦合作用下CFL加固RC梁的疲劳实验方法。在3个温度和3个载荷水平下实施了温度-随机载荷耦合作用下的三点弯曲疲劳实验,初步探讨了温度-随机载荷作用下加固梁的疲劳破坏机理,并提出了温度-随机载荷耦合下加固梁疲劳寿命的半经验公式。     

Axial crack propagation and arrest in a pressurized cylinder: An experimental-numerical analysis

The feasibility of using a previously developed crack-kinking criterion to predict crack arrest at a tear strap in a pressurized fuselage was studied with instrumented axial rupture tests of 21 models of an idealized fuselage. A rapidly propagating axial crack, which was initiated from a precrack, kinked immediately upon extension and propagated diagonally until it turned circumferentially and propagated along the tear straps. An elastodynamic finite element analysis of the rupturing model fuselage yielded the mixed-mode stress intensity factors,K _I andK _II , and the remote stress component, σ _OX . This numerical procedure was also used to predict the crack trajectories in full-scale fuselage rupture tests. All numerical results agreed well with their measured counterparts regardless of size.     

考虑非线性变形的航天器柔性附件建模方法

针对航天器的柔性附件,将其简化为常见的大范围运动空间柔性梁结构。根据柔性体的非线性变形原理,考虑了弯曲和扭转的非线性因素的影响,在柔性梁的三个变形方向上均考虑了变形的二次耦合项。利用有限元方法进行离散并用Lagrange方程建立了非线性变形模式下的动力学方程,包含了较为完全的刚度矩阵和各种耦合项。对一大范围运动的空间梁进行了仿真计算,表明在运动速度较大并且基座具有大范围运动时,一次耦合模型与本文模型有一定差异,且初始变形对两种模型也会产生影响。     

混合专家系统及其在有限元模型化中的应用

本文结合传统专家系统和人工神经网络的优势建立了混合专家系统模型，并在此基础上建立了“飞机结构机身框有限元模型化专家系统”，能够自动地实现机身框一类结构的有限元模型化，本文采用人工神经网络解决结构类型的分类和识别、采用知识系统解决单元自动选取都取得了良好的效果。     

钢筋混凝土双肢剪力墙静力弹塑性分析

建立了由墙肢单元模型、连粱单元模型和连接单元模型组成的钢筋混凝土双肢剪力墙的静力弹塑性分析计算模型。墙肢单元采用以有限元为基础的宏模型;按是否出现对角线剪切破坏,分别建立短连粱计算模型和长连粱计算模型;为计及连粱与墙肢连接界面的相对位移,建立用复合弹簧模拟的连接单元计算模型;给出了确定模型参数的方法。对有关文献的短连粱和长连粱双肢剪力墙试件进行了静力弹塑性分析,分析结果与试验结果符合较好。     

鸭式旋翼/机翼飞机悬停及小速度前飞气动干扰实验研究

鸭式旋翼/机翼飞机是一种新概念可垂直起降高速飞行器,为了解该飞机在悬停及小速度前飞时的全机气动干扰特性,在南京航空航天大学开口风洞中进行了飞机全机气动力实验,实验采用多台测力天平分别测量主机翼和机身的气动力.结果表明,悬停时受主机翼高速旋转产生的下洗尾流影响,机身产生了较大的法向力和低头力矩;前飞时下洗尾流对机身的法向力和俯仰力矩有比较严重的干扰,对滚转力矩和偏航力矩干扰较小,对侧向力有一定影响.实验结果为飞机的飞行动力学特性研究以及控制律设计提供了参考.＃     

Nonlinear resonances in an axially excited beam carrying a top mass: simulations and experiments

In this paper, nonlinear resonances in a coupled shaker-beam-top mass system are investigated both numerically and experimentally. The imperfect, vertical beam carries the top mass and is axially excited by the shaker at its base. The weight of the top mass is below the beam’s static buckling load. A semi-analytical model is derived for the coupled system. In this model, Taylor-series approximations are used for the inextensibility constraint and the curvature of the beam. The steady-state behavior of the model is studied using numerical tools. In the model with a single beam mode, parametric and direct resonances are found, which affect the dynamic stability of the structure. The model with two beam modes not only shows an additional second harmonic resonance, but also reveals some extra small resonances in the low-frequency range, some of which can be identified as combination resonances. The experimental steady-state response is obtained by performing a (stepped) frequency sweep-up and sweep-down with respect to the harmonic input voltage of the amplifier-shaker combination. A good correspondence between the numerical and experimental steady-state responses is obtained.     

复合材料/金属混合结构热应力分布规律

以飞机机身典型部位复合材料与Z型长桁螺栓连接为研究对象,采用Python脚本语言编程,在ABAQUS平台建立了6种紧固长度有限元模型,模拟飞机在高空低温的飞行环境,得到了混合结构的应力、应变分布规律。数值仿真结果表明:铝梁顶部应变结果呈现中间高、两边低的现象,紧固螺栓应变结果则呈现出相反的趋势;末端紧固件承受的剪切载荷最大,而中心的紧固件剪切载荷最小;该温度场结果与已有文献的试验测试结果误差在3℃以内,对复合材料与金属混合结构的设计具有一定意义。     

An unstructured grid Reynolds stress model for separated turbulent flow simulations

Most of the turbulence models in the literature contain simplified assumptions which make them computationally inexpensive but of limited accuracy for the solution of separated turbulent flows. Dramatic improvements in computer processing speed and parallel processing make it possible to use more complete models, such as Reynolds Stress Models, for separated turbulent flow simulations, which is the focus of this work. The Reynolds Stress Model consists of coupling the Reynolds transport equations with the Favre–Reynolds averaged Navier–Stokes equations, which results in a system of 12 coupled non-linear partial differential equations. The solutions are obtained by running the PUMA_RSM computational fluid dynamics code on unstructured meshes. The equations are solved all the way to the wall without using any wall functions. Results for high Reynolds number flow around a 6:1 prolate spheroid and a Bell 214ST fuselage are presented. For the prolate spheroid basic flow features such as cross-flow separation are simulated. Predictions of circumferential locations of cross flow separation points are in good agreement with the experiment. A grid refinement study is performed to improve the computations. The fine mesh solution predicted locations of primary and secondary separation points with errors of roughly 2° and 0°, respectively. Flow simulations around an isolated Bell 214ST helicopter fuselage were also performed. Predicted pressure and drag force correlate well with the wind tunnel data, with a less than 10% deviation from the experiment. Drag predictions also show relative speed of Reynolds Stress Model compared to Large Eddy Simulation to compute time averaged quantities. For numerical solutions parallel processing is applied with the MPI communication standard. The code used in this study is run on Beowulf clusters. The parallel performance of the code PUMA_RSM is analysed and presented.     

Sliding mesh algorithm for CFD analysis of helicopter rotor–fuselage aerodynamics

The study of rotor–fuselage interactional aerodynamics is central to the design and performance analysis of helicopters. However, regardless of its significance, rotor–fuselage aerodynamics has so far been addressed by very few authors. This is mainly due to the difficulties associated with both experimental and computational techniques when such complex configurations, rich in flow physics, are considered. In view of the above, the objective of this study is to develop computational tools suitable for rotor–fuselage engineering analysis based on computational fluid dynamics (CFD). To account for the relative motion between the fuselage and the rotor blades, the concept of sliding meshes is introduced. A sliding surface forms a boundary between a CFD mesh around the fuselage and a rotor‐fixed CFD mesh which rotates to account for the movement of the rotor. The sliding surface allows communication between meshes. Meshes adjacent to the sliding surface do not necessarily have matching nodes or even the same number of cell faces. This poses a problem of interpolation, which should not introduce numerical artefacts in the solution and should have minimal effects on the overall solution quality. As an additional objective, the employed sliding mesh algorithms should have small CPU overhead. The sliding mesh methods developed for this work are demonstrated for both simple and complex cases with emphasis placed on the presentation of the inner workings of the developed algorithms. Copyright © 2008 John Wiley & Sons, Ltd.