A rigid-flexible coupling finite element model of coupler for analyzing train instability behavior during collision

Rail vehicles generate huge longitudinal impact loads in collisions.If unreasonable matching exists between the compressive strength of the intermediate coupler and the structural strength of the car body,the risk of car body structure damage and train derailment will increase.Herein,a four-stage rigid-flexible coupling finite element model of the coupler is established considering the coupler buckling load.The influence of the coupler buckling load on the train longitudinal-vertical-hori-zontal buckling behavior was studied,and the mechanism of the train horizontal buckling instability in train collisions was revealed.Analysis results show that an intermediate coupler should be designed to ensure that the actual buckling load is less than the compressive load when the car body structure begins to deform plastically.The actual buckling load of the coupler and the asymmetry of the structural strength of the car body in the lateral direction are two important influencing factors for the lateral buckling of a train collision.If the strength of the two sides of the car body structure in the lateral direction is asymmetrical,the deformation on the weaker side will be larger,and the end of the car body will begin to deflect under the action of the coupler force,which in turn causes the train to undergo sawtooth buckling.

Ride comfort evaluation for road vehicle based on rigid-flexible coupling multibody dynamics

In the present research two different whole vehicle multibody models are established respectively, including rigid and rigid-flexible coupling multibody vehicle models. The former is all composed by rigid bodies while in the later model, the flexible rear suspension is built based on the finite element method （FEM） and mode superposition method, in which the deformations of the components are considered. The ride simulations with different speeds are carried out on a 3D digitalized road, and the weighted root mean square （RMS） of accelerations on the seat surface,backrest and at the feet are calculated. The comparison between the responses of the rigid and rigid-flexible coupling multibody models shows that the flexibility of the vehicle parts significantly affects the accelerations at each position, and it is necessary to take the flexibility effects into account for the assessment of ride comfort. C 2013 The Chinese Society of Theoretical and Applied Mechanics. [doi： 10.1063/2.1301304]

Rigid-Flexible Coupling Dynamic Analysis of Sub-Launched Vehicle During the Vertical Tube-Exit Stage

During the launching stage,hydrodynamic pressure and adapters' reaction loads can influence the vehicle's rigid motion as well as cause its structural vibration,which is a typical rigid-flexible coupling dynamic problem. This paper presents a 2-D rigid-flexible coupling model to calculate the vehicle's dynamic responses in that period.The vehicle was equivalent to a flexure beam with axial deformation. Hybrid coordinate and modal superposition methods were used to describe its large rigid displacement and small deformation. By the second Lagrange equation,the vehicle centroid's displacements,rotational angle and modal coordinates were chosen as generalized coordinates and then the vehicle 's rigid-flexible coupling dynamic equations were obtained. By numerical simulation,the results of vehicle's motion parameters and transverse internal loads were acquired.The calculation results showed that differences of the vehicle's motion parameters between the rigid-flexible coupling model and the rigid body assumption are noticeable and the peak magnitude of the vehicle's transverse internal loads in the rigid-flexible coupling model is higher remarkably than that in the rigid body assumption.

Dynamic Simulation for Rigid-Flexible Coupling Model of Gear Transmission System Based on ADAMS

The influence of the flexible body for the motion of gear transmission system is analyzed and the foundation for a more accurate assessment of gear transmission system is established when it has battle damage faults. By using Pro / E software,the virtual prototype model of gear transmission system in the speed reducer is established,and the rigid model and rigid-flexible coupling model are simulated respectively in ADAMS to obtain the data of gear meshing force. It can be concluded that rigid-flexible coupling model can reflect the real motion better than rigid model by comparing the simulation data of two models.

Nonlinear dynamic analysis on rigid-flexible coupling system of an elastic beam

Previous work examined the effect of the attached stiffness matrix terms on stability of an elastic beam undergoing prescribed large overall motion. The aim of the present work is to extend the nonlinear formulations to an elastic beam with free large overall motion. Based on initial stress method, the nonlinear coupling equations of elastic beams are obtained with free large overall motion and the attached stiffness matrix is derived by solving sub-static formulation. The angular velocity and the tip deformation of the elastic pendulum are calculated. The analytical results show that the simulation results of the present model are tabled and coincide with the one-order approximate model. It is shown that the simulation results accord with energy conservation principle.

An analysis on a rigid-flexible coupling system of an oscillating massand a rotating disk

A mass-rod-disk system consisting of an oscillating mass attached to a rigid rotating disk by an elastic rod is designed to study rigid-flexible coupling mechanism.Suppose the rod is lightweight and has enough stiffness,the theorems of linear momentum and angular momentum are applied to the mass-rod-disk system based on the kinematic description of the system.With respect to two deflections of the mass and one angular velocity of the system,a group of nonlinear differential equations are established where the tangential inertial force,centrifugal force,Coriolis force as well as the moments of additional inertial forces take important effects on the dynamic response.For the sake of description,these three types of inertial forces mentioned before are referred to as additional inertial forces in this paper.The horizontal deflections of the mass and the angular velocity of the disk rotating about a fixed-axis are numerically solved for the prescribed external torque.The oscillating trajectory of the mass is deeply influenced by the additional inertial forces,meanwhile the dynamic fluctuations of the angular velocity and rotary inertia of the system are strongly affected by the mass oscillation.

A Study of Dynamic Analysis Method for the Rigid-Flexible Coupled Bar Linkage System

In order to present a dynamic analysis method for the rigid-flexible coupled bar linkage system(RFCBLS),the flexible element motion equation was gotten by Lagrange Equation and the rigid element motion equation was gotten based on rigid constraint conditions.The multi-body system(MBS) is a complex mechanism and its components have quite different rigidities.If it is considered as a rigid MBS(RMBS) to do its dynamic analysis,elastic deformation's ignorance will lead to inaccurate analysis.If it is considered as a flexible MBS(FMBS) to establish,analyze,and solve the model,quite large system equations make it difficult to solve.The better method is as follows:the complex mechanism system is regarded as a rigid-flexible coupled system(RFCS) to make dynamic characteristic of rigid components be equivalent,system equation is established by FMBS' way,and system equation dimensions are reduced by transition matrices' introduction.A dynamic analysis method for rigid element and flexible element coupling was presented based on the FMBS.The analyzed crank slide-block mechanism results show that the dynamic analysis method for RFCBLS is quick and convenient.

Numerical simulation of aircraft arresting process with an efficient full-scale rigid-flexible coupling dynamic model

The arresting process of carrier-based aircraft is widely recognized as a challenging task,characterized by the highest accident rate among all carrier-based aircraft operations.Dynamic simulation plays a crucial role in assessing the intricate responses of the arresting process,favoring the design of carrier-based aircraft.An efficient and accurate rigid-flexible coupling model for analyzing the dynamic response of the arresting process is proposed.By combining the dynamic characteristics of airframe,landing gear,arresting hook and arresting gear system,the rigid-flexible coupling dynamic model is established to reflect the relative motion of the coupling parts and arresting load.The dynamic model is verified through simulations of landing gear landing drops and by comparing the arresting simulation results with corresponding data in the US military standard.Additionally,simulations of the arresting process under different off-center distance and aircraft yaw angle are conducted to obtain the dynamic response of the aircraft during the arresting process.The result indicates that the rigid-flexible coupling dynamic model proposed is effective for analyzing the arresting dynamics response of carrier-based aircraft.The axial force of the arresting cable on both sides of the hook engagement point,pitch and yaw angle of aircraft are inconsistent under yaw and off-center arresting.The analysis method and obtained results provide valuable references for assessing the dynamic responses of carrier-based aircraft during arresting process and offer valuable in-sights in the design of carrier-based aircraft.

MODEL OF CENTRIFUGAL EFFECT AND ATTITUDEMANEUVER STABILITY OF A COUPLEDRIGID-FLEXIBLE SYSTEM

The influences of nonlinear centrifugal force to large overall attitude motion of coupled rigid-flexible system was investigated. First the nonlinear model of the coupled rigid-flexible system was deduced from the idea of “centrifugal potential field', and then the dynamic effects of the nonlinear centrifugal force to system attitude motion were analyzed by approximate calculation; At last, the Lyapunov function based on energy norm was selected, in the condition that only the measured values of attitude and attitude speed are available, and it is proved that the PD feedback control law can ensure the attitude stability during large angle maneuver.

离心叶轮失速涡结构演化与耦合特征研究

为深入解析离心压气机旋转失速的涡流耦合演化机理,基于Eckardt离心叶轮全通道非定常数值模拟数据,利用涡系识别法和傅里叶频谱分析等方法研究了失速工况下叶轮中关键涡流结构的空间分布特征及非定常演化规律,发现失速流场同时存在两类涡流结构:叶片前缘龙卷风涡和叶顶泄漏涡,两类流动结构交替演化、相互作用,形成了以63%叶轮转速周向传播的失速团,促使离心叶轮失速。具体体现为:叶顶泄漏涡形成并发展,裹挟、牵引叶片前缘分离涡从叶顶开始剥离,直至完全从叶片吸力面脱落。脱落后的分离涡沿周向运动,受到叶片阻挡产生溢流,该溢流流体在叶片压力面与吸力面横向压差的作用下演变为龙卷风涡,该龙卷风涡在周向运动过程中被叶片“截断”为两段而后向下游扩散并逐渐耗散消失。之后新的叶顶泄漏涡又逐渐兴起,形成下一个涡流演化周期。两种涡结构此消彼长、周而复始,共同构成了失速演化特征。

浅谈离心风机安装技术要点

基于离心风机的构造特性和现场安装经验,详细探讨了影响风机安装品质的关键步骤,包括基础验收、轴承座调整、轴承安装、转子叶轮、主轴水平度、风机机壳、主轴密封、联轴器对中安装等环节。

Design and implementation of rigid-flexible coupling for a half-flexible single jack nozzle

The aerodynamic design of a rigid-flexible coupling profile is the decisive factor for the flow-field quality of a supersonic free jet wind tunnel nozzle, and its mechanic dynamic features are the key for engineering implementation of continuous Mach number regulations. To fulfill the requirements of a free jet inlet/engine compatibility test within a wide simulation envelop, both uniform flow-fields of continuous acceleration and deceleration are necessary. In this paper, the aerodynamic design methods of an expansion wall and machinery implementation plan for the halfflexible single jack nozzle were researched. The profile control in nozzle flexible plate design was studied with a rigid-flexible coupling method. Design and calculations were performed with the help of numerical simulation. The technique of axial free stretching of the flexible plate was used to improve the matching performance between the designed elasticity profile and the theoretical one, and the rigid-flexible coupling structure was calibrated by wind tunnel tests. Results indicate that the flexible plate aerodynamic design method used here is effective and feasible. Via rigidflexible coupling design, the flexible plate agrees with the rigid body very well, and continuous Mach number changes can be achieved during the tests. The nozzle’s exit flow-field uniformity meets the requirements of China Military Standard(GJB).

Rigid-flexible coupling dynamic modeling and vibration control for flexible spacecraft based on its global analytical modes

In this study, we used global analytical modeswfny(GAMs) to develop a rigid-flexible dynamic modeling approach for spacecraft with large flexible appendages(SwLFA). This approach enables the convenient and precise calculation of the natural characteristics for designing an attitude control law for the spacecraft while simultaneously suppressing the active vibration of its flexible appendages. We simplify the flexible spacecraft as a rigid-flexible coupling hub-beam system with tip mass and derive the system's governing equations of motion based on Hamilton's principle. By solving the linearized form of those equations with their associated boundary conditions, we obtain the frequencies as well as the corresponding GAMs of flexible spacecraft,which we use to discretize the equations of motion. Using this approach, we performed numerical simulations to investigate the system's global modes and assess the performance of the controller based on the GAM model. The results reveal that the GAM model can be used to directly calculate the exact global modes of SwLFAs and that the controller based on the discrete GAM model can achieve a control-index for a SwLFA in a shorter time with less input energy than other methods.

A Robust Strategy for Precise Fabrication of Rigid-Flexible Coupling Dendrimers toward Self-Coordinated Hierarchical Assembly

Advances in nanotechnology depend upon expanding the ability to create biologically inspired complex materials with well-defined multidimensional structures.Fabrication of hybrid hierarchical structures by combining colloidal organic and inorganic building blocks remains a challenge due to the difficulty in preparing a diverse spectrum of rigid-flexible coupling units of precise shape and size.Herewe reportageneral strategy for crafting amyriad of uniform aggregates via manipulating self-assembly of distinct dendimers with precisely controlled polyhed raloligomeric silse squioxane(POSS)-embedded cores integrating stiffness and ductility.The rigidity of POSS units exerts steric effects onself-amplification of hydrophobic do mains while the flexibility from internally ductile linkages provides ideal scenarios in establishing self-adaptive structural optimization,which subsequently drive the assemblies to proceed into hierarchical self-assembly via multiple coordination effects,generating highly complex multi compartment micelles(MCMs)without any preprocessing.Our facile approach enables a robust modular nanofabrication of well-organized dendrimers toward artificial functional systems with defined geometric architectures and intriguing functions for advanced biological applications.

MODELING AND ANALYSIS OF A COUPLED RIGID_FLEXIBLE SYSTEM

Correct predictions of the behavior of flexible bodies undergoing large rigid-body motions and small elastic vibrations is a subject of major concern in the field of flexible multibody system dynamics. Because of failing to account for the effects of dynamic stiffening, conventional methods based on the linear theories can lead to erroneous results in many practical applications. In this paper, the idea of 'centrifugal potential field', which induced by large overall rotation is introduced, and the motion equation of a coupled rigid-flexible system by employing Hamilton's principle is established. Based on this equation, first it is proved that the elastic motion of the system has periodic property, then by using Frobenius' method its exact solution is obtained. The influences of large overall rigid motion on the elastic vibration mode shape and frequency are analysed through the numerical examples.

A DYNAMIC MODEL FOR ROCKET LAUNCHER WITHCOUPLED RIGID AND FLEXIBLE MOTION

The dynamics of a coupled rigid-flexible rocket launcher is reported. The coupled rigid-flexible rocket launcher is divided into two subsystems, one is a system of rigid bodies, the other a flexible launch tube which can undergo large overall motions spatially. First, the mathematical models for these two subsystems were established respectively. Then the dynamic model for the whole system was obtained by considering the coupling effect between these two subsystems. The approach, which divides a complex system into several simple subsystems first and then obtains the dynamic model for the whole system via combining the existing dynamic models for simple subsystems, can make the modeling procedure efficient and convenient.

一种离心式空气压缩机转子升级改造

DA1000-5X离心式空气压缩机属于七十年代的产品,产品布置为电机-变速机-压缩机,联接方式为齿式联轴器联接。该转子升级改造主要通过CFD计算流体力学方法,获得各级不同马赫数的性能曲线;按照现场提供的入口参数,对该空气压缩机进行气动性能数值计算,通过优化叶轮形线提高整机的多变效率。新转子叶轮由铆接叶轮改换为焊接叶轮,联轴器由齿式联轴器更换为膜片联轴器,升级改造后新转子保证了压缩机长期稳定运行。

超临界二氧化碳离心叶轮耦合优化设计

自循环机匣处理能够显著提升超临界二氧化碳离心叶轮小流量区域的气动性能,但对大流量工况附近的性能提升不明显。为此,考虑自循环机匣与叶轮关键参数的耦合效应,对机匣几何和叶轮叶片掠角实施耦合优化,实现了叶轮性能的全面提升。耦合优化后叶轮在大流量工况、设计工况及小流量工况下的效率分别提升了3.51%、2.60%、4.43%。耦合优化的扩稳增效机理为:在大流量工况下改善了叶片前缘进口攻角,减小了叶轮内部亚临界区,抑制了冷凝的同时改善了叶轮内部流通能力;设计工况下机匣的抽吸量增大,叶顶附近更多低能流体被移除,改善了叶轮下游流场结构;小流量工况下显著减小了叶轮内部堵塞面积,叶轮流动稳定性增强,同时改善了机匣回流造成的掺混损失,叶轮效率提升。

基于故障树法的离心叶轮端齿裂纹故障分析

某航空发动机压气机离心叶轮端齿产生裂纹故障,以此为例,采用故障树分析法,通过冶金分析、修理质量复查、装配质量复查、故障件复查和强度寿命验算,确定端齿裂纹原因。结果表明,端齿修理中部分尺寸未进行加工或加工不到位,造成离心叶轮端齿齿顶倒角与对象件端齿根部圆角发生干涉,产生应力集中,导致端齿产生疲劳裂纹。在此基础上提出相应的改进措施和建议,避免类似故障的发生。

风电机组叶轮结构频率与激励转频的潜在共振分析

大兆瓦机组叶片柔性度越来越大,其耦合模态复杂程度也越来越高。以某大兆瓦级风电机组为例,建立仿真模型,计算叶轮耦合模态频率,并分析自由模态能量占比;绘制坎贝尔图,找出潜在的共振点。现场机组装置叶片载荷采集系统进行潜在共振工况复现,并与正常运行工况的叶根载荷、机舱侧向振动频域进行对比分析,验证仿真的正确性,从而指导整机设计运行转频范围的选定。利用仿真与实测双重验证,确认了机组潜在共振点的激励程度。