Monolithic Coupling of the Pressure and Rigid Body Motion Equations in Computational Marine Hydrodynamics

In Fluid Structure Interaction(FSI) problems encountered in marine hydrodynamics, the pressure field and the velocity of the rigid body are tightly coupled. This coupling is traditionally resolved in a partitioned manner by solving the rigid body motion equations once per nonlinear correction loop, updating the position of the body and solving the fluid flow equations in the new configuration. The partitioned approach requires a large number of nonlinear iteration loops per time–step. In order to enhance the coupling, a monolithic approach is proposed in Finite Volume(FV) framework,where the pressure equation and the rigid body motion equations are solved in a single linear system. The coupling is resolved by solving the rigid body motion equations once per linear solver iteration of the pressure equation, where updated pressure field is used to calculate new forces acting on the body, and by introducing the updated rigid body boundary velocity in to the pressure equation. In this paper the monolithic coupling is validated on a simple 2D heave decay case. Additionally, the method is compared to the traditional partitioned approach(i.e. "strongly coupled" approach) in terms of computational efficiency and accuracy. The comparison is performed on a seakeeping case in regular head waves, and it shows that the monolithic approach achieves similar accuracy with fewer nonlinear correctors per time–step. Hence, significant savings in computational time can be achieved while retaining the same level of accuracy.

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.

Dynamic modeling and simulation for the flexible spacecraft with dynamic stiffening

A rigid flexible coupling physical model which can represent a flexible spacecraft is investigated in this paper. By applying the mechanics theory in a non-inertial coordinate system,the rigid flexible coupling dynamic model with dynamic stiffening is established via the subsystemmodeling framework. It is clearly elucidated for the first time that,dynamic stiffening is produced by the coupling effect of the centrifugal inertial load distributed on the beamand the transverse vibration deformation of the beam. The modeling approach in this paper successfully avoids problems which are caused by other popular modeling methods nowadays： the derivation process is too complex by using only one dynamic principle; a clearly theoretical explanation for dynamic stiffening can＇t be provided. First,the continuous dynamic models of the flexible beamand the central rigid body are established via structural dynamics and angular momentumtheory respectively. Then,based on the conclusions of orthogonalization about the normal constrained modes,the finite dimensional dynamic model suitable for controller design is obtained. The numerical simulation validations showthat： dynamic stiffening is successfully incorporated into the dynamic characteristics of the first-order model established in this paper,which can indicate the dynamic responses of the rigid flexible coupling system with large overall motion accurately,and has a clear modeling mechanism,concise expressions and a good convergence.

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.

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 NEW AEROMECHANICAL STABILITY ANALYSIS METHODOLOGY FOR COUPLED ROTOR/FUSELAGE SYSTEM OF HELICOPTERS

The aeromechanical st ability for the coupled rotor/fuselage system of helicopters in forward flight i s investigated. The periodic time-varying equations of motion are developed thr ough building a new 24DOF coupled rigid/elastic blended element based on the fle xible multibody system theory in this paper. It accounts for the effects of prec one, sweep, and the moderately large elastic deflections on the blade and elasti city of shaft and fuselage of the helicopter. The dynamic coupling between the r igid motion of blades about the flap, lag and pitch hinges of articulated rotor and moderately large elastic deflections are included. There is no restriction o n the rotation amplitudes of flap, lag and pitch in the formulation. The stabili ty of periodic solution is studied using the Floquet theory. The transition matr ix is calculated by the Newmark integration method. The aeromechanical stability of a new helicopter is studied. The results show that it is stable in the given forward flight. But the instability arises with the decrease of the bending and torsion stiffness of the shaft.

Dynamic analysis on generalized linear elastic body subjected to large scale rigid rotations

The dynamic analysis of a generalized linear elastic body undergoing large rigid rotations is investigated. The generalized linear elastic body is described in kine- matics through translational and rotational deformations, and a modified constitutive relation for the rotational deformation is proposed between the couple stress and the curvature tensor. Thus, the balance equations of momentum and moment are used for the motion equations of the body. The floating frame of reference formulation is applied to the elastic body that conducts rotations about a fixed axis. The motion-deformation coupled model is developed in which three types of inertia forces along with their incre- ments are elucidated. The finite element governing equations for the dynamic analysis of the elastic body under large rotations are subsequently formulated with the aid of the constrained variational principle. A penalty parameter is introduced, and the rotational angles at element nodes are treated as independent variables to meet the requirement of C1 continuity. The elastic body is discretized through the isoparametric element with 8 nodes and 48 degrees-of-freedom. As an example with an application of the motion- deformation coupled model, the dynamic analysis on a rotating cantilever with two spatial layouts relative to the rotational axis is numerically implemented. Dynamic frequencies of the rotating cantilever are presented at prescribed constant spin velocities. The maximal rigid rotational velocity is extended for ensuring the applicability of the linear model. A complete set of dynamical response of the rotating cantilever in the case of spin-up maneuver is examined, it is shown that, under the ultimate rigid rotational velocities less than the maximal rigid rotational velocity, the stress strength may exceed the material strength tolerance even though the displacement and rotational angle responses are both convergent. The influence of the cantilever layouts on their responses and the multiple displacement trajectories observed in the floating frame is simultaneously investigated. The motion-deformation coupled model is surely expected to be applicable for a broad range of practical applications.

HAMILTONIAN STRUCTURE FOR RIGID BODY WITH FLEXIBLE ATTACHMENTS IN A CIRCULAR ORBIT

Hamiltonian structure of a rigid body in a circular orbit is established in this paper. With the reduction technique, the Hamiltonian structure of a rigid body in a circular orbit is derived from Lie-Poisson structure of semidirect product, and Hamiltonian is derived from Jacobi's integral. The above method can be generalized to establish the Hamiltonian structure of a rigid body with a flexible attachment in a circular or- bit. At last, an example of stability analysis is given.

连续变弯度后缘飞机的滚转机动载荷减缓

变弯度后缘机翼具有变形连续、阻力较小、气动噪声较低等优势,越来越多地应用于新概念飞行器的设计之中。基于此,提出一种基于变弯度后缘的飞行器刚弹耦合动力学建模方法,并针对变弯度后缘飞机缩比模型开展了滚转机动仿真分析与风洞试验。结果表明:变弯度后缘可以操纵飞机在2 s内进行180°滚转机动。相较于外侧后缘单独变形,通过内外后缘协同变形可以降低30%以上的滚转机动附加载荷。另外,对比表明滚转角仿真结果与风洞试验数据误差小于6%,验证了所提方法的准确性。

运载火箭姿态控制速率陀螺自适应加权方法

针对运载火箭反馈控制回路中弹性振动信号与刚体信号存在耦合,会明显降低姿控系统稳定性的问题,提出了一种速率陀螺自适应加权方法,该方法适用于弹性振动的模态振型斜率和频率存在偏差的情况。将速率陀螺观测信号转换为频域表达,采用插值离散傅里叶变换方法辨识弹性频率;基于频域信号提出了速率陀螺加权系数矩阵自适应更新算法,分步抑制了各阶弹性振动信号;开展了不同偏差情况下的仿真校验工作。仿真结果表明,速率陀螺自适应加权方法可实现对速率陀螺测量信号中弹性振动信号的显著抑制,从源头上减小弹性振动信号对姿控系统稳定性的不利影响,从而提高运载火箭姿态控制器的性能,降低控制器的设计难度。

平台运动对15 MW风机气弹性的影响研究

随着人们对风力发电经济性要求的提高,风机叶片逐渐变得更长、更柔软,风电场也在不断向深远海发展。因此有必要研究气弹性耦合情况下平台运动对风机叶片和风机发电功率的影响。基于弹性致动线模型,研究了纵摇、纵荡运动对浮式风机叶片气弹性的影响,分析了气动功率、气动推力和叶片变形。研究发现:由于强迫运动产生了额外的附加速度,15 MW风机气动功率波动可达3个标准差,风机的平均气动功率也因此而减小;叶片弯曲和扭转变形沿叶片展向呈非线性分布,叶尖挥舞变形最大值可达14 m,在设计塔架、叶片预倾角时应当预留出一定的变形空间;由于平台纵摇运动附加在各截面处的速度不同,叶片的变形会呈现出非对称的波动,这会使风力机叶片产生额外的气动载荷波动和结构响应。

转子偏心效应下大范围转动弹性梁外激励非线性动力学行为与振动机制

为实现大范围转动弹性梁类柔性机械的高速、安全、平稳运行,综合应用Galerkin模态截断法和Hamilton原理建立弹性梁刚-柔耦合动力学模型,并建立转子偏心运动微分方程;基于行波叠加原理,应用高阶Runge-Kutta法完成非线性动力学解耦;应用时、频域分析法解析转子偏心效应下弹性梁的振动机制以及外激励下的频谱响应特性。研究结果表明:外激励响应在转子偏心效应下会衍生新的低频谐波分量,转速和激励幅值的增加会导致频域内多个低频谐波分量高于主振,易引发不同程度的间歇性振动;外激励频率提高会引起频域谱峰后移,数值仿真5~35 Hz频段的外激励,当频率为25 Hz时其低频谐波分量是主振幅值的2倍,高达0.181 mm,进而呈现明显的外激励突发性激振。因此,借助时、频域分析可有效解析具有随机性的间歇性或突发性振动产生机制,可为大型旋转柔性机械的动力学优化设计提供重要的理论基础和数据支持。

薄壁四点接触球轴承-腕部关节系统接触动力学分析

在机器人实际工况中,针对含有薄壁四点接触球轴承的机器人腕部关节系统的运动稳定性问题,对腕部系统模型进行了简化设计和仿真研究。在考虑薄壁结构的弹性变形和动态接触作用耦合影响的基础上,建立了刚柔耦合工业机器人腕部关节系统模型,分析了不同受载工况和正反转驱动下的变形规律和动态特性。首先,基于多体动力学和Hertz接触理论,设计了包含薄壁四点接触球轴承和中空轴及基座的腕部关节系统刚柔耦合接触动力学仿真模型;然后,考虑薄壁中空轴、基座、轴承套圈和保持架的结构弹性变形、钢球和套圈滚道、保持架的动态接触作用,研究了机器人腕部关节系统两种实际工况对保持架和钢球角速度、保持架和薄壁基座振动位移、钢球与套圈的动态接触力的影响;最后,计算分析了两种工况下腕部关节系统的动态载荷规律和振动响应特性。研究结果表明:在相对较大的径向载荷作用下,保持架和钢球会出现打滑现象,速度呈现周期波动,保持架和基座具有更好的运动稳定性,其薄壁轴承内部载荷降低,主副接触对均承担联合载荷,轴承内部载荷稳定性也更好。该仿真模型及结果可以为薄壁腕部关节系统的动力学分析与设计提供参考。

飞机货舱门锁闩机构运动可靠性分析

飞机货舱门锁闩机构在舱门打开阶段协助提升电机进行舱门预位,磨损产生的铰链间隙会引起输出角度误差,降低锁闩机构运动可靠度。为了分析铰链磨损对于锁闩机构运动可靠度的影响,根据锁闩机构工作原理建立可靠度计算模型;建立货舱门刚柔耦合动力学模型计算铰链接触力;采用Archard磨损模型计算铰链磨损量,基于等效杆长理论将铰链磨损量转换成杆长变化量,建立参数化模型进行可靠度分析;利用孔销接触模型进行可靠度结果验证。结果表明:该可靠度分析方法能够保证计算精度,提高分析效率。

潮湿细粒煤炭筛分抗堵机理及参数优化研究

深部筛分是实现潮湿细粒煤高效分级的重要途径,但会出现筛面堵塞的问题,刚柔耦合弹性筛分方法被用于克服堵塞。探究了进料速率和物料含水率对筛分性能的影响及相关机理,对3 mm湿细粒煤进行刚柔耦合弹性筛分与刚性筛分对比实验,进一步明确了筛分过程中颗粒的空间分布规律。当外部含水率为11.31%时,筛分效率达到83.15%,总错配物率为6.40%,有效提高了潮湿细粒煤的筛分性能。

混合式三稳态压电能量俘获器动力性能分析

为了提高压电能量俘获器在低强度外界激励下的俘能表现,基于三稳态压电悬臂梁能量俘获器模型,在U形框架和基底之间以及压电悬臂梁固定端与U形框架之间分别装置一个弹性放大器,提出一种混合式三稳态压电能量俘获器(TPEH+DEM)模型。基于Hamilton原理建立了TPEH+DEM系统的非线性力电耦合运动方程,并利用谐波平衡法分析了弹性放大器的质量和弹簧刚度、磁铁之间相对距离、负载电阻等对TPEH+DEM系统能量收集水平的影响。结果表明:在一定的外界激励频率范围内,TPEH+DEM系统的响应输出功率存在两个峰值,合理调节弹性放大器的质量和刚度能使系统在较低的外界激励强度下进入阱间运动,产生很高的输出功率。相比于仅带有弹性基底的传统三稳态压电能量俘获器,TPEH+DEM模型在低频外界激励下具有更好的俘能表现。

刚柔耦合关节SCARA机器人的双柔性动力学模型

针对电子装配机器人高速高精要求,提出一种能够利用柔性铰链变形补偿轴承摩擦死区,实现高精度定位运动的刚柔耦合关节SCARA机器人的概念设计,并建立考虑柔性铰链变形与机械臂一阶弹性变形的双柔性动力学模型。首先,设计一种刚柔耦合轴承的结构,通过轴承中柔性铰链的变形量主动补偿摩擦死区引起的定位误差;在每个关节处引入两个扭转弹簧,分别模拟柔性铰链和机械臂的弹性变形;其次,建立关节的摩擦模型以模拟关节摩擦环境;然后,使用拉格朗日动力学方法建立包含摩擦信息与振动信息的动力学模型。设计开环和闭环的数值仿真进行验证,结果表明该模型理论分析的有效性。

基于CFD/CSD耦合的高速射弹尾拍载荷特性研究

为提高射弹尾拍载荷的预测精度,建立了一套基于计算流体动力学(CFD)/计算结构动力学(CSD)双向耦合分析的计算方法和程序。射弹流体计算主控方程采用耦合SSTk-ω湍流模型和Schnerr-Sauer空化模型的Navier-Stokes方程,射弹结构计算采用基于模态叠加法简化的结构动力学方程,流固耦合界面插值采用径向基函数法,网格变形采用弹簧网格法。分别对泡型计算方法和流固耦合方法进行验证,在此基础上,计算对比1 000 m/s速度下射弹刚体和弹性体的尾拍泡型、结构变形和尾拍流体载荷特性差异。计算表明:弹性体尾拍过程,射弹泡型会产生弹身“二次拍击”、“局部沾湿”和沾湿面积增大等特殊现象,结构变形由弹性一弯模态主导,较大的变形引起流体载荷增大27%~105%,尾拍姿态角增大13%,尾拍频率增加20%,流固耦合效应对尾拍泡型、尾拍载荷和尾拍弹道均产生了较强的影响。

基于仿蟹刚柔耦合机构的搜救机器人设计

搜救机器人是重要的探测仪器平台。针对现有搜救机器人的刚性结构环境适应性差的问题,本文提出一种基于仿蟹刚柔耦合机构的搜救机器人设计方法。本文首先进行了机器人的机构设计;其次根据螃蟹运动实验结果设计了机器人的横向运动步态,并通过仿真验证了步态设计的可行性;再次设计了机器人的软硬件系统;最后对机器人在多种地形下的行走能力进行了实验测试,并开展了暗光环境适应性、人员探测和避障能力等功能测试实验。结果表明,该体积小巧、控制简单的机器人可以实现基本的运动功能,横向运动中最大速度约为3.4 cm/s,最小功耗约为8.6 W,转向运动的角度范围为±90°。机器人具有良好的地形和环境适应性,并可以完成环境感知和人员探测等搜救功能。

扣件弹性垫层劣化对高速列车-道岔系统动力特性的影响

随着高速铁路运营时长的增加,道岔区扣件弹性垫层会发生劣化,对列车过岔的动力学性能产生不利影响。为研究扣件弹性垫层劣化对高速列车道岔系统动力特性的影响,考虑道岔区钢轨的柔性变形,以高速铁路18号无砟道岔为研究对象,建立车辆-道岔刚柔耦合动力学模型,通过时域和频域分析,研究扣件弹性垫层劣化位置、劣化程度、劣化个数及行车速度对列车道岔系统动力特性的影响。研究结果表明:扣件弹性垫层劣化位置影响较大,其中尖轨顶宽40 mm处为扣件弹性垫层劣化的最不利位置;随劣化程度的增加,车岔系统各动力学指标呈增大趋势,其中垂向指标影响更为显著;扣件弹性垫层劣化个数的增加对尖轨尖端的横向动力学指标产生不利影响,9组扣件连续劣化时横向力较1组扣件弹性垫层劣化时增大21.3%;当车辆以250 km/h速度过岔时,扣件弹性垫层劣化对列车道岔系统动力特性的影响最为显著。轴箱振动加速度对扣件弹性垫层劣化较敏感,可在一定程度上反映扣件弹性垫层的劣化。研究成果可为道岔区刚度优化和养护维修提供一定的理论指导。