挠性航天器太阳翼全局模态动力学建模与实验研究

现代柔性航天器通常安装有大型太阳翼为其在轨运行提供所需动力. 航天器入轨后太阳翼展开并锁定成为铰链连接多板结构, 此类结构质量轻、跨度大、刚度低的特点使其低频振动和非线性振动问题越来越凸显. 分析和处理此类结构出现的复杂振动问题的关键在于建立系统精确的非线性动力学模型. 为此, 本文提出铰链连接多板结构解析全局模态的提取方法, 获取太阳翼的固有频率和解析函数表征的全局模态. 提出可变刚度的扭转弹簧等效模型, 考虑铰链非线性刚度及摩擦力矩等因素, 通过全局模态离散得到系统的低维高精度非线性动力学模型, 研究了太阳翼在周期激励作用下的非线性特性. 开展太阳翼地面振动实验研究, 采用锤击法获取系统模态, 利用振动台施加正弦扫频激励, 将物理实验结果与理论结果进行对比, 从而验证全局模态动力学建模方法的合理性与准确性. 结果表明, 铰链刚度等结构参数对系统固有特性的影响较大, 铰链的存在会使太阳翼的动态响应出现跳跃等非线性现象. 全局模态动力学建模方法能很好地解决多板结构在非经典边界下解析全局模态求解的困难, 系统全局模态反映的是系统各个部件弹性振动的真实模态, 所建立的动力学模型具有低维高精度的特点, 对于复杂组合结构非线性动力学建模具有重要的参考价值.      

全柔性空间机器人运动振动一体化输入受限重复学习控制

探究基座、臂、关节全柔性影响下空间机器人动力学模拟、运动控制及基座、臂、关节三重柔性振动主动抑制的问题, 设计了不基于系统模型信息的运动振动一体化输入受限重复学习控制算法. 将柔性基座与关节等效为线性弹簧与扭转弹簧, 柔性臂视为欧拉-伯努利梁模型, 利用拉格朗日方程与假设模态法建立动力学模型, 然后, 用奇异摄动理论将模型分解为包含刚性变量与臂柔性振动的慢变子系统, 包含基座、关节柔性振动的快变子系统, 并分别设计相应的子控制器, 构成了带关节柔性补偿的一体化控制算法. 针对慢变子系统, 提出输入受限重复学习控制算法, 由双曲正切函数, 饱和函数与重复学习项构成, 双曲正切函数与饱和函数实现输入力矩受限要求, 重复学习项补偿周期性系统误差, 以完成对基座姿态、关节铰周期轨迹的渐进稳定追踪. 然而, 为了同时抑制慢变子系统臂的柔性振动, 运用虚拟力的概念, 构造同时反映臂柔性振动与系统刚性运动的混合轨迹, 提出了基于虚拟力概念的输入受限重复学习控制器, 保证基座、关节轨迹精确追踪的同时, 对臂的柔性振动主动抑制. 针对快变子系统, 采用线性二次最优控制算法抑制基座与关节的柔性振动. 仿真结果表明: 控制器适用于一般柔性非线性系统, 满足输入力矩受限要求, 实现对周期信号的高精度追踪, 有效抑制基座、臂、关节的柔性振动, 证实算法的可行性.      

Control structure interaction in the nonlinear analysis of flexible mechanical systems

The effect of the control structure interaction on the feedforward control law as well as the dynamics of flexible mechanical systems is examined in this investigation. An inverse dynamics procedure is developed for the analysis of the dynamic motion of interconnected rigid and flexible bodies. This method is used to examine the effect of the elastic deformation on the driving forces in flexible mechanical systems. The driving forces are expressed in terms of the specified motion trajectories and the deformations of the elastic members. The system equations of motion are formulated using Lagrange's equation. A finite element discretization of the flexible bodies is used to define the deformation degrees of freedom. The algebraic constraint equations that describe the motion trajectories and joint constraints between adjacent bodies are adjoined to the system differential equations of motion using the vector of Lagrange multipliers. A unique displacement field is then identified by imposing an appropriate set of reference conditions. The effect of the nonlinear centrifugal and Coriolis forces that depend on the body displacements and velocities are taken into consideration. A direct numerical integration method coupled with a Newton-Raphson algorithm is used to solve the resulting nonlinear differential and algebraic equations of motion. The formulation obtained for the flexible mechanical system is compared with the rigid body dynamic formulation. The effect of the sampling time, number of vibration modes, the viscous damping, and the selection of the constrained modes are examined. The results presented in this numerical study demonstrate that the use of the driving forees obtained using the rigid body analysis can lead to a significant error when these forces are used as the feedforward control law for the flexible mechanical system. The analysis presented in this investigation differs significantly from previously published work in many ways. It includes the effect of the structural flexibility on the centrifugal and Coriolis forces, it accounts for all inertia nonlinearities resulting from the coupling between the rigid body and elastic displacements, it uses a precise definition of the equipollent systems of forces in flexible body dynamics, it demonstrates the use of general purpose multibody computer codes in the feedforward control of flexible mechanical systems, and it demonstrates numerically the effect of the selected set of constrained modes on the feedforward control law.     

含间隙铰接的柔性航天器刚柔耦合动力学与控制研究

大型柔性航天器展开锁定后,运动副中仍存在大量无法消除的间隙. 铰链间隙直接影响柔性航天器的姿态 运动和有效载荷的指向精度及稳定度,会对航天器的动力学特性造成较大的影响. 针对这一问题, 提出一种含间隙铰 接的航天器刚柔耦合动力学建模与控制方法. 首先建立含间隙的铰链精确动力学模型,从而构建含间隙铰接的柔性结构 动力学模型. 然后利用哈密顿原理和模态离散方法,建立含间隙铰接柔性航天器离散形式的刚柔耦合非线性动力学 模型,采用 Newmark 算法对非线性动力学方程进行求解. 基于压电纤维复合材料 (macro fiber composite, MFC) 驱动器 构建航天器的刚-柔-电耦合动力学方程,采用最优控制设计控制律. 分析了铰链参数、中心刚体转动惯量、间隙尺寸和间隙数目对航天器动力学特性的影响,着重研究了铰链间隙对航天器姿态运动和结构振动的影响作用. 最后采用 MFC 驱动器对航天器施加主动控制. 结果表明,铰链参数和中心刚体转动惯量影响航天器的固有频率;随着铰链间隙尺寸的增大及间隙数目的增多,航天器的整体刚度逐渐减小,而航天器的姿态角和振动位移响应不断增大;通过基于 MFC 的主动控制,能够实现含间隙铰接航天器姿态运动与结构振动的协同控制,并缓解间隙对系统动态特性造成的影响.      

DYNAMICS AND CONTROL OF RIGID-FLEXIBLE COUPLING FLEXIBLE SPACECRAFT WITH JOINT CLEARANCE1)

大型柔性航天器展开锁定后,运动副中仍存在大量无法消除的间隙. 铰链间隙直接影响柔性航天器的姿态 运动和有效载荷的指向精度及稳定度,会对航天器的动力学特性造成较大的影响. 针对这一问题, 提出一种含间隙铰 接的航天器刚柔耦合动力学建模与控制方法. 首先建立含间隙的铰链精确动力学模型,从而构建含间隙铰接的柔性结构 动力学模型. 然后利用哈密顿原理和模态离散方法,建立含间隙铰接柔性航天器离散形式的刚柔耦合非线性动力学 模型,采用 Newmark 算法对非线性动力学方程进行求解. 基于压电纤维复合材料 (macro fiber composite, MFC) 驱动器 构建航天器的刚-柔-电耦合动力学方程,采用最优控制设计控制律. 分析了铰链参数、中心刚体转动惯量、间隙尺寸和间隙数目对航天器动力学特性的影响,着重研究了铰链间隙对航天器姿态运动和结构振动的影响作用. 最后采用 MFC 驱动器对航天器施加主动控制. 结果表明,铰链参数和中心刚体转动惯量影响航天器的固有频率;随着铰链间隙尺寸的增大及间隙数目的增多,航天器的整体刚度逐渐减小,而航天器的姿态角和振动位移响应不断增大;通过基于 MFC 的主动控制,能够实现含间隙铰接航天器姿态运动与结构振动的协同控制,并缓解间隙对系统动态特性造成的影响.     

基于虚拟力概念的柔性臂空间机器人模糊退步自适应控制算法设计

讨论了漂浮基柔性臂空间机器人系统的动力学模拟、运动轨迹跟踪控制算法设计及柔性振动主动抑制。采用多体动力学建模方法并结合假设模态法,建立了漂浮基柔性臂空间机器人的系统动力学模型。基于该模型,针对系统惯性参数未知情况,提出了刚性运动基于模糊基函数网络自适应调节的退步控制算法,以完成柔性臂空间机器人载体姿态及机械臂各关节铰的协调运动。然后,为了主动抑制系统柔性振动,运用虚拟力的概念,构造了同时反映柔性模态和刚性运动轨迹的混合期望轨迹,通过改造原有的控制算法,提出了基于虚拟力概念的模糊退步自适应控制算法;这样不但保证了之前刚性运动控制方案对模型不确定的鲁棒性,而且能主动抑制柔性振动,从而提高了轨迹跟踪性能。理论分析及数值仿真算例均表明了控制方法的可行性。     

DYNAMIC ANALYSIS OF FLEXIBLE BODY WITH DEFINITE MOVING ATTITUTE

The nonlinear dynamic control equation of a flexible multi-body system with definite moving attitude is discussed.The motion of the aircraft in space is regarded as known and the influence of the flexible structural members in the aircraft on the motion and attitude of the aircraft is analyzed.By means of a hypothetical mode,the defor- mation of flexible members is regarded as composed of the line element vibration in the axial direction of rectangular coordinates in space.According to Kane’s method in dy- namics,a dynamic equation is established,which contains the structural stiffness matrix that represents the elastic deformation and the geometric stiffness matrix that represents the nonlinear deformation of the deformed body.Through simplification the dynamic equation of the influence of the planar flexible body with a windsurfboard structure on the spacecraft motion is obtained.The numerical solution for this kind of equation can be realized by a computer.     

UNCONSTRAINED MODAL ANALYSIS OF DYNAMIC MODEL OF FLEXIBLE SPACECRAFT$^{\bf 1)}$

挠性航天器动力学建模中的挠性耦合影响系数是动力学建模中的重要力学概念,它反映了航天器姿态和轨道运动与挠性附件的弹性振动效应. 挠性耦合影响系数间的恒等式关系,即惯性完备性准则,是挠性航天器动力学模型降阶和模态截断的重要依据. 以中心刚体带挠性附件航天器为研究对象,采用约束模态和非约束模态法描述挠性附件结构变形,利用欧拉-拉格朗日方程建立挠性航天器的动力学模型. 基于 Hughes 的研究成果,对挠性航天器的非约束模态恒等式及其用于动力学模型降阶的惯性完备性准则进行了证明和应用研究. 探讨了两种动力学模型惯量间的关系,并利用约束模态惯性完备性准则,推导了非约束模态惯性完备性准则. 最后,对中心刚体带双侧太阳帆板和带单侧太阳帆板构成的挠性航天器模型进行数值仿真计算,求出挠性附件非约束模态平动耦合系数,分析了非约束模态特征值和平动耦合系数随着刚柔质量比的变化情况,并尝试用非约束模态惯性完备性准则的质量特征恒等式对挠性航天器模型进行了检验.     

挠性航天器动力学模型的非约束模态分析

挠性航天器动力学建模中的挠性耦合影响系数是动力学建模中的重要力学概念,它反映了航天器姿态和轨道运动与挠性附件的弹性振动效应. 挠性耦合影响系数间的恒等式关系,即惯性完备性准则,是挠性航天器动力学模型降阶和模态截断的重要依据. 以中心刚体带挠性附件航天器为研究对象,采用约束模态和非约束模态法描述挠性附件结构变形,利用欧拉-拉格朗日方程建立挠性航天器的动力学模型. 基于 Hughes 的研究成果,对挠性航天器的非约束模态恒等式及其用于动力学模型降阶的惯性完备性准则进行了证明和应用研究. 探讨了两种动力学模型惯量间的关系,并利用约束模态惯性完备性准则,推导了非约束模态惯性完备性准则. 最后,对中心刚体带双侧太阳帆板和带单侧太阳帆板构成的挠性航天器模型进行数值仿真计算,求出挠性附件非约束模态平动耦合系数,分析了非约束模态特征值和平动耦合系数随着刚柔质量比的变化情况,并尝试用非约束模态惯性完备性准则的质量特征恒等式对挠性航天器模型进行了检验.      

空间网格结构动力分析的非线性模态方法

空间网格结构因自由度数多且无简化的力学模型,非线性动力分析通常要耗费大量时间．传统的非线性模态方法用于求解多高层结构的局部非线性问题已获得良好的效果,但对系统非线性问题的应用尚缺少研究．对比分析多高层结构和空间网格结构动力性能差异,指出网格结构动力非线性分析存在的问题．以主振型理论和切线刚度分离法为基础,将非线性模态方法用于几何非线性效应显著的空间网格结构动力分析．通过对运动方程的非线性恢复力进行拆分,形成线性表达形式,然后解耦到主振型所在的广义坐标系,以达到缩减自由度数量的目的．并通过实例验证非线性模态方法的高效性与适用性．     

平动柔性矩形薄板的动力学特性与屈曲分析

应用Hamilton变分原理建立了平动状态下对边简支对边自由矩形薄板的非线性动力学方程,分别应用假设模态法和康特洛维奇法分析了板的前4阶近似振动频率、临界分岔值及板的前3阶后屈曲近似解,并比较了取不同阶数假设模态对分析结果的影响．分析表明整体平动可使柔性多体系统中的柔性构件产生动力刚化和动力软化效应,且软化效应还可使系统平衡位置发生分岔而失稳;在动力刚化和动力软化情况下,柔性构件模态出现的顺序均可能发生改变,此性质在柔性多体系统动力学简化建模特别是模态截断时应引起足够的重视．     

Wave-based control of planar motion of beam-like mass–spring arrays

Wave-based control (WBC) is a simple and relatively new technique for motion control of under-actuated flexible systems. To date it has been mainly applied to rectilinear lumped flexible systems. The current work focuses on a development of WBC to control two-dimensional beam-like structures in which an actuator, attached to one end, acts to translate and rotate the structure through an arbitrary path in the plane. In this work, first a lumped model of a beam is developed using mass–spring arrays. The lumped beam model is of interest here as a benchmark control challenge. It can also be considered as a model of various lumped or distributed mass structures. To check the latter, the mode shapes and frequencies are first compared with those of classical beam theory. This involved a new technique to find mode shapes and frequencies for arrays. The control strategy is then presented and tested for a range of manoeuvres. As a system to be controlled, the mass–spring array presents many challenges. It has many degrees of freedom, many undamped vibration modes, is highly under-actuated, and sensing of system states is difficult. Despite these challenges, WBC performs well, combining a fairly rapid response with active vibration damping and zero steady-state error. The controller is simple to implement and of low order. It does not need or use any system model and is very robust to system changes.     

挠性根部梁的动力学建模

挠性根部梁具有整体平动和转动自由度，其传统模型只适宜根部挠性很小的梁．采用柔性多体系统的建模方法建立了挠性根部Euler—Bernoulli梁的非线性动力学模型及线性耦合模型，所建模型不受根部挠性大小的限制；既可描述挠性根部梁的耦合振动，也可分别退化为固支梁或刚性梁的动力学模型；且线性耦合模型可线性变换为挠性根部梁传统模型．作为算例，采用假设模态法分析了两类线性模型的振动特性，表明线性耦合模型优于挠性根部梁传统模型．     

A nonlinear finite-element approach for kineto-static analysis of multibody systems

Methods that treat rigid/flexible multibody systems undergoing large motion as well as deformations are often accompanied with inefficiencies and instabilities in the numerical solution due to the large number of state variables, differences in the magnitudes of the rigid and flexible body coordinates, and the time dependencies of the mass and stiffness matrices. The kineto-static methodology of this paper treats a multibody mechanical system to consist of two collections of bulky (rigid) bodies and relatively flexible ones. A mixed boundary condition nonlinear finite element problem is then formulated at each time step whose known quantities are the displacements of the nodes at the boundary of rigid and flexible bodies and its unknowns are the deformed shape of the entire structure and the loads (forces and moments) at the boundary. Partitioning techniques are used to solve the systems of equations for the unknowns, and the numerical solution of the rigid multibody system governing equations of motion is carried out. The methodology is very much suitable in modelling and predicting the impact responses of multibody system since both nonlinear and large gross motion as well as deformations are encountered. Therefore, it has been adopted for the studies of the dynamic responses of ground vehicle or aircraft occupants in different crash scenarios. The kineto-static methodology is used to determine the large motion of the rigid segments of the occupant such as the limbs and the small deformations of the flexible bodies such as the spinal column. One of the most dangerous modes of injury is the amount of compressive load that the spine experiences. Based on the developed method, a mathematical model of the occupant with a nonlinear finite element model of the lumbar spine is developed for a Hybrid II (Part 572) anthropomorphic test dummy. The lumbar spine model is then incorporated into a gross motion occupant model. The analytical results are correlated with the experimental results from the impact sled test of the dummy/seat/restraint system. With this extended occupant model containing the lumbar spine, the gross motion of occupant segments, including displacements, velocities and accelerations as well as spinal axial loads, bending moments, shear forces, internal forces, nodal forces, and deformation time histories are evaluated. This detailed information helps in assessing the level of spinal injury, determining mechanisms of spinal injury, and designing better occupant safety devices.     

二元复合材料板的自由振动: 半解析法

二元复合材料板是超材料板结构中常见的单元之一. 针对由材料参数相差两个量级的基体和嵌入体组成的二元复合材料板, 提出结构自由振动的半解析模型, 并对其振动特性进行了研究. 基于区域分解法和二元材料的分布, 将二维平板分解成两个子区域. 通过在振型函数中附加区域试函数, 来描述复合材料板面内刚度突变引起局部位移和转角的非光滑性. 基于二元复合材料板的基本边界条件和两子区连接处的变形协调条件, 构造了新的振型函数. 基于经典薄板理论, 利用带特殊试函数的里兹法, 求得不同几何构型下二元复合材料板的固有频率和振型, 并研究了嵌入体的尺寸和位置对结构振动特性的影响规律. 通过收敛分析并与有限元仿真结果对比, 验证了本文方法的准确性. 研究结果表明: 传统的全局试函数在分析具有振动局部化的模态时会得到不准确的结果, 而附加区域试函数可以显著提高里兹法的收敛速度以及结果的准确性; 嵌入体位置对低阶固有频率的作用不明显, 却能显著改变低阶振型节线的分布和振动局部化发生的区域.      

漂浮基柔性关节空间机器人自适应滑模运动控制及振动主动抑制

讨论了关节柔性且系统参数不确定的漂浮基空间机器人系统的动力学建模过程、运动轨迹跟踪控制算法设计及系统柔性振动的主动抑制问题。利用系统动量、动量矩守恒关系和拉格朗日法对系统动力学进行分析,并建立系统动力学方程。基于奇异摄动法将系统分解为表示系统刚性运动部分的慢变子系统和表示系统柔性运动部分的快变子系统。针对慢变子系统提出了一种自适应滑模控制算法。该控制算法是由基于滑模面的等效控制项、自适应控制项和PID反馈控制项组成。因此,它集合了滑模控制、自适应算法和PID技术的优点,且弥补了三种算法各自的缺点。该控制算法能够有效地补偿系统的转动误差和不确定参数,提高控制系统的精度。针对快变子系统,提出基于速度差值的反馈控制算法来抑制柔性关节引起的系统柔性振动,保证系统的稳定性。最后,通过仿真实验证明了提出的混合控制算法的有效性。     

ON THE NATURAL FREQUENCIES,COMPLEX MODE FUNCTIONS,AND CRITICAL SPEEDS OF AXIALLY TRAVELING LAMINATED BEAMS:PARAMETRIC STUDY

The dynamic response of an axially traveling laminated composite beam is investigated analytically,with special consideration to natural frequencies,complex mode functions and critical speeds of the system.The equation of motion for a symmetrically laminated system,which is in the form of a continuous gyroscopic system,is considered;the equation of motion is not discretized — no spatial mode function is assumed.This leads to analytical expressions for the complex mode functions and critical speeds.A paramet...     

An anti-disturbance PD control scheme for attitude control and stabilization of flexible spacecrafts

This paper studies the attitude control problem of spacecrafts with flexible appendages. It is well known that the unwanted vibration modes, model uncertainty and space environmental disturbances may cause degradation of the performance of attitude control systems for a flexible spacecraft. In this paper, the vibration from flexible appendages is modeled as a derivative-bounded disturbance to the attitude control system of the rigid hub. A disturbance-observer-based control (DOBC) is formulated for feedforward compensation of the elastic vibration. The model uncertainty and space environmental disturbances as well as other noises are merged into an “equivalent” disturbance. We design a composite controller with a hierarchical architecture by combining DOBC and PD control, where DOBC is used to reject the vibration effect from the flexible appendages. Numerical simulations are performed to demonstrate that by using the composite hierarchical control law, disturbances can be effectively attenuated and the robust dynamic performances be enhanced.     

大范围运动细长柔性空间结构动力学特性分析

自由-自由边界无约束状态的细长柔性空间结构大范围运动时的动力学特性对整体结构运动分析和运动控制系统设计具有极其重要的作用。通过浮动坐标系建立结构的运动学关系;借助假设模态法对结构变形进行变量分离;利用Lagrange’s方程建立了结构的刚柔耦合振动方程;再通过Rayleigh-Ritz法,以无大范围运动时的振型函数作为基本解组,得到了大范围运动影响下的结构振动特征方程,求解该方程得到了结构频率和振型。通过几组数值算例的对比分析,指出了非耦合模型和耦合模型下结构频率及振型之间的差异。     

大型柔性航天器动力学与振动控制研究进展

随着航天重大工程的逐步实施,航天器正朝着超高速、超大尺度、多功能的方向发展,其面临的发射和运行环境也更加恶劣.航天器发射过程中的振动及其主/被动控制、在轨运行中大型柔性航天器动力学建模与动态响应分析、结构振动与飞行器姿态的混合控制等问题越来越复杂且难于处理;航天器结构的大型化和柔性化(如大阵面天线和太阳翼等)也对其地面试验和半实物仿真提出了挑战.本文着重介绍大型柔性航天器涉及到的动力学与振动控制问题,包括航天器发射过程中的整星隔振,大型柔性结构动力学建模与振动响应分析,大型柔性航天器的结构振动与姿轨控耦合动力学及其混合控制等.提炼出航天动力学与控制领域中亟待解决的若干基础科学问题,包括:多刚柔体系统动力学建模与模型降阶(涉及大变形柔性体动力学建模、多求解器合作仿真、模型降阶、组合结构动力学建模的解析方法等);复杂结构状态空间模型构建方法与能控性(涉及状态空间模型构建的理论与实验方法、复杂结构振动控制系统的能观性与能控性等);航天器姿态运动与大型柔性结构振动的混合控制律设计(涉及姿态机动与结构振动的鲁棒混合控制、执行机构与压电控制器的协同控制等).