非线性气动弹性系统的鲁棒稳定性分析

基于结构奇异值理论和特征多项式的值域方法,研究了带有结构和气动参数不确定性的非线性二元机翼的鲁棒稳定性问题.机翼模型包括非线性的扭转弹簧和能够反映失速效应的非线性气动模型.针对零摄动,使用肛方法分析线性化系统在平衡点的鲁棒稳定性.针对非零摄动,将平衡点位置看作关于不确定参数的函数并展开为泰勒级数,从而在μ方法的框架下考虑平衡点的不确定性.此外,计算不确定特征多项式的值域范围,并使用除零条件来判断其鲁棒稳定性.仿真数值结果给出了鲁棒颤振速度的上下界,表明了方法的有效性.     

复合材料机翼鲁棒气动弹性优化设计

针对气动弹性结构, 利用遗传-敏度混合算法开展鲁棒优化设计。以大展弦比复合材料机翼的鲁棒气动弹性结构优化设计为例验证了鲁棒设计方法的适用性和有效性, 比较了鲁棒结构优化设计与传统优化设计的区别。研究结果表明: 在设计变量存在不确定性的情况下, 考虑鲁棒性约束优化得到的结构较传统优化结构具有更好的抗干扰性; 但鲁棒性的满足是以增加结构质量为代价的, 鲁棒性要求越高, 结构增重越明显。      

参数不确定非线性系统的鲁棒镇定与鲁棒跟踪设计

针对参数不确定非线性系统的鲁棒镇定和鲁棒跟踪问题，提出了一种基于Lyapunov稳定性理论的非线性动态鲁棒控制器设计方法，将设计过程分为两步，第一步是针对标系统设计使其实现控制目标的控制器，第二步是在第一步的基础上，进一步设计控制器抑制由于不确定性因素所产生的原系统与标称系统之间的偏差，其优点是在设计的第一步可以直接利用基于精确数学模型建立的非线性控制系统设计方法，数值仿真验证了设计方法的正确性。     

一种考虑概率分布的鲁棒优化模型

文章以随机规划中的机会约束思想为指导,根据随机参数的概率分布情况,提出了两种鲁棒性条件约束,并在此基础上建立了一种新的鲁棒优化模型,使模型的可行解控制在一定的鲁棒性指标的范围内。该模型不但可处理约束两端同时含有随机参数的情况,还可以方便地推广到非线性模型中。仿真实例说明了模型的有效性。     

价格不确定供应链的多目标运作鲁棒模型

建立了由一个制造商和一个供应商构成的多产品、多阶段供应链在原材料和最终产品的市场价格均不确定情况下运作的鲁棒模型.采用区间不确定性描述价格的不确定性.供应链的运作模型为一个多目标规划问题,满足诸如供应链协调运作、所有供应链成员的目标利润尽可能最大、对应于不确定供求价格的决策的鲁棒性等多个相互冲突的目标.数值算例的结果表明,一定范围内的市场价格波动不改变供应链的运作策略,仅对其运作性能产生一定影响,即所提出的模型是鲁棒的.     

车辆悬架不确定性对行驶平顺性能影响的鲁棒保守性分析

车辆悬架系统中参数不确定性和未建模动态不确定性的存在,使鲁棒控制器的设计显得尤为重要,可是,由于系统设计中对模型不确定性处理的方法问题,导致闭环系统设计的鲁棒保守性增大,进而低估了车辆平顺性的鲁棒性能.通过线性分式变换理论对二自由度车辆主动悬架系统进行混合不确定建模分析,利用混合μ分析方法有效的降低了H∞控制和复数μ综合控制设计鲁棒控制器的保守性,使得车辆主动悬架系统的鲁棒性得到更好的保证.     

多源不确定性条件下气动弹性系统颤振可靠性分析方法

传统的气动弹性系统颤振分析模型大多是在确定性参数条件下建立的,当系统中存在不确定因素时,按确定性方法设计的气动弹性系统存在颤振失效风险.以概率和非概率区间模型为基础,建立了单源不确定性条件下颤振可靠性分析模型;在此基础上,针对含随机和区间多源不确定参数的气动弹性系统颤振可靠性分析问题,提出一种基于分步求解策略的新型混合...     

振动系统鲁棒μ-synthesis控制实验研究

基于结构奇异值μ-synthesis鲁棒控制理论，研究振动响应的主动控制问题，提出设计鲁棒μ-synthesis控制器的方法。采用dSPACE DS 1103为控制器硬件，建立以压电陶瓷为致动器的单输入单输出薄板振动主动控制实验系统，且附加质量被粘贴到薄板上以测试系统鲁棒性能。实验结果表明，通过对性能加权函数和鲁棒加权函数的选取，系统能在指定频带上取得良好的减振控制效果，当压电板发生一定程度的质量摄动时，系统依然能保持稳定且仍具有较好的控制效果。     

不确定环境下的单机成套订单鲁棒计划

讨论了不确定环境下订单数量可变的单机成套计划的优化问题,利用对偶变换给出了该问题的鲁棒整数规划模型,并设计了相应的遗传算法。算法对约束条件难点的处理采用了四种不同的方法即死亡惩罚、罚函数法、修补方法和解码方法,以检验算法的性能。最后进行了数值仿真实验,以比较不同算法的有效性。     

随机不确定系统的鲁棒H∞控制

本文研究随机系统的鲁棒H∞控制问题。假设不确定参数矩阵是时变,范数有界的,外部干扰是一个随机过程。借助于线性矩阵不等式给出了系统是鲁棒H∞可控的一个充分条件。与用代数Riccati-型方程给出的确定性系统的有关结论相比,本文所得到的定理具有计算上的优点。     

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.     

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.     

不确定系统稳定性的仿射不等式分析

针对不确定系统的区间表示不能描述变量间的相关性,相应的区间算法容易导致误差爆炸的缺点,提出了不确定系统的仿射表示法及系统稳定性的仿射不等式判断方法.首先将系统中的不确定信息用仿射参数来表示,得到不确定控制系统传递函数的仿射形式,然后通过求解含仿射参数的不等式组求得了满足系统的稳定性条件时各噪声允许的范围.算例表明,由于考虑了变量间的相关性,相对于区间算法,所提方法可以在更大的不确定范围内判断出系统的稳定性,算例验证了该方法的有效性.     

Approximate analysis of response variability of uncertain linear systems

A probabilistic methodology is presented for obtaining the variability and statistics of the dynamic response of multi-degree-of-freedom linear structures with uncertain properties. Complex mode analysis is employed and the variability of each contributing mode is analyzed separately. Low-order polynomial approximations are first used to express modal frequencies, damping ratios and participation factors with respect to the uncertain structural parameters. Each modal response is then expanded in a series of orthogonal polynomials in these parameters. Using the weighted residual method, a system of linear ordinary differential equations for the coefficients of each series expansion is derived. A procedure is then presented to calculate the variability and statistics of the uncertain response. The technique is extended to the stochastic excitation case for obtaining the variability of the response moments due to the variability of the system parameters. The methodology can treat a variety of probability distributions assumed for the structural parameters. Compared to existing analytical techniques, the proposed method drastically reduces the computational effort and computer storage required to solve for the response variability and statistics. The performance and accuracy of the method are illustrated by examples.     

A robust optimisation model for hybrid remanufacturing and manufacturing systems under uncertain return quality and market demand

In remanufacturing research, most researchers predominantly emphasised on the recovery of whole product (core) rather than at the component level due to its complexity. In contrast, this paper addresses the challenges to focus on remanufacturing through component recovery, so as to solve production planning problems of hybrid remanufacturing and manufacturing systems. To deal with the uncertainties of quality and quantity of product returns, the processing time of remanufacturing, remanufacturing costs, as well as market demands, a robust optimisation model was developed in this research and a case study was used to evaluate its effectiveness and efficiency. To strengthen this research, a sensitivity analysis of the uncertain parameters and the original equipment manufacturer’s (OEM’s) pricing strategy was also conducted. The research finding shows that the market demand volatility leads to a significant increase in the under fulfilment and a reduction in OEM’s profit. On the other hand, recovery cost reduction, as endogenous cost saving, encourages the OEM to produce more remanufactured products with the increase in market demand. Furthermore, the OEM may risk profit loss if they raise the price of new products, and inversely, they could gain more if the price of remanufactured products is raised.     

分布式任务关键系统生存性自动分析与验证

提出了一种应用概率模型检测技术进行分布式任务关键系统生存性的量化分析研究方法.该方法对攻击者和系统的交互行为进行精简抽象,在此基础上使用PRISM高级语言构造连续时间马尔可夫链系统概率模型.针对不同程度的攻击故障及系统服务水平,以连续随机逻辑建立系统生存性的形式化规约.借助概率模型检测工具PRISM对模型进行统计和验证,并图形化地表示出系统生存性的自动分析结果.理论分析和实验结果验证了上述方法的合理性和有效性,这些结果可在理论上指导可生存系统的设计和实现.     

Robust aeroelastic control of two-dimensional supersonic flapped wing systems

Summary The performance of a robust control strategy applied to a two-dimensional supersonic flap-wing aeroelastic system impacted by a pressure pulse in the subcritical supersonic flight speed regime is analyzed. The piston theory aerodynamic model modified to account for the flap deflection has been considered. The study is carried-out via implementation of the Linear Quadratic Gaussian (LQG) control methodology with sliding mode observer. Its performance toward suppressing flutter, reducing the vibrational level amplitudes, as well as toward eliminating the observation spillover due to the unmeasured states is revealed through numerical simulations, and pertinent conclusions are outlined.     

Aerodynamic and mechanical hierarchical aeroelastic analysis of composite wings

Abstract

The coupled bending-torsion flutter is here investigated through Carrera Unified Formulation (CUF). The hierarchical capabilities of CUF offer a procedure to obtain refined one-dimensional models that, by going beyond the assumptions of classical theories, accurately describe the kinematics of structures. Aerodynamic loadings have been determined according to Theodorsen theory, from which the steady formulation can be easily obtained. The displacement variables over the cross section (x-z plane) are approximated by x,z polynomials of any order, N. The finite element method is used to solve the governing equations, which are derived in a weak form through the principle of virtual displacements. The equations are written in terms of “fundamental nuclei,” which do not vary with the theory order, N. Several wing configurations have been studied, giving great attention to thin-walled box beams made of orthotropic material. The effects of sweep angle and lamination scheme on flutter conditions have been investigated, and the results have been compared with solutions obtained from two-dimensional theories, experimental tests, and aeroelastic analyses carried out with the doublet lattice method (DLM). The unsteady theory, combined with advanced beam theories, represents a computationally cheap tool for preliminary aeroelastic studies of complex wing structures.     

Simplified robust and multiobjective optimization of piezoelectric energy harvesters with uncertain parameters

International Journal of Mechanics and Materials in Design - Harvesting energy from mechanical vibrations using piezoelectric materials presents itself as an interesting alternative energy source,...