Hysteresis and the nonlinear equivalent piezoelectric coeffcient of MFCs for actuation

The hysteretic behavior and nonlinearity of the equivalent material coefficient of macro fiber composites (MFC) under staircase input conditions are investigated using the Preisach model. Based on a database of first order reversal curves, formulas are derived to predict the hysteresis of strain output and nonlinearity of the equivalent piezoelectric coefficient of MFCs. Formulae are verified by comparing the predicted strains with the measured strains of three MFC specimens, which are driven by a random sequence of staircase voltage inputs. The coefficients obtained by the formulae and experimentation coincide. Further results indicate that the equivalent piezoelectric strain coefficient depends greatly on the value of drive voltage across the entire input range, and the coefficient is asymmetric across the negative and positive input ranges. Deflection testing of an MFC composite cantilever demonstrates the importance of taking the nonlinearity of the equivalent piezoelectric coefficient into consideration in the application of actuation.     

Hysteresis and the nonlinear equivalent piezoelectric coefficient of MFCs for actuation

The hysteretic behavior and nonlinearity of the equivalent material coefficient of macro fiber composites(MFC) under staircase input conditions are investigated using the Preisach model.Based on a database of first order reversal curves, formulas are derived to predict the hysteresis of strain output and nonlinearity of the equivalent piezoelectric coefficient of MFCs. Formulae are verified by comparing the predicted strains with the measured strains of three MFC specimens,which are driven by a random sequence of staircase voltage inputs. The coefficients obtained by the formulae and experimentation coincide. Further results indicate that the equivalent piezoelectric strain coefficient depends greatly on the value of drive voltage across the entire input range, and the coefficient is asymmetric across the negative and positive input ranges. Deflection testing of an MFC composite cantilever demonstrates the importance of taking the nonlinearity of the equivalent piezoelectric coefficient into consideration in the application of actuation.     

Nonlinear hysteresis identification and compensation based on the discrete Preisach model of an aircraft morphing wing device manipulated by an SMA actuator

The conception of aircraft morphing wings thrives in aeronautics since the appearance of shape memory alloys(SMAs). An aircraft morphing wing device, manipulated by an SMA actuator, inherits the intrinsic nonlinear hysteresis from the SMA actuator, ending up with control disadvantages. Conventionally, systems with SMA actuators are constrained to bi-stable states to bypass the hysteresis region. Rather than retreating a morphing wing device to bi-stable states, this paper is dedicated to transcend the morphing wing device beyond the customary limit. A methodology of discrete Preisach modeling, which identifies the hysteresis of the morphing wing device, is proposed herein. An array of discrete equal-distance points is applied to the Preisach plane in order to derive the Preisach density over the partitioned unit of the Preisach plane. Discrete Preisach modeling is fulfilled by the discrete first-order reversible curve(DFORC). By utilizing the discrete Preisach model, the aircraft morphing wing device is simulated; the validity and accuracy of discrete Preisach modeling are demonstrated by contrasting the simulated outcome with experimental data of the major hysteretic loop and the wingspan-wise displacement over time; a comparison between simulation and experimental results exhibits consistency. Afterwards, a hysteresis compensation strategy put forward in this paper is implemented for quasi-linear control of the aircraft morphing wing device, which manifests a compensated shrinking hysteresis loop and attains the initiative of extending the morphing range to the intrinsic hysteretic region.     

Aerodynamics of smart flap under ground effect

Aerodynamic characteristics of two-dimensional smart flap under the ground effect have been assessed by a numerical simulation. In this process, a pressure-based implicit procedure to solve Navier–Stokes equations on a nonorthogonal mesh with collocated finite volume formulation is used. The boundedness criteria for this procedure are determined from the Normalized Variable Diagram (NVD) scheme. The procedure incorporates the k–ε eddy–viscosity turbulence model. Cantilever beam with uniformly varying load with roller support at the free end is considered for the configuration of the smart flap. The method is first validated against experimental data. Then, the algorithm is applied for turbulent aerodynamic flows around airfoil with smart and conventional flaps for different attack angle, flap angle and ground clearance where the results of two flaps are compared. The comparisons show that the quality of the solution is considerable.     

颤振边界预测的系统稳定性分析方法

对颤振边界预测方法中的颤振裕度法与自回归滑动平均模型（ARMA）稳定性分析方法进行研究,采用数值仿真算例研究这两种方法受参数识别误差的影响,采用风洞颤振试验算例对比分析其预测颤振边界的有效性与准确性,结果表明:①颤振裕度法的判据受阻尼比识别误差的影响较小,相对于阻尼比识别误差更容易受频率识别误差的影响,ARMA稳定性分析方法的判据相对于颤振裕度法更易受阻尼比识别误差的影响,颤振裕度法比ARMA稳定性分析方法鲁棒性更高;②对于机翼弯扭耦合颤振,两方法的判据变化趋势相近,相差采样频率4次方的数量级,两者随着风速的增加具有平缓的下降趋势,有助于较早地预测颤振边界;③对于面内弯曲为主的颤振,ARMA稳定性分析方法比颤振裕度法适用性更好。      

Comparison of two reliability models for performance degradation analysis

In order to investigate the general reliability assessment methods based on performance degradation data, two commonly used stochastic process approaches, bilinear process method and random-effect model were studied. Analyzing procedure and effectiveness of these two methodologies were studied and compared. Meanwhile, the two approaches were illustrated through practical applications. The residual plots and the 10th percentile curves of the two methods were presented to demonstrate the comparative results. The random-effect model yielded more volatile residuals and a lower and unsafe 10th percentile curve. Consequently the bilinear process model can be concluded to derive more reasonable results due to its one-stage estimation property.     

Active vibration control of piezoelectric bonded smart structures using PID algorithm

Thin-walled structures are sensitive to vibrate under even very small disturbances. In order to design a suitable controller for vibration suppression of thin-walled smart structures, an electro-mechanically coupled finite element(FE) model of smart structures is developed based on first-order shear deformation(FOSD) hypothesis. Considering the vibrations generated by various disturbances, which include free and forced vibrations, a PID control is implemented to damp both the free and forced vibrations. Additionally, an LQR optimal control is applied for comparison.The implemented control strategies are validated by a piezoelectric layered smart plate under various excitations.     

压电智能反射面静态形状控制与作动器位置优化

为了提高反射面的精度,建立了压电智能反射面的形状控制模型,对该结构的力学建模方法、形状控制方法和作动器优化配置算法进行了研究。首先,将蜂窝夹层结构的压电智能反射面等效为多层复合板,根据虚功原理推导了结构的有限元方程。然后,根据建立的有限元方程,推导了反射面变形的均方根误差与作动器控制电压的关系式,以均方根误差最小为优化目标,建立了形状控制优化模型,将作动器控制电压的优化转化为约束优化问题的求解。最后,采用模拟退火算法对压电作动器进行了优化配置。为了验证形状控制的可行性及优化算法的有效性,以300mm口径的平面压电智能反射面为例进行仿真,分析结果表明,通过压电作动器的控制,可以使反射面的重力变形误差减小97%以上,对于给定数目的作动器,通过模拟退火算法优化,可使其布置在最佳的位置。     

Constrained layer damping treatment of a model support sting

In transonic wind tunnel tests, the pulsating airflow is prone to induce the first order resonance of the sting support system. The resonance limits the wind tunnel test envelope, makes the test data inaccurate, and brings potential security risks. In this paper, a model support sting with constrained layer damping (CLD) treatment is proposed to reduce the first order resonance response. The CLD treatment mainly consists of material selection and geometric optimization processes. The damping performance of the optimized CLD sting is compared with an AISI 1045 steel sting with the identical diameter in laboratory. The frequency response curves of the CLD sting support system and the AISI 1045 steel sting support system are obtained by sine sweep tests. The test results show that the first order resonance response of the CLD sting support system is 37.3% of that of the AISI 1045 steel sting support system. The first order damping ratios are calculated from the frequency response curves by half power point method. It is found that the first order damping ratio of the CLD sting support system is approximately 2.6 times that of the AISI 1045 steel sting support system.     

自动计算NURBS初始权因子的方法

通过对NURBS曲线权因子几何属性的深入分析,给出了一个直观、简洁和客观计算权因子的一般方法 ;在此基础上,提出了利用线性插值法和嵌入ANN算法的自动计算NURBS权因子的具体方法。根据NURBS控制多边形的形状以及曲线的形状约束条件,自动计算出NURBS曲线的一组初始权因子。     

基于自适应代理模型的气动优化方法

气动优化设计中,为了减少优化系统的计算周期,提高搜索效率,引入结构简单、计算量较小的代理模型,而运用有效的插值和选样方法(自适应选样)可以大大减少建立代理模型的时间。因此本文提出了一种基于自适应代理模型的气动优化方法。首先对自适应代理模型进行研究,建立了 Kriging 自适应代理模型和支持向量回归自适应代理模型,这两种自适应代理模型在相同样本点情况下比一般代理模型拥有更高的预测能力,然后将这其应用到翼型优化设计中,取得了良好的优化效果,从而表明这两种自适应代理模型不仅简单实用,而且明显提高了气动分析的计算效率。     

Acceleration sensors based modal identification and active vibration control of flexible smart cantilever plate

Some flexible appendages of spacecrafts, such as solar panels, are cantilever plate structures. Thus, vibration problem is unavoidable when there is slewing maneuver or external disturbance excitation. Vibration of such cantilever plate structures includes coupled bending and torsional motion. Furthermore, the low amplitude vibration near the equilibrium point is very difficult to be quickly suppressed due to nonlinear factors of the hardware in the system, which is harmful to stability and attitude control accuracy. To solve these problems, acceleration sensor-based modal identification and active vibration control methods are presented for the first two bending and the first two torsional modes vibration of the cantilever plate. Optimal placements of three acceleration sensors and PZT patches actuators are performed to decouple the bending and torsional vibration of such cantilever plate for sensing and actuating, and identifications are achieved by experiments. A nonlinear control method is presented to suppress both high and low amplitude vibrations of flexible smart cantilever plate significantly. Experimental comparison researches are conducted by using acceleration proportional feedback and the presented nonlinear control algorithms. The experimental results demonstrate that the presented acceleration sensor-based methods can suppress the vibration of cantilever plate effectively.     

短纤维增强热塑性树脂复合材料断裂机理研究

测定了两种短碳纤维(CF)增强热塑性树脂复合材料(CF/PPS和CF/PES-C)的抗拉强度(σ_y)、杨氏模量(E)反断裂韧性(K_(IC)等性能随碳纤维体积分数(0～40vol％)的变化。杨氏模量随CF含量增加而线性增加,Krenchel系数为0.05。σ_y和K_(IC)随CF增多而增大,在25vol％处出现峰值。根据裂纹钉扎模型,结合对负载-位移曲线及断口形貌,着重从界面结合力特征进行分析;计算得两种复合材料的等效裂纹张力分別为26kJ/m和2.1kJ/m。     

某型飞机平尾转轴可靠性灵敏度分析

采用了基于改进一次二阶矩法、基于Monte-Carlo直接模拟法、基于重要抽样法的可靠性灵敏度分析方法以及一种基于重要抽样的可靠性灵敏度分析方法,对某型飞机平尾转轴进行可靠性灵敏度的求解,并分析了某型飞机平尾转轴可靠性灵敏度随变异系数变化的趋势,为其可靠性设计提供了参考信息。通过4种方法结果相比较,可以说明各种方法的特点并验证了它们在工程问题上的可行性。     

非线性方程新解法及其在颤振分析中的应用

 从解析函数保角变换出发提出一种求解非线性方程的新算法——正交搜索法。将该算法用于弹性飞机颤振分析问题，可以准确地解出各种状态下的振动模态。该算法可由计算机自动完成，计算过程简便、直观，对飞机设计及颤振主动抑制系统的综合均有参考价值。     

On deflection as a performance criterion in detection

The performance of detection systems is usually characterized by the receiver operating characteristics (ROC) curves. Because of the complexity of the calculation of such curves simpler performance criteria are useful. Among these, the deflection criterion, or output signal-to-noise ratio, is one of the most interesting. The advantages and limitations of the deflection are first analyzed. Attention is especially paid to the relation between singular detection and infinite deflection. Maximization of the deflection in the class of linear-quadratic (L-Q) systems is also discussed and it is shown that in order to detect a deterministic signal in some kinds of non-gaussian noise a quadratic term can introduce an almost singular detection. This situation is analyzed by computer simulations and comparisons between results obtained via the deflection or the ROC curves indicate the interest of the deflection in the analysis of the performance of some nonlinear system     

利用恢复系数预报梁结构弹性正碰载荷的两种有效近似法

对于小球撞击欧拉－贝努利梁问题,应用撞击力模型,给出预报撞击力的两种方法。方法1基于位移协调方程,分别考虑碰撞发生阶段结束和恢复阶段结束两个时刻的位移协调方程。方法2基于梁的动力微分方程,利用撞击系统的动量守恒原理和恢复系数概念。两种方法均得到撞击过程中撞击力随时间变化的曲线。分析结果与已有结果进行比较,结果符合较好。其中方法1大幅简化计算量,可推广到小球与板撞击问题中去;方法2能够较好地描述撞击力,同时可分析各种因素对接触撞击力的影响。     

基于漏斗试样的C250钢高温扭转低周疲劳行为

C250钢的扭转疲劳破坏是其主要失效形式之一。为了获得航空材料C250钢的扭转疲劳特性,并消除等直圆棒试样在扭转试验中产生的弊端,依据漏斗试样完成了C250钢在3种高温(150、200、350℃)环境下的扭转低周疲劳试验,获得了在扭转低周疲劳下的扭矩-名义扭转角曲线。基于试验结果,利用FAT方法分析得到了C250钢在3种高温环境下的材料循环本构关系,利用该循环本构关系对漏斗试样进行三维扭转有限元分析,获得漏斗根部剪切应力与扭矩之间的转换公式及漏斗根部剪切应变与名义扭转角之间的转换公式。基于以上试验与分析方法,得到了材料的剪切应变幅-倍循环次数曲线、剪切应力幅-循环分数曲线以及剪切应力-剪切应变的稳定滞回线,发现材料呈现出循环软化特性,并基于Manson-Coffin模型对材料寿命进行了分析。     

变结构系统的递阶切换模式

 本文研究关于线性多变量变结构系统的递阶切换模式及其切换函数c与变结构控制u（x,s）的设计问题。文中提出了两种递阶一切换模式，并按模式的到达条件及对滑动模态的极点配置的原则给出了各种情况下切换函数及变结构控制的设计方法。此种模式的最大优点是系统的控制容许失误。