This work is an experimental study of applying an impedance-based health monitoring technique to complex structures. The work is presented in three parts. In the first part we consider effects of the following three factors on damage detection abilities: actuator excitation level, test wire length and ambient conditions (temperature, structural loading and vibration). It was concluded that increasing the applied voltage improves the signal to noise ratio and damage detection abilities. Test wire lengths under 30m do not affect damage detection abilities. The technique is able to distinguish and detect damage even with variations in temperature, structural loading and vibration. In the second part we apply our health monitoring technique to a complex truss structure and a massive steel steam header. We discovered that with multiplexing (acquiring a single signal from distributed actuators) the actuators on the truss structure we could detect damage but with less location information. Damage detection on the steel pipe ended in inconclusive results. The use of this technique on massive structures needs further investigation. Finally, we conducted a detailed experimental study of monitoring the integrity of composite-reinforced masonry structures. We developed a software package which enables even a casual user to determine if significant damage has occurred in these structures. The technique was successfully applied to detect damage (particularly due to delamination) in these composite-concrete structures. Most significantly, the technique was also able to detect damage well in advance of actual failure. This work relies mainly on frequency response plots and damage metric charts to present the data and to arrive at any conclusions. While frequency response plots give a qualitative approach to the analysis, damage metric charts attempt to quantify the data. / Master of Science

In this report, a novel smart nanocantilever with self-deflection sensor using embedded piezo-resistor and self-actuation using integrated piezo-electric actuator is proposed, designed and simulated to enable highly sensitive label free biosensor and ultra-short cantilever probe for AFM applications. The smart nanocantilever comprises of a triangular Si3N4 nanocantilever (10µm long, 400nm width and 100nm thickness) connected to a multi-layer support structure (Si3N4 (100nm)/PZT (100nm)) having n-type silicon piezo resistor (7µm long ,2µm width and 20nm thickness) embedded in the Si3N4 layer in both the support structure and nanocantilever. The nanocantilever is designed to maximize the resonance frequency and lower spring constant whereas piezoelectric actuator and piezo resistor is designed to maximize excitation and maximize change in resistance of nanocantilever respectively. The results show that the nanocantilever enhances sensitivity in static mode by factor of 36.5 while in dynamic mode by a factor of 658 for AFM application. For biosensor application, the nanocantilever enhanced the sensitivity in static and dynamic mode by factors of 5.6 and 13.8, respectively. / I denna rapport presenteras en ny, smart nano-kantilever med självdetektion via sensorer som använder inbäddade piezoresistorer, och självpådrivning via integrerade piezoelektriska pådrivare. Dessa är designade och simulerade för att möjliggöra högsensitiva titelfria biosensorer och ultrakorta kantilever-prober för AFM-applikation. Den smarta nano-kantilevern består av en triangulär Si3N4 nano-kantilever (10µm lång, 400nm bred and 100nm djup) kopplad till en stödstruktur med flera lager (Si3N4 (100nm)/PZT (100nm)) och med en n-typ silikon piezoresistor (7µm lång ,2µm bred and 20nm djup) inbäddad i Si3N4 – lagret i både stödstrukturen och i nano-kantilevern. Denna är designad för att maximera resonansfrekvens och sänka fjädringskonstanten, medan den piezo-elektriska pådrivaren och piezo-resistorn är designade för att maximera excitering samt resistansändring för nano-kantilevern. Resultatet i denna rapport visar att nano-kantilevern förstärker känslighet i statiskt läge med en faktor på 36,5, med motsvarande faktor på 658 i dynamiskt läge för AMF- applikation. För biosenor-applikation förstärkte nano-kantilevern känsligheten i statiskt och dynamiskt läge med 5,6 och 13,8 respektive.

The dissertation focuses on one of the major research needs in the area of adaptive /intelligent/smart structures, the development and application of finite element analysis and genetic algorithms for optimal design of large-scale adaptive structures. We first review some basic concepts in finite element method and genetic algorithms, along with the research on smart structures. Then we propose a solution methodology for solving a critical problem in the design of a next generation of large-scale adaptive structures -- optimal placements of a large number of actuators to control thermal deformations. After briefly reviewing the three most frequently used general approaches to derive a finite element formulation, the dissertation presents techniques associated with general shell finite element analysis using flat triangular laminated composite elements. The element used here has three nodes and eighteen degrees of freedom and is obtained by combining a triangular membrane element and a triangular plate bending element. The element includes the coupling effect between membrane deformation and bending deformation. The membrane element is derived from the linear strain triangular element using Cook's transformation. The discrete Kirchhoff triangular (DKT) element is used as the plate bending element. For completeness, a complete derivation of the DKT is presented. Geometrically nonlinear finite element formulation is derived for the analysis of adaptive structures under the combined thermal and electrical loads. Next, we solve the optimization problems of placing a large number of piezoelectric actuators to control thermal distortions in a large mirror in the presence of four different thermal loads. We then extend this to a multi-objective optimization problem of determining only one set of piezoelectric actuator locations that can be used to control the deformation in the same mirror under the action of any one of the four thermal loads. A series of genetic algorithms, GA Version 1, 2 and 3, were developed to find the optimal locations of piezoelectric actuators from the order of 10<SUP>21</SUP> ~ 10<SUP>56</SUP> candidate placements. Introducing a variable population approach, we improve the flexibility of selection operation in genetic algorithms. Incorporating mutation and hill climbing into micro-genetic algorithms, we are able to develop a more efficient genetic algorithm. Through extensive numerical experiments, we find that the design search space for the optimal placements of a large number of actuators is highly multi-modal and that the most distinct nature of genetic algorithms is their robustness. They give results that are random but with only a slight variability. The genetic algorithms can be used to get adequate solution using a limited number of evaluations. To get the highest quality solution, multiple runs including different random seed generators are necessary. The investigation time can be significantly reduced using a very coarse grain parallel computing. Overall, the methodology of using finite element analysis and genetic algorithm optimization provides a robust solution approach for the challenging problem of optimal placements of a large number of actuators in the design of next generation of adaptive structures. / Ph. D.

La thèse porte de manière générale sur les polymères électrostrictifs qui peuvent être utilisés soit comme actionneurs électromécaniques souples, soit comme capteurs ou récupérateurs d’énergie. Le premier chapitre est une introduction générale aux systèmes couplés électromécaniques. Le choix des matériaux est exposé et porte sur les élastomères diélectriques et les polyuréthanes (PU) chargés par des nanoparticules conductrices de noir de carbone (CB). Le second chapitre porte sur la réalisation des films. Des particules de CB sous forme de micelles préformées et une technique « solution-cast » sont employées dans cette optique. Ce procédé permet une bonne dispersion des charges. Une amélioration de la déformation d’un facteur 1,6 est obtenue par introduction de particules de CB à 0.89 vol%. Le troisième chapitre présente la modélisation de phénomènes comme la saturation de la polarisation qui implique directement une saturation de la déformation. En modélisant la polarisation comme une fonction non-linéaire dépendant de deux variables (la permittivité bas niveau et un champ de saturation), on décrit ainsi correctement plusieurs phénomènes qui ne peuvent être interprétés par une approche linéaire et homogène. Les simulations effectuées montrent une bonne corrélation avec les expérimentations menées. Le quatrième chapitre propose une comparaison entre les films PU purs et chargés. Cette analyse porte non seulement sur des mesures mécaniques et électriques mais également en XRD ou en DSC afin de détecter le niveau de cristallisation. Une dispersion importante a ainsi été observée visuellement. Des déformations de l’ordre de 50 % ont ainsi été obtenues. Le cinquième chapitre porte sur l’effet lié à l’injection de charges électriques par bombardement électronique (HEBI), sur la déformation électrostrictive. Une telle approche permet ainsi un gain d’un facteur de l’ordre de 2 sur la déformation et semble réduire les pertes de façon très conséquente. / In a general manner, the present thesis focuses on electrostrictive polymers which can be used either as flexible electromechanical actuators or as sensors or energy harvesters. Chapter 1 is a general introduction to electro-mechanical coupled systems. The choice of the materials is described and focuses on dielectric elastomers, polyurethane (PU) with conductive carbon black (CB) nano-particle fillers. Chapter 2 focuses on the film synthesis. CB nano-particles in the form of micelles and solution cast method were employed to provide good filler dispersion. The strain enhancement of a factor of 1.6 was obtained by 0.89 vol% CB doping. Chapter 3 exposes the modeling of electrostrictive actuation and in particular the saturation of the polarization. By modeling the polarization as a nonlinear function depending on two variables (low-level permittivity and saturation field), it is therefore possible to describe several phenomena that cannot be explained by a classical linear and homogeneous approach. Simulations performed using such an approach show a good agreement with experimental results. Chapter 4 presents the comparison between pure PU and composite films. It includes mechanical/electrical characterization as well as XRD or DSC measurements to detect the crystallization level. High dispersion level was visually confirmed. Strains of the order of 50 % were reached. Chapter 5 deals with the effect of electric charge injection by homogeneous electron beam irradiation (HEBI) on the electrostrictive strain. This technique therefore permits a gain of 2 on the obtained strain and seems to significantly reduce the losses in the material as well.

As estruturas aeronáuticas estão sujeitas a uma variedade de fenômenos aeroelásticos que podem comprometer o desempenho das aeronaves. Com o desenvolvimento de novos materiais, essas estruturas têm se tornado mais leves e flexíveis, e portanto mais sujeitas a problemas aeroelásticos, tais como flutter e buffeting. Pesquisadores têm trabalhado em soluções alternativas para resolver esses problemas aeroelásticos indesejáveis. Uma dessas soluções envolve o conceito de estruturas inteligentes, que são aquelas que apresentam atuadores e sensores incorporados, integrado com sistema de controle e processamento de sinal, possibilitando a adaptação do sistema estrutural a mudanças nas condições operacionais. Modelos matemáticos que incorporam elementos atuadores e sensores são de grande importância nas fases preliminares de análise de estruturas aeronáuticas inteligentes. Neste contexto, métodos de modelagem são necessários para capturar a ação da dinâmica estrutural e de carga aerodinâmica. O presente trabalho apresenta o estudo de um controlador difuso ativo para resposta aeroelástica de uma asa inteligente com atuadores piezelétricos incorporados. Características não-lineares da resposta aeroelástica são analisadas para condições críticas de flutter. É utilizado o método de elementos finitos para o modelo estrutural não-linear e o método de malha de vórtices para o modelo aerodinâmico não-estacionário. / Aeronautical structures are submitted to a variety of aeroelastic phenomena that may compromise its performance. With this development of new materials, aeronautical structures have become lighter, more flexible, and more subjected to aeroelastic problems, such as flutter and buffeting. Researchers have been working on alternatives to solve these undesired aeroelastic problems, as the recent concept of smart or intelligent structures. Smart structures are those that present embedded sensors and actuators, integrated with control systems and signal processing, to enable the adaptation of the structural system to changes in the operational conditions. Mathematical models that incorporate actuator elements or sensors are of great importance in preliminary phases of analysis of smart aeronautical structures. In this context, modeling methods are necessary to capture dynamic-structural behavior and unsteady aerodynamic loading. The present work is the study of an active fuzzy controller for aeroelastic response of a smart wing with embedded piezoelectric actuators. Nonlinear characteristics of aeroelastic responses are analyzed for critical flutter conditions. The finite elements method for the nonlinear structural model and vortex-lattice method for the unsteady aerodynamic model has been used.

This thesis represents the work that has been done by the author in the area of vibration analysis and control of smart structures during his PhD candidature. The research was concentrated on flexible structures, using piezoelectric materials as actuators and sensors. The thesis consists of four major parts. The first part (Chapter 2) is the modelling of piezoelectric laminate structures using modal analysis and finite element methods. The second part (Chapter 4) involves the model correction of pointwise and spatial models of resonant systems. The model correction solution compensates for the errors associated with the truncation of high frequency modes. The third part (Chapter 5) is the optimal placement methodology for general actuators and sensors. In particular, optimal placement of piezoelectric actuators and sensors over a thin plate are considered and implemented in the laboratory. The last part (Chapters 6 to 8) deals with vibration control of smart structures. Several different approaches for vibration control are considered. Vibration control using resonant, spatial H-2 and H-infinity control is proposed and implemented on real systems experimentally. It is possible, for certain modes, to obtain the very satisfactory result of up to 30 dB vibration reduction. / PhD Doctorate

Conformal airborne antennas have several advantages compared to externally mounted antennas, and they will play an important role in future aircrafts. However, they are subjected to vibration induced deformations which degrade their electromagnetic performances. With the motivation of suppressing such vibrations, use of active vibration control techniques with piezoelectric actuators is investigated in this study. At first, it is aimed to control the first three bending modes of a cantilever beam. In this scope, four different modal controllers / positive position feedback (PPF), resonant control (RC), integral resonant control (IRC) and positive position feedback with feed-through (PPFFT) are designed based on both reduced order finite element model and the system identification model. PPFFT, is a modified version of PPF which is proposed as a new controller in this study. Results of real- time control experiments show that PPFFT presents superior performance compared to its predecessor, PPF, and other two methods. In the second part of the study, it is focused on controlling the first three modes of a rectangular plate with four clamped edges. Best location alternatives for three piezoelectric actuators are determined with modal strain energy method. Based on the reduced order finite element model, three PPFFT controllers are designed for three collocated transfer functions. Disturbance rejection performances show the convenience of PPFFT in multi-input multi-output control systems. Performance of the control system is also verified by discrete-time simulations for a random disturbance representing the in-flight aircraft vibration characteristics.

A novel combined piezoelectric-composite actuator configuration is proposed and analytically modeled in this work. The actuator is a low complexity, active compliant mechanism obtained by coupling a modified star cross sectional configuration composite beam with a helicoidal bimorph piezoelectric actuator coiled around it. This novel actuator is a good candidate as a hinge tension-torsion bar actuator for a helicopter rotor blade flap or blade tip and mirror rotational positioning. In the wing tip case, the tip deflection angle is different only according to the aerodynamic moment depending on the hinge position of the actuator along the chord and applied voltage because there is no centrifugal force. For an active blade tip subject to incompressible flow and 2D quasi steady airloads, its twist angle is related not only to aerodynamic moment and applied voltage but also to coupling terms, such as the trapeze effect and the tennis racquet effect. Results show the benefit of hinge position aft of the aerodynamic center, such that the blade tip response is amplified by airloads. Contrary to this effect, results also show that the centrifugal effects and inertial effect cause an amplitude reduction in the response. Summation of these effects determines the overall blade tip response. The results for a certain hinge position of Xh=1.5% chord aft of the quarter chord point proves that the tip deflection target design range[-2,+2] can be achieved for all pitch angle configurations chosen.

No description available.

Flexible structures are increasingly used in various applications such as aerospace, automotive and so on. Since they are lightly damped and susceptible to vibrations, active vibration control is desirable. In practice, in addition to achieving effective vibration reduction, we have also to consider the required control energy to avoid the energy insufficiency, the control input to avoid control saturation and reduce the effects of measurement noises. On the other hand, as flexible structures have infinite number of resonant modes and only the first few can be employed in the system modeling and the controller design, there always exist neglected high-frequency dynamics, which can induce the spillover instability. Furthermore, the parametric uncertainties on modal parameters can degrade the control performances and even destabilize the closed-loop system. In this context, a quantitative robust control methodology for active vibration control of flexible structure is proposed in this thesis. Phase and gain control polices are first proposed to enforce frequency-dependent phase and gain requirements on the controller, which can be realized by the output feedback H1 control design. The phase and gain control polices based H1 control can make a trade-off among the complete set of control objectives and offer a qualitative robust controller. Especially, the LPV H1 control is used to reduce the required control energy for LPV systems. The generalized polynomial chaos (gPC) framework with finite element analysis is employed for uncertainty quantification. It allows us to investigate the effects of structural property uncertainties on natural frequencies and achieve their probabilistic information. Then, in the presence of parametric and dynamic uncertainties, µ / v analysis and the random algorithm using Monte Carlo Method are used to quantitatively ensure the closed-loop stability and performance robustness properties both in deterministic and probabilistic senses. The proposed quantitative robust control methodology is thus developed by employing various techniques from automatic control and mechanical engineering, thus reducing the gap between them for robust vibration control of flexible structures. Its effectiveness are verified by numerical simulations and experimental validation on LTI and LPV non-collocated piezoelectric cantilever beams.