Perturbation Analysis for Robust Damage Detection with Application to Multifunctional Aircraft Structures

The most widely known form of multifunctional aircraft structure is smart structures for structural health monitoring (SHM). The aim is to provide automated systems whose purposes are to identify and to characterize possible damage within structures by using a network of actuators and sensors. Unfortunately, environmental and operational variability render many of the proposed damage detection methods difficult to successfully be applied. In this paper, an original robust damage detection approach using output-only vibration data is proposed. It is based on independent component analysis and matrix perturbation analysis, where an analytical threshold is proposed to get rid of statistical assumptions usually performed in damage detection approach. The effectiveness of the proposed SHM method is demonstrated numerically using finite element simulations and experimentally through a conformal load-bearing antenna structure and composite plates instrumented with piezoelectric ceramic materials.FUI MSIE (Pole Astech

Principal component analysis and perturbation theory–based robust damage detection of multifunctional aircraft structure

A fundamental problem in structural damage detection is to define an efficient feature to calculate a damage index. Furthermore, due to perturbations from various sources, we also need to define a rigorous threshold whose overtaking indicates the presence of damages. In this article, we develop a robust damage detection methodology based on principal component analysis. We first present an original damage index based on projection of the separation matrix, and then, we drive a novel adaptive threshold that does not rely on statistical assumptions. This threshold is analytic, and it is based on matrix perturbation theory. The efficiency of the method is illustrated using simulations of a composite smart structure and experimental results performed on a conformal load-bearing antenna structure laboratory test

Nonlinear structural damage detection based on cascade of Hammerstein models

Structural damages can result in nonlinear dynamical signatures that can significantly enhance their detection. An original nonlinear damage detection approach is proposed that is based on a cascade of Hammerstein models representation of the structure. This model is estimated by means of the Exponential Sine Sweep Method from only one measurement. On the basis of this estimated model, the linear and nonlinear parts of the output are estimated, and two damage indexes (DIs) are proposed. The first DI is built as the ratio of the energy contained in the nonlinear part of an output versus the energy contained in its linear part. The second DI is the angle between the subspaces obtained from the nonlinear parts of two set of outputs after a principal component analysis. The sensitivity of the proposed DIs to the presence of damages as well as their robustness to noise are assessed numerically on spring-mass-damper structures and experimentally on actual composite plates with surface-mounted PZT-elements. Results demonstrate the effectiveness of the proposed method to detect a damage in nonlinear structures and in the presence of noise

Detection of structural damage using the exponential sine sweep method

Structural damages can result in nonlinear dynamical responses. Thus, estimating the nonlinearities generated by damages potentially allows detecting them. In this paper, an original approach called the ES2D (Exponential Sine Sweep Damage Detection) is proposed for nonlinear damage detection. This approach is based on a damage index that reflects the ratio of the energy contained in the nonlinear part of the output versus the energy contained in its linear part. For this, we suppose that the system under study can be modeled as a cascade of Hammerstein models, made of N branches in parallel composed of an elevation to the nth power followed by a linear filter called the nth order kernel. The Exponential Sine Sweep Method (ESSM) is then used to identify the linear and nonlinear parts of the model. Exponential sine sweeps are a class of sine sweeps that allow estimating a system’s first kernels in a wide frequency band from only one measurement. The ES2D method is illustrated experimentally on two actual composite plates with surface-mounted PZT-elements: one healthy and one damaged (impact). A given propagation path between a sensor and an actuator in the system is here under investigation. Using the ESSM, the first kernels modeling this propagation path are estimated for both the damaged and undamaged states. On the basis of these estimated first Kernels, the damage index is built. Its detecting efficiency and its insensitivity to environmental noise are then assessed

Contrôle santé des structures composites : approche expérimentale et statistique

The aviation industry uses materials always more effective for its aircraft and space systems. The aircraft are equipped with antenna arrays to make communications. Our thesis falls within the MSIE project (Matériaux et Structures Intelligentes pour l'Electromagnétisme). The objective of this project is to meet the demands of the aviation industry, to evaluate the concept of new materials that enable the realization of compact and reconfigurable antenna composite structures. This adaptability assumes that these structures are also equipped with sensors/actuators able to perform an active control. It then necessary to add to these future structures a Structural Health Monitoring systems (SHM) to detect possible damage (impact, delamination between the host structure and the antenna array, fiber breakage, etc...), which may occur during the flight or during the aging of the structure. The development of the SHM systems is the core of our thesis. For this purpose, we have built experimental tests that took into account the industrial requirements. These experimental tests include antenna composite structures equipped with piezoelectric sensors and actuators. Through the information received from the sensors, we developed two damage detection methodologies, based on Principal Component Analysis (PCA) and Independent Component Analysis (ICA). These methods are statistical approaches, which have the particularity of not requiring any knowledge of the mechanical model of the structure to be monitored. These two methods are a way to extract features from the piezoelectric sensors of the structure in a healthy and in an unknown state. The comparison between these characteristics allowed us to calculate for each method, a damage index. Furthermore, to robustify the decision, we have associated to this damage index, a bound that decides if the structure is in healthy or damaged state. We have successfully applied the two methods to detect damage in antenna composite structures, namely: impact, delamination of the composite structures.L'industrie aéronautique utilise des matériaux toujours plus performants pour ses avions et systèmes spatiaux. Ainsi, pour réaliser les communications, les avionneurs souhaiteraient aller vers une réelle intégration des structures antennaires à la structure de l'avion et donc de passer de la structure antennaire vue comme équipement embarqué à la structure antennaire devenue équipement intégré. Notre travail de thèse se situe dans le cadre du projet MSIE (Matériaux et Structures Intelligentes pour l'Electromagnétisme). L'objectif de ce projet est de répondre aux demandes du secteur aéronautique, en évaluant le concept de nouveaux matériaux susceptibles de permettre la réalisation de structures antennaires conformées, compactes et reconfigurables. Cette adaptabilité suppose que ces structures soient reconfigurables et donc capables, une fois munies de capteurs/actionneurs, de réaliser un contrôle actif de la directivité, du rendement et du gain des structures antennaires. Il est alors apparu nécessaire d'adjoindre à ces futures structures, une fonction de Contrôle santé ou Structural Health Monitoring "SHM", de manière à pouvoir détecter d'éventuels endommagements (impact, délaminage entre le réseau d'antennes et la structure composite, rupture des fibres, etc....) susceptibles de se produire au cours du vol ou au cours du vieillissement de la structure. C'est dans le développement de la fonction SHM que s'inscrit ce travail de thèse. A cet effet, nous avons réalisé des dispositifs expérimentaux en tenant compte des demandes de l'industriel. Ces dispositifs comportent des structures composites antennaires munies de capteurs et d'actionneurs piézoélectriques. A travers les informations transmises par les capteurs, nous avons développé deux méthodes de détection de l'endommagement à base d'Analyse en Composantes Principales (ACP) et d'Analyse en Composantes Indépendantes (ACI). Ces deux méthodes sont des approches statistiques qui ne nécessitent pas la connaissance du modèle mécanique de la structure à surveiller. Il s'agit de méthodes traitant des observations vectorielles (multivariées) transmises par les capteurs piézoélectriques, afin d'en extraire des caractéristiques de fonctionnement de la structure à l'état sain et de la structure dans un état inconnu. La comparaison entre ces caractéristiques nous a permis de calculer pour chacune des deux méthodes, un résidu indicateur d'endommagement. Nous avons complété ce résidu par une robustification de la prise de décision et cela par le calcul d'une borne, au-delà de laquelle l'endommagement est détecté

Contrôle santé des structures composites

L'industrie aéronautique utilise des matériaux toujours plus performants pour ses avions et systèmes spatiaux. Ainsi, pour réaliser les communications, les avionneurs souhaiteraient aller vers une réelle intégration des structures antennaires à la structure de l'avion et donc de passer de la structure antennaire vue comme équipement embarqué à la structure antennaire devenue équipement intégré. Notre travail de thèse se situe dans le cadre du projet MSIE (Matériaux et Structures Intelligentes pour l'Electromagnétisme). L'objectif de ce projet est de répondre aux demandes du secteur aéronautique, en évaluant le concept de nouveaux matériaux susceptibles de permettre la réalisation de structures antennaires conformées, compactes et reconfigurables. Cette adaptabilité suppose que ces structures soient reconfigurables et donc capables, une fois munies de capteurs/actionneurs, de réaliser un contrôle actif de la directivité, du rendement et du gain des structures antennaires. Il est alors apparu nécessaire d'adjoindre à ces futures structures, une fonction de Contrôle santé ou Structural Health Monitoring "SHM", de manière à pouvoir détecter d'éventuels endommagements (impact, délaminage entre le réseau d'antennes et la structure composite, rupture des fibres, etc....) susceptibles de se produire au cours du vol ou au cours du vieillissement de la structure. C'est dans le développement de la fonction SHM que s'inscrit ce travail de thèse. A cet effet, nous avons réalisé des dispositifs expérimentaux en tenant compte des demandes de l'industriel. Ces dispositifs comportent des structures composites antennaires munies de capteurs et d'actionneurs piézoélectriques. A travers les informations transmises par les capteurs, nous avons développé deux méthodes de détection de l'endommagement à base d'Analyse en Composantes Principales (ACP) et d'Analyse en Composantes Indépendantes (ACI). Ces deux méthodes sont des approches statistiques qui ne nécessitent pas la connaissance du modèle mécanique de la structure à surveiller. Il s'agit de méthodes traitant des observations vectorielles (multivariées) transmises par les capteurs piézoélectriques, afin d'en extraire des caractéristiques de fonctionnement de la structure à l'état sain et de la structure dans un état inconnu. La comparaison entre ces caractéristiques nous a permis de calculer pour chacune des deux méthodes, un résidu indicateur d'endommagement. Nous avons complété ce résidu par une robustification de la prise de décision et cela par le calcul d'une borne, au-delà de laquelle l'endommagement est détecté.The aviation industry uses materials always more effective for its aircraft and space systems. The aircraft are equipped with antenna arrays to make communications. Our thesis falls within the MSIE project (Matériaux et Structures Intelligentes pour l'Electromagnétisme). The objective of this project is to meet the demands of the aviation industry, to evaluate the concept of new materials that enable the realization of compact and reconfigurable antenna composite structures. This adaptability assumes that these structures are also equipped with sensors/actuators able to perform an active control. It then necessary to add to these future structures a Structural Health Monitoring systems (SHM) to detect possible damage (impact, delamination between the host structure and the antenna array, fiber breakage, etc...), which may occur during the flight or during the aging of the structure. The development of the SHM systems is the core of our thesis. For this purpose, we have built experimental tests that took into account the industrial requirements. These experimental tests include antenna composite structures equipped with piezoelectric sensors and actuators. Through the information received from the sensors, we developed two damage detection methodologies, based on Principal Component Analysis (PCA) and Independent Component Analysis (ICA). These methods are statistical approaches, which have the particularity of not requiring any knowledge of the mechanical model of the structure to be monitored. These two methods are a way to extract features from the piezoelectric sensors of the structure in a healthy and in an unknown state. The comparison between these characteristics allowed us to calculate for each method, a damage index. Furthermore, to robustify the decision, we have associated to this damage index, a bound that decides if the structure is in healthy or damaged state. We have successfully applied the two methods to detect damage in antenna composite structures, namely: impact, delamination of the composite structures.PARIS-Arts et Métiers (751132303) / SudocSudocFranceF

Detection of structural damage using the exponential sine sweep method

International audienceStructural damages can result in nonlinear dynamical responses. Thus, estimating the nonlinearities generated by damages potentially allows detecting them. In this paper, an original approach called the ES2D (Exponential Sine Sweep Damage Detection) is proposed for nonlinear damage detection. This approach is based on a damage index that reflects the ratio of the energy contained in the nonlinear part of the output versus the energy contained in its linear part. For this, we suppose that the system under study can be modeled as a cascade of Hammerstein models, made of N branches in parallel composed of an elevation to the nth power followed by a linear filter called the nth order kernel. The Exponential Sine Sweep Method (ESSM) is then used to identify the linear and nonlinear parts of the model. Exponential sine sweeps are a class of sine sweeps that allow estimating a system's first kernels in a wide frequency band from only one measurement. The ES2D method is illustrated experimentally on two actual composite plates with surface-mounted PZT-elements: one healthy and one damaged (impact). A given propagation path between a sensor and an actuator in the system is here under investigation. Using the ESSM, the first kernels modeling this propagation path are estimated for both the damaged and undamaged states. On the basis of these estimated first Kernels, the damage index is built. Its detecting efficiency and its insensitivity to environmental noise are then assessed

Active Damage Detection and Localization Applied to Composite Structure Using Piezoceramic Patches

8 pagesInternational audienceThis paper describes the application of an active structural health monitoring technique for a composite plate bonded with a distributed piezoceramic patches array. An optimal placement of these patches has been proposed using grammians of controllability and observability and the H∞ modal norm. The proposed approach was established via finite element modelization (FE) of the composite structure. With this optimal placement, an active structural health monitoring scheme has been accomplished. Therefore, using spatial information given by the distributed sensors, we propose two damage indices (DI). These indices are able to detect and localize damages. The first DI is based upon non-parametric frequency response function estimates; the damage is detectable when changes in the estimates exceed their normal statistical bounds. The second DI uses change in the energy signal sensor to localize damage existing in the composite structure. The efficiency of the proposed approach is demonstrated through experimental tests