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Prof. Dr. Carlos E S Cesnik
Department of Aerospace Engineering, University of Michigan, FXB 1320 Beal Avenue, Ann Arbor, MI 48109, USA

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0 Structural Dynamics
0 Structural Mechanics
0 Aeroservoelasticity
0 Model reduction
0 Computational and experimental aeroelasticity

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Structural Dynamics

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Research article
Published: 21 January 2021 in Journal of Fluids and Structures
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High-performance flutter and post-flutter predictions are critical in the design of a vast range of nonlinear fluid-structural systems. However, these predictions are often unfeasible due to their high computational cost. Moreover, traditional methods for flutter and post-flutter predictions are model intrusive and limited to one varying parameter at a time. To address these shortcomings, this paper introduces a novel output-based method for forecasting flutter bifurcations and post-flutter dynamics in nonlinear fluid-structural systems with multiple varying parameters. The proposed method uses only output data from a handful of transient responses in the pre-flutter regime to predict the flutter boundary and a range of the bifurcation diagram. The method is demonstrated in analytical systems where the predicted bifurcation diagrams match the exact solutions. Next, the method is applied to a geometrically nonlinear wing considering variations in the flow speed and torsion stiffness. The predicted bifurcation diagrams closely agree with time-marching solutions despite the proposed method requires only a handful of transient calculations. These results show that the proposed method enables computationally efficient and accurate output-based flutter bifurcation forecasting in nonlinear fluid-structural systems with multiple varying parameters.

ACS Style

Cristina Riso; Carlos E.S. Cesnik; Bogdan I. Epureanu. Output-based flutter bifurcation forecasting in nonlinear fluid-structural systems with multiple varying parameters. Journal of Fluids and Structures 2021, 101, 103201 .

AMA Style

Cristina Riso, Carlos E.S. Cesnik, Bogdan I. Epureanu. Output-based flutter bifurcation forecasting in nonlinear fluid-structural systems with multiple varying parameters. Journal of Fluids and Structures. 2021; 101 ():103201.

Chicago/Turabian Style

Cristina Riso; Carlos E.S. Cesnik; Bogdan I. Epureanu. 2021. "Output-based flutter bifurcation forecasting in nonlinear fluid-structural systems with multiple varying parameters." Journal of Fluids and Structures 101, no. : 103201.

Book chapter
Published: 06 December 2017 in Wear in Advanced Engineering Applications and Materials
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This chapter presents an efficient modeling technique for guided wave propagation in composite structures using a finite difference based numerical scheme — the Local Interaction Simulation Approach (LISA). It starts with an introduction to fundamentals of multimodal dispersive guided waves, the challenges associated with guided wave based Structural Health Monitoring (SHM) techniques in composite structures, and corresponding state-of-the-art modeling strategies. The chapter then describes the LISA formulation derivation from the elastodynamic wave equations considering general anisotropic material properties. Kelvin-Voigt viscoelastic model is integrated to handle the damping effects. The UM-LISA software framework and its implementation with Compute Unified Device Architecture (CUDA) are then discussed. The Absorbing Layers with Increasing Damping (ALID) boundary model is added to the framework to minimize model size and reduce the computational burden in simulations. A case study of ultrasonic guided wave generation and propagation in a highly anisotropic unidirectional composite plate and experimental verification using Scanning Laser Doppler Vibrometry highlight the quality and prowess of the method. Modeling of guided wave propagation in complex-geometry composite panel with stiffeners is presented at the end of the chapter as an example of the applicability of the new technique in practical structural configurations.

ACS Style

Yanfeng Shen; Carlos E. S. Cesnik; M H Ferri Aliabadi; Z Sharif Khodaei. Modeling Guided Wave Propagation in Composite Structures Using Local Interaction Simulation Approach. Wear in Advanced Engineering Applications and Materials 2017, 8, 47 -91.

AMA Style

Yanfeng Shen, Carlos E. S. Cesnik, M H Ferri Aliabadi, Z Sharif Khodaei. Modeling Guided Wave Propagation in Composite Structures Using Local Interaction Simulation Approach. Wear in Advanced Engineering Applications and Materials. 2017; 8 ():47-91.

Chicago/Turabian Style

Yanfeng Shen; Carlos E. S. Cesnik; M H Ferri Aliabadi; Z Sharif Khodaei. 2017. "Modeling Guided Wave Propagation in Composite Structures Using Local Interaction Simulation Approach." Wear in Advanced Engineering Applications and Materials 8, no. : 47-91.

Journal article
Published: 01 February 2017 in Ultrasonics
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This article presents a parallel algorithm to model the nonlinear dynamic interactions between ultrasonic guided waves and fatigue cracks. The Local Interaction Simulation Approach (LISA) is further developed to capture the contact-impact clapping phenomena during the wave crack interactions based on the penalty method. Initial opening and closure distributions are considered to approximate the 3-D rough crack microscopic features. A Coulomb friction model is integrated to capture the stick-slip contact motions between the crack surfaces. The LISA procedure is parallelized via the Compute Unified Device Architecture (CUDA), which enables parallel computing on powerful graphic cards. The explicit contact formulation, the parallel algorithm, as well as the GPU-based implementation facilitate LISA's high computational efficiency over the conventional finite element method (FEM). This article starts with the theoretical formulation and numerical implementation of the proposed algorithm, followed by the solution behavior study and numerical verification against a commercial finite element code. Numerical case studies are conducted on Lamb wave interactions with fatigue cracks. Several nonlinear ultrasonic phenomena are addressed. The classical nonlinear higher harmonic and DC response are successfully captured. The nonlinear mode conversion at a through-thickness and a half-thickness fatigue crack is investigated. Threshold behaviors, induced by initial openings and closures of rough crack surfaces, are depicted by the proposed contact LISA model.

ACS Style

Yanfeng Shen; Carlos E.S. Cesnik. Modeling of nonlinear interactions between guided waves and fatigue cracks using local interaction simulation approach. Ultrasonics 2017, 74, 106 -123.

AMA Style

Yanfeng Shen, Carlos E.S. Cesnik. Modeling of nonlinear interactions between guided waves and fatigue cracks using local interaction simulation approach. Ultrasonics. 2017; 74 ():106-123.

Chicago/Turabian Style

Yanfeng Shen; Carlos E.S. Cesnik. 2017. "Modeling of nonlinear interactions between guided waves and fatigue cracks using local interaction simulation approach." Ultrasonics 74, no. : 106-123.

Journal article
Published: 09 August 2016 in Smart Materials and Structures
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This paper presents a new hybrid modeling technique for the efficient simulation of guided wave generation, propagation, and interaction with damage in complex composite structures. A local finite element model is deployed to capture the piezoelectric effects and actuation dynamics of the transmitter, while the global domain wave propagation and interaction with structural complexity (structure features and damage) are solved utilizing a local interaction simulation approach (LISA). This hybrid approach allows the accurate modeling of the local dynamics of the transducers and keeping the LISA formulation in an explicit format, which facilitates its readiness for parallel computing. The global LISA framework was extended through the 3D Kelvin–Voigt viscoelasticity theory to include anisotropic damping effects for composite structures, as an improvement over the existing LISA formulation. The global LISA framework was implemented using the compute unified device architecture running on graphic processing units. A commercial preprocessor is integrated seamlessly with the computational framework for grid generation and material property allocation to handle complex structures. The excitability and damping effects are successfully captured by this hybrid model, with experimental validation using the scanning laser doppler vibrometry. To demonstrate the capability of our hybrid approach for complex structures, guided wave propagation and interaction with a delamination in a composite panel with stiffeners is presented.

ACS Style

Yanfeng Shen; Carlos E S Cesnik. Hybrid local FEM/global LISA modeling of damped guided wave propagation in complex composite structures. Smart Materials and Structures 2016, 25, 095021 .

AMA Style

Yanfeng Shen, Carlos E S Cesnik. Hybrid local FEM/global LISA modeling of damped guided wave propagation in complex composite structures. Smart Materials and Structures. 2016; 25 (9):095021.

Chicago/Turabian Style

Yanfeng Shen; Carlos E S Cesnik. 2016. "Hybrid local FEM/global LISA modeling of damped guided wave propagation in complex composite structures." Smart Materials and Structures 25, no. 9: 095021.

Journal article
Published: 01 July 2015 in The Aeronautical Journal
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An experimental, remotely-piloted aircraft has been designed and fabricated at University of Michigan that is aeroelastically representative of very flexible aircraft. Known as X-HALE, this Experimental High-Altitude Long-Endurance aircraft exhibits geometrically nonlinear behaviour and displays specific aeroelastic characteristics designed into the experiment. This paper presents the data from the initial flight tests of the lightly instrumented X-HALE Risk Reduction Vehicle that confirm the expected aeroelastic characteristics. This opens the way for future flight tests with a fully-instrumented platform which will provide data to support validation of coupled, nonlinear aeroelastic/flight dynamic codes.

ACS Style

J. R. Jones; C. E. S. Cesnik. Preliminary flight test correlations of the X-HALE aeroelastic experiment. The Aeronautical Journal 2015, 119, 855 -870.

AMA Style

J. R. Jones, C. E. S. Cesnik. Preliminary flight test correlations of the X-HALE aeroelastic experiment. The Aeronautical Journal. 2015; 119 (1217):855-870.

Chicago/Turabian Style

J. R. Jones; C. E. S. Cesnik. 2015. "Preliminary flight test correlations of the X-HALE aeroelastic experiment." The Aeronautical Journal 119, no. 1217: 855-870.

Journal article
Published: 01 July 2015 in Journal of the American Helicopter Society
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ACS Style

Devesh Kumar; Carlos E. S. Cesnik. Corrigendum Performance Enhancement in Dynamic Stall Condition Using Active Camber Deformation. Journal of the American Helicopter Society 2015, 60, 1 -1.

AMA Style

Devesh Kumar, Carlos E. S. Cesnik. Corrigendum Performance Enhancement in Dynamic Stall Condition Using Active Camber Deformation. Journal of the American Helicopter Society. 2015; 60 (3):1-1.

Chicago/Turabian Style

Devesh Kumar; Carlos E. S. Cesnik. 2015. "Corrigendum Performance Enhancement in Dynamic Stall Condition Using Active Camber Deformation." Journal of the American Helicopter Society 60, no. 3: 1-1.

Research article
Published: 27 May 2015 in Journal of Intelligent Material Systems and Structures
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This article presents the development of a mixed-variable optimization framework for the design of composite rotor blades with active flaps in order to maximize the control authority for vibration reduction. For the studies presented in this article, the amplitude of dynamic twist at the blade tip at 4/rev flap actuation frequency is used as the objective function, and it is shown that there is a direct correlation between the amplitude of dynamic twist and the vibration reduction authority of active flaps. The optimization framework developed includes Intelligent Cross-section Generator as the cross section and mesh generator, University of Michigan/Variational Asymptotic Beam Sectional Analysis for the cross-sectional analysis, and Rotorcraft Comprehensive Analysis System for the aeroelastic analysis of active rotor blades. The optimization problem is solved using a surrogate-based approach in combination with the efficient global optimization algorithm. The optimum results with both mixed and continuous design variables are obtained for three different spanwise locations of active flap.

ACS Style

Devesh Kumar; Carlos Es Cesnik. New strategy for designing composite rotor blades with active flaps. Journal of Intelligent Material Systems and Structures 2015, 27, 1176 -1188.

AMA Style

Devesh Kumar, Carlos Es Cesnik. New strategy for designing composite rotor blades with active flaps. Journal of Intelligent Material Systems and Structures. 2015; 27 (9):1176-1188.

Chicago/Turabian Style

Devesh Kumar; Carlos Es Cesnik. 2015. "New strategy for designing composite rotor blades with active flaps." Journal of Intelligent Material Systems and Structures 27, no. 9: 1176-1188.

Journal article
Published: 01 April 2015 in Journal of the American Helicopter Society
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ACS Style

Devesh Kumar; Carlos E. S. Cesnik. Performance Enhancement in Dynamic Stall Condition Using Active Camber Deformation. Journal of the American Helicopter Society 2015, 60, 1 -12.

AMA Style

Devesh Kumar, Carlos E. S. Cesnik. Performance Enhancement in Dynamic Stall Condition Using Active Camber Deformation. Journal of the American Helicopter Society. 2015; 60 (2):1-12.

Chicago/Turabian Style

Devesh Kumar; Carlos E. S. Cesnik. 2015. "Performance Enhancement in Dynamic Stall Condition Using Active Camber Deformation." Journal of the American Helicopter Society 60, no. 2: 1-12.

Conference paper
Published: 23 March 2015 in Health Monitoring of Structural and Biological Systems 2015
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This paper presents a hybrid modeling technique for the efficient simulation of guided wave propagation and interaction with damage in composite structures. This hybrid approach uses a local finite element model (FEM) to compute the excitability of guided waves generated by piezoelectric transducers, while the global domain wave propagation, wave-damage interaction, and boundary reflections are modeled with the local interaction simulation approach (LISA). A small-size multi-physics FEM with non-reflective boundaries (NRB) was built to obtain the excitability information of guided waves generated by the transmitter. Frequency-domain harmonic analysis was carried out to obtain the solution for all the frequencies of interest. Fourier and inverse Fourier transform and frequency domain convolution techniques are used to obtain the time domain 3-D displacement field underneath the transmitter under an arbitrary excitation. This 3-D displacement field is then fed into the highly efficient time domain LISA simulation module to compute guided wave propagation, interaction with damage, and reflections at structural boundaries. The damping effect of composite materials was considered in the modified LISA formulation. The grids for complex structures were generated using commercial FEM preprocessors and converted to LISA connectivity format. Parallelization of the global LISA solution was achieved through Compute Unified Design Architecture (CUDA) running on Graphical Processing Unit (GPU). The multi-physics local FEM can reliably capture the detailed dimensions and local dynamics of the piezoelectric transducers. The global domain LISA can accurately solve the 3-D elastodynamic wave equations in a highly efficient manner. By combining the local FEM with global LISA, the efficient and accurate simulation of guided wave structural health monitoring procedure is achieved. Two numerical case studies are presented: (1) wave propagation in a unidirectional CFRP composite plate; (2) wave propagation in a stiffened cross-ply CFRP plate with delamination.

ACS Style

Yanfeng Shen; Carlos E. S. Cesnik. Hybrid local FEM/global LISA modeling of guided wave propagation and interaction with damage in composite structures. Health Monitoring of Structural and Biological Systems 2015 2015, 9438, 94380J .

AMA Style

Yanfeng Shen, Carlos E. S. Cesnik. Hybrid local FEM/global LISA modeling of guided wave propagation and interaction with damage in composite structures. Health Monitoring of Structural and Biological Systems 2015. 2015; 9438 ():94380J.

Chicago/Turabian Style

Yanfeng Shen; Carlos E. S. Cesnik. 2015. "Hybrid local FEM/global LISA modeling of guided wave propagation and interaction with damage in composite structures." Health Monitoring of Structural and Biological Systems 2015 9438, no. : 94380J.

Journal article
Published: 15 February 2013 in CEAS Aeronautical Journal
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The original version of this article unfortunately contained mistakes. Equations 11, 12, and 13 were incorrect. The corrected equations are given below.

ACS Style

Kalyan S. Nadella; Carlos E. S. Cesnik. Erratum to: Local interaction simulation approach for modeling wave propagation in composite structures. CEAS Aeronautical Journal 2013, 4, 49 -50.

AMA Style

Kalyan S. Nadella, Carlos E. S. Cesnik. Erratum to: Local interaction simulation approach for modeling wave propagation in composite structures. CEAS Aeronautical Journal. 2013; 4 (1):49-50.

Chicago/Turabian Style

Kalyan S. Nadella; Carlos E. S. Cesnik. 2013. "Erratum to: Local interaction simulation approach for modeling wave propagation in composite structures." CEAS Aeronautical Journal 4, no. 1: 49-50.

Journal article
Published: 23 January 2013 in CEAS Aeronautical Journal
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This paper presents a local interaction simulation approach (LISA) numerical method to analyze the guided wave propagation in composite structures. The method is based on recursive iterative equations, derived from the elastodynamic equilibrium equations. Derivation of the iterative equations is presented for a generalized orthotropic medium in a non-principal axis frame with non-uniform spatial discretizations. The new iterative equations have the capability to model generic laminated composite plates. The results show the validation of the numerical simulations through comparisons with experimental studies of laminated composite plates.

ACS Style

Kalyan S. Nadella; Carlos E. S. Cesnik. Local interaction simulation approach for modeling wave propagation in composite structures. CEAS Aeronautical Journal 2013, 4, 35 -48.

AMA Style

Kalyan S. Nadella, Carlos E. S. Cesnik. Local interaction simulation approach for modeling wave propagation in composite structures. CEAS Aeronautical Journal. 2013; 4 (1):35-48.

Chicago/Turabian Style

Kalyan S. Nadella; Carlos E. S. Cesnik. 2013. "Local interaction simulation approach for modeling wave propagation in composite structures." CEAS Aeronautical Journal 4, no. 1: 35-48.

Journal article
Published: 31 August 2011 in International Journal of Solids and Structures
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This paper introduces a strain-based geometrically nonlinear beam formulation for structural and aeroelastic modeling and analysis of slender wings of very flexible aircraft. With beam extensional strain, twist, and bending curvatures defined as the independent degrees of freedom, the equations of motion are derived through energy methods. Some special treatments are applied to the formulation to effectively model split-beam systems and beam configurations with multiple nodal displacement constraints. Using the strain-based formulation, solutions of different beam configurations under static loads and forced dynamic excitations are compared against ones from other geometrically nonlinear beam formulations.

ACS Style

Weihua Su; Carlos E.S. Cesnik. Strain-based geometrically nonlinear beam formulation for modeling very flexible aircraft. International Journal of Solids and Structures 2011, 48, 2349 -2360.

AMA Style

Weihua Su, Carlos E.S. Cesnik. Strain-based geometrically nonlinear beam formulation for modeling very flexible aircraft. International Journal of Solids and Structures. 2011; 48 (16-17):2349-2360.

Chicago/Turabian Style

Weihua Su; Carlos E.S. Cesnik. 2011. "Strain-based geometrically nonlinear beam formulation for modeling very flexible aircraft." International Journal of Solids and Structures 48, no. 16-17: 2349-2360.

Proceedings article
Published: 24 March 2011 in SPIE Smart Structures and Materials + Nondestructive Evaluation and Health Monitoring
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Composite structures are being extensively used in the modern industries because of their superior strength to weight ratio, high stiffness, and long fatigue life. The ability to tailor the material properties along different directions also increases the avenues of composites material application. The ever-increasing demand for composite structures and the need to ensure the structural integrity necessitates the development of sustainable and efficient structural health monitoring (SHM) systems. Guided wave (GW) methods offer an attractive solution for SHM due to their tunable sensitivity to different defects and their ability to interrogate large structural surfaces. Because of the anisotropy present in the composite materials, the development of the SHM methods is significantly more complex and challenging than in the case of isotropic materials. This paper presents numerical simulations based on the local interaction simulation approach (LISA) to characterize the propagation of GW in laminated composite plates.

ACS Style

Kalyan S. Nadella; Carlos E. S. Cesnik. Local interaction simulation of guided-wave propagation in composite plates. SPIE Smart Structures and Materials + Nondestructive Evaluation and Health Monitoring 2011, 7984, 1 .

AMA Style

Kalyan S. Nadella, Carlos E. S. Cesnik. Local interaction simulation of guided-wave propagation in composite plates. SPIE Smart Structures and Materials + Nondestructive Evaluation and Health Monitoring. 2011; 7984 ():1.

Chicago/Turabian Style

Kalyan S. Nadella; Carlos E. S. Cesnik. 2011. "Local interaction simulation of guided-wave propagation in composite plates." SPIE Smart Structures and Materials + Nondestructive Evaluation and Health Monitoring 7984, no. : 1.

Journal article
Published: 01 January 2011 in AIAA Journal
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ACS Style

Satish K. Chimakurthi; Carlos E. S. Cesnik; Bret K. Stanford. Flapping-Wing Structural Dynamics Formulation Based on a Corotational Shell Finite Element. AIAA Journal 2011, 49, 128 -142.

AMA Style

Satish K. Chimakurthi, Carlos E. S. Cesnik, Bret K. Stanford. Flapping-Wing Structural Dynamics Formulation Based on a Corotational Shell Finite Element. AIAA Journal. 2011; 49 (1):128-142.

Chicago/Turabian Style

Satish K. Chimakurthi; Carlos E. S. Cesnik; Bret K. Stanford. 2011. "Flapping-Wing Structural Dynamics Formulation Based on a Corotational Shell Finite Element." AIAA Journal 49, no. 1: 128-142.

Chapter
Published: 22 August 2009 in Flying Insects and Robots
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Aerodynamics, structural dynamics, and flight dynamics of natural flyers intersect with some of the richest problems in micro-air vehicles (MAVs), including massively unsteady three-dimensional separation, transition in boundary and shear layers, vortical flows, unsteady flight environment, aeroelasticity, and adaptive control being just a few examples. A challenge is that the scaling of both fluid dynamics and structural dynamics between smaller natural flyer and practical flying hardware/lab experiment (larger dimension) is fundamentally difficult. The interplay between flexible structures and aerodynamics motivated by the MAV development is discussed in this chapter. For fixed wings, membrane materials exhibit self-initiated vibration even in a steady free stream which lowers the effective angle of attack of the membrane structure compared to that of the rigid wing. For flapping wings, structural flexibility can enhance leading-edge suction via increasing the effective angle of attack, resulting in higher thrust generation.

ACS Style

W. Shyy; Y. Lian; S.K. Chimakurthi; J. Tang; C.E.S. Cesnik; B. Stanford; P.G. Ifju. Flexible Wings and Fluid-Structure Interactions for Micro-Air Vehicles. Flying Insects and Robots 2009, 143 -157.

AMA Style

W. Shyy, Y. Lian, S.K. Chimakurthi, J. Tang, C.E.S. Cesnik, B. Stanford, P.G. Ifju. Flexible Wings and Fluid-Structure Interactions for Micro-Air Vehicles. Flying Insects and Robots. 2009; ():143-157.

Chicago/Turabian Style

W. Shyy; Y. Lian; S.K. Chimakurthi; J. Tang; C.E.S. Cesnik; B. Stanford; P.G. Ifju. 2009. "Flexible Wings and Fluid-Structure Interactions for Micro-Air Vehicles." Flying Insects and Robots , no. : 143-157.

Research article
Published: 06 August 2009 in Journal of Intelligent Material Systems and Structures
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A modally selective, variable-length anisotropic piezocomposite transducer is designed for guided wave (GW) structural health monitoring applications. The transducer dimensions needed to maximize individual modes are selected based on 3D elasticity models for GW excitation by finite dimensional transducers. This theory is used to determine these transducer dimensions as a function of the wave phase velocity, and normalized by the substrate thickness. The design and fabrication of the transducer are subsequently described, and a set of experimental tests is conducted in pristine isotropic structures to characterize the actuation and sensing performance of the device. It is shown that the transducer dimensions can be tailored to obtain specific symmetric to antisymmetric mode transmission and sensing ratios.

ACS Style

Ken I. Salas; Carlos E.S. Cesnik. Design and Characterization of a Variable-Length Piezocomposite Transducer for Structural Health Monitoring. Journal of Intelligent Material Systems and Structures 2009, 21, 349 -360.

AMA Style

Ken I. Salas, Carlos E.S. Cesnik. Design and Characterization of a Variable-Length Piezocomposite Transducer for Structural Health Monitoring. Journal of Intelligent Material Systems and Structures. 2009; 21 (3):349-360.

Chicago/Turabian Style

Ken I. Salas; Carlos E.S. Cesnik. 2009. "Design and Characterization of a Variable-Length Piezocomposite Transducer for Structural Health Monitoring." Journal of Intelligent Material Systems and Structures 21, no. 3: 349-360.

Journal article
Published: 01 August 2009 in AIAA Journal
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ACS Style

Satish Kumar Chimakurthi; Jian Tang; Rafael Palacios; Carlos E. S. Cesnik; Wei Shyy. Computational Aeroelasticity Framework for Analyzing Flapping Wing Micro Air Vehicles. AIAA Journal 2009, 47, 1865 -1878.

AMA Style

Satish Kumar Chimakurthi, Jian Tang, Rafael Palacios, Carlos E. S. Cesnik, Wei Shyy. Computational Aeroelasticity Framework for Analyzing Flapping Wing Micro Air Vehicles. AIAA Journal. 2009; 47 (8):1865-1878.

Chicago/Turabian Style

Satish Kumar Chimakurthi; Jian Tang; Rafael Palacios; Carlos E. S. Cesnik; Wei Shyy. 2009. "Computational Aeroelasticity Framework for Analyzing Flapping Wing Micro Air Vehicles." AIAA Journal 47, no. 8: 1865-1878.

Journal article
Published: 01 June 2009 in The Aeronautical Journal
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Structural Health Monitoring (SHM) is the component of damage prognosis systems responsible for interrogating a structure to detect, locate, and identify any damage present. Guided wave (GW) testing methods are attractive for this application due to the GW ability to travel over long distances with little attenuation and their sensitivity to different damage types. The Composite Long-range Variable-direction Emitting Radar (CLoVER) transducer is introduced as an alternative concept for efficient damage interrogation in GW SHM systems. This transducer has an overall ring geometry, but is composed of individual wedge-shaped anisotropic piezocomposite sectors that can be individually excited to interrogate the structure in a particular direction. The transducer is shown to produce actuation amplitudes larger than those of a similarly sized ring configuration for the same electric current input. The electrode pattern design used allows each sector to act as an independent actuator and sensor element, decreasing the number of separate transducers needed for inspection. The fabrication and characterisation procedures of these transducers are described, and their performance is shown to be similar to that of conventional piezocomposite transducers. Experimental studies of damage detection demonstrating the proposed interrogation approach are also presented for simulated structural defects.

ACS Style

K. I. Salas; C. E. S. Cesnik. CLoVER: an alterntive concept for damage interrogation in structural health monitoring systems. The Aeronautical Journal 2009, 113, 339 -356.

AMA Style

K. I. Salas, C. E. S. Cesnik. CLoVER: an alterntive concept for damage interrogation in structural health monitoring systems. The Aeronautical Journal. 2009; 113 (1144):339-356.

Chicago/Turabian Style

K. I. Salas; C. E. S. Cesnik. 2009. "CLoVER: an alterntive concept for damage interrogation in structural health monitoring systems." The Aeronautical Journal 113, no. 1144: 339-356.

Journal article
Published: 20 May 2008 in Journal of Intelligent Material Systems and Structures
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Elevated temperatures can cause significant changes in guided-wave (GW) propagation and transduction for structural health monitoring (SHM). This work focuses on GW SHM using surface-bonded piezoelectric wafer transducers in metallic plates for the temperature range encountered in internal spacecraft structures (20—150°C). First, studies done to determine a suitable bonding agent are documented. This is then used in controlled experiments to examine changes in GW propagation and transduction using PZT-5A piezoelectric wafers under quasi-statically varying temperature (also from 20 to 150°C). Modeling efforts to explain the experimentally observed increase in time-of-flight and change in sensor response peak-to-peak magnitude with increasing temperature are detailed. Finally, these results are used in detection and location of mild and moderate damage using the pulse-echo GW testing approach within the temperature range.

ACS Style

Ajay Raghavan; Carlos E.S. Cesnik. Effects of Elevated Temperature on Guided-wave Structural Health Monitoring. Journal of Intelligent Material Systems and Structures 2008, 19, 1383 -1398.

AMA Style

Ajay Raghavan, Carlos E.S. Cesnik. Effects of Elevated Temperature on Guided-wave Structural Health Monitoring. Journal of Intelligent Material Systems and Structures. 2008; 19 (12):1383-1398.

Chicago/Turabian Style

Ajay Raghavan; Carlos E.S. Cesnik. 2008. "Effects of Elevated Temperature on Guided-wave Structural Health Monitoring." Journal of Intelligent Material Systems and Structures 19, no. 12: 1383-1398.

Journal article
Published: 30 April 2008 in International Journal of Solids and Structures
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The paper presents a one-dimensional model for anisotropic active slender structures that captures arbitrary cross-sectional deformations. The 1-D geometrically-nonlinear static problem is derived by an asymptotic reduction process from the equations of 3-D electroelasticity. In addition to the conventional (bending–extension–shear–twist) beam strain measures, it includes a Ritz approximation to account for arbitrary deformation shapes of the finite-size cross-sections. As a particular case, closed-form analytical expressions are derived for the linear static equilibrium of a composite thin strip with surface-mounted piezoelectric actuators. This solution is based on a boundary-layer approximation to the static equilibrium equations in regions where Saint-Venant’s principle for elastic bodies cannot be applied and includes camber bending deformations to account for the local bimoments induced by the distributed actuation in a finite-width strip.

ACS Style

Rafael Palacios; Carlos E.S. Cesnik. On the one-dimensional modeling of camber bending deformations in active anisotropic slender structures. International Journal of Solids and Structures 2008, 45, 2097 -2116.

AMA Style

Rafael Palacios, Carlos E.S. Cesnik. On the one-dimensional modeling of camber bending deformations in active anisotropic slender structures. International Journal of Solids and Structures. 2008; 45 (7-8):2097-2116.

Chicago/Turabian Style

Rafael Palacios; Carlos E.S. Cesnik. 2008. "On the one-dimensional modeling of camber bending deformations in active anisotropic slender structures." International Journal of Solids and Structures 45, no. 7-8: 2097-2116.