https://sam.ensam.eu:443 The DSpace digital repository system captures, stores, indexes, preserves, and distributes digital research material. Thu, 14 May 2026 19:06:57 GMT 2026-05-14T19:06:57Z http://hdl.handle.net/10985/26936 FBG based structural health monitoring of engine blades towards intelligent structures and CBM GALANOPOULOS, George; PAUNIKAR, Shweta; RÉBILLAT, Marc; ZAROUCHAS, Dimitrios Structural Health Monitoring (SHM) has been gaining increased attention over the past decades as an important step towards Condition Based Maintenance (CBM). Measurements from the SHM systems provide the necessary information to monitor the condition of a (sub)component or structure and enable the use of this knowledge for maintenance task when needed, increasing availability and safety while reducing downtime related costs [1]. On the final level of SHM lie diagnostics and prognostics [2, 3], whose output inform about the current and future state of the (sub)component and their accuracy impact the effectiveness of the CBM decision making, and hence a capable sensor network is important. In this research our focus lies with monitoring the structural integrity of composite aircraft engine blades, through a capable network of SHM technologies. Engine blades are an important part of any aircraft and their integrity is imperative for its safe operation. A common yet critical damage case is impact damage (cause by hail or bird strikes) which can significantly reduce the load bearing capabilities of the blade. The aim is to demonstrate the feasibility, effectiveness and usefulness of different SHM systems in identifying the existence of damage, monitoring the damage and degradation growth and eventually use robust and reliable indicators to estimate the remaining useful life. To accomplish that task, a subpart of the engine blade is manufactured from 3D-woven CFRP preforms via the injection molding technique. The panels are curved and their length is 800mm while their width is 350mm. A secondary adhesively bonded steel edge is also adhered to the entire length of the panel with a width of 50mm. The panels are subjected to a repeated 4-point bending load-unload scheme with increased severity to simulate low frequency fatigue at ~0.02 Hz and introduce controlled and gradual degradation. First, one panel is subjected to 4-point bending quasi-static loading to determine the failure load which was approximated at 22kN through finite element analysis. Experimental collapse was reached at 28 kN and with this a guide the load envelope was decided. The loads include [4, 8, 12, 14, 16, 18, 20, 22, 24, 26, 28] kN and each load is applied for 400 cycles. Impact damage is also introduced to most of the panels in order to create a damage area to monitor. Regarding the SHM systems employed, the panel is equipped with state of the art FBG sensors and piezoelectric sensors. In this work, the data from the optical fibers are studied more in depth. The fibers can either be surface mounted (tensiled side of the panel) or embedded during the layup process or a combination of both. The majority of optical fibers run across the length of the panel at different width locations, two focused in the middle section, and one close to each of the edges. The sensors are used to monitor the strain field and it is attempted to correlate damage formulation and overall degradation with alterations to the strain field [4]. The first indication of degradation can be observed by analyzing the data collected from the hydraulic machine. By processing the load and displacement data, the experimental stiffness can be calculated as the slope of a linear equation between the load and displacement during the loading part. What was observed, is that at first the experimental stiffness slightly increases after the first load case, attributed to the increased robustness of the panel after significant bending. A somewhat constant stiffness follows, until the time close to failure, where rapid stiffness drop can be seen. This is accompanied by the first visible mode of damage in the form of skin tears and fiber cracking at the top surface close to the loading pins. Final collapse is dominated by matrix and fiber breakage close to the loading pin locations which extend across the entire width of the panel. These results are summarized in Figure 1 and Figure 2. FBG data are dependent on the type of FBG. Embedded FBG sensors display a mixture of tension and compression behavior while surface mounted show predominantly tension strains with increased intensity as the max load increases. An example of strains from embedded and surface mounted FBG sensors can be seen in Figure 3. The end goal of analyzing the FBG data is to extract capable indicators, similar to [5], and correlate the online SHM measurements to the degradation, as observed by the stiffness reduction, in a semi-quantitative way. In this research the use of strain based SHM sensors for degradation monitoring is demonstrated. Strain based indicators were used in an attempt to capture degradation evolution in large curved composite panels representative of aircraft engine blades. An unprecedented experimental campaign was launched on engine blade panels, which are subjected to fatigue-like 4-point bending load, and are mounted with state of the art SHM systems. The raw strains are transformed into an informative measure of degradation, demonstrating the feasibility, effectiveness and usefulness of such sensors for diagnostic and prognostic tasks, a first step towards a CBM paradigm. 1. Kessler, S.S. and S.M. Spearing, Design of a piezoelectric-based structural health monitoring system for damage detection in composite materials. Smart Structures and Materials 2002: Smart Structures and Integrated Systems, 2002. 4701: p. 86-96. 2. Ling, Y. and S. Mahadevan, Integration of structural health monitoring and fatigue damage prognosis. Mechanical Systems and Signal Processing, 2012. 28: p. 89-104. 3. Loutas, T., N. Eleftheroglou, and D. Zarouchas, A data-driven probabilistic framework towards the in-situ prognostics of fatigue life of composites based on acoustic emission data. Composite Structures, 2017. 161: p. 522-529. 4. Broer, A., et al., Fusion-based damage diagnostics for stiffened composite panels. Structural Health Monitoring-an International Journal, 2022. 21(2): p. 613-639. 5. Galanopoulos, G., et al., A novel strain-based health indicator for the remaining useful life estimation of degrading composite structures. Composite Structures, 2023. 306. Sun, 01 Sep 2024 00:00:00 GMT http://hdl.handle.net/10985/26936 2024-09-01T00:00:00Z GALANOPOULOS, George PAUNIKAR, Shweta RÉBILLAT, Marc ZAROUCHAS, Dimitrios Structural Health Monitoring (SHM) has been gaining increased attention over the past decades as an important step towards Condition Based Maintenance (CBM). Measurements from the SHM systems provide the necessary information to monitor the condition of a (sub)component or structure and enable the use of this knowledge for maintenance task when needed, increasing availability and safety while reducing downtime related costs [1]. On the final level of SHM lie diagnostics and prognostics [2, 3], whose output inform about the current and future state of the (sub)component and their accuracy impact the effectiveness of the CBM decision making, and hence a capable sensor network is important. In this research our focus lies with monitoring the structural integrity of composite aircraft engine blades, through a capable network of SHM technologies. Engine blades are an important part of any aircraft and their integrity is imperative for its safe operation. A common yet critical damage case is impact damage (cause by hail or bird strikes) which can significantly reduce the load bearing capabilities of the blade. The aim is to demonstrate the feasibility, effectiveness and usefulness of different SHM systems in identifying the existence of damage, monitoring the damage and degradation growth and eventually use robust and reliable indicators to estimate the remaining useful life. To accomplish that task, a subpart of the engine blade is manufactured from 3D-woven CFRP preforms via the injection molding technique. The panels are curved and their length is 800mm while their width is 350mm. A secondary adhesively bonded steel edge is also adhered to the entire length of the panel with a width of 50mm. The panels are subjected to a repeated 4-point bending load-unload scheme with increased severity to simulate low frequency fatigue at ~0.02 Hz and introduce controlled and gradual degradation. First, one panel is subjected to 4-point bending quasi-static loading to determine the failure load which was approximated at 22kN through finite element analysis. Experimental collapse was reached at 28 kN and with this a guide the load envelope was decided. The loads include [4, 8, 12, 14, 16, 18, 20, 22, 24, 26, 28] kN and each load is applied for 400 cycles. Impact damage is also introduced to most of the panels in order to create a damage area to monitor. Regarding the SHM systems employed, the panel is equipped with state of the art FBG sensors and piezoelectric sensors. In this work, the data from the optical fibers are studied more in depth. The fibers can either be surface mounted (tensiled side of the panel) or embedded during the layup process or a combination of both. The majority of optical fibers run across the length of the panel at different width locations, two focused in the middle section, and one close to each of the edges. The sensors are used to monitor the strain field and it is attempted to correlate damage formulation and overall degradation with alterations to the strain field [4]. The first indication of degradation can be observed by analyzing the data collected from the hydraulic machine. By processing the load and displacement data, the experimental stiffness can be calculated as the slope of a linear equation between the load and displacement during the loading part. What was observed, is that at first the experimental stiffness slightly increases after the first load case, attributed to the increased robustness of the panel after significant bending. A somewhat constant stiffness follows, until the time close to failure, where rapid stiffness drop can be seen. This is accompanied by the first visible mode of damage in the form of skin tears and fiber cracking at the top surface close to the loading pins. Final collapse is dominated by matrix and fiber breakage close to the loading pin locations which extend across the entire width of the panel. These results are summarized in Figure 1 and Figure 2. FBG data are dependent on the type of FBG. Embedded FBG sensors display a mixture of tension and compression behavior while surface mounted show predominantly tension strains with increased intensity as the max load increases. An example of strains from embedded and surface mounted FBG sensors can be seen in Figure 3. The end goal of analyzing the FBG data is to extract capable indicators, similar to [5], and correlate the online SHM measurements to the degradation, as observed by the stiffness reduction, in a semi-quantitative way. In this research the use of strain based SHM sensors for degradation monitoring is demonstrated. Strain based indicators were used in an attempt to capture degradation evolution in large curved composite panels representative of aircraft engine blades. An unprecedented experimental campaign was launched on engine blade panels, which are subjected to fatigue-like 4-point bending load, and are mounted with state of the art SHM systems. The raw strains are transformed into an informative measure of degradation, demonstrating the feasibility, effectiveness and usefulness of such sensors for diagnostic and prognostic tasks, a first step towards a CBM paradigm. 1. Kessler, S.S. and S.M. Spearing, Design of a piezoelectric-based structural health monitoring system for damage detection in composite materials. Smart Structures and Materials 2002: Smart Structures and Integrated Systems, 2002. 4701: p. 86-96. 2. Ling, Y. and S. Mahadevan, Integration of structural health monitoring and fatigue damage prognosis. Mechanical Systems and Signal Processing, 2012. 28: p. 89-104. 3. Loutas, T., N. Eleftheroglou, and D. Zarouchas, A data-driven probabilistic framework towards the in-situ prognostics of fatigue life of composites based on acoustic emission data. Composite Structures, 2017. 161: p. 522-529. 4. Broer, A., et al., Fusion-based damage diagnostics for stiffened composite panels. Structural Health Monitoring-an International Journal, 2022. 21(2): p. 613-639. 5. Galanopoulos, G., et al., A novel strain-based health indicator for the remaining useful life estimation of degrading composite structures. Composite Structures, 2023. 306. http://hdl.handle.net/10985/26937 Using Novel Printed Piezoelectric Sensors for Monitoring the Health of a Composite Foreign Object Damage Panel PAUNIKAR, Shweta; RÉBILLAT, Marc This research focuses on the structural health monitoring (SHM) of a foreign object damage (FOD) composite panel substructure of an aircraft engine fan blade equipped with an architecture array of novel screen printed piezoelectric sensors and is being carried out within the purview of the MORPHO – H2020 project. The state of the art printing technology ensures that architecture network of printed sensor is not only non-intrusive and lightweight but can also be printed during the manufacturing process before the structure goes into service. The FOD panel in this work is made of 3D woven composite, measuring approximately 800 mm x 350 mm, with a stainless-steel leading edge bonded to one of the longer edges and hosts a network of 5 arrays of 5 printed sensors each. The printed sensors can potentially be used in multiple ways to analyse the health of the host structure. Since the fabrication process of the sensors is an on-going research, first the electromechanical behaviour of the sensors is analysed with the help of impedance measurements. It is observed that the printing process ensures repeatability. Secondly, the performance of the printed sensors in case of impact loading is discussed here, as bird impact is one of the leading causes of engine fan blade failure. The impact response measured by the printed sensors is studied to detect the impact location on the FOD panel. Next, the ability of the printed sensors to sense ultrasonic guided wave responses generated by standard ceramic piezoelectric disc actuators is demonstrated. Finally, the health of these printed sensors upon undergoing multi-load multi-cycle bending tests is also discussed here. The ultimate goal of this project is to create diverse diagnostic and prognostic techniques for estimating the remaining lifespan and Structural Health Monitoring (SHM) of the FOD panel based on the range of measurements gathered using the printed sensors. Sun, 01 Sep 2024 00:00:00 GMT http://hdl.handle.net/10985/26937 2024-09-01T00:00:00Z PAUNIKAR, Shweta RÉBILLAT, Marc This research focuses on the structural health monitoring (SHM) of a foreign object damage (FOD) composite panel substructure of an aircraft engine fan blade equipped with an architecture array of novel screen printed piezoelectric sensors and is being carried out within the purview of the MORPHO – H2020 project. The state of the art printing technology ensures that architecture network of printed sensor is not only non-intrusive and lightweight but can also be printed during the manufacturing process before the structure goes into service. The FOD panel in this work is made of 3D woven composite, measuring approximately 800 mm x 350 mm, with a stainless-steel leading edge bonded to one of the longer edges and hosts a network of 5 arrays of 5 printed sensors each. The printed sensors can potentially be used in multiple ways to analyse the health of the host structure. Since the fabrication process of the sensors is an on-going research, first the electromechanical behaviour of the sensors is analysed with the help of impedance measurements. It is observed that the printing process ensures repeatability. Secondly, the performance of the printed sensors in case of impact loading is discussed here, as bird impact is one of the leading causes of engine fan blade failure. The impact response measured by the printed sensors is studied to detect the impact location on the FOD panel. Next, the ability of the printed sensors to sense ultrasonic guided wave responses generated by standard ceramic piezoelectric disc actuators is demonstrated. Finally, the health of these printed sensors upon undergoing multi-load multi-cycle bending tests is also discussed here. The ultimate goal of this project is to create diverse diagnostic and prognostic techniques for estimating the remaining lifespan and Structural Health Monitoring (SHM) of the FOD panel based on the range of measurements gathered using the printed sensors. http://hdl.handle.net/10985/26084 Single atom convolutional matching pursuit: Theoretical framework and application to Lamb waves based structural health monitoring RODRIGUEZ, Sebastian; RÉBILLAT, Marc; PAUNIKAR, Shweta; MARGERIT, Pierre; MONTEIRO, Eric; CHINESTA SORIA, Francisco; MECHBAL, Nazih Lamb Waves (LW) based Structural Health Monitoring (SHM) aims to monitor the health state of thin structures. An Initial Wave Packet (IWP) is sent in the structure and interacts with boundaries, discontinuities, and with eventual damages thus generating many wave packets. An issue with LW based SHM is that at least two LW dispersive modes simultaneously exist. Matching Pursuit Method (MPM), which approximates a signal as a sum of delayed and scaled atoms taken from a known dictionary, is limited to nondispersive signals and relies on a priori known dictionary and is thus inappropriate for LW-based SHM. Single Atom Convolutional MPM, which addresses dispersion by decomposing a signal as delayed and dispersed atoms and limits the learning dictionary to only one atom, is alternatively proposed here. Its performances are demonstrated on numerical and experimental signals and it is used for damage monitoring. Beyond LW-based SHM, this method remains very general and applicable to a large class of signal processing problems. Sun, 01 Jun 2025 00:00:00 GMT http://hdl.handle.net/10985/26084 2025-06-01T00:00:00Z RODRIGUEZ, Sebastian RÉBILLAT, Marc PAUNIKAR, Shweta MARGERIT, Pierre MONTEIRO, Eric CHINESTA SORIA, Francisco MECHBAL, Nazih Lamb Waves (LW) based Structural Health Monitoring (SHM) aims to monitor the health state of thin structures. An Initial Wave Packet (IWP) is sent in the structure and interacts with boundaries, discontinuities, and with eventual damages thus generating many wave packets. An issue with LW based SHM is that at least two LW dispersive modes simultaneously exist. Matching Pursuit Method (MPM), which approximates a signal as a sum of delayed and scaled atoms taken from a known dictionary, is limited to nondispersive signals and relies on a priori known dictionary and is thus inappropriate for LW-based SHM. Single Atom Convolutional MPM, which addresses dispersion by decomposing a signal as delayed and dispersed atoms and limits the learning dictionary to only one atom, is alternatively proposed here. Its performances are demonstrated on numerical and experimental signals and it is used for damage monitoring. Beyond LW-based SHM, this method remains very general and applicable to a large class of signal processing problems. http://hdl.handle.net/10985/27081 Screen Printed Piezoelectric Transducers for Structural Health Monitoring of Curved Thick Composite Panels RÉBILLAT, Marc; PAUNIKAR, Shweta; GALANOPOULOS, George; MARGERIT, Pierre; WIRTH, Ingo; MONTEIRO, Eric; ZAROUCHAS, Dimitrios; MECHBAL, Nazih This research focuses on the development and experimental validation of a novel printed piezoelectric transducers network employed on a foreign object damage panel substructure of an aircraft engine fan blade. The main goal of the work is to leverage the screen printing technology to fabricate arrays of piezoelectric transducers and ultimately employ these trans- ducers for operations, enabling the development of structural health monitoring methods for the panel. The printed transducer is made up of a piezoelectric layer sandwiched between two silver electrodes, each printed in a controlled manner. Upon printing and drying of the layers, the transducers undergo polarization. The electromechanical behaviour of the printed transducers, characterized using impedance measurements, exhibits high repeatability, thus indicating its potential for large scale industrial deployment. Following this, it is demon-strated that the transducers are capable of accurately sensing impact, which is one the mostcommon yet critical sources of damage to an engine fan blade. It is also shown that the printed transducers are able to detect acoustic emission events. The ability of the printed transducers to actuate and sense guided wave signals over a range of ultrasonic frequencies is also demonstrated. Furthermore, apart from the noticeable advantages of the non-intrusive nature, and negligible weight as compared to their traditional ceramic counterparts, the printed piezoelectric transducers can potentially be integrated into the manufacturing process in the future, and the presence of transducer arrays ensures the availability of other transducers in case of an individual failure during service. This innovative printing technol-ogy for PZT transducer networks thus holds significant promise in bridging the gap between research advancements and the industrial implementation of SHM technology. Wed, 01 Jan 2025 00:00:00 GMT http://hdl.handle.net/10985/27081 2025-01-01T00:00:00Z RÉBILLAT, Marc PAUNIKAR, Shweta GALANOPOULOS, George MARGERIT, Pierre WIRTH, Ingo MONTEIRO, Eric ZAROUCHAS, Dimitrios MECHBAL, Nazih This research focuses on the development and experimental validation of a novel printed piezoelectric transducers network employed on a foreign object damage panel substructure of an aircraft engine fan blade. The main goal of the work is to leverage the screen printing technology to fabricate arrays of piezoelectric transducers and ultimately employ these trans- ducers for operations, enabling the development of structural health monitoring methods for the panel. The printed transducer is made up of a piezoelectric layer sandwiched between two silver electrodes, each printed in a controlled manner. Upon printing and drying of the layers, the transducers undergo polarization. The electromechanical behaviour of the printed transducers, characterized using impedance measurements, exhibits high repeatability, thus indicating its potential for large scale industrial deployment. Following this, it is demon-strated that the transducers are capable of accurately sensing impact, which is one the mostcommon yet critical sources of damage to an engine fan blade. It is also shown that the printed transducers are able to detect acoustic emission events. The ability of the printed transducers to actuate and sense guided wave signals over a range of ultrasonic frequencies is also demonstrated. Furthermore, apart from the noticeable advantages of the non-intrusive nature, and negligible weight as compared to their traditional ceramic counterparts, the printed piezoelectric transducers can potentially be integrated into the manufacturing process in the future, and the presence of transducer arrays ensures the availability of other transducers in case of an individual failure during service. This innovative printing technol-ogy for PZT transducer networks thus holds significant promise in bridging the gap between research advancements and the industrial implementation of SHM technology. http://hdl.handle.net/10985/27082 Screen Printed Piezoelectric Transducers for Structural Health Monitoring of Curved Thick Composite Panels RÉBILLAT, Marc; PAUNIKAR, Shweta; GALANOPOULOS, George; WIRTH, Ingo; MONTEIRO, Eric; ZAROUCHAS, Dimitri; MECHBAL, Nazih This research focuses on the development and experimental validation of a novel printed piezoelectric transducers network employed on a foreign object damage panel substructure of an aircraft engine fan blade. The main goal of the work is to leverage the screen printing technology to fabricate arrays of piezoelectric transducers and ultimately employ these transducers for operations, enabling the development of structural health monitoring methods for the panel. The printed transducer is made up of a piezoelectric layer sandwiched between two silver electrodes, each printed in a controlled manner. Upon printing and drying of the layers, the transducers undergo polarization. The electromechanical behaviour of the printed transducers, characterized using impedance measurements, exhibits high repeatability, thus indicating its potential for large scale industrial deployment. Following this, it is demonstrated that the transducers are capable of accurately sensing impact, which is one the most common yet critical sources of damage to an engine fan blade. It is also shown that the printed transducers are able to detect acoustic emission events. The ability of the printed transducers to actuate and sense guided wave signals over a range of ultrasonic frequencies is also demonstrated. Furthermore, apart from the noticeable advantages of the non-intrusive nature, and negligible weight as compared to their traditional ceramic counterparts, the printed piezoelectric transducers can potentially be integrated into the manufacturing process in the future, and the presence of transducer arrays ensures the availability of other transducers in case of an individual failure during service. This innovative printing technology for PZT transducer networks thus holds significant promise in bridging the gap between research advancements and the industrial implementation of SHM technology. Tue, 01 Apr 2025 00:00:00 GMT http://hdl.handle.net/10985/27082 2025-04-01T00:00:00Z RÉBILLAT, Marc PAUNIKAR, Shweta GALANOPOULOS, George WIRTH, Ingo MONTEIRO, Eric ZAROUCHAS, Dimitri MECHBAL, Nazih This research focuses on the development and experimental validation of a novel printed piezoelectric transducers network employed on a foreign object damage panel substructure of an aircraft engine fan blade. The main goal of the work is to leverage the screen printing technology to fabricate arrays of piezoelectric transducers and ultimately employ these transducers for operations, enabling the development of structural health monitoring methods for the panel. The printed transducer is made up of a piezoelectric layer sandwiched between two silver electrodes, each printed in a controlled manner. Upon printing and drying of the layers, the transducers undergo polarization. The electromechanical behaviour of the printed transducers, characterized using impedance measurements, exhibits high repeatability, thus indicating its potential for large scale industrial deployment. Following this, it is demonstrated that the transducers are capable of accurately sensing impact, which is one the most common yet critical sources of damage to an engine fan blade. It is also shown that the printed transducers are able to detect acoustic emission events. The ability of the printed transducers to actuate and sense guided wave signals over a range of ultrasonic frequencies is also demonstrated. Furthermore, apart from the noticeable advantages of the non-intrusive nature, and negligible weight as compared to their traditional ceramic counterparts, the printed piezoelectric transducers can potentially be integrated into the manufacturing process in the future, and the presence of transducer arrays ensures the availability of other transducers in case of an individual failure during service. This innovative printing technology for PZT transducer networks thus holds significant promise in bridging the gap between research advancements and the industrial implementation of SHM technology. http://hdl.handle.net/10985/27061 Printed PZT Transducers Network for the Structural Health Monitoring of Foreign Object Damage Composite Panel PAUNIKAR, Shweta; GALANOPOULOS, GEORGIOS; RÉBILLAT, Marc; WIRTH, Ingo; MONTEIRO, Eric; MARGERIT, Pierre; MECHBAL, Nazih The work presented here focuses on the structural health monitoring (SHM) of a foreign object damage (FOD) composite panel equipped with an innovative printed piezoelectric transducer network. The 3D woven composite FOD panel measures approximately 800 mm x 320 mm, is curved with a cross-sectional thickness varying from approximately 2 mm to 12 mm, and a stainless-steel leading edge is bonded at one of its sides. The core idea explored here is to rely on an innovative screen-printing technology to print a full piezoelectric transducer allowing to successfully achieve SHM on such a complex composite structure. This work is being carried out within the European project MORPHO – H2020. After printing a 25 elements PZT network, a four points bending fatigue experimental campaign using the PZT network along with other sensor technologies (embedded optical fibres with FBG sensors and acoustic emission sensors) is carried out. This unique experimental campaign allows to generate data and will help to develop diagnostic and prognostic methodologies for remaining life estimation and SHM of the FOD panel. It is demonstrated here through impedance measurements that the printing process associated with the printed PZT transducers is highly repeatable thus validating its use at a larger industrial scale. Furthermore, the printed piezoelectric transducers electromechanical behaviour is characterized and they are shown to be able to detect foreign object impact and to size and localize resulting damage using Lamb waves signals collected at different locations of the network. This innovative printing technology for PZT transducers network is thus extremely promising. It is furthermore highly advantageous to use the printed transducers for SHM instead of regular ceramic ones as this technology is non-intrusive, add negligible weight, can be printed during the manufacturing process, and arrays of transducers ensure easy availability of another transducer in case of failure of one. Mon, 01 Jul 2024 00:00:00 GMT http://hdl.handle.net/10985/27061 2024-07-01T00:00:00Z PAUNIKAR, Shweta GALANOPOULOS, GEORGIOS RÉBILLAT, Marc WIRTH, Ingo MONTEIRO, Eric MARGERIT, Pierre MECHBAL, Nazih The work presented here focuses on the structural health monitoring (SHM) of a foreign object damage (FOD) composite panel equipped with an innovative printed piezoelectric transducer network. The 3D woven composite FOD panel measures approximately 800 mm x 320 mm, is curved with a cross-sectional thickness varying from approximately 2 mm to 12 mm, and a stainless-steel leading edge is bonded at one of its sides. The core idea explored here is to rely on an innovative screen-printing technology to print a full piezoelectric transducer allowing to successfully achieve SHM on such a complex composite structure. This work is being carried out within the European project MORPHO – H2020. After printing a 25 elements PZT network, a four points bending fatigue experimental campaign using the PZT network along with other sensor technologies (embedded optical fibres with FBG sensors and acoustic emission sensors) is carried out. This unique experimental campaign allows to generate data and will help to develop diagnostic and prognostic methodologies for remaining life estimation and SHM of the FOD panel. It is demonstrated here through impedance measurements that the printing process associated with the printed PZT transducers is highly repeatable thus validating its use at a larger industrial scale. Furthermore, the printed piezoelectric transducers electromechanical behaviour is characterized and they are shown to be able to detect foreign object impact and to size and localize resulting damage using Lamb waves signals collected at different locations of the network. This innovative printing technology for PZT transducers network is thus extremely promising. It is furthermore highly advantageous to use the printed transducers for SHM instead of regular ceramic ones as this technology is non-intrusive, add negligible weight, can be printed during the manufacturing process, and arrays of transducers ensure easy availability of another transducer in case of failure of one.