“…The numerical low energy impact simulation, FE modeling and analysis, was developed at CIRA and has already been published in literature, 6,9,10,46,47 but it has not been the aim of this study. To be precise, the numerical approach determines the damage extent after the impact event by using an explicit finite element code.…”
Section: Shm System Architecture and Methodologymentioning
confidence: 99%
“…Consequently, it could be possible to improve the composite structure's static strength (compression after impact), for a reduced damage size detection, as illustrated in the simple scheme of Figure 4 and reported in literature. 2,6,9,10 Figure 4.Higher allowable compressive strain by SHM.…”
Section: Design and Maintenance Perspectivesmentioning
confidence: 99%
“…Instead, the use of an offline SHM system could reduce many of the current uncertainties and overdesigns, subsequently permitting the use of increased design allowable which would lead to lighter and more efficient structures. SHM systems would allow more acceptable designs thanks to a more reliable detection of damage, which can be smaller than the current BVID (about 0.8 mm, and dictated by the visual inspection 2,9,10 ). Consequently, it could be possible to improve the composite structure's static strength (compression after impact), for a reduced damage size detection, as illustrated in the simple scheme of Figure 4 and reported in literature.…”
Section: Design and Maintenance Perspectivesmentioning
confidence: 99%
“…This result has already been thoroughly examined, numerically and experimentally in literature. 6,9,10…”
Section: Implications For the Designmentioning
confidence: 99%
“…higher design allowable) than the current ongoing ones dictated by the traditional design approach. 2,6,9,10 Besides, the use of bonded parts, if monitored by sensors, can also overcome the current long-term adhesive performance uncertainties.…”
This detailed study proposes a structural health monitoring system which enables the identification, localisation, and correct measurement analysis, in relation to the damage and debonding induced by low energy impacts within aircraft composite wing panels. The said system has been envisaged as an offline system which aims to be considered as a valid alternative method in relation to the current first two maintenance approach levels: visual inspection, which is to be followed if necessary by ultrasonic scanning techniques. The architecture includes two different technologies which act at different frequency ranges: high-frequency sensors/actuators piezoceramics and low-frequency distributed fiber optic sensors. Experimental and numerical results on small stiffened panels are illustrated in this study, where technological verification and validation have been assessed within a laboratory-controlled environment. In addition, the potential benefit by utilising such techniques within the design of the aircraft composite structures has also been illustrated; in comparison with the current aircraft composite structures, a higher weight saving and better performing structures is foreseen.
“…The numerical low energy impact simulation, FE modeling and analysis, was developed at CIRA and has already been published in literature, 6,9,10,46,47 but it has not been the aim of this study. To be precise, the numerical approach determines the damage extent after the impact event by using an explicit finite element code.…”
Section: Shm System Architecture and Methodologymentioning
confidence: 99%
“…Consequently, it could be possible to improve the composite structure's static strength (compression after impact), for a reduced damage size detection, as illustrated in the simple scheme of Figure 4 and reported in literature. 2,6,9,10 Figure 4.Higher allowable compressive strain by SHM.…”
Section: Design and Maintenance Perspectivesmentioning
confidence: 99%
“…Instead, the use of an offline SHM system could reduce many of the current uncertainties and overdesigns, subsequently permitting the use of increased design allowable which would lead to lighter and more efficient structures. SHM systems would allow more acceptable designs thanks to a more reliable detection of damage, which can be smaller than the current BVID (about 0.8 mm, and dictated by the visual inspection 2,9,10 ). Consequently, it could be possible to improve the composite structure's static strength (compression after impact), for a reduced damage size detection, as illustrated in the simple scheme of Figure 4 and reported in literature.…”
Section: Design and Maintenance Perspectivesmentioning
confidence: 99%
“…This result has already been thoroughly examined, numerically and experimentally in literature. 6,9,10…”
Section: Implications For the Designmentioning
confidence: 99%
“…higher design allowable) than the current ongoing ones dictated by the traditional design approach. 2,6,9,10 Besides, the use of bonded parts, if monitored by sensors, can also overcome the current long-term adhesive performance uncertainties.…”
This detailed study proposes a structural health monitoring system which enables the identification, localisation, and correct measurement analysis, in relation to the damage and debonding induced by low energy impacts within aircraft composite wing panels. The said system has been envisaged as an offline system which aims to be considered as a valid alternative method in relation to the current first two maintenance approach levels: visual inspection, which is to be followed if necessary by ultrasonic scanning techniques. The architecture includes two different technologies which act at different frequency ranges: high-frequency sensors/actuators piezoceramics and low-frequency distributed fiber optic sensors. Experimental and numerical results on small stiffened panels are illustrated in this study, where technological verification and validation have been assessed within a laboratory-controlled environment. In addition, the potential benefit by utilising such techniques within the design of the aircraft composite structures has also been illustrated; in comparison with the current aircraft composite structures, a higher weight saving and better performing structures is foreseen.
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