Abstract
The technology of hardware-in-the-loop simulations (HILS) plays an important role in the design of complex systems, for example, the structural health monitoring (SHM) of aircrafts. Due to the high performance of personal computers, HILS can provide practical solutions to many problems in engineering and sciences, especially in the huge systems, giant dams for civil engineering, and aircraft system. This study addresses the HILS in hole/crack identification in composite laminates. The multiple loading modes method is used for hole/crack identification. The signals of strains measured from the data-acquisition (DAQ) devices are accomplished by the graphical software LabVIEW. The results represent the actual responses of multiple loading mode tests of real specimens. A personal computer is employed to execute the identification work according to the strain data from DAQ devices by using a nonlinear optimization approach. When all the criteria are satisfied, the final identification results will be obtained. HILS will achieve real time identification of hole/crack in the composite plate by using the actual response measured from the sensors. Not only the size, but also the location and orientation of the crack/hole in a composite plate are successfully identified herein.
Highlights
Studies on structural health monitoring (SHM) are popular because the significant development of computer power, data processing capability, and modern sensor technology make real time detection of fractures possible
The aim of this paper is to demonstrate an experiment on hole/crack identification in a composite plate by using measured information from static loading
It is well known that crack identification is more difficult than hole identification because of the nonsensitive response of crack parameters to the strains around the plate [15]
Summary
Studies on structural health monitoring (SHM) are popular because the significant development of computer power, data processing capability, and modern sensor technology make real time detection of fractures possible. The various types of sensors are installed onto or embedded in the object’s structure and mass data related to the object’s certain conditions are automatically collected [1,2,3]. Aircraft structural maintenance is one of the critical operations to guarantee continued airworthiness. Composite structures, compared to metallic structures, have more complex damage modes because of their anisotropic properties. The records of wing structural damages for two types of Boeing aircraft fleet in a 10-year period were obtained. Dents are the most frequent damage mode (38%), followed by paint peeling off (24%). The damage mode for wind erosion is 12%, 2% for hole damage, and 8% for delamination [3]. The detection of defects, such as cracks, holes, and delamination in composite structures is increasingly important during maintenance
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