Embodiments described herein utilize Non-Destructive Inspection (NDI) scan data obtained during a process performed on a surface of a structure to update a location of an NDI scanner on the surface. A subsurface feature within the structure is detected based on the NDI scan data, which are correlated with pre-defined position data for the subsurface feature. A measured location of the NDI scanner on the surface is corrected based on the pre-defined position data for the subsurface feature.

A method of detecting a deformation in a lattice structure comprises capturing first image data of the lattice structure via a first image capturing device with a first telecentric lens and a second image capturing device with a second telecentric lens. The first telecentric lens is directed toward the lattice structure, and the second telecentric lens is spaced apart from the first telecentric lens and also directed toward the lattice structure. The method includes compressing the lattice structure; capturing second image data of the lattice structure via the first and second image capturing devices; and detecting the deformation based at least in part on the first and second image data.

A time point is acquired by steps including a data acquisition step of acquiring time-series data indicating a time change of a displacement of a structure based on a physical quantity generated at a predetermined observation point in the structure as a response caused by a movement of a formation moving object formed with one or more moving objects on the structure; a removing step of removing a vibration component included in the time-series data; and a time point acquisition step of acquiring an entry time point at which the formation moving object enters the structure and an exit time point at which the formation moving object exits from the structure, based on the time-series data after the vibration component is removed.

A first index value, which is an index value of a deflection amount of a structure generated at an observation point, and a second index value, which is an index value of a deflection amount at a designated position in the structure, are acquired based on the number of moving objects formed in a formation moving object, an entry time point, an exit time point, and environment information. An estimated value of the deflection amount of the structure at the designated position is derived based on time-series data measured at the observation point, the first index value, and the second index value.

An aviation component inspection device includes a camera, a display, an input device, and a computer. The camera is configured to capture images of an aviation component under inspection. The computer is configured to receive an image from the camera, evaluate the image with one or more machine-learning aviation component-detection models. Each machine-learning aviation component-detection model is previously trained to output at least one confidence score indicating a confidence that a corresponding aviation component is present in the image. The computer is configured to present, via the display, a list of candidate aviation components based on corresponding confidence scores output by the one or more machine-learning aviation component-detection models, and add data previously-associated with a selected candidate aviation component from the list to a digital inspection report responsive to receiving user verification, via the input device, confirming the selected candidate aviation component is present in the image.

A packaging fill material for electrical packaging includes a base material, and a plurality of frangible capsules distributed in the base material. Each frangible capsule includes a liquid penetrant contrast agent therein having a different radiopacity than the base material. In response to a crack forming in the packaging fill material, at least one of the plurality of frangible capsules opens, releasing the liquid penetrant contrast agent into the crack. Cracks can be more readily identified in an IC package including the packaging fill material. The liquid penetrant contrast agent may have a radiopacity that is higher than the base material. Inspection can be carried out using electromagnetic analysis using visual inspection or digital analysis of the results to more easily identify cracks.

A system for monitoring the degradation status of refueling hoses on air includes a device with at least one sensor adapted to produce data about the external surface of the refueling hose. The method for monitoring the degradation status of refueling hoses on air includes moving a device with at least one sensor along a refueling hose or moving a refueling hose with respect to the device, producing data about the external surface of the refueling hose from the at least one sensor, and analyzing the data for monitoring the degradation status of the refueling hose. It allows providing a system and method for monitoring the degradation status of refueling hoses on air that reduces the risk of personal injury associated to hose damage inspection and is cost saving.

A system for estimating both thickness and wear state of refractory material (1) of a metallurgical furnace (12), including at least on processor including a database of simulated frequency domain data named simulated spectra representing simulated shock waves reflected in simulated refractory materials of known state and thickness, each simulated spectrum being correlated with both known state and thickness data of the considered simulated refractory material, wherein the at least one processor is configured to record a reflected shock wave as a time domain signal, and to convert it into frequency domain data named experimental spectrum, and are further configured to compare the experimental spectrum with at least a plurality of simulated spectra from the database, to determine the best fitting simulated spectrum with the experimental spectrum and to estimate thickness and state of the refractory material (1) of the furnace (12) using known state and thickness data correlated with the best fitting simulated spectrum.

A modular and autonomous assembly for detecting the angular position of the blades of an impeller intended to be mounted on a turbine engine, the assembly comprises at least one electrical power source allowing the operation of the elements of the detection assembly independently of the turbine engine on which it is intended to be carried, at least one first sensor intended to be associated with the first impeller, at least one second sensor intended to be associated with the second impeller, and a main housing including a processing unit and storage means.

A method of determining the location and size of a crack in a blade includes measuring a time of arrival of a tip of the blade at an angular position in a rotation, using the time of arrival to calculate a displacement of the tip of the blade, and using the displacements to calculate a first vibration condition and a second vibration condition for the blade. The method also includes comparing the first vibration condition and the second vibration condition for the blade to a predetermined baseline first vibration condition and a predetermined baseline second vibration condition for the blade to determine a change in the first vibration condition and a change in the second vibration condition, and using the magnitude of the change in the second vibration condition relative to the change in the first vibration condition to determine the likely location of the crack and using the magnitude of the change in the first vibration condition and the change in the second vibration condition to determine the size of the crack.