This aircraft inspection support device includes a first imaging unit configured to capture a measurement information image displayed on a measurement instrument-side display unit of a specific measurement instrument associated with a model of an aircraft or an inspection target of an aircraft component, the measurement instrument-side display unit being configured to display measurement information on the inspection target, and an operator-side display unit configured to display the measurement information image so as to be visible to an inspection operator who is performing an inspection operation near the inspection target.

A non-contact non-destructive testing method includes spatially and/or temporally controlling a laser excitation light based on a predetermined pattern. The laser excitation light is projected onto a surface of a test object to generate acoustic waves on the test object. The acoustic waves apply stress loading to the test object. The method also includes imaging the test object with and without stress loading using shearography imaging, and analyzing shearography imaging data to determine a presence of a defect in the test object.

A system for assembling two parts, in particular parts forming the fuselage or the wings of an aircraft, includes a positioning aid guiding positioning tools so as to juxtapose the two parts at the level of an assembly zone. The assembly system further includes a set of eddy current sensors positioned in at least one of the two parts to determine the separation of the two parts at the level of the assembly zone. If the separation does not conform to a predetermined criterion the positioning tools move at least one of the parts.

This defect inspection apparatus (100) is provided with an excitation unit (1), a laser illumination unit (2), an interference unit (30), an imaging unit (31), a holding member (4) for holding the imaging unit at a position spaced apart from an inspection target (90) by a predetermined distance, a connecting member (5) for connecting the holding member or the imaging unit and the excitation unit, and a controller (6) for generating an image (61) related to the propagation of an elastic wave on an inspection target.

A motorized rolling maintenance cart that utilizes the angled trailing edge geometry of an airfoil-shaped body (such as a wind turbine blade or rotor blade) to traverse the length of the airfoil-shaped body. The trailing edge-following maintenance cart may be used to carry personnel doing maintenance activities on the blades, such as local repairs or re-painting. In accordance with one aspect, the maintenance cart carries non-destructive inspection sensor units or other maintenance hardware over the surface of the airfoil-shaped body (e.g., in a spanwise direction). In accordance with another aspect, the trailing edge-following maintenance cart is configured to also provide fall protection to one or more independently movable crawler vehicles by means of cables. Alternative embodiments may include only one of the two aspects.

Devices for maintaining crawler alignment on complex-shaped blades and for enabling the blade crawler to traverse over trailing edge protrusions. Using ball and socket bearings or air pads in place of alignment wheels, the crawler will be able to track along complex-geometry rotor blades, propellers and other airfoils. Using an oversized-diameter roller, a semi-flexible roller, or a dual-roller arrangement, the crawler will be able to traverse over trailing edge protrusions.

A device for imaging defects in a structure includes N transmitters and P receivers to be distributed over at least one surface of the structure and a central unit controlling the transmitters and receivers to sequentially record Q≤N×P signals (S) obtained from electrical signals provided by the receivers of Q different transmitter/receiver pairs, after reception of mechanical waves transmitted by the transmitters of these Q pairs. It further stores Q first and Q second corresponding reference signals (S.sub.REF1, S.sub.REF2), representative of the structure without defects and differing by random noise. A central processing unit is programmed to: correlate each signal obtained with the corresponding first reference signal, in such a way as to construct an image of probabilities of defects; correlate each first reference signal with the corresponding second reference signal, in such a way as to construct a reference noisy image; and subtract the reference noisy image from the image of probabilities of defects.

An ultrasonic flaw detector for a composite material constituted by a plurality of materials which are different in physical properties from one another includes: a section specifier configured to specify first and second sections of an RF signal of a reflected wave of an ultrasonic wave with which the composite material is irradiated, a material reflected wave being possibly generated in the first section, an interface reflected wave being possibly generated in the second section; a material flaw determiner configured to determine whether or not a value of the RF signal exceeds a positive first threshold in the first section; and an interface flaw determiner configured to determine whether or not the value of the RF signal falls below a negative second threshold in the second section.

Disclosed herein is a non-destructive inspection system. The non-destructive inspection system comprises a motion platform and a tool assembly. The tool assembly is coupled to the motion platform such that the tool assembly is movable relative to the motion platform. The tool assembly comprises an inspection tool assembly that comprises a base structure coupled to the tool assembly and a plurality of probe assemblies coupled to the base structure. Each probe assembly comprises a first linear actuator and a probe, different from the probe of any other one of the plurality of probe assemblies, for inspecting a different structural feature of a structure. Each probe is moveable, along a first axis relative to another one of the probes and substantially perpendicular to the base structure, using the first linear actuator of the corresponding one of the plurality of probe assemblies.

A method and system provide for reducing gaps between two mating parts. Either or both parts may be nondestructively inspected at a plurality of locations on a surface to gather a data set relating to the part thickness. The data set may be used to calculate a set of as-built thickness values for the part and a set of deviations from a design model. A mating area may be determined for mating surfaces of the parts. One or more layers of sacrificial material in the mating area may be prepared for any deviations greater than a design allowance. The system may include a ply cutting device and an additive manufacturing device coupled to a computer to receive the sacrificial material layer data and shim data and to cut the one or more layers of sacrificial material and to construct the shim. A shim may be constructed for any deviations equal to or greater than a minimum shim thickness. The one or more layers of sacrificial material may be applied to the part, cured, and machined to a desired thickness. The shim may be applied between the part surfaces. The parts may be fitted and assembled together.