The invention relates to achieve a rapid, reproducible and reliable characterization of the quality of ply-by-ply machining of multilayer materials. This method for inspecting ply-by-ply machining of a part (10) made of multilayer composite material under repair by machining a ply-by-ply staggered or continuously sloped cut out in a stack of plies of various successive orientations includes taking images (IA to ID), under lighting of different orientations (12), of a surface area (10a) of the machined part (10) to be inspected; performing an analysis by comparing the images (IA to ID) pixel by pixel (P0) in order to define the orientation of each pixel (P0) as corresponding to that of the image in which this pixel has a higher brightness; if the pixel has a similar brightness in all the images (IA à ID), this pixel (Pr) is attributed to a resin; constructing a map (5) in units of ply of the surface area to be inspected (10a) by applying the preceding analysis to all of the pixels; estimating a machining quality level from the map (5) produced, and archiving (2m) each map (5) thus produced as a machining result.

The present disclosure describes one or more systems, methods, routines and/or techniques for thermal management. One or more systems, methods, routines and/or techniques may provide advice or guidance (e.g., to a repair technician) regarding how to perform a hot bond repair, for example, on an aircraft component that has been damaged. The thermal management advisor may provide advice or guidance regarding how to prepare a repair field prior to running a thermal survey. For example, thermal management advisor may recommend a particular heat blanket, a configuration of the heat blanket, placement of various temperature sensors and other preparation guidance. The thermal management advisor may provide advice or guidance regarding how to alter or manage the repair setup during a thermal survey and during the actual curing process. For example, thermal management advisor may recommend particular temperature sensors or areas of the repair field that should be insulated.

A method for repairing a honeycomb core sandwich structural body according to the present invention is a method in which a damaged portion that is formed in a honeycomb core sandwich structural body where a honeycomb structured core is held between a first outer skin and a second outer skin and that reaches the core through the first outer skin is repaired, the method including: a repair material mounting step of mounting a repair material on the damaged portion, the repair material including a patch that covers an opening of the damaged portion, and one or a plurality of braces that support the patch; a patch bonding step of bonding the patch to the first outer skin; and a brace bonding step of bonding the brace to the second outer skin or the core.

A method of repairing a damaged spar cap of a wind turbine blade of a wind turbine, the damaged spar cap including carbon fiber-reinforced plastic and the method having the steps of: removing a damaged carbon fiber-reinforced plastic part from the damaged spar cap to obtain a corresponding recess in the damaged spar cap, applying an adhesive to the recess, and fitting at least one patch including carbon fiber-reinforced plastic into the recess, is provided.

The present invention provides an aircraft structure comprising a structural component and a set of reinforcing straps for reinforcing the structural component, wherein the set comprises a first reinforcing strap having an inner and outer surface, wherein the inner surface is attached to a first surface of the structural component such that the first reinforcing strap extends longitudinally along the structural component and a second reinforcing strap having an inner and outer surface, wherein the inner surface is attached to the outer surface of the first reinforcing strap such that the second reinforcing strap extends longitudinally along the first reinforcing strap. The invention also provides an aircraft, a method of reinforcing an aircraft structure and a method of inspecting an aircraft structure.

The present invention provides an aircraft structure comprising a structural component and a set of reinforcing straps for reinforcing the structural component, wherein the set comprises a first reinforcing strap having an inner and outer surface, wherein the inner surface is attached to a first surface of the structural component such that the first reinforcing strap extends longitudinally along the structural component and a second reinforcing strap having an inner and outer surface, wherein the inner surface is attached to the outer surface of the first reinforcing strap such that the second reinforcing strap extends longitudinally along the first reinforcing strap. The invention also provides an aircraft, a method of reinforcing an aircraft structure and a method of inspecting an aircraft structure.

A repair patch for a composite edge includes a plurality of laminations laid face-to-face in a lamination direction defined along a thickness direction of the blade edge. At least an uppermost one of the laminations includes first and second transverse peripheral edges and at least the first peripheral edge includes a first portion defining a first edge plane at a first axial location along the second peripheral edge and a second portion defining a second edge plane at a second axial location along the second peripheral edge.

A repair patch for a composite edge includes a plurality of laminations laid face-to-face in a lamination direction defined along a thickness direction of the blade edge. At least an uppermost one of the laminations includes first and second transverse peripheral edges and at least the first peripheral edge includes a first portion defining a first edge plane at a first axial location along the second peripheral edge and a second portion defining a second edge plane at a second axial location along the second peripheral edge.

A quick-repair patch for renovating external damage, and quick-repair method for quick repairs of local and structurally mechanically irrelevant damage to aircraft components. The quick-repair patch has a layer structure with a plastic film, to which lightning protection is applied, and an adhesive layer, which is arranged at least on the plastic film. The quick-repair patch can be adhesively bonded to the damage such that the lightning protection is in electrical contact with the lightning protection of the component. The quick-repair patch can have a QR code or an RFID tag, by which specifications relating to the quick-repair patch or to the quick repair can be stored or retrieved.

A quick-repair patch for renovating external damage, and quick-repair method for quick repairs of local and structurally mechanically irrelevant damage to aircraft components. The quick-repair patch has a layer structure with a plastic film, to which lightning protection is applied, and an adhesive layer, which is arranged at least on the plastic film. The quick-repair patch can be adhesively bonded to the damage such that the lightning protection is in electrical contact with the lightning protection of the component. The quick-repair patch can have a QR code or an RFID tag, by which specifications relating to the quick-repair patch or to the quick repair can be stored or retrieved.