A conditioning agent (typically for use in repairing a flaw in a glazing panel) is contained in a sealed container which is itself disposed internally of a flexible outer walled container. Pressure applied to the outer flexible walled container can cause release of the conditioning agent from the internal conditioning agent container. The conditioning agent preparation may comprise a hygroscopic solvent (such as acetone) combined with one or more primer additives to prime the surface of the glazing panel for repair.

A robot end effector for surface preparation in an automated inspection and repair system for composite parts has an end effector body and a plasma control unit and a plasma jet nozzle supported on the end effector body. The plasma control unit directs a jet of atmospheric plasma through the plasma jet nozzle. A slave tool changer is secured to the end effector body. The slave tool changer releasably and operatively connects the robot end effector to an industrial robot such that the industrial robot can move the robot end effector along a composite part as the plasma control unit directs a jet of atmospheric plasma through the plasma jet nozzle toward the composite part to clean the composite part and increase a surface free energy of the composite part.

A machine tool arranged to deliver an energy source through a processing head onto a work-piece, wherein; the machine-tool has a clamping mechanism arranged to temporarily receive the processing-head, or another machining or processing-head, to process a work-piece; the processing-head comprising one or more guiding mechanisms arranged to direct the energy source onto a work-piece and a processing-head docking-manifold arranged to have connected thereto one or more media to be, in use, supplied to the processing-head to facilitate processing of the work-piece; wherein the processing-head docking-manifold allows the one or more media to be supplied to the processing-head when the processing-head is connected to the clamping mechanism; and wherein the machine-tool also comprises at least one mechanism arranged to move a supply docking-manifold into and/or out of connection with the processing-head docking-manifold such that when the two manifolds are connected the or each media is supplied to the processing head.

A machine tool arranged to deliver an energy source through a processing head onto a work-piece, wherein; the machine-tool has a clamping mechanism arranged to temporarily receive the processing-head, or another machining or processing-head, to process a work-piece; the processing-head comprising one or more guiding mechanisms arranged to direct the energy source onto a work-piece and a processing-head docking-manifold arranged to have connected thereto one or more media to be, in use, supplied to the processing-head to facilitate processing of the work-piece; wherein the processing-head docking-manifold allows the one or more media to be supplied to the processing-head when the processing-head is connected to the clamping mechanism; and wherein the machine-tool also comprises at least one mechanism arranged to move a supply docking-manifold into and/or out of connection with the processing-head docking-manifold such that when the two manifolds are connected the or each media is supplied to the processing head.

An apparatus is provided for analysis of a repair for a structure by identifying component parts of the structure that have common material properties and geometric constraints, and based thereon determining a generic repair component for the component parts that also have the common material properties and the geometric constraints. A set of loads are extracted from a loads model of the undamaged structure and redistributed in a loads redistribution model at a damaged or defective portion of the component part. The set of redistributed loads indicate loading incurred by the generic repair component under an external load. The apparatus then uses the redistributed loads to perform an analysis to determine a margin of safety of the generic repair component and, in instances in which the margin of safety is positive, outputs the material properties and geometric constraints of the generic repair component to a fabrication system for production thereof.

A method of inspection and repair of a joint in an assembly. The joint is formed by a first work piece and a second work piece. An adhesive placed between the first and second work pieces to define the joint. The assembly includes an ultrasonic welding device including an ultrasonic horn configured to deliver ultrasonic energy to the joint. A controller is operatively connected to the ultrasonic welding device. The controller includes a processor and tangible, non-transitory memory on which is recorded instructions for executing a method of inspecting and repairing the adhesive-bonded joint. The controller is programmed to deliver a first ultrasonic pulse (P1) to the joint, via the ultrasonic welding device, and determine an adhesive coverage (AC) based at least partially on the first ultrasonic pulse (P1).

A method of inspection and repair of a joint in an assembly. The joint is formed by a first work piece and a second work piece. An adhesive placed between the first and second work pieces to define the joint. The assembly includes an ultrasonic welding device including an ultrasonic horn configured to deliver ultrasonic energy to the joint. A controller is operatively connected to the ultrasonic welding device. The controller includes a processor and tangible, non-transitory memory on which is recorded instructions for executing a method of inspecting and repairing the adhesive-bonded joint. The controller is programmed to deliver a first ultrasonic pulse (P1) to the joint, via the ultrasonic welding device, and determine an adhesive coverage (AC) based at least partially on the first ultrasonic pulse (P1).

An indication device for monitoring the structural integrity of a repair location on a laminate structure, produced from a composite material, of a part of an aircraft outer skin is specified. The indication device has at least one elongate, thin indicator strip. The indicator strip is detachably applied to the outer layer of the laminate structure in the immediate vicinity of the repair location. The indicator strip is designed to indicate a predefined residual strength of an adhesive joint of a repair patch to the surrounding composite material.

An indication device for monitoring the structural integrity of a repair location on a laminate structure, produced from a composite material, of a part of an aircraft outer skin is specified. The indication device has at least one elongate, thin indicator strip. The indicator strip is detachably applied to the outer layer of the laminate structure in the immediate vicinity of the repair location. The indicator strip is designed to indicate a predefined residual strength of an adhesive joint of a repair patch to the surrounding composite material.

An additive manufacturing machine for repairing a component includes a build platform that supports the component and a powder dispensing assembly for selectively depositing additive powder over the build platform. A powder seal assembly includes a powder support plate positioned above the build platform and defining an aperture for receiving the component without contacting the component. A clamping mechanism is movable relative to the powder support plate and defines a void for receiving a resilient sealing element around the aperture. An actuating mechanism, such as bolts or a linear actuator, moves the clamping mechanism toward the powder support plate to deform the resilient sealing element until the resilient sealing element contacts and forms a seal with the component.