The present invention is an automated wind turbine servicing system that includes a rover, and uses an active electro-mechanical gripping roller system to attach to the horizontally positioned airfoil and navigate along it in order to clean, inspect, service (paint, remove material or repair), or otherwise maintain the wind turbine airfoil. An electromechanical compression system adapts to various turbine airfoil profiles so that it can be used to service many different types of wind turbines. The rover operates on a horizontal airfoil rather than a vertical airfoil to utilize gravity and prevent movement along the chord of the airfoil. Once secured to the airfoil, the rover activates a drive system that propels the rover along the airfoil as it travels along the upper edge, using wind pressure, the rover wheels' frictional adherence to the airfoil, and gravity to assist in coupling the rover to the airfoil. The rover, which preferably includes a robotic arm, is able to utilize multiple tools to perform various tasks such as inspecting, cleaning, sanding, repairing, painting and laying leading edge protection tape as well as vortex generators on the surface of the airfoil.

A first thermoplastic component and a second thermoplastic component including a first joint portion and a second joint portion, respectively, are provided. A least a portion of a surface area of each of the first and second joint portions include a respective first and second mating surface. The first and second mating surfaces of the respective first and second joint portions are positioned in contact with one another. The first and second joint portions are fusion joined. Fusion joining the first and second joint portions forms a fused unitary portion of the first and second thermoplastic components.

Disclosed herein is a method of repairing surface damage in an exterior surface of a hollow bladder, made of a cured elastomer. The method comprises placing first strips, made of an uncured elastomer, at least partially within the surface damage in the exterior surface of the hollow bladder in a side-by-side arrangement. The method also comprises sealing the surface damage, the first strips, and a portion of the exterior surface surrounding the surface damage in a vacuum bag. The method further comprises reducing pressure within the vacuum bag relative to outside the vacuum bag. The method additionally comprises while the pressure within the vacuum bag is reduced, heating the first strips from within the vacuum bag to cure the first strips.

The invention relates to a high-strength and permanently elastic curable adhesive for bonding at least two surfaces, of which at least one surface is a surface of a permanently elastic plastic wherein the adhesive is an adhesive that cures in at least two different hardening mechanisms, wherein the first hardening mechanism comprises a chemical reaction to form a chemical bond including a sulphur atom, and the second hardening mechanism comprises the formation of crystalline structures from amorphous polymers. The invention also relates to a method for high-strength and permanently elastic bonding of at least two surfaces to one another, of which at least one surface is that of a permanently elastic plastic, by means of such an adhesive, said method comprising the steps of: applying the adhesive to at least a first of the surfaces to be connected, ensuring conditions under which at least the first hardening mechanism of the adhesive can take place, bringing the first surface into contact with the second surface, and ensuring conditions under which the second hardening mechanism of the adhesive can take place.

The present invention provides a composition as well as a method for repairing deep scratches, gouges, etc. and which is particularly useful for aircraft and aerospace transparency repair. The composition is a blend of a polishable two-part, solvent-free, polyurethane coating composition for repairing the transparencies and which, after application, cures to a thermoset polyurethane. An optical grid is emplaced over the area to be repaired prior to applying the blend.

A method of repairing a surface defect with a patch is provided. A fibrous substrate is impregnated with a formulation that includes a polyester resin, a crosslinking agent, a solvent, and a particulate filler. The fibrous substrate is contacted with the surface defect. The formulation is exposed to actinic radiation to induce cure of the formulation to form the patch to repair the surface defect. A kit is also provided that includes a bottle containing the formulation. A sheet of fibrous support material is also provided that is adapted to receive the formulation therethrough. Instructions for repairing a surface defect by the aforementioned method are also provided as part of the kit. 3D printing of an article to fit in the surface defect is also disclosed.

The present invention provides a composition as well as a method for repairing deep scratches, gouges, etc. and which is particularly useful for aircraft and aerospace transparency repair. The composition is a polishable two-part, solvent-free, composition polyurethane coating for repairing the transparencies and which, after application, cures to a thermoset polyurethane.

Provided herein are abrasive compositions that use surfactants containing block copolymers of both propylene oxide and ethylene oxide moieties. Abrasive compositions derived from these copolymers were capable of providing both superior levels of cut rate while preserving a high quality surface finish on gelcoat surfaces comparable to those achieved using conventional rubbing compounds.

A method of repairing damage to a composite material having a composite substrate and at least one layer of shielding material includes: a) removing damage to the at least one layer of shielding material by creating a hole in the at least one layer of shielding material; b) applying a patch of shielding material in the region of the hole via a resin, wherein a ratio of a resin weight to a weight of the patch of shielding material lies in a range between about 0.45-0.55; and c) curing the resin, wherein an absorptive, consumable material is positioned in contact with the resin during at least a portion of the curing.

The present disclosure provides a method of repairing a damaged portion of a panel formed of composite material. The method includes preparing the damaged portion for repair and applying a pressure responsive adhesive layer to substantially cover the damaged portion. The method also includes disposing a vacuum-assisted resin transfer molding repair patch assembly to substantially cover the damaged portion and substantially covering the repair patch assembly with a vacuum bag assembly. Resin is introduced into and impregnates the repair patch assembly. The repair patch assembly is cured after being impregnated.