An autonomous or semi-autonomous cell for inspecting composite parts, verifying repairs made to such parts, and facilitating repairs to composite parts. The cell employs automated inspection, damage assessment, and repair systems. An industrial robot automatically attaches to a set of interchangeable inspection and repair end effectors to carry out the inspection, verification, and repair processes. The cell can be equipped with fixtures for supporting a rotorcraft blade and rotating the blade within the cell so that the robot can access the entire blade. Processes are provided for performing inspections, tracking the inspection data for parts in a database, and carrying out repairs. Over time, a software applicant can use the inspection data to train a machine learning model for recognizing damage to the composite part based on inspection images.

Methods and apparatus for performing repair operations using an unmanned aerial vehicle (UAV). A UAV carries a repair patch ensemble containing all repair materials (including a repair patch, a heating blanket and other ensemble materials) in a prepackaged form to the repair area. During flight of the UAV, the repair patch is vacuum adhered to the heating blanket. Vacuum pressure is also used to hold the repair patch ensemble in position on the composite surface of the structure. Then the hot bond process is enacted to bond the repair patch to the repair area. In accordance with one embodiment, the hot bond process involves heating the repair patch to adhesively bond the repair patch while applying vacuum pressure to consolidate the composite material. Then the repair patch is released from the ensemble and residual ensemble materials (heating blanket, bleeder material, and release films) are removed by the UAV.

This invention relates to a multi-part kit system to repair damaged products used in industrial applications, comprising a part A which comprises A1) MDI prepolymer, A2) fumed silica and A3) plasticizer; a part B which comprises B1) hydroquinone di-(2-hydroxyethyl)ether and B2) plasticizer; and a part C which comprises C1) polyol, C2) optionally catalyst and C3) optionally plasticizer.

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 for repairing a composite structure using pre-cured plugs. In accordance with one method, composite material is removed from a first composite laminate to form a cavity bounded by a tapered internal surface that extends from an opening at an outer mold line surface of the first composite laminate. In addition, a second composite laminate is machined to form a plug having a tapered surface. Then the plug is placed so that the tapered surface of the plug opposes the tapered internal surface of the first composite laminate. Thereafter, the tapered surface of the plug is bonded to the tapered internal surface of the first composite laminate. Optionally, a hole is drilled in the plug for receiving a fastener.

Provided herein is a method to reinforce a junction of fiber-composite aircraft components forming an elongate conduit. The method comprises (a) abrading the junction and (b) applying sealant along the junction from a tool moveable through the conduit, the tool exerting force on an interior surface of the conduit opposite the junction.

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 repair and reinforcement method for an aircraft is provided. The method includes cleaning a corroded portion of a structure of the aircraft, applying an adhesive layer to the cleaned portion of the structure and forming a polymer matrix composite (PMC) patch for application to the adhesive.

A tire repair tool includes a housing, an electric motor disposed within a motor housing portion, a battery receiving portion configured to receive a battery pack to power the electric motor, an actuator configured to selectively activate the electric motor, and a chuck rotatably driven by the motor and configured to receive one of a plurality of different tire repair accessories. The tire repair tool further includes a multi-speed gearbox disposed within the motor housing portion having a plurality of different gear ratios, a mode selector operative to adjust the multi-speed gearbox between the plurality of different gear ratios, and an electronic speed control system configured to operate the electric motor at less than its capable maximum operating speed when the gearbox is operated in each of the plurality of different gear ratios to further reduce a rotational speed of the chuck.

This invention relates generally to a nozzle, method thereof and a kit set for the same for spreading material on curved surface, in the field of repairing services for wind turbine blades and other similar composite components. More particularly, the present invention relates to a nozzle for spreading material on a leading edge of a wind turbine blade for guiding the material along the surface, generally, for repairing or upgrading. In addition it relates to a method and a kit for performing the application.