This application provides an intelligent robot for cleaning and mending a net cage and a method of using the intelligent robot, including: a control system, a main body, an attraction module, a motion module, a cleaning module and a mending module. The main body includes a streamlined pressure casing, and a drive mechanism and a water ballast tank which are located in the pressure casing. The attraction module includes electromagnets which are symmetrically provided at a bottom of the pressure casing. The motion module includes first and second motion mechanisms which are symmetrically provided at opposite sides of the pressure casing. A traveling path of the first motion mechanisms is perpendicular to a traveling path of the second motion mechanisms. The intelligent robot achieves cleaning and mending for both sides of the net cage, and is simple to operate, safe, high-efficient, economical and convenient.

This application provides an intelligent robot for cleaning and mending a net cage and a method of using the intelligent robot, including: a control system, a main body, an attraction module, a motion module, a cleaning module and a mending module. The main body includes a streamlined pressure casing, and a drive mechanism and a water ballast tank which are located in the pressure casing. The attraction module includes electromagnets which are symmetrically provided at a bottom of the pressure casing. The motion module includes first and second motion mechanisms which are symmetrically provided at opposite sides of the pressure casing. A traveling path of the first motion mechanisms is perpendicular to a traveling path of the second motion mechanisms. The intelligent robot achieves cleaning and mending for both sides of the net cage, and is simple to operate, safe, high-efficient, economical and convenient.

A method of making an aircraft blade is provided. The method comprises the steps of: assembling two or more fibre-reinforced thermoplastic composite parts into a blade assembly; and welding the fibre-reinforced thermoplastic composite parts together utilising an additional thermoplastic located at least at locations where the parts will abut when assembled. The additional thermoplastic has a melting or softening temperature lower than a melting temperature of each of the fibre-reinforced thermoplastic composite parts being assembled. The step of welding comprises heating the blade assembly to a temperature above the melting/softening temperature of the additional thermoplastic and below the melting temperature of each of the fibre-reinforced thermoplastic composite parts so as to melt/soften the additional thermoplastic and thereby weld the fibre-reinforced thermoplastic composite parts together to form the aircraft blade.

A method of making an aircraft blade is provided. The method comprises the steps of: assembling two or more fibre-reinforced thermoplastic composite parts into a blade assembly; and welding the fibre-reinforced thermoplastic composite parts together utilising an additional thermoplastic located at least at locations where the parts will abut when assembled. The additional thermoplastic has a melting or softening temperature lower than a melting temperature of each of the fibre-reinforced thermoplastic composite parts being assembled. The step of welding comprises heating the blade assembly to a temperature above the melting/softening temperature of the additional thermoplastic and below the melting temperature of each of the fibre-reinforced thermoplastic composite parts so as to melt/soften the additional thermoplastic and thereby weld the fibre-reinforced thermoplastic composite parts together to form the aircraft blade.

Methods of fabricating wind turbine blades, leading edge protection surfaces of wind turbine blades and wind turbine protection shields using coreactive additive manufacturing. The blades, surfaces (605), and protection shields can include a single layer or multiple layers of a cured composition applied using coreactive manufacturing such as three-dimensional printing. Methods of repairing leading edge (601) surfaces of wind turbine blades include applying one or more layers of a coreactive composition onto the damaged leading edge surfaces using coreactive additive manufacturing or applying a leading edge protection shield onto a damaged leading edge (601) of a wind turbine blade.

Described is a heated gaseous welder system and associated methods of welding plastic with the heated gaseous welder system. The heated gaseous welder system includes a welding tool and a welder control unit. The welder control unit includes a gaseous control system and a heater control system. The gaseous control system is configured to selectively supply a gas to the welding tool and control at least one characteristic of the gas supplied to the welding tool. The heater control system is configured to selectively control power supplied to the welding tool.

A simple and easy repair kit to restore the structural integrity of damaged agricultural bins, specifically to repair a corner of a bin. The repair kit consists of two parts: a structural tube and a collar.

A simple and easy repair kit to restore the structural integrity of damaged agricultural bins, specifically to repair a corner of a bin. The repair kit consists of two parts: a structural tube and a collar.

Methods for repairing composite component voids are provided. For example, one method comprises locating a void in a composite component and subjecting the composite component to a process for repair. The process for repair includes creating a flow path through the void, applying a filler material to the composite component at the flow path, and processing the composite component having the filler material. In some embodiments, the flow path has a first opening on a first side of the composite component and a second opening on a second, opposite side of the composite component. In other embodiments, at least one portion of the flow path extends at a first angle with respect to a lateral direction defined by the CMC component, and at least another portion extends at a second angle with respect to the lateral direction.

Methods for repairing composite component voids are provided. For example, one method comprises locating a void in a composite component and subjecting the composite component to a process for repair. The process for repair includes creating a flow path through the void, applying a filler material to the composite component at the flow path, and processing the composite component having the filler material. In some embodiments, the flow path has a first opening on a first side of the composite component and a second opening on a second, opposite side of the composite component. In other embodiments, at least one portion of the flow path extends at a first angle with respect to a lateral direction defined by the CMC component, and at least another portion extends at a second angle with respect to the lateral direction.