The present disclosure relates to a method of assembling hardpoints in aeronautical structures, and more specifically, the disclosed method allows knowing the relative deviation of the hardpoints and of the positioning elements of the hardpoints with respect to a laser beam emitted by a laser collimator fixed to an adjustable support which can be adjusted in at least two directions in space, and by using a correction algorithm, it is possible to know the displacement necessary for locating the positioning elements such that they are aligned with respect to the hardpoints, the positioning elements in turn being moved as a result of the movement of the driven linear tables in one or in several iterative steps, at which time the position thereof is fixed and they are ready for the rest of the hardpoints to be assembled.

The present disclosure relates to a method of assembling hardpoints in aeronautical structures, and more specifically, the disclosed method allows knowing the relative deviation of the hardpoints and of the positioning elements of the hardpoints with respect to a laser beam emitted by a laser collimator fixed to an adjustable support which can be adjusted in at least two directions in space, and by using a correction algorithm, it is possible to know the displacement necessary for locating the positioning elements such that they are aligned with respect to the hardpoints, the positioning elements in turn being moved as a result of the movement of the driven linear tables in one or in several iterative steps, at which time the position thereof is fixed and they are ready for the rest of the hardpoints to be assembled.

A torque transmitting coupling assembly for a wind turbine configured to rotatably couple a first coupling part to a second coupling part, wherein the first coupling part and the second coupling part are configured to rotate about a longitudinal axis of the torque transmitting coupling assembly, wherein the torque transmitting coupling assembly includes a torque transmitting ring and a compression ring.

An assembly apparatus includes a retainer, a position measurement device, and a machining device. The retainer is configured to hold an assembly. The position measurement device is configured to measure a difference between an intended machining position and an actual machining position of a first coupling hole in a first assembly component. The first coupling hole is capable of being coupled to the assembly. The machining device is configured to form a second coupling hole capable of communicating with the first coupling hole in the assembly based on a reference position set on the assembly and the difference.

A template holding jig for holding a template for use with a router for routing a workpiece is provided. The holding jig may also be part of a workpiece joining jig that includes a plurality of templates. The template holding jig includes a template support, a workpiece support and a template guide. The template support defines a template support plane. The workpiece support defines a workpiece support plane extending perpendicular to the template support plane. The template guide defines at least one abutment preventing motion of a template located on the template support parallel to a first axis being parallel to the workpiece support plane and parallel to the template support plane. The at least one abutment permits motion of the template parallel to a second axis being orthogonal to the workpiece support plane and perpendicular to the first axis and parallel to the template support plane.

A template holding jig for holding a template for use with a router for routing a workpiece is provided. The holding jig may also be part of a workpiece joining jig that includes a plurality of templates. The template holding jig includes a template support, a workpiece support and a template guide. The template support defines a template support plane. The workpiece support defines a workpiece support plane extending perpendicular to the template support plane. The template guide defines at least one abutment preventing motion of a template located on the template support parallel to a first axis being parallel to the workpiece support plane and parallel to the template support plane. The at least one abutment permits motion of the template parallel to a second axis being orthogonal to the workpiece support plane and perpendicular to the first axis and parallel to the template support plane.

A representative system includes an alignment tool for aligning attachment interfaces of horizontally-oriented launch vehicle portions. The tool can include a receiver assembly for connecting to a first launch vehicle portion and an actuation assembly for connecting to a second launch vehicle portion. When a first connecting element of the receiver assembly is engaged with a second connecting element of the actuation assembly, the second connecting element can apply force to the receiver assembly, and the actuator assembly applies an opposite force to the second launch vehicle portion, to align fastening features in the launch vehicle portions and/or to reshape the launch vehicle portions. A representative method includes connecting the alignment tool to the launch vehicle portions and operating the tool to apply oppositely-directed forces to align the launch vehicle portions for installing fasteners to connect the launch vehicle portions. One or more bracing beams can connect two tools together.

A tolerance compensation subassembly in the form of a tolerance compensation element or a tolerance compensation region to improve the production, maintenance and repair of aircraft. The tolerance compensation subassembly contains an actuator which is formed from an electro-active polymer so that the tolerance compensation subassembly is electrically switchable between a fixed state and a non-fixed state. As a result, automation of the assembly of aircraft components on each other can be enabled or facilitated.

A tolerance compensation subassembly in the form of a tolerance compensation element or a tolerance compensation region to improve the production, maintenance and repair of aircraft. The tolerance compensation subassembly contains an actuator which is formed from an electro-active polymer so that the tolerance compensation subassembly is electrically switchable between a fixed state and a non-fixed state. As a result, automation of the assembly of aircraft components on each other can be enabled or facilitated.

A method for installing sensors to a vehicle includes fixing a plurality of tolerance compensators to the vehicle. The method includes fixing a plurality of sensor brackets to a jig. The method includes fixing the jig to a vehicle. The method includes, after fixing the sensor brackets to the jig and the jig to the vehicle, fixing the sensor brackets to the vehicle by connecting the tolerance compensators to the sensor brackets and adjusting dimensions of the tolerance compensators to maintain positions of the sensor brackets relative to the vehicle and each other, the positions defined by the jig.