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.

The present invention relates to a blade (7) comprising: —a composite material structure (17), —a blade root fastening portion (9) further comprising a shoulder (10) extending into the recess from the wall—a base (18) arranged in the recess and comprising a support member configured to abut against the shoulder (10) of the blade root fastening portion (9) and a passage (39) formed in the support member, the sections (23) of the blade root portion (22) of the composite material structure extending through the passage (39), and—a blocking part (19) arranged in the recess between the two sections (23) of the blade root portion (22) such that each section of the blade root portion (23) is pressed against the support member by the blocking part (19).

Fan or propeller vane (1) for an aircraft turbomachine, the vane being made from a composite material and comprising a blade (2) and a base (3), the base being formed by a longitudinal end (41) of a spar (4) which is formed by a fibrous reinforcement formed from threads woven in three dimensions and a portion (42) of which extends inside the blade (2), the blade (2) having an aerodynamic profile which is defined by a skin (5) which is formed by woven threads and which surrounds the portion of the spar, the spar (4) and the skin (5) being embedded in a polymerised resin, characterised in that the portion (42) of the spar comprises projecting longitudinal stiffening members (6) which together delimit spaces (8) for receiving longitudinal inserts (7) which are formed from a honeycomb material.

An apparatus for securing first and second skins to a core in a composite rotor blade includes an elongated member configured to be installed through a passage in the core of the composite rotor blade. The elongated member has a first end configured to be attached to an outer surface of the first skin and a second end configured to be attached to an outer surface of the second skin. The apparatus also includes a first patch configured to adhere the first end to the outer surface of the first skin, and a second patch configured to adhere the second end to the outer surface of the second skin such the elongated member extends from the outer surfaces of the first and second skins through the passage in the core.

A resin fan includes a semi-molded article in which a first circular plate and blades are integrated. While the semi-molded article is retained, a composite mold is moved to a secondary molding side, a second mold is put in a first position and a third mold is moved to the first position and inserted into the first mold. An intermediate part extends over the inner surface-side of a large-bend part, and causes the end of the third mold to engage with the first mold. Next, resin is poured into a secondary forming mold, and a second circular plate is integrally molded continuous with the blades of the semi-molded article, and a fan is molded. Together with the opening of the second mold and the composite mold, the third mold and the composite mold are opened, each of the molds is moved to a second position.

The invention provides a fitted platform (1) for positioning between two adjacent blades of an aviation turbine engine fan, said platform comprising a flow passage wall (10) made of composite material having a central portion (16) and first and second margins (18) each extending in a longitudinal direction of said wall, each margin extending over a determined distance (D) from the central portion (16) in a transverse direction of said wall, said flow passage wall comprising fiber reinforcement densified by a matrix, the platform being characterized in that the fiber reinforcement present in the central portion (16) presents three-dimensional weaving, and in that the fiber reinforcement present in the first and second margins (18) presents two-dimensional weaving, at least in part. The invention also provides a fan module, a turbine engine, and a method of fabricating such a platform.

Embodiments are directed to systems and methods for two or more cured composite assemblies that are bonded together to form a tubular composite structure, wherein each of the cured composite assemblies do not have a tubular shape. The tubular composite structure may form a spar for an aerodynamic component, for example. The two or more cured composite assemblies may comprise carbon or fiberglass composite materials or a combination of materials. Each of the cured composite assemblies may further comprise axial edges that are configured to be bonded to another of the cured composite assemblies, wherein the axial edges have a sloped shape. An adhesive agent may be applied on the axial edges for bonding two cured composite assemblies. Alternatively, or additionally, one or more fasteners may be used to attach the axial edges of at least two cured composite assemblies.

A method of fabricating a fiber structure by multilayer three-dimensional weaving between a plurality of weft yarns and of warp yarns, the fiber structure having at least first and second portions that are adjacent in the warp direction, the first portion presenting, in a direction perpendicular to the warp and weft directions, a thickness greater than the thickness of the second portion, includes making the first portion using a step of three-dimensionally weaving warp and weft layers in which a fiber fabric is formed in the form of a Mock-Leno weave grid in a core of the first portion together with skins at a surface of the first portion, a weave of the skins being modified locally so as to deflect certain warp yarns from said skins and weave them with the fiber fabric in the form of the Mock-Leno weave grid.

There is disclosed a tool for manufacturing a composite component, the tool comprising: a skin composed of fibre reinforced plastic and defining a layup surface for the composite component, the skin having a plurality of passageways extending from the layup surface to an opposing surface of the skin; a backing secured to the skin, the backing and the skin defining a cavity therebetween; a support core disposed within the cavity and comprising a gas-permeable material in fluid communication with the passageways; and a conduit extending through the backing such that the conduit is in fluid communication with the gas-permeable material.

A method for additively printing extension segments on workpieces using an additive manufacturing machine includes controlling, with a computing system, an operation of a print head of the machine such that a region of interest of a build plate of the machine is scanned with an electromagnetic radiation beam. Additionally, the method includes receiving, with the computing system, data associated with reflections of the beam off of the build plate as the region interest is scanned. Furthermore, the method includes receiving, with the computing system, data associated with a location of the beam relative to the build plate. Moreover, the method includes determining, with the computing system, a location of a workpiece interface based on the received data. In addition, the method includes controlling, with the computing system, the operation of the print head such that an extension segment is additively printed on the determined workpiece interface.