A non-destructive inspection system is presented. The non-destructive inspection system comprises a robotic end effector having an extendable actuator and a flange-mounted roller containing an ultrasonic sensor, the flange-mounted roller connected to the extendable actuator by a pivot connection, the extendable actuator configured to extend the flange-mounted roller until the flange-mounted roller contacts an inspection surface.

Pre-impregnated composite material (prepreg) that can be cured/molded to form aerospace composite parts. The prepreg includes carbon reinforcing fibers and an uncured resin matrix. The resin matrix includes an epoxy resin component, polyethersulfone as a toughening agent, a thermoplastic particle component, a nanoparticle component and a curing agent.

A process for producing a polymeric stiffened sheet-like component, for example a panel, for aircraft construction. Production includes integration of hollow stiffening profiles, for example closed omega stringers, onto a sheet-like component, for example an external skin, where the stringers and external skin are produced from thermoplastic composite material. The stringers are integrated onto the external skin by establishing contact between the stringers and the external skin and melting thermoplastic composite material with exposure to heat and pressure at the areas of contact between external skin and stringers. Melting of the other sections of the stringers is avoided with a pressurized cooling fluid with a temperature significantly below the melting point of thermoplastic composite material, the fluid flowing through the airtight enclosed space in the stringers. Use of closed airtight thermoplastic omega stringers allows integration of the stringers onto the external skin in absence of any flexible tube within the stringers.

A method for manufacturing a one-piece reinforced structure and obtained structure is provided, the method using base components made of partially-cured composite material and joining the base components together, applying a coating made of composite material on the base components, and applying heat on the assembly formed by the base components covered with the coating until a complete curing of the assembly is obtained, such that a one-piece reinforced structure made of composite material is obtained formed by the coating and the base components adhered to the coating, wherein the base components that form part of the very manufactured structure act as a mould during the manufacturing process, thus preventing the need to use moulds on which the composite material is deposited that must be subsequently removed from the final obtained structure.

A composite panel assembly including a first panel with a first skin, a second skin, a core, and an assembly flange. A second panel includes a first skin, a second skin, a core, and an assembly flange. A fastening device is adapted to fasten the assembly flange of the first panel to the assembly flange of the second panel, wherein the core of one of the first panel or the second panel includes reinforcing pins and a high-density portion placed along the assembly flange.

An aircraft including a main landing gear compartment which comprises a rear transverse wall, and a base wall forming a sealed barrier between a first, pressurized area and a second, non-pressurized area. The main landing gear compartment includes a body, produced in a single piece from composite material, separating the first, pressurized area and the second, non-pressurized area. The body includes a first part corresponding to the base wall, as well as a second part corresponding to the rear transverse wall. At least two longitudinal beams made of composite material, are connected to the body. This single body makes it possible to eliminate a large number of parts, to simplify the assembly process, and to reduce the duration thereof.

A system and method of a modular floor assembly and installation on an aircraft is presented in embodiments herein. A floor assembly comprising an underlayment layer and a decorative layer may be assembled to provide an aircraft floor that meets Federal Aviation Regulations. The floor assembly may comprise structural, adhesive, and magnetic layers creating a floor assembly that may be quickly and easily removable for maintenance and access to compartments below the floor assembly.

A composite structure includes a first composite skin and a second composite skin spaced from the first composite skin. The first composite skin and the second composite skin define a longitudinal cavity therebetween. The composite structure further includes a plurality of spars located in the longitudinal cavity and laterally spaced from one another. The plurality of spars extends between and connects the first composite skin and the second composite skin. The composite structure further includes at least one rib located within the longitudinal cavity between a first spar and a second spar of the plurality of spars. The first spar is laterally adjacent the second spar. The at least one rib is in contact with the first composite skin, the second composite skin, the first spar and the second spar.

Disclosed is a take-off and landing station (1) for a flying vehicle (2) for transporting people and/or loads, which flying vehicle takes off and lands vertically and comprises a flight module (3), having a plurality of drive units (17) arranged on a supporting framework structure (16) of the flight module (3), and a transportation module (4), which can be coupled to the flight module (3). The take-off and landing station (1) comprises a holding apparatus (21) having a plurality of gripper elements and support elements (11) for supporting, fixing and/or orienting the supporting framework structure (16) during take-off and landing of the flying vehicle (2) or the flight module (3).

A carrier film set configured to apply a number of stiffener assemblies to a layup mandrel, the carrier film set comprising: a number of alignment features configured to align the carrier film set relative to the layup mandrel; and a number of indexing features configured to index the number of stiffener assemblies onto the carrier film set.