Auto-aligning vacuum presses, that include a mobile assembly with a first platen, a vacuum docking station with a second platen, a first locating device to guide the mobile assembly to a desired location along the Y-axis as the mobile assembly moves along the X-axis into the vacuum station, and a second locating device to guide one of the first and second platens along the Z-axis into sealing engagement with the other platen.

A method of manufacturing a composite part having a curved or radiused corner to avoid wrinkling or bridging of outer-most composite plies during consolidation and cure, including laying up composite material on male or female tooling to form two flanges extending at a first angle relative each other and a curved or radiused corner extending between the two flanges. Then the method may include changing an orientation of one or both of the flanges of the composite material, such that the two flanges extend at a second included angle relative each other. The second included angle is smaller than the first angle. The method may also include a step of consolidating the composite material before, after, or during the step of changing the orientation of the composite material to the second angle, as well as a step of curing the composite material oriented at the second angle.

The present invention relates to sandwich panels used as aircraft interior parts. In addition to provide a finishing function, the sandwich panels need to have certain mechanical properties and have sufficient fire resistance to retard the spread of fire within the vehicle interior. The present invention provides an aircraft interior panel with skins comprising natural fiber reinforced composites based either on an inorganic thermoset resin or a thermoplastic resin. Such panels provide the required flame and heat resistance, allow easy recycling and disposal, are cheaper and offer significant weight savings over conventional sandwich panels.

A composite prepreg laminate such as a hat type-stringer is formed on a contoured mandrel using a combination of mechanical sweeping and vacuum forming.

A method for producing a hollow composite structure, such as a spar beam for a wind turbine blade, includes placing a membrane within a mold tool, the membrane being permeable to air and impermeable to resin. A mandrel is placed within the mold tool, the mandrel enclosed in an air tight layer that includes a vent. Fiber reinforcement material is placed around the mandrel within the mold tool and the membrane is sealed at least partly around the fiber reinforcement material and mandrel. The mold tool is closed with the vent line from the mandrel extending through the sealed membrane to outside of the mold tool. A vacuum is drawn in the mold tool while the mandrel is vented to outside of the mold tool, and while the vacuum is being drawn, resin is infused into the mold tool around the mandrel such that the resin is drawn towards the membrane.

A processing apparatus such as a heating and/or debulking apparatus that may be used to debulk a plurality of uncured composite layers to form an article such as an aircraft component may include a plurality of interconnected smart susceptor heater blankets. The plurality of smart susceptor heater blankets may be connected in series or in parallel, and may be controlled to uniformly heat the component during formation. The plurality of smart susceptor heater blankets may be supported by a deployment system that lowers the plurality of smart susceptor heater blankets toward, and raises the plurality of smart susceptor heater blankets away from, a working surface.

A processing apparatus such as a heating and/or debulking apparatus that may be used to debulk a plurality of uncured composite layers to form an article such as an aircraft component may include a plurality of interconnected smart susceptor heater blankets. The plurality of smart susceptor heater blankets may be connected in series or in parallel, and may be controlled to uniformly heat the component during formation.

A method of forming a barrel portion including obtaining a mandrel shaped to define at least an inner surface of a barrel portion of the bat, wrapping a first plurality of layers of fiber composite material about the mandrel, placing a removable material over a first portion of the first plurality of layers, and wrapping a second plurality of layers of fiber composite material over the removable material and the portion of the first plurality of layers not covered by the removable material for form an assembly. The method further includes separating the mandrel from the assembly, inserting an expandable member within the assembly, inserting the assembly into a barrel-forming mold, and molding the assembly in a single molding cycle, curing the first and second layers with the removable material to form the barrel portion of the bat, and removing the removable material and the member from the barrel portion.

A processing apparatus such as a heating and/or debulking apparatus that may be used to debulk a plurality of uncured composite layers to form an article such as an aircraft component may include a plurality of interconnected smart susceptor heater blankets. The plurality of smart susceptor heater blankets may be connected in series or in parallel, and may be controlled to uniformly heat the component during formation.

There is disclosed a lay-up apparatus for laying up fibre reinforcement material, the lay-up apparatus comprising a lay-up tool defining a lay-up surface, a placement head having a flexible membrane which is conformable to the layup surface, and a membrane vacuum port extending through the membrane and configured to hold a ply against the membrane when suction is applied through the membrane vacuum port. The placement head is configured to cooperate with the lay-up tool so that when a ply is held against the membrane, an airtight chamber is formed between the membrane and the lay-up tool. The lay-up tool comprises a consolidation vacuum port configured to permit evacuation of the airtight chamber to cause the membrane and ply to move towards the lay-up surface.