Abstract: Systems and methods are provided for splicing airframe components. One embodiment is a method for assembling an airframe of an aircraft. The method includes forming a first skin of a first circumferential section of fuselage, the first skin including a distal portion comprising a lip and a shoulder, aligning a second skin of a second circumferential section of fuselage with the shoulder such that the lip overlaps the second skin, and affixing the first skin and the second skin together via a circumferential splice.

Abstract: A lamination head for laying up a composite laminate includes a material supply drum supporting roll of layup material backed by a backing layer, a first and second separation device respectively having a first and second horn, and a first and second compaction device. When the first separation device is extended, the first horn is in close proximity to the first compaction device, causing a layup material to separate from the backing layer and move underneath the first compaction device as the lamination head moves along a first direction of travel. When the second separation device is extended, the second horn is in close proximity to the second compaction device, causing the layup material to separate from the backing layer and move underneath the second compaction device as the lamination head moves along a second direction of travel opposite the first direction of travel.

Abstract: A self-threading lamination head has a material supply drum, a backing layer collection drum, and a material threading system. The material supply drum supports a material roll of layup material backed by a backing layer. The material threading system includes at least one threading belt located on one side of the lamination head. The threading belt is supported by belt rollers driven by a belt drive motor. A belt-mounted layer engagement device is coupled to the threading belt for engaging a backing layer leading edge portion. The backing layer collection drum collects the backing layer as the lamination head applies the layup material onto a substrate. The belt drive motor drives the threading belt over the belt rollers and causes the belt-mounted layer engagement device to thread the backing layer through the lamination head, and position the backing layer leading edge portion proximate the backing layer collection drum.

Abstract: An apparatus for processing a composite structure includes a first processing-tool and a second processing-tool that are movable between an open position, in which the first processing-tool and the second processing-tool are separated from each other, and a closed position, in which the first processing-tool and the second processing-tool are configured to be sealed to each other. In the closed position, the first processing-tool and the second processing-tool are configured to be sealed to a mandrel-tool, located between the first processing-tool and the second processing-tool and supporting the composite structure. In the closed position, the first processing-tool, the second processing-tool, and the mandrel-tool form a vessel, configured to apply at least one of pressure and heat to the composite structure.

Abstract: Methods and apparatus involved in the process of hardening a composite part are disclosed herein. The methods include applying a preform to a mandrel, covering the preform with a caul plate, sealing the caul plate to the mandrel, pushing the caul plate toward the preform and the mandrel and hardening the preform into a composite part while the caul plate is held against the preform. The apparatus include a mandrel, a caul plate which defines a surface of a preform and where the caul plate may include a rigid material and seals disposed between the mandrel and the caul plate. In an additional aspect, the apparatus may include a sealed chamber with a mandrel and a caul plate and a circumferential seal between the mandrel and the caul plate.

Abstract: A method of processing a composite structure includes a step of positioning a first processing tool of a tooling assembly and a second processing-tool of the tooling assembly from an open position, in which the first processing-tool and the second processing-tool are spaced apart, to a closed position, in which the first processing-tool and the second processing-tool are sealed to each other and are sealed to a mandrel-tool, supporting the composite structure, to form a vessel that surrounds the composite structure. The method also includes a step of processing the composite structure.

Abstract: Described are methods and systems for manufacturing curved composite stringers. Such composite stringers may have in-plane and/or out-of-plane bends, which are formed while shaping composite charges. Specifically, a composite charge is shaped using a pallet, comprising a plurality of independent pallet portions, rotatably coupled to each other. A hat portion is formed when a part of this charge is conformed to a cavity in the pallet. The pallet portions are rotated relative to each other while forming the hat portion and/or when the hat portion already conforms to the cavity. In some examples, the die is bent together with the charge, when the pallet portions are rotated. This rotation produces one or more of in-plane and/or out-of-plane bends. In some examples, flange portions of the composite charge are positioned in a temporary orientation, e.g., to enable bending of the charge and reduce wrinkles.

Abstract: A method of fabricating a composite structure is presented. The method comprises laying up a plurality of composite plies over a layup mandrel; positioning a first caul plate and a second caul plate over the plurality of composite plies, leaving composite material exposed; removing at least part of the composite material exposed between the first caul plate and the second caul plate to separate a first composite section from a second composite section; curing the first composite section and the second composite section to form a first composite part and a second composite part; and removing the first composite part and the second composite part from the layup mandrel immediately following curing.

Abstract: A method of producing a composite part using first and second mandrels is presented, wherein each of the mandrels has a respective side, a respective generally planar tool surface for forming a respective portion of the composite part thereon and a respective chamfer between the respective side and the respective tool surface. The method includes disposing the first and second mandrels with their respective sides abutted with each other such that the tool surfaces are flush with each other and define a generally planar combined surface and the chamfers define a trough, placing an elastomeric plug in the trough, wherein the elastomeric plug substantially fills the trough, and applying a layer of composite material across the generally planar combined surface and across a top surface of the elastomeric plug so as to form the composite part. A tooling set for producing a composite part using the method is also presented.

Abstract: A membrane assembly for vacuum bagging includes an elongate sheet of flexible material capable of being rolled up into a cylindrical configuration and unrolled from the cylindrical configuration into a flattened-out configuration, a bistable tape spring attached to or captured by the elongate sheet, and an inflatable tube attached to or captured by the elongate sheet. The bistable tape spring has a first stable state which is a straightened-out state, a second stable state which is a rolled-up state, and a transition state between the first and second stable states. The inflatable tube is sealed at one end and has an orifice at the other end for admission of a fluid therethrough for inflation of the inflatable tube.

Abstract: Described are methods and systems for manufacturing curved composite stringers. Such composite stringers may have in-plane and/or out-of-plane bends, which are formed while shaping composite charges. Specifically, a composite charge is shaped using a pallet, comprising a plurality of independent pallet portions, rotatably coupled to each other. A hat portion is formed when a part of this charge is conformed to a cavity in the pallet. The pallet portions are rotated relative to each other while forming the hat portion and/or when the hat portion already conforms to the cavity. In some examples, the die is bent together with the charge, when the pallet portions are rotated. This rotation produces one or more of in-plane and/or out-of-plane bends. In some examples, flange portions of the composite charge are positioned in a temporary orientation, e.g., to enable bending of the charge and reduce wrinkles.

Abstract: Provided are methods and devices for supporting of variety of different pre-cured composite stringers after forming and prior to curing. A post-forming processing device comprises a base with a channel for receiving hat portions of different stringers. The device also comprises a support structure, at least partially extending within the channel. The support structure is configured to conform to different hat portions and to retain the shape of these hat portions. For example, the support structure is made from a flexible material, which conforms to any shape variations. In some examples, the support structure is made from a jamming material that is reshaped together with each of the pre-cured composite stringers. A post-forming processing device is used for supporting different pre-cured composite stringers while various operations are performed on these stringers, such as stringer trimming, inspection, installation of bladders and noodles, and the like.

Abstract: A manufacturing system includes a first mandrel, a second mandrel, and laminate securing mechanisms. The first mandrel has a first mandrel surface and a first mandrel surface edge. The second mandrel has a second mandrel surface and a second mandrel surface edge, and is positionable in a closed position in which the first mandrel surface edge and the second mandrel surface edge are in contact to form a continuous mandrel surface collectively defined by the first mandrel surface and the second mandrel surface. The second mandrel translates to an open position defining a gap between the first mandrel surface edge and the second mandrel surface edge for receiving a forming die. The laminate securing mechanisms secure the composite laminate on at least one of the first mandrel and the second mandrel during trimming and/or forming of the composite laminate.

Abstract: A manufacturing system includes a plurality of lamination heads and a head-moving system defining a continuous loop lamination path configured to move the lamination heads in series along the lamination path. The manufacturing system also includes at least one lamination mandrel positioned along a portion of the lamination path. The lamination heads are each configured to dispense a layup material onto the at least one lamination mandrel or onto layup material previously applied onto the lamination mandrel while the lamination heads are moved by the head-moving system through one or more revolutions of the lamination path to lay up a composite laminate.

Abstract: A lamination head having bi-directional layup capability has a material supply drum configured to support a material roll of backed material which is comprised of layup material backed by a backing layer. A backing layer separation assembly receives the backed material from the material supply drum and has a backing layer directional control device and first and second backing layer separation mechanisms. The backing layer directional control device in the first mode separation position is aligned with the first backing layer separation mechanism for separating the backing layer from the layup material as the lamination head moves along a first direction of travel. The backing layer directional control device in the second mode separation position is aligned with the second backing layer separation mechanism for separating the backing layer from the layup material as the lamination head moves along a second direction of travel.

Abstract: A system for manufacturing a composite assembly includes a first mandrel, a second mandrel, a first wrap plate, and a second wrap plate. The first wrap plate and the second wrap plate are positionable in side-by-side relation for receiving a wrap material stack. The first wrap plate and/or the second wrap plate are translatable to a wrap plate open position defining a wrap plate gap between the first and second wrap plate surface edge for receiving a bladder. The second mandrel is translatable to a mandrel open position defining a mandrel gap between the first and second mandrel surface edge. The wrap plate gap and the mandrel gap are configured to receive the wrap material stack formed around a bladder. The first and second wrap plate are configured to fold a first and second material stack base portion into overlapping relation with each other on the bladder top.

Abstract: 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.

Abstract: A lamination head has a material supply drum, a backing layer collection drum, and a backing layer separation assembly. The material supply drum supports a material roll of backed material comprising layup material backed by a backing layer. The backing layer collection drum moves from a collection drum home position to a collection drum engagement position proximate the material supply drum, engage a backing layer leading edge on the material roll, and moves back to the collection drum home position while dispensing a threadable portion of at least the backing layer. The backing layer separation assembly has a backing layer separation device and a backing layer separation mechanism. The backing layer separation device translates from a separation device home position to a separation device engagement position and pulls the threadable portion into proximity to the backing layer separation mechanism for separating the backing layer from the layup material.

Abstract: A method of fabricating a composite structure is presented. The method comprises laying up a plurality of composite plies over a layup mandrel; positioning a first caul plate and a second caul plate over the plurality of composite plies, leaving composite material exposed; removing at least part of the composite material exposed between the first caul plate and the second caul plate to separate a first composite section from a second composite section; curing the first composite section and the second composite section to form a first composite part and a second composite part; and removing the first composite part and the second composite part from the layup mandrel immediately following curing.

Abstract: A plurality of segments of radius filler is positioned onto a radius filler forming tool. The plurality of segments of radius filler is applied to a stringer in a single placement step.