Abstract: A flexible composite that can be set to become rigid or semi-rigid includes a first layer and a second layer opposing the first layer and separated from the first layer by a space. A fill material capable of setting to a rigid or semi-rigid solid is located in the space. A plurality of elements extend substantially into the space from the first layer and/or the second layer and which may pass through the opposing layer or join with other elements present in the space from an opposing layer, thereby forming linking elements for joining the layers together. The unset fill material is provided in the space at a pressure such that tension is applied one or more of the linking elements and to cause the first and/or second layers to bulge outwards relative to the longitudinal length of said one or more linking elements under tension.

Abstract: The present invention relates to a flexible composite that can be set to become rigid or semi-rigid, the composite comprising: a first layer; a second layer opposing the first layer and separated from the first layer by a space; a fill material located in the space between the first and second layers, which is capable of setting to a rigid or semi-rigid solid on the addition of a liquid, gas or radiation; a plurality of elements extending substantially into the space from the first layer and/or the second layer and which may pass through the opposing layer or join with other elements present in the space from an opposing layer, thereby forming linking elements for joining the layers together; and wherein the unset fill material is provided in the space at a pressure such that tension is applied one or more of the linking elements and to cause the first and/or second layers to bulge outwards relative to the longitudinal length of said one or more linking elements under tension.

Abstract: The present disclosure provides a keel beam assembly, an aircraft including the keel beam assembly, and a method of aircraft manufacture using the keel beam assembly. An illustrative keel beam assembly comprises a pair of keel chords extending outside an aircraft fuselage and forming at least part of a lower keel box portion of a keel box. An upper keel box portion of the keel box is coupled to the pair of keel chords and has an aft end engaged with and secured to an aft wheel well bulkhead (AWWB).

Abstract: A connector to connect a center wing box to a bulkhead of an aircraft. The connector includes a panel with a first edge positioned at the center wing box, an opposing second edge positioned at the bulkhead, and a central section. A first flexible seal extends across the panel and provides for relative movement between the first edge and the central section. A second flexible seal extends across the panel and provides for relative movement between the second edge and the central section.

Abstract: A joint for connecting a center wing box to a bulkhead of an aircraft. The joint includes a flex angle member with a first section shaped to abut against and be connected to the center wing box, a second section shaped to abut against and be connected to a first side of the deck of the bulkhead, and an intermediate rounded corner positioned between the first and second sections. First support members are attached to the center wing box at first pins and support a first side of the second section of the flex angle member. Second support members are attached to the web of the bulkhead at second pins and support a second side of the second section of the flex angle member. The first support members are positioned on a first side of the deck of the bulkhead and the second support members are positioned on an opposing second side of the deck.

Abstract: Described herein are aircraft, comprising rear spar integration assemblies, and methods of manufacturing these aircraft. Specifically, an aircraft comprises a keel beam and a center wing box, comprising a rear spar. The rear spar is attached to the keel beam using a rear spar integration assembly. The assembly comprises a rear spar stiffener, attached to the rear spar, and having a stiffener load axis. The assembly also comprises and a keel beam fitting, attached to the keel beam, and having a fitting load axis. The rear spar stiffener is also attached to the keel beam fitting, e.g., using splice plates. More specifically, the fitting load axis is offset relative to the stiffener load axis along the primary axis of the aircraft. This offset is designed to compensate for a bending moment at the keel beam-rear spar interface, which allows reducing the size and/or the number of fasteners needed.

Abstract: Methods of making articles with a 3D printer using biomaterials that retain physical properties and biological activity are discussed. Methods can include providing a crosslinkable material and a biomaterial to a 3D printer, and crosslinking the materials to form an implant. Biomaterials can include, among other things, bone, or tissue.

Abstract: The present invention relates to shaped, bone fiber-based products and methods to make the same.

Abstract: Pressure decks, aircraft that incorporate the pressure decks, and methods of manufacturing the pressure decks, where the pressure decks include a planar center deck section configured to be attached to a keel beam of the aircraft and a pair of diagonal deck panels each extending inwardly and downwardly from a front wing spar to the planar center deck section. The pressure deck attaches the front wing spar to the keel beam at positions selected to minimize deflection stresses on the pressure deck exerted by relative movement between the front wing spar and the keel beam.

Abstract: The present invention relates to shaped, bone fiber-based products and methods to make the same.

Abstract: A joint for connecting a center wing box to a bulkhead of an aircraft. The joint includes a flex angle member with a first section shaped to abut against and be connected to the center wing box, a second section shaped to abut against and be connected to a first side of the deck of the bulkhead, and an intermediate rounded corner positioned between the first and second sections. First support members are attached to the center wing box at first pins and support a first side of the second section of the flex angle member. Second support members are attached to the web of the bulkhead at second pins and support a second side of the second section of the flex angle member. The first support members are positioned on a first side of the deck of the bulkhead and the second support members are positioned on an opposing second side of the deck.

Abstract: A connector to connect a center wing box to a bulkhead of an aircraft. The connector includes a panel with a first edge positioned at the center wing box, an opposing second edge positioned at the bulkhead, and a central section. A first flexible seal extends across the panel and provides for relative movement between the first edge and the central section. A second flexible seal extends across the panel and provides for relative movement between the second edge and the central section.

Abstract: The present disclosure provides a keel beam assembly, an aircraft including the keel beam assembly, and a method of aircraft manufacture using the keel beam assembly. An illustrative keel beam assembly comprises a pair of keel chords extending outside an aircraft fuselage and forming at least part of a lower keel box portion of a keel box. An upper keel box portion of the keel box is coupled to the pair of keel chords and has an aft end engaged with and secured to an aft wheel well bulkhead (AWWB).

Abstract: Embodiments for aircraft pressure deck. One embodiment is a pressure deck of an aircraft. The pressure deck includes beams extending longitudinally along a fuselage of the aircraft, and a web attached to an underside of the beams, the web including arches between adjacent beams to allow the pressure deck to flex laterally. The pressure deck also includes a box structure between a middle pair of the beams and configured to transfer load forward to a rear spar of a wing of the aircraft and aft to an aft wheel well bulkhead of the aircraft. The pressure deck further includes a first intercostal outboard from the box structure and configured to stabilize a first outboard pair of the beams, and a second intercostal outboard from the first intercostal and coupled between a second outboard pair of the beams via a swing link to allow the second intercostal to flex laterally.

Abstract: Described herein are aircraft, comprising rear spar integration assemblies, and methods of manufacturing these aircraft. Specifically, an aircraft comprises a keel beam and a center wing box, comprising a rear spar. The rear spar is attached to the keel beam using a rear spar integration assembly. The assembly comprises a rear spar stiffener, attached to the rear spar, and having a stiffener load axis. The assembly also comprises and a keel beam fitting, attached to the keel beam, and having a fitting load axis. The rear spar stiffener is also attached to the keel beam fitting, e.g., using splice plates. More specifically, the fitting load axis is offset relative to the stiffener load axis along the primary axis of the aircraft. This offset is designed to compensate for a bending moment at the keel beam-rear spar interface, which allows reducing the size and/or the number of fasteners needed.

Abstract: Embodiments for aircraft pressure deck. One embodiment is a pressure deck of an aircraft. The pressure deck includes beams extending longitudinally along a fuselage of the aircraft, and a web attached to an underside of the beams, the web including arches between adjacent beams to allow the pressure deck to flex laterally. The pressure deck also includes a box structure between a middle pair of the beams and configured to transfer load forward to a rear spar of a wing of the aircraft and aft to an aft wheel well bulkhead of the aircraft. The pressure deck further includes a first intercostal outboard from the box structure and configured to stabilize a first outboard pair of the beams, and a second intercostal outboard from the first intercostal and coupled between a second outboard pair of the beams via a swing link to allow the second intercostal to flex laterally.

Abstract: Pressure decks, aircraft that incorporate the pressure decks, and methods of manufacturing the pressure decks, where the pressure decks include a planar center deck section configured to be attached to a keel beam of the aircraft and a pair of diagonal deck panels each extending inwardly and downwardly from a front wing spar to the planar center deck section. The pressure deck attaches the front wing spar to the keel beam at positions selected to minimize deflection stresses on the pressure deck exerted by relative movement between the front wing spar and the keel beam.

Abstract: Techniques are disclosed to remedy thermal issues associated with antenna systems. These techniques include implementing heat pipes coupled between an external mast having antenna circuitry mounted thereon and an internal heatsink inside an environmentally-controlled location. This configuration thermally regulates heat associated with active antennas mounted to the mast, which is externally mounted onto the roof of a vehicle. The heat pipes carry heat from the mast down through the roof to the internal heatsink. The aspects described herein allow for car manufacturers to integrate mmWave technology into their vehicles while avoiding large and unsightly cooling mechanisms that would otherwise adversely impact aerodynamics and fuel efficiency.

Abstract: An appliance containment device may include a shell having a shell floor and a shell wall, and a cover having a cover floor and a cover wall. The cover wall and shell wall may be coupled together. A first mat may be coupled to the cover floor. A container cavity for receiving portions of an appliance may be formed above the cover floor and shell floor, and the cavity may be bounded horizontally by the shell wall and cover wall. Lower portions of an appliance may be positioned in the container cavity. Optionally, the device may include an encasement which may be positioned around the upper portions of the appliance with lower portions of the encasement extending into the container cavity, thereby allowing the device to encase the appliance within the shell, cover, and encasement.

Abstract: An appliance containment device may include a shell having a shell floor and a shell wall, and a cover having a cover floor and a cover wall. The cover wall and shell wall may be coupled together. A first mat may be coupled to the cover floor. A container cavity for receiving portions of an appliance may be formed above the cover floor and shell floor, and the cavity may be bounded horizontally by the shell wall and cover wall. Lower portions of an appliance may be positioned in the container cavity. Optionally, the device may include an encasement which may be positioned around the upper portions of the appliance with lower portions of the encasement extending into the container cavity, thereby allowing the device to encase the appliance within the shell, cover, and encasement.