A device for attaching an object to an attachment rail, particularly a seat rail, in an aircraft or spacecraft. A base part has a support surface to be placed onto an outer surface of the rail, and a locking element to partially protrude from the support surface along a line of protrusion. The base part and locking element are coupled or configured to be coupled wherein the locking element can be moved relative to the base part along the line of protrusion and rotated with respect to the base part. An end section of the locking element has a tip portion shaped in a dovetail-type manner. The device includes a tensioning arrangement for tensioning the locking element with respect to the rail. An arrangement includes such a device as well as an attachment rail with a rail main body and a plurality of bushes. A method for attaching an object, and a seat rail are disclosed.

Example methods and systems for isolating and alleviating load in an aircraft are described, comprising providing a sliding joint between a seat track and a flight deck floor panel. The sliding joint comprises a lug comprising a first end and a second end opposite the first end, wherein the first end is adapted to attach to the seat track and the second end comprises an elongate aperture, and a clevis comprising an oblate shaped slider bushing that is coupled to the lug.

An aircraft has an aft main cargo cabin with a low deck floor, and a rear access configured to provide access to the aft main cargo cabin from behind the fuselage. The deck floor of the aft main cargo cabin is lower than a first deck floor of a forward main cabin of a forward section of the fuselage. The aft main cargo cabin has a second height that is greater than the first height of the forward main cabin, allowing the aft main cargo cabin to accommodate oversize cargo with larger dimension(s). The aircraft may be built with such an aft main cargo cabin and rear access, or may be a modified aircraft that includes such an aft main cargo cabin and rear access. Related methods of reconfiguring a base aircraft into a modified aircraft having such an aft main cargo cabin and rear access are also disclosed.

An aircraft has an aft main cargo cabin with a low deck floor, and a rear access configured to provide access to the aft main cargo cabin from behind the fuselage. The deck floor of the aft main cargo cabin is lower than a first deck floor of a forward main cabin of a forward section of the fuselage. The aft main cargo cabin has a second height that is greater than the first height of the forward main cabin, allowing the aft main cargo cabin to accommodate oversize cargo with larger dimension(s). The aircraft may be built with such an aft main cargo cabin and rear access, or may be a modified aircraft that includes such an aft main cargo cabin and rear access. Related methods of reconfiguring a base aircraft into a modified aircraft having such an aft main cargo cabin and rear access are also disclosed.

A heater panel includes a core and a heater/dielectric layer including a positive thermal coefficient (PTC) heater layer between a pair of dielectric layers. A structural facing is included, wherein the heater/dielectric layer is bonded directly between the core and the structural facing. A second structural facing can be bonded to the core opposite the heater/dielectric layer. An impact layer can be bonded to the structural facing, e.g., the first structural facing described above, opposite the heater/dielectric layer. The heater layer can be formed by direct writing a heating element pattern onto a dielectric layer bonded to the core.

A heater panel includes a core and a heater/dielectric layer including a positive thermal coefficient (PTC) heater layer between a pair of dielectric layers. A structural facing is included, wherein the heater/dielectric layer is bonded directly between the core and the structural facing. A second structural facing can be bonded to the core opposite the heater/dielectric layer. An impact layer can be bonded to the structural facing, e.g., the first structural facing described above, opposite the heater/dielectric layer. The heater layer can be formed by direct writing a heating element pattern onto a dielectric layer bonded to the core.

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 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.

There is provided an anti-ballistic aerospace structure, said structure comprising a strike layer defining an outwardly facing surface and an opposing capture layer defining an inwardly facing surface and an intermediate structural layer arranged between the strike layer and capture layer, wherein the intermediate structural layer is spaced relative to the strike layer to define a space between the intermediate structural layer and the strike layer, said space comprising one or more reinforcement elements, and wherein the strike layer is formed of a fiber reinforced plastic laminate comprising at least one metallic layer.

There is provided an anti-ballistic aerospace structure, said structure comprising a strike layer defining an outwardly facing surface and an opposing capture layer defining an inwardly facing surface and an intermediate structural layer arranged between the strike layer and capture layer, wherein the intermediate structural layer is spaced relative to the strike layer to define a space between the intermediate structural layer and the strike layer, said space comprising one or more reinforcement elements, and wherein the strike layer is formed of a fiber reinforced plastic laminate comprising at least one metallic layer.