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.

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.

A pressure deck system for a fuselage of an aircraft. The pressure deck system comprises a first sloping outboard pressure panel, a first longitudinal stiffener connected to the first sloping outboard pressure panel, a second sloping outboard pressure panel opposite the first sloping outboard pressure panel, a second longitudinal stiffener connected to the second sloping outboard pressure panel, pressure panels between the first sloping outboard pressure panel and the second sloping outboard pressure panel and forming the an upper barrier of a wheel well, longitudinal beams connected to the pressure panels and supporting a cabin floor of the fuselage, and a sloping pressure deck connecting a number of these components to the rear spar of the center wing box. A waterline of the pressure deck system is de-coupled from a side-of-body waterline in the fuselage.

A pressure deck system for a fuselage of an aircraft. The pressure deck system comprises a first sloping outboard pressure panel, a first longitudinal stiffener connected to the first sloping outboard pressure panel, a second sloping outboard pressure panel opposite the first sloping outboard pressure panel, a second longitudinal stiffener connected to the second sloping outboard pressure panel, pressure panels between the first sloping outboard pressure panel and the second sloping outboard pressure panel and forming the an upper barrier of a wheel well, longitudinal beams connected to the pressure panels and supporting a cabin floor of the fuselage, and a sloping pressure deck connecting a number of these components to the rear spar of the center wing box. A waterline of the pressure deck system is de-coupled from a side-of-body waterline in the fuselage.

A galley system within an internal cabin of an aircraft includes one or more inboard cart compartments that are configured to removably retain one or more first galley carts, and one or more outboard cart compartments. The outboard cart compartment(s) are configured to removably retain one or more second galley carts. The inboard cart compartment(s) extend forwardly and/or rearwardly in relation to the outboard cart compartment(s).

An airframe design may include a bonded frame or assembly, and one or more components that may be removably attached to the bonded frame. The bonded frame may include struts, central bulkheads, a tail section, a plurality of wing sections, and motor mounts that are adhered together using adhesive. The one or more attachable components may include a forward fuselage, motors, propellers, motor pod fairings, stabilizer fins, and landing gear that are attached using fasteners. The bonded frame may reduce the number of parts of the airframe design and may also reduce complexity, cost, and weight, while also increasing stiffness and strength. Further, the various attachable components may facilitate fabrication, assembly, and maintenance of an aerial vehicle having the airframe design.

An airframe design may include a bonded frame or assembly, and one or more components that may be removably attached to the bonded frame. The bonded frame may include struts, central bulkheads, a tail section, a plurality of wing sections, and motor mounts that are adhered together using adhesive. The one or more attachable components may include a forward fuselage, motors, propellers, motor pod fairings, stabilizer fins, and landing gear that are attached using fasteners. The bonded frame may reduce the number of parts of the airframe design and may also reduce complexity, cost, and weight, while also increasing stiffness and strength. Further, the various attachable components may facilitate fabrication, assembly, and maintenance of an aerial vehicle having the airframe design.

A mold assembly for manufacturing a composite part with a stiffener, the mold assembly includes a bottom mold configured to form a first surface of the composite part, wherein the bottom mold has at least one elongated recess configured to form a stiffener in the composite part; a feeder unit having a shape corresponding to the at least one elongated recess, wherein the feeder unit is configured to fit at least partially into the at least one elongated recess; and a top mold configured to form a second surface of the composite part opposite to the first surface. Also a method of manufacturing a composite part using such a mold assembly, which includes draping a flat laminate over the bottom mold and pushing portions of the laminate into the at least one elongated recess.

Described herein are methods of forming uncured sealant assemblies and also methods of forming seals between various parts using such assemblies. In some examples, an uncured sealant assembly comprises two protective layers and an uncured sealant layer, disposed in between. The uncured sealant assembly is stored and provided at a cure-inhibiting temperature, selected to minimize the curing rate of the uncured sealant layer. The size and the shape of the uncured sealant layer are specifically selected to ensure the complete coverage of the faying surfaces, filling of all gaps and voids between the faying surfaces, and controlling the shape and size of uncured sealant squeeze out between the faying surfaces. In some examples, the size and shape of the uncured sealant layer maybe be specifically selected to have no uncured sealant squeeze out between parts.

An aircraft includes an airframe defining a first enclosed space, an engine bay disposed within the first enclosed space, and a cooling system. The engine bay includes a firebox defining a second enclosed space and an engine disposed at least partially within the second enclosed space. The cooling system is configured to selectively fluidly couple the first enclosed space with the second enclosed space.