Abstract: A mold for molding aircraft components is provided. The mold includes a mold first part, a mold second part, and a mold insert, the mold first part and mold insert combining to form a cavity defining the shape of an aircraft component. The cavity may be filled with reinforcing fiber and then infused with matrix material to form a fiber-reinforced composite part. The mold may include one or more sensors to monitor data related to a molding process such as pressure, temperature, and material flow.

Abstract: Aspects relate to systems and methods for controlling landing gear of an aircraft. An exemplary system includes a nose gear located at a nose of the aircraft, where the nose gear includes a nose piston configured to allow for displacement of a nose wheel relative the aircraft, a main gear located aft of the nose gear, where the main gear includes a main piston configured to allow for displacement of a main wheel relative the aircraft, a hydraulic circuit in fluidic communication with each of the nose piston and the main piston, and a compliant element in fluidic communication with the hydraulic circuit and configured to provide a compliant response at one or both of the nose piston and the main piston.

Abstract: A freighter aircraft for long-distance travel, the freighter aircraft comprising a blended wing body having a main body, a transition, and wings with no clear demarcation between the wings and the main body along a leading edge of the freighter aircraft, at least a propulsor, the at least a propulsor attached to a portion of the main body and configured to propel the freighter aircraft through air, a fuel storage located within the blended wing body, the fuel storage having a fuel capacity wherein the fuel capacity is configured for long-range flight, and a cargo bay located within the main body; the cargo bay configured to have a freighter capacity, wherein freighter aircraft is a long-range aircraft, the freighter aircraft including a ton-miles per sortie between 135,000 and 450,000.

Abstract: A composite assembly for an aircraft, the composite assembly including a first carbon fiber material structured for a portion of an outer skin surface of an aircraft, a second carbon fiber material stitched to the first carbon fiber material, wherein the second carbon fiber material is structured for a structural component of the aircraft, and wherein the stitching is configured to bind the first carbon fiber material and the second carbon fiber material, and wherein the aircraft further includes a single deck, wherein a cargo compartment and a passenger compartment are located on or above the single deck.

Abstract: A composite assembly for a blended wing body aircraft, the composite assembly comprising: a first assembly comprising a first molded part, wherein the first molded part comprises a first plurality of fibers, the first molded part partially infused with a first resin, a second assembly oriented relative to the first assembly, the second assembly comprising a second molded part wherein the second molded part comprises a second plurality of fibers, the second molded part partially infused with a second resin, and a joining region, the joining region comprising at least a portion of first plurality of fibers and at least a portion of second plurality of fibers, the at least a portion of first plurality of fibers and the at least a portion of second plurality of fibers substantially adjacent and infused with a third resin.

Abstract: The present disclosure is directed to a blended wing body aircraft including a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the aircraft; a cabin located within the main body and a transitional portion of the blended wing body; and a plurality of transmissive panels integrated into a ceiling of the cabin configured to transmit light from outside the blended wing body aircraft to inside the cabin.

Abstract: An aircraft with carbon fiber material comprising a blended wing body having a main body and wings with no clear demarcation between the wings and the main body along a leading edge of the aircraft, wherein the blended wing body comprises, at least an outer skin surface comprising a carbon fiber material, at least a structural element comprising the carbon fiber material, and at least a portion of the main body comprising the carbon fiber material and configured to contain a pressure vessel and at least a propulsor, the at least a propulsor attached to the blended wing body and configured to propel the aircraft.

Abstract: In an aspect, an aircraft fueling apparatus is disclosed. The apparatus includes at least a container comprising a fuel tank configured to store liquified gas fuel. The apparatus may also include a translocation device configured to carry the at least a container. An orientation guidance track may also be included in the apparatus. The orientation guidance track may be configured to direct a movement of the translocation device to a first position.

Abstract: A liquified gas fuel tank incorporated into an aircraft is disclosed. The liquified gas fuel tank includes a plurality of compartments. The liquified gas fuel tank includes one or more septa configured to structurally support each compartment of the plurality of compartments at the fluid connection, wherein each of the one or more septa are configured to extend vertically from a base of a main body of the aircraft to a top of the main body of the aircraft. The liquified gas fuel tank includes a sensing component which includes one or more sensors. The sensing component also includes a gas evacuation element configured to identify a gas concentration within at least one compartment. Additionally, the sensing component includes a controller communicatively connected to the gas evacuation element. The controller is configured to receive an indication and toggle the gas evacuation element as a function of the indication.

Abstract: an aircraft with high transport efficiency, wherein the aircraft include a blended wing body with a downward depressed upper aft surface, configured to operate at a high cruising level within a high cruise altitude range, wherein the blended wing body include a main body configured to accommodate a payload, and at least a wing, wherein the blended wing body include no striking demarcation between the main body and the at least a wing and at least a propulsor attached to the blended wing body and configured to propel the aircraft.

Abstract: A system for providing favorable environment for propulsion system of a blended wing body aircraft, wherein the system comprises a blended wing body, wherein the blended wing body comprises a main body, wherein the main body comprises a main body shaping comprising an upper aft surface configured to provide a favorable environment for a propulsion system of the blended wing body aircraft, and the propulsion system mounted to the upper aft surface of the main body, wherein the propulsion system comprises one or more prime movers, and a nacelle covering the one or more prime movers.

Abstract: An airframe of a blended wing body aircraft with a non-cylindrical pressure vessel and methods of manufacture. The airframe includes a plurality of longitudinal stiffeners running substantially parallel to a longitudinal axis of the airframe and extending from a top side of the airframe to a bottom side of the airframe. The airframe includes at least a laterally outermost bulkhead configured to resist a cabin pressure. The airframe includes a skin comprising an outer mold line of the airframe that is configured to attach to the plurality of longitudinal stiffeners at the top side of the airframe and the bottom side of the airframe. In some embodiments, the airframe may include an aft pressure bulkhead.

Abstract: An apparatus for ingesting boundary layer flow on an aircraft, the apparatus includes a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and main body of the aircraft, wherein the blended wing body includes a nacelle located aft of a leading edge of the blended wing body, wherein the nacelle includes a propulsor configured to propel the aircraft, a primary duct, and a flow augmentation arrangement, wherein the flow augmentation arrangement is configured to accelerate a boundary layer flow in the airflow, wherein the flow augmentation arrangement further includes a secondary duct, wherein the secondary duct configured to ingest the boundary layer flow in the airflow from an inlet proximal to a forward portion of the nacelle to an outlet proximal to a rear portion of the nacelle and a tertiary duct between the primary duct and the secondary duct.

Abstract: Aspects relate to blended wing body aircraft having a passenger compartment. Blended wing body aircraft may include a freighter aircraft, a tanker aircraft, a passenger aircraft, or the like. Blended wing body aircraft may include an upper seating area, such as a passenger compartment, configured to accommodate passengers or personnel of aircraft without sacrificing space of a main region of a fuselage of the aircraft.

Abstract: Aspects related to aircraft for commercial air travel and methods of manufacture. An aircraft includes a blended wing body, a single deck located within the blended wing body, wherein the single deck additionally includes a passenger compartment located in a lateral middle portion of the blended wing body and at least a cargo store located laterally outside the passenger compartment, and a landing gear, wherein the landing gear includes at least a nose gear located substantially forward of the single deck and at least a main gear located substantially aft of the single deck, wherein one or more of the at least a nose gear and the at least a main gear occupies a gear housing that overlaps with a plane coincident with at least a portion of the single deck.

Abstract: The present disclosure is directed to a blended wing body aircraft including a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the aircraft. The blended wing body aircraft also includes a plurality of transparent panels located in the top surface of the main body, wherein the plurality of transparent panels are located in channels, wherein the plurality of transparent panels allow the transmission of visible light.

Abstract: Certain aspects relate to a blended wing body aircraft with a fuel cell and methods of use. An exemplary aircraft includes a blended wing body, at least a propulsor mechanically affixed to the aircraft and configured to propel the aircraft, at least a first fuel store configured to store a first fuel, and at least a fuel cell configured to combine the first fuel with oxygen to produce electricity.

Abstract: Described herein is a blended wing body aircraft. In some embodiments, a blended wing body aircraft may include a passenger cabin separated into two or more cabin bays. In some embodiments, two or more cabin bays may be separated by a structural element that runs through the passenger cabin along the longitudinal axis of the aircraft.

Abstract: Aspects relate to aircraft and methods of use for aerodynamic control with winglet surfaces. In an aspect an exemplary aircraft includes a first wing having a first winglet at a distal end of the wing, wherein the first winglet comprises at least a first control surface at a first trailing edge of the first winglet and a second wing having a second winglet at a distal end of the wing, wherein the second winglet comprises at least a second control surface at a second trailing edge of the second winglet.