Abstract: A system for carrying out a Resin Transfer Molding process including a molding tool having an upper mold half and a lower mold half which form a mold cavity configured for placement of a preform, a main control unit, more than one injection units configured to supply a resin mixture into the mold cavity, more than one injection points fluidly connecting the more than one injection units to the molding tool, one or more venting hoses configured to expel an excess of the resin mixture, more than one resin outlets fluidly connecting the one or more venting hoses to the molding tool and one or more flow direction sensors connected to the main control unit, wherein the main control unit is configured to monitor a behavior of the resin mixture from the more than one injection points to the mold cavity using the one or more flow direction sensors.

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: 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: Aspects relate to systems and methods for folding wings on an aircraft. An exemplary system includes a blended wing body, where the blended wing body includes a main body and at least a wing, a hinge located on the at least a wing and configured to allow folding of the at least a wing, an actuation system configured to fold the at least a wing, and a controller configured to control the at least an actuation system.

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 non-coupled landing gear for an aircraft includes at least a nose gear and at least a main gear. The at least a nose gear disposed forward of a neutral point of an aircraft by a first distance and the at least a main gear disposed aft of the neutral point of the aircraft by a second distance. The at least a nose gear and the at least a main gear are uncoupled from each other.

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 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 blended wing body (BWB) aircraft having 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 BWB aircraft, a passenger cabin located within the main body and a galley located within the passenger cabin, wherein the galley includes a substantially triangular shape.

Abstract: Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.

Abstract: A tanker aircraft for long-distance travel, the tanker aircraft including 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 tanker aircraft, a fuel storage located within the blended wing body, the fuel storage comprising a first fuel store, the first fuel store located within the transition and configured for long range flight and a second fuel store the second fuel store having a tanker capacity and a refueling boom system having a flying boom, the flying boom extending from the blended wing body, wherein the tanker aircraft is a long-range tanker aircraft.

Abstract: Disclosed herein is an aircraft with engines positioned so as to avoid damage to other components of the aircraft. The aircraft may include a blended wing body aircraft. The engines may be positioned aft of a pressure vessel of the aircraft. The engines may be positioned aft of and/or above a fuel store of the aircraft. Such engine positioning may reduce the likelihood of damage to a pressure vessel and/or fuel store in the event of engine failure.

Abstract: Methods and systems for venting a fuel tank includes a fuel tank on a blended wing body aircraft. A fuel tank may include a vent. A vent line is connected to the vent. The vent line is heated. The vent line is attached to an external fuel tank configured to store the collected boil-off gaseous fuel from the aircraft fuel tank.

Abstract: A blended wing body (BWB) aircraft having 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 BWB aircraft, a passenger cabin located within the main body having one or more cross aisles extending along a lateral axis, wherein a shape of the passenger cabin is asymmetrical about a lateral axis, more than one passenger bays located within the passenger cabin, wherein each of the more than one passenger bays are separated by at least one cross aisle of the one or more cross aisles and one or more lavatories situated outside the more than one passenger bays and substantially adjacent to a perimeter of the passenger cabin, wherein each of the one or more lavatories are linked to one cross aisle of the one or more cross aisles.

Abstract: A blended wing body (BWB) aircraft having 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 BWB aircraft, a passenger cabin located within the main body and a galley located within the passenger cabin, wherein the galley includes a substantially triangular shape.

Abstract: A blended wing body aircraft, comprising a cabin, wherein the cabin comprises a first set of bays comprising a first plurality of seats arranged in a first seating configuration, wherein each bay of the first set of bays is associated with a first bay width, a second set of bays comprising a second plurality of seats arranged in a second seating configuration different than the first seating configuration, a central galley complex positioned in a front center location located between the first set of bays and the second set of bays, a central passage separating the first set of bays, the central galley complex, and the second set of bays, and at least a lavatory positioned outside the first set of bays and the second set of bays, along a perimeter of the cabin.

Abstract: A blended wing body (BWB) aircraft including a blended wing body having a main body and wings with no clear demarcation between the wings and the main body along leading edges of the BWB aircraft, a passenger cabin located within the main body and more than one passenger bays located within the passenger cabin, wherein a perimeter of at least one passenger bay is demarcated by at least a divider and wherein the at least one passenger bay is substantially parallel to at least one leading edge of the BWB aircraft.

Abstract: A blended wing body (BWB) aircraft having 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 BWB aircraft, a passenger cabin located within the main body having one or more cross aisles extending along a lateral axis, wherein a shape of the passenger cabin is asymmetrical about a lateral axis, more than one passenger bays located within the passenger cabin, wherein each of the more than one passenger bays are separated by at least one cross aisle of the one or more cross aisles and one or more lavatories situated outside the more than one passenger bays and substantially adjacent to a perimeter of the passenger cabin, wherein each of the one or more lavatories are linked to one cross aisle of the one or more cross aisles.

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 aircraft including a blended wing body aircraft (BWB) having a main body and wings with no clear demarcation between the wings and the main body along a leading edge of the aircraft, a rear spar located within the main body, one or more gear wells located on a lower surface of the rear spar, a landing gear system having at least a main gear the at least a main gear situated in one of the one or more gear wells, and one or more propulsors located directly above the one or more gear wells, wherein at least one propulsor is located over the at least one gear well of the one or more gear wells.