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: Aspects relate to an aircraft having a controllable center of gravity and methods of controlling the center of gravity. An exemplary aircraft having a controllable center of gravity includes a first tank configured to store a first portion of a ballast, a second tank configured to store a second portion of the ballast disposed substantially aft of the first tank, at least a pipe configured to provide fluidic communication between the first tank and the second tank, at least a pump configured to pump the ballast bidirectionally between the first tank and the second tank by way of the at least a pipe, and a controller in communication with the at least a pump and configured to control a ballast ratio of the first portion of the ballast relative the second portion of the ballast and affect an aircraft center of gravity.

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: A blended wing body (BWB) aircraft comprising a first composite part comprising, a first dry carbon fiber sheet having a width greater than 3 inches and comprising a first layer comprising dry carbon fibers, a second layer disposed on top of the first layer comprising dry carbon fibers, a stitching extending through the first dry carbon fiber sheet, wherein the stitching is configured to bind the first dry carbon fiber sheet together, and a resin matrix, wherein the stitching and the first dry carbon fiber sheet are embedded within the resin matrix to create a single unified structure. BWB aircraft further comprises a blended wing body, having no clear demarcation along a leading edge of the BWB aircraft from a wing to a nose of the blended wing body, and wherein the first composite part comprises a portion of the blended wing body.

Abstract: An aircraft comprising a plurality of modules is disclosed. The aircraft in includes a blended wing body (BWB) aircraft. The blended wing body aircraft comprises a main body, a transition, and wings with no clear demarcation between the wings and the main body along a leading edge of the BWB aircraft. The blended wing aircraft additionally comprises a cabin containing a plurality of modular receptacles. A plurality of modules is configured to be removably attached to the plurality of modular receptacles. Additionally, at least a propulsor is mechanically attached to the blended wing body aircraft.

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: An aircraft with an engine support structure, the aircraft including at least an engine wherein the at least engine is top mounted to an aircraft, a main body, and an engine support structure including a plurality of hoop structures, wherein at least one horseshoe structure is located forward of the center of gravity to the at least engine.

Abstract: A modular blended wing body (BWB) aircraft includes common components containing a nose structure having a left aft edge and a right aft edge intersecting on a centerline of the BWB on one end and intersecting on a leading edge of the BWB on another end, and two wing structures attached to the nose structure, wherein the at least two rear structures includes a left-wing structure arranged on the left side of the centerline, wherein the left-wing structure includes a left forward edge, and a right-wing structure arranged on the right side of the centerline, wherein the right-wing structure includes a right forward edge, and wherein the left-wing structure and the right-wing structure are laterally symmetrical to the centerline, and wherein there is no clear demarcation between the at least two wing structures and the nose structure of the plurality of common components of the BWB aircraft.

Abstract: A modular blended wing body (BWB) aircraft includes common components containing a nose structure having a left aft edge and a right aft edge intersecting on a centerline of the BWB on one end and intersecting on a leading edge of the BWB on another end, and two wing structures attached to the nose structure, wherein the at least two rear structures includes a left-wing structure arranged on the left side of the centerline, wherein the left-wing structure includes a left forward edge, and a right-wing structure arranged on the right side of the centerline, wherein the right-wing structure includes a right forward edge, and wherein the left-wing structure and the right-wing structure are laterally symmetrical to the centerline, and wherein there is no clear demarcation between the at least two wing structures and the nose structure of the plurality of common components of the BWB aircraft.

Abstract: An apparatus for virtually displaying an external visual environment of an aircraft, the apparatus comprising an input device, wherein the input device is configured to receive external aircraft data of an aircraft, at least a processor, a memory communicatively connected to the at least a processor, wherein the memory contains instructions configuring the processor to obtain the external aircraft data from the input device, determine a location of one or more passengers, generate a field of view as a function of the external aircraft data and the location of the one or more passengers and transmit the field of view to a display device.

Abstract: A commercial aircraft for short distance air travel, the commercial aircraft comprising a blended wing body aircraft 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 commercial aircraft, a passenger cabin, the passenger cabin located within the main body and having a wide body passenger capacity, at least a propulsor, the at least a propulsor attached to a portion of the main body and configured to propel the blended wing body commercial 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 a fuel capacity associated with short-range flight, and a landing gear, the landing gear located on an undercarriage of the blended wing body, the landing gear configured for the short-range flight.

Abstract: A system and method for a blended wing body aircraft with permanent tanks is presented. The aircraft comprises a blended wing body and at least a tank permanently attached the blended wing body. The at least a tank is configured to store liquified gas fuel and further comprises at least a vent configured to vent gaseous fuel from the at least a tank and an insulation to reduce thermal transfer to the liquified gas fuel inside of the at least a tank.

Abstract: An aircraft component including a structural foam having a predetermined shape, an outer flange located near a first end of the structural foam, an inner flange located near a second end of the structural foam, a web skin encapsulating the inner flange and at least a portion of the structural foam wherein the structural foam is affixed to the web skin, wherein the aircraft component comprises a portion of a blended wing body aircraft (BWB), the BWB having no demarcation between a wing and a main body of the BWB.

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 system and method for a blended wing body aircraft with permanent tanks is presented. The aircraft comprises a blended wing body and at least a tank permanently attached the blended wing body. The at least a tank is configured to store liquified gas fuel and further comprises at least a vent configured to vent gaseous fuel from the at least a tank and an insulation to reduce thermal transfer to the liquified gas fuel inside of the at least a tank.

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: A coupled landing gear apparatus for an aircraft including at least a nose gear disposed forward of a neutral point of an aircraft by a first distance and 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 in communication with one another.

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: A commercial aircraft for long distance air travel, the commercial aircraft comprising, a blended wing body aircraft 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 commercial aircraft, a passenger cabin, the passenger cabin located within the main body and having a single aisle passenger capacity, at least a propulsor, the at least a propulsor attached to a portion of the main body and configured to propel the blended wing body aircraft through air, and a fuel storage having a fuel capacity, the fuel capacity configured for long range flight, wherein the commercial aircraft is configured for long-range flight.

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.