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: Described herein is a blended wing body aircraft. In some embodiments, a blended wing body aircraft may include a set of passenger loading doors on a first lateral side of the aircraft, and a set of passenger unloading doors on the second lateral side of the aircraft. In some embodiments, this configuration may allow for more efficient loading and unloading of blended wing body aircraft.

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, at least a rib, wherein the at least a rib runs longitudinally from fore to aft of the main body, and 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 channels are separated by the at least a rib.

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.

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: Technologies for providing emergency egress routes for a blended wing body aircraft are described herein. In some examples, the emergency egress routes are through a side cabin bulkhead and aft one or more cargo holds. In some examples, the blended wing body aircraft has wings that are high geometry wings. In these examples, the emergency egress routes do not penetrate an aft spar, reducing weight and increasing the integrity of the aircraft.

Abstract: A system for manufacturing modular aircraft includes at least at least a common tooling component, including at least one or more of a first component in a shape of a nose and a second component in a shape of a wing. The system further including at least a modular tooling component in a shape of a main body, wherein connecting the at least a common tooling components to the at least modular component forms a mold in a shape of at least a portion of a blended wing body (BWB) aircraft with no clear demarcation between the shape of the wing and a shape of a main body along an edge of the shape of the BWB.

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 system for modular aircraft includes at least a common component, wherein the at least a common component includes at least a flight component. The system includes at least a modular component, wherein the at least modular component includes at least a fuselage component and a collar component. The system includes at least an interface component, wherein the at least an interface component is configured to connect the at least a common component at a first end to the at least a modular component at a second end.

Abstract: An aircraft with a mid-market passenger capacity, wherein the aircraft comprises, a blended wing body aircraft 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 main body is structured to comprise a passenger cabin configured to have a mid-market passenger capacity, wherein the main body is structured to comprise a structural element, the structural element extending vertically from a lower surface of the main body toward an upper surface of the main body, and at least a propulsor, the at least a propulsor attached to the main body and configured to propel the aircraft.

Abstract: A system for modular aircraft includes at least a common component, wherein the at least a common component includes at least a flight component. The system includes at least a modular component, wherein the at least modular component includes at least a fuselage component and a collar component. The system includes at least an interface component, wherein the at least an interface component is configured to connect the at least a common component at a first end to the at least a modular component at a second end.

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, at least a rib, wherein the at least a rib runs longitudinally from fore to aft of the main body, and 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 channels are separated by the at least a rib.

Abstract: A system for modular aircraft includes at least a common component, wherein the at least a common component includes at least a flight component. The system includes at least a modular component, wherein the at least modular component includes at least a fuselage component and a collar component. The system includes at least an interface component, wherein the at least an interface component is configured to connect the at least a common component at a first end to the at least a modular component at a second end.

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 transparent panels in a ceiling of the cabin configured to transmit light from outside the blended wing body aircraft to inside the cabin.

Abstract: A system for manufacturing modular aircraft includes at least a common tooling component, wherein the at least a common tooling component is configured to manufacture at least a flight component. The system includes at least a modular tooling component, wherein the at least modular tooling component wherein the at least a modular tooling component is configured to manufacture at least a fuselage component and a collar component. The system includes at least a tooling interface component, wherein the at least a tooling interface component is configured to mechanically connect the at least a common tooling component at a first end to the at least a modular tooling component at a second end.

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: 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: 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: 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: An aircraft for use in fixed wing flight mode and rotor flight mode while maintaining a horizontal fuselage is provided. The aircraft can include a fuselage, wings, rotor, and a plurality of engines. The rotor can comprise a wing attachment assembly further comprising a rotating support. A rotating section can comprise a central support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the rotor providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the rotor, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed-wing flight mode.