The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

A method of manufacturing a hollow composite structure is provided. The method includes forming a first portion of the hollow composite structure having at least one open region and at least one wall, the at least one wall partially defining a hollow interior. The method also includes bonding a laminate shell to the first portion of the hollow composite structure proximate to at least one location of the wall to cover the open region and enclose the hollow interior. The method further includes disposing a second portion of the hollow composite structure over the laminate shell, the second portion comprising a plurality of plies. The method yet further includes curing the first portion and the second portion during a final cure.

A trunk route aircraft has at least one wing for supporting the aircraft during flight, and at least one propulsor for forward propulsion of the aircraft. The trunk route aircraft further includes a pressurized trunk route fuselage having a double-bubble cross-sectional shape and a generally vertically-oriented longitudinal bulkhead dividing the trunk route fuselage interior into two side-by-side trunk route payload compartments. The longitudinal bulkhead is loaded in tension when the trunk route fuselage is pressurized. The trunk route payload compartments are each configured to receive a plurality of lightweight ISO (International Organization for Standardization) geometry containers arranged end-to-end, or a plurality of container inserts arranged end-to-end, each container insert also configured to be received within the lightweight ISO-geometry container, or a combination of one or more lightweight ISO-geometry containers and one or more container inserts arranged end-to-end.

An aerial vehicle including a main body having a leading edge. An inlet is recessed aft from the leading edge. Forward protrusions extend from the main body on opposite sides of the inlet. An outlet nozzle is proximate to an aft end. The inlet is in fluid communication with the outlet nozzle. Wings extend from the main body.

An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.

Disclosed are apparatus, systems, and methods, including a cargo transport system comprising a spine assembly, a container assembly, and an outer fairing. The spine assembly comprises a rigid spine and a plurality of mounts arranged on the rigid spine in a plurality of mount rows. The container assembly comprises a plurality of containers secured to the spine assembly using at least a subset of the plurality of mounts. The outer fairing at least partially encloses the container assembly. Each container of the plurality of containers comprises a plurality of fittings for securing the container to the spine assembly and/or another container of the container assembly. The container assembly is enclosed within a pressurization space for pressurizing the container assembly.

An air transport vehicle that capitalizes on the strengths and complexities of a fixed and rotary winged aircraft. The air transport vehicle comprises a body aerodynamically designed to avoid substantial drag. The vehicle has a plurality of rotors configured to generate vertical thrust with a rear rotor configured to generate forward thrust. Additionally, each of the rotors are connected to the fixed wing elements and the fixed wing is positioned about the center of mass of the fuselage. Furthermore, each of the rotors are positioned at a fixed tilt angle such that the stability of the vehicle is maintained in a number of different flight configurations.

An aircraft is provided including a fuselage that extends along a longitudinal direction between a forward end and an aft end. A boundary layer ingestion fan is mounted to the fuselage at the aft end and is configured for ingesting boundary layer airflow off the surface of the fuselage. The fuselage defines a profile proximate the boundary layer ingestion fan that is optimized for ingesting a maximum amount of boundary layer air and improving propulsive efficiency of the aircraft. More specifically, the fuselage defines a cross sectional profile upstream of the boundary layer ingestion fan that has more cross sectional area in a top half relative to a bottom half as defined relative to a centerline of the boundary layer ingestion fan.

A method is provided. An airship is maneuvered to a desired location and oriented with the thruster such that ambient wind is traveling in a direction that is substantially parallel to the longitudinal axis of the fuselage. The airflow from the ambient wind is straightened with the flow straightener to generate a substantially laminar flow. The turbine is engaged with the airflow generated by the ambient wind to generate electricity, and the electricity generated by the turbine is rectified with the rectifier and stored in the storage array.

A fixed-wing cargo aircraft having a kinked fuselage is disclosed. The fuselage contains a continuous interior cargo bay, and includes a forward portion, an aft portion, and a kinked portion forming a junction in the fuselage between the forward and aft portions. The kinked portion contains a transition region of the cargo bay and defines a bend between a forward centerline and an aft centerline. The kinked portion is formed with a forward transverse frame section, a separate aft transverse frame section, and a plurality of longitudinal frame elements extending between the forward and aft frame sections, the forward frame being coupled to an aft end of the forward portion and the aft frame section being coupled to a forward end of the aft portion such that the aft frame section is angled with respect to the forward frame section about a lateral axis of the cargo aircraft.