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.

An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.

A flexible strengthening joint for a pressurized vessel includes an outer skin having a localized abrupt change in shape. The outer skin includes a first skin section and a second skin section, the localized abrupt change in shape being located at a junction between the first skin section and the second skin section. A reinforcing bulkhead is located in the interior of the pressurized vessel. The reinforcing bulkhead includes a first bulkhead section that is directly attached to the first section of the outer skin and a second bulkhead section that unattached directly to the first section. A kick frame is located in the interior, the kick frame spanning at least the second bulkhead section. At least one intercostal is secured to the second bulkhead section. The at least one intercostal is also secured to the kick frame.

An aircraft with a lifting body fuselage profile having a nose end, tail end and having an upper surface between the nose and the tail end and a lower surface between the nose and the tail end. The profile of the upper surface having a section of a first ellipse starting at the nose end and a first circle arc transitioning from the first ellipse section to the tail end. The profile of the lower surface having a second circle arc transitioning from the section of the first ellipse of the upper surface at the nose end and transitioning to a straight line. The profile of the lower surface having a third circle arc transitioning from the straight line and a fourth circle arc transitioning from the third circle arc and ending at the tail end.

An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.

This invention is focus on how to make a quieter supersonic flight. Several techniques and methods have been crafted to solve the noise problem of the sonic boom. Sonic boom is propagated from aircraft to the ground, so add interference media between them to block the noise wave could reduce the sonic boom level. Using special designed wings could also reduce noise wave. Part of the special wings design is inspired from the bird flock's flight. Using active shock wave to blow away the air at the windward front of the aircraft or using holes at the fuselage bottom to flow away the air underneath the fuselage could reduce the noise wave propagated to travel to the ground.

A pressure vessel includes at least one pair of side bulkheads spaced apart from each other. In addition, the pressure vessel includes at least one substantially flat panel having at least one panel span extending between the pair of side bulkheads and being in non-contacting proximity to the side bulkheads. The panel and the side bulkheads collectively form at least a portion of a structural assembly enclosing the pressure vessel. The pressure vessel also includes a plurality of panel braces coupling the side bulkheads to the panel at a plurality of panel attachment nodes distributed along the panel span. At least two of the panel braces have a different axial stiffness configured to result in the outward deflection of the panel attachment nodes by substantially equal deflection amounts when the panel is subjected to an out-of-plane pressure load during internal pressurization of the pressure vessel.

A public transportation system combines a unique combination of components that includes interoperable electric-powered vehicles, facilities, hardware and software having specifications, standards, processes, capabilities, nomenclature, and concepts of operations that together include a concerted, comprehensive, multi-modal, future system for moving people and goods that is herein named Quiet Urban Air Delivery (QUAD) and in which uniquely-capable, ultra-quiet, one to six-seat, electrically-powered, autonomous aircraft (SkyQarts) fly sub-193 kilometer trips on precise trajectories with negligible control latency and perform extremely short take-offs and landings (ESTOL) with curved traffic patterns at a highly-distributed network of very small, airports (“SkyNests”) that themselves have standardized compatible facilities that interoperate with SkyQarts as well as with versatile, autonomous electric-powered payload carts (EPCs) and robotic delivery carts (RDCs) to provide safe, fast, on-demand, community-acceptable, environmentally friendly, high-capacity, affordable door-to-door delivery of both passengers and cargo across urban, suburban and rural settings across the globe.

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.

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.