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.

IPC Classes  ?

• F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
• B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
• B64C 21/02 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
• B64B 1/24 - Arrangement of propulsion plant
• B64D 27/00 - Arrangement or mounting of power plants in aircraftAircraft characterised by the type or position of power plants
• B64D 29/00 - Power-plant nacelles, fairings or cowlings

Abstract

Technologies for providing blended wing body aircraft control surfaces are described herein. In some examples, one or more of the control surfaces have angular configurations that reduce the formation of air vortexes when in upward or downward configurations, thereby reducing the drag on the aircraft when the control surfaces are being used.

IPC Classes  ?

• B64C 9/12 - Adjustable control surfaces or members, e.g. rudders surfaces of different type or function being simultaneously adjusted
• B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
• B64C 3/52 - Warping
• B64C 9/04 - Adjustable control surfaces or members, e.g. rudders with compound dependent movements
• B64C 9/06 - Adjustable control surfaces or members, e.g. rudders with two or more independent movements
• B64C 39/10 - All-wing aircraft

Abstract

GG) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive pitch angle for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.

IPC Classes  ?

• B64C 25/10 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
• B64C 25/00 - Alighting gear
• B64C 25/14 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like fore-and-aft
• B64C 25/18 - Operating mechanisms
• B64C 25/20 - Operating mechanisms mechanical
• B64C 25/22 - Operating mechanisms fluid

Abstract

GG) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive pitch angle for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.

IPC Classes  ?

• B64C 25/10 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
• B64C 25/00 - Alighting gear
• B64C 25/14 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like fore-and-aft
• B64C 25/18 - Operating mechanisms
• B64C 25/20 - Operating mechanisms mechanical
• B64C 25/22 - Operating mechanisms fluid

Abstract

Technologies are described herein for a drag recovery scheme. In various examples, a recovery engine is placed within a vortex flow of air caused by the impingement of air upon a nacelle of a main engine. The propeller of the recovery engine can use the vortex flow of air to provide additional thrust the aircraft, thus reducing the load on the main engines or providing an increased velocity.

IPC Classes  ?

• B64D 27/02 - Aircraft characterised by the type or position of power plants

Abstract

Technologies for providing noise shielding are described herein. In some examples, noise shields are installed proximate to one or more of the main engines of the aircraft. The noise shields can be extended during terminal operations and retracted during flight operations.

IPC Classes  ?

• F02K 1/44 - Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction
• B64C 1/40 - Sound or heat insulation
• B64C 39/00 - Aircraft not otherwise provided for
• B64C 39/10 - All-wing aircraft
• F02K 1/00 - Plants characterised by the form or arrangement of the jet pipe or nozzleJet pipes or nozzles peculiar thereto
• F02K 1/34 - Plants characterised by the form or arrangement of the jet pipe or nozzleJet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise

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.

IPC Classes  ?

• B64C 39/10 - All-wing aircraft
• B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens
• B64C 1/24 - Steps mounted on, and retractable within, fuselages
• B64C 1/32 - Severable or jettisonable parts of fuselage facilitating emergency escape
• B64C 39/00 - Aircraft not otherwise provided for
• B64D 25/14 - Inflatable escape chutes

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.

IPC Classes  ?

• B64C 27/16 - Drive of rotors by means, e.g. propellers, mounted on rotor blades
• B64C 27/24 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft

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.

IPC Classes  ?

• B64C 27/24 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
• B64C 27/22 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
• B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
• B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft

Abstract

Systems and methods for mechanically rotating an aircraft about its center-of-gravity (CG) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive angle of attack for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.

IPC Classes  ?

• B64C 25/00 - Alighting gear
• B64C 25/10 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
• B64C 25/14 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like fore-and-aft
• B64C 25/20 - Operating mechanisms mechanical
• B64C 25/22 - Operating mechanisms fluid
• B64C 25/26 - Control or locking systems therefor

Abstract

An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating 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 fuselage 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 fuselage, 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.

IPC Classes  ?

• B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
• B64C 39/02 - Aircraft not otherwise provided for characterised by special use