149results about "All-wing aircraft" patented technology

Disclosed herein is an aircraft with engines positioned so as to avoid damage to other components of the aircraft. The aircraft may include a blended wing body aircraft. The engines may be positioned aft of a pressure vessel of the aircraft. The engines may be positioned aft of and / or above a fuel store of the aircraft. Such engine positioning may reduce the likelihood of damage to a pressure vessel and / or fuel store in the event of engine failure.

An assembly is provided for an aircraft. This assembly includes a first propulsor rotor, a powerplant and a propulsion system housing. The powerplant is configured to drive rotation of the first propulsor rotor about an axis. The propulsion system housing includes an inner structure and an outer structure with a bypass flowpath radially between the inner structure and the outer structure. The bypass flowpath is downstream of the first propulsor rotor and extends axially along the inner structure and the outer structure within the propulsion system housing. The inner structure extends axially along and circumferentially around the powerplant. The outer structure extends axially along and partially circumferentially about the first propulsor rotor to cover an outer periphery of a first circumferential sector of the first propulsor rotor. A remaining second circumferential sector of the first propulsor rotor is open to an environment outside of the propulsion system housing.

An aircraft 10 comprising a first swept wing 14A and a second swept wing 14B, each swept wing having an inner wing section 26A, 26B comprising an integrated payload fuselage 20 and an outer wing secti

An airframe includes a body, a first wing, a second wing and a vane. The body extends longitudinally along a longitudinal centerline from a forward end of the body to an aft end of the body. The first wing and the second wing are disposed to opposing lateral sides of the body. The vane projects vertically out from the body to a tip of the vane. The vane extends longitudinally along the body from a leading edge of the vane to a trailing edge of the vane. A first open rotor propulsion system is vertically above and mounted to the body. A second open rotor propulsion system is vertically above and mounted to the body. The vane is configured as a structural barrier laterally between the first open rotor propulsion system and the second open rotor propulsion system.

An aircraft structure including an outer mold line skin, one or more frames located on an inner surface of the outer mold line skin having an outer flange attached to an inner surface of the outer mold line skin, a first core filler in contact with the outer flange, an inner flange in contact with the first core filler and a web skin, wherein the web skin and the outer flange encapsulate the inner flange and at least a portion of the first core filler, and an arched inner mold line skin located between each frame of the one or more frames, wherein the arched inner mold line skin is in contact with each web skin of the one or more web skins.

Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.

An assembly is provided for an aircraft. This aircraft assembly includes an airframe structure, a propulsion system and a vane. The airframe structure includes a fuselage and at least two wings. The fuselage extends longitudinally along a longitudinal centerline from a forward end of the fuselage to an aft end of the fuselage. The wings extend laterally from opposing sides of the fuselage. The propulsion system is mounted to the airframe structure. The propulsion system includes an airflow inlet into the propulsion system. The airflow inlet is spaced vertically out from a top side of the airframe structure. The vane projects vertically out from the top side of the airframe structure to a distal end of the vane. The vane laterally overlaps and is longitudinally forward of the airflow inlet.

An aircraft with a multi-walled fuel tank and method of manufacturing is presented. The aircraft includes a blended wing body and a fuel tank attached to the blended wing body configured to store liquified gas fuel. The fuel tank includes an inner wall, outer wall, and interstitial volume in between that is filled with insulation. The interstitial volume includes a reflective film layer and a structural insulation layer.

An aircraft including a blended wing body aircraft (BWB) having a main body and wings with no clear demarcation between the wings and the main body along a leading edge of the aircraft, a rear spar located within the main body, one or more gear wells located on a lower surface of the rear spar, a landing gear system having at least a main gear the at least a main gear situated in one of the one or more gear wells, and one or more propulsors located directly above the one or more gear wells, wherein at least one propulsor is located over the at least one gear well of the one or more gear wells.

A blended wing aircraft is provided, including a body having a fuselage and a pair of wings extending outward from the fuselage; and an aircraft engine defining an outlet and including a thrust reverser assembly, the thrust reverser assembly including a deployable structure extending less than 360 degrees around the outlet.

The invention provides a flying wing layout multi-rotor vertical take-off and landing aircraft, and belongs to the technical field of aircrafts. The front coaxial reversal dual-rotor power system comprises a ducted upper rotor and a ducted lower rotor, the ducted upper rotor and the ducted lower rotor are coaxially arranged and are opposite in rotating direction, and the ducted upper rotor and the ducted lower rotor are arranged at the front part of the wing body fusion machine body; the rear thrust tiltable rotor wing system comprises a left rotor wing and a right rotor wing which are symmetrically arranged on the left side and the right side of the rear part of the wing body fusion machine body. The ducted upper rotor and the ducted lower rotor which are coaxially arranged and opposite in rotating direction are arranged, the upper rotor and the lower rotor rotate in opposite directions, reaction torques of the upper rotor and the lower rotor are counteracted, an additional anti-torque device is not needed, the structure is simplified, and the layout space of the front portion of the aircraft body is greatly saved.

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.

Consisting of a flap-type aerodynamic surface on the wing(s) (2) above the fuselage (1) of an aircraft with control surfaces (5) of the wing (2), the length of the device in the wing span direction being greater than or equal to the mid-chord of the flap, and comprising a thrust propeller engine (4), converting it into a propulsive flapper (3).

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.

There is provided a restraint tool which restrains a lithium metal battery including a plurality of battery cells, including: a restraint member which includes: a plate-shaped member which is made of a rubber-based material and include a plate-shaped base and a plurality of protrusions on the base; and a frame member into which the plate-shaped member is fitted; and a fixing member which fixes the plate-shaped member fitted into the frame member in a pressurized state in which the plate-shaped member is pressed against the lithium metal battery. In the restraint tool, due to elasticity of the plate-shaped member, a pressure applied by the restraint tool to the plurality of battery cells in charging the plurality of battery cells is 5 MPa or less, and a pressure applied by the restraint tool to the plurality of battery cells in discharging the plurality of battery cells is 0.1 MPa or more.

Disclosed herein is an aircraft with engines positioned so as to avoid damage to other components of the aircraft. The aircraft may include a blended wing body aircraft. The engines may be positioned aft of a pressure vessel of the aircraft. The engines may be positioned aft of and / or above a fuel store of the aircraft. Such engine positioning may reduce the likelihood of damage to a pressure vessel and / or fuel store in the event of engine failure.

The invention relates to an aircraft (2) comprising a wing (4) and means (6, 30) for propelling the aircraft (2); the wing (4) having a flexible, airtight envelope (18) designed to contain air; the flexible envelope (18) being configured such that, when it contains air in a nominal inflation state, the aerodynamic profile of the flexible envelope (18) alone generates the lift of the wing (4). The aircraft (2) may be a piloted aircraft of the airplane type or an unpiloted aircraft of the drone type. Abstract figure: Fig. 1

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.

An assembly for an aircraft (20) includes a vertical stabilizer (30), a first turbine engine (25A; 104), a second turbine engine (25B; 104) and an actuation system (86). The vertical stabilizer (30) extends spanwise from a stabilizer base (68) to a stabilizer tip (58). The vertical stabilizer (30) extends longitudinally from a stabilizer leading edge (62) to a stabilizer trailing edge (64). The vertical stabilizer (30) extends laterally between a stabilizer first side (66A) and a stabilizer second side (66B). The first turbine engine (25A; 104) is movably mounted to the vertical stabilizer (30) at the stabilizer first side (66A). The second turbine engine (25B; 104) is moveably mounted to the vertical stabilizer (30) at the stabilizer second side (66B). The actuation system (86) is configured to move the first turbine engine (25A; 104) and the second turbine engine (25B; 104) relative to the vertical stabilizer (30).

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 and a galley located within the passenger cabin, wherein the galley includes a substantially triangular shape.

A multi-segment oblique flying wing aircraft which has three distinct segments including two outer wing segments and a central wing segment. The central segment may be thicker in the vertical direction and adapted to hold pilots and passengers. The outer wing segments may be substantially thinner and may taper as they progress outboard from the wing center. The multi-segment oblique flying wing aircraft be adapted for rotating into a high speed flight configuration, or may be adapted for take-off and cruise at a constant angle. In an extreme flight case, the central wing segment may rotate to a local sweep of ninety degrees.

Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.

An aircraft 310 has a pair of swept wings 314A meeting at a central region 312. Each wing has an inner wing section 326A containing an integrated payload fuselage (fig.1,20); a thinner thickness oute

A freighter aircraft for long-distance travel, the freighter aircraft comprising 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 freighter aircraft, at least a propulsor, the at least a propulsor attached to a portion of the main body and configured to propel the freighter 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 long-range flight, and a cargo bay located within the main body; the cargo bay configured to have a freighter capacity, wherein freighter aircraft is a long-range aircraft, the freighter aircraft including a ton-miles per sortie between 135,000 and 450,000.

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.

------ Vector-Tripping Aircraft The present invention relates to a vector-tripping aircraft (1), comprising: a wing in the form of a wing (2); a tail in the form of at least one rear aileron (3) carried by said wing (2); and an engine assembly (4) connected to said wing (2) for thrusting the aircraft (1), characterized in that said engine assembly (4) is disposed in front of said wing (2) and is connected to it by at least one arm (6), and that it comprises at least one turbine (10) configured to create, in operation, a jet of air discharged towards said wing (2) by a steerable nozzle (11). Figure to be published with the abbreviation: Figure 1

The present invention relates to an aircraft (1) comprising: a main fuselage formed of a central wing (10), centered on a longitudinal axis (X10); two lateral wings (20) mechanically connected to the central wing (10); and at least one propulsion system (40); characterized in that the aircraft (1) comprises an electrical energy storage system (30) electrically connected to the propulsion system (40) and providing fully electric propulsion for the aircraft (1). Abstract figure: 1

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 and a galley located within the passenger cabin, wherein the galley includes a substantially triangular shape.