99results about "All-wing aircraft" patented technology

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.

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.

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.

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.

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.

------ 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.

An oblique flying wing aircraft with internal ducting and airflow. The aircraft may have propulsion units within the wing body. The propulsion units may be off-axis internal to the wing to utilize locations with larger internal space available. In some aspects, the multi-segment oblique flying wing aircraft may have 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.

A system is provided for an aircraft. This aircraft system includes an aircraft and an air system. The airframe includes a body and a vane connected to the body. The vane projects spanwise away from the body to a vane tip. The vane extends longitudinally between a leading edge and a trailing edge. The vane extends laterally between a first vane side and a second vane side. The air system includes a circuit inlet, a circuit outlet and an air circuit. The circuit inlet is arranged with the body and laterally offset from the vane. The circuit outlet is arranged with the vane. The air circuit extends within the airframe from the circuit inlet to the circuit outlet.

An aircraft (10) comprising: a starboard swept wing (14) and a port swept wing, each swept wing having an inner wing section (32) comprising an integrated payload fuselage (20) and an outer wing section (30) for extending the wingspan, in which each outer wing section has a thickness less than a thickness of the corresponding inner wing section; and in which a sweep angle of the inner wing section is greater than a sweep angle of the outer wing section a front spar 36 close to a leading edge (18) of each wing, in at least the outer wing section, and a rear spar (38) close to a trailing edge (22) of each wing, for carrying loads along each wing; a central region (12) where the starboard swept wing meets the port swept wing; a starboard transition region where the starboard inner wing section meets the starboard outer wing section; a port transition region where the port inner wing section meets the port outer wing section; and a load-bearing structural element (40) disposed across each wing from the front spar to the rear spar in the transition region for carrying loads between the front spar and the rear spar of each wing.

An aerial vehicle includes a wing body, a first wingtip, a second wingtip, a first edge, and a second edge. The aerial vehicle includes a pair of coaxial rotors configured to rotate in opposite rotational directions about a vehicle axis and a drive assembly configured to rotate the coaxial rotors. A controller is configured to selectively control thrust produced by the coaxial rotors. Selective control of the thrust produced by the coaxial rotors induces a pitch motion of the aerial vehicle to transition between a horizontal flight state and a vertical flight state. In the horizontal flight state, a collective thrust from the coaxial rotors is directed forward. In the vertical flight state, the collective thrust from the coaxial rotors is directed upward.

A proprotor-driven powered-lift aircraft (PPLA) has at least four proprotors, each of which, in rotation, sweeping a respective annulus of radial extent re that covers, by axis- orthogonal projection, a collective length of 2.1 x re of parallel leading edges of two or more wings to provide a blown wing enhancement that permits pitch transition during flight with greater control throughout the transition. The PPLA preferably has at least three substantially parallel wings, and at least four proprotors, each of which proprotors: affixed to a bracing extended between two of the at least three wings. Hover mode and forward flight modes can both have excellent control, allowing for better flight efficiency.

The invention discloses a power system and method suitable for a diamond-shaped or four-star dart-shaped unmanned aerial vehicle. The power system comprises an engine, a supersonic air inlet channel, an air inlet straight pipe, an exhaust straight pipe, a convergent-divergent spray pipe, a subsonic air inlet channel, an air connecting pipe, a fuel gas connecting pipe, a convergent spray pipe, a first valve, a second valve, a third valve and a fourth valve. In the working process, the two independent air inlet and exhaust pipelines are controlled through the valves, it is ensured that air inlet flow is matched with the requirement of the engine in each flight mode, air loss stability or performance loss caused by rotation is avoided, and the working efficiency and stability of the engine are improved.

Methods and systems for venting a fuel tank includes a fuel tank on a blended wing body aircraft. A fuel tank may include a vent. A vent line is connected to the vent. The vent line is heated. The vent line is attached to an external fuel tank configured to store the collected boil-off gaseous fuel from the aircraft fuel tank.

An assembly is provided for an aircraft. This assembly includes a vertical stabilizer, a first turbine engine, a second turbine engine and an actuation system. The vertical stabilizer extends spanwise from a stabilizer base to a stabilizer tip. The vertical stabilizer extends longitudinally from a stabilizer leading edge to a stabilizer trailing edge. The vertical stabilizer extends laterally between a stabilizer first side and a stabilizer second side. The first turbine engine is movably mounted to the vertical stabilizer at the stabilizer first side. The second turbine engine is moveably mounted to the vertical stabilizer at the stabilizer second side. The actuation system is configured to move the first turbine engine and the second turbine engine relative to the vertical stabilizer.

The invention discloses a wing body fusion aircraft and a control method thereof, the aircraft comprises an aircraft body, a left wing and a right wing, and the wing body fusion aircraft is characterized in that the total wingspan length of the aircraft is S; the length L of the machine body is larger than or equal to 0.4 S and smaller than or equal to 0.6 S; the chord length Lr of the wing roots of the ends, connected with the fuselage, of the left wing and the right wing meets the condition that Lr is larger than or equal to 0.2 S and smaller than or equal to 0.4 S; the wing tip chord length Lt of one end, far away from the fuselage, of each of the left wing and the right wing meets the condition that Lt is greater than or equal to 0.1 S and less than or equal to 0.2 S. Through collaborative innovation of pneumatic, power and structure, long-time and low-power-consumption continuous flight of the wing body fusion aircraft is achieved.

The present application discloses an aircraft. The aircraft comprises (i) a first wing and a second wing, (ii) a fuselage disposed between the first wing and the second wing, and (iii) a first landing gear system disposed at an aft of the aircraft. The first landing gear system comprises a first leg and a second leg that are configured to at least partially rotate around an axis defined by a length of the first wing when the first leg and the second leg are transitioned to a deployed state or a stowed state. The first landing gear system comprises a first actuation system comprising at least a first actuator and a first shock absorber.

An information processing apparatus is provided, including: a prediction result obtainment unit which obtains a result of prediction of weather in stratosphere; and a flight path determination unit which determines a flight path of a flight vehicle based on the result of prediction of weather in stratosphere such that the flight vehicle flies through an area in stratosphere that has been predicted to satisfy a predetermined stratospheric path condition, wherein the flight vehicle functions as a stratospheric platform, and forms a wireless communication area by emitting a beam and provides a wireless communication service to a user terminal in the wireless communication area.

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 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.

An aircraft structure which extends along a longitudinal axis, a lateral axis and a vertical axis, wherein the aircraft structure includes an upper shell and a lower shell that together surround an interior compartment designed for accommodating an aircraft cabin, and a pillar arrangement with at least one support pillar which extends through the interior compartment and connects the upper shell to the lower shell and supports same in relation to each other. An aircraft structure can be provided which is particularly efficient, in particular has a low weight and requires little space and outlay on assembly is achieved in that the interior of the support pillar has at least one flow duct for the conduction of air-conditioned air.