189results about "All-wing aircraft" patented technology

A tanker aircraft for long-distance travel, the tanker aircraft including 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 tanker aircraft, a fuel storage located within the blended wing body, the fuel storage comprising a first fuel store, the first fuel store located within the transition and configured for long range flight and a second fuel store the second fuel store having a tanker capacity and a refueling boom system having a flying boom, the flying boom extending from the blended wing body, wherein the tanker aircraft is a long-range tanker aircraft.

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 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 and an outer wing section (30A, 30B) for extending the wingspan, in which each outer wing section has a thickness less than a thickness of the corresponding inner wing section, a central region (12) where the first swept wing meets the second swept wing, a first transition region (23A) where the first inner wing meets the first outer wing section, a second transition region (23B) where the second inner wing meets the second outer wing section, in which at least one extension (44) having an internal volume is provided behind the trailing edge of the wings, the at least one extension being disposed in the central region.

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.

A blended wing body (BWB) aircraft comprising a first composite part comprising, a first dry carbon fiber sheet having a width greater than 3 inches and comprising a first layer comprising dry carbon fibers, a second layer disposed on top of the first layer comprising dry carbon fibers, a stitching extending through the first dry carbon fiber sheet, wherein the stitching is configured to bind the first dry carbon fiber sheet together, and a resin matrix, wherein the stitching and the first dry carbon fiber sheet are embedded within the resin matrix to create a single unified structure. BWB aircraft further comprises a blended wing body, having no clear demarcation along a leading edge of the BWB aircraft from a wing to a nose of the blended wing body, and wherein the first composite part comprises a portion of the blended wing body.

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.

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.

A commercial aircraft for short distance air travel, the commercial aircraft comprising a blended wing body aircraft 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 commercial aircraft, a passenger cabin, the passenger cabin located within the main body and having a wide body passenger capacity, at least a propulsor, the at least a propulsor attached to a portion of the main body and configured to propel the blended wing body commercial 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 a fuel capacity associated with short-range flight, and a landing gear, the landing gear located on an undercarriage of the blended wing body, the landing gear configured for the short-range flight.

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.

A composite assembly for a blended wing body aircraft, the composite assembly comprising: a first assembly comprising a first molded part, wherein the first molded part comprises a first plurality of fibers, the first molded part partially infused with a first resin, a second assembly oriented relative to the first assembly, the second assembly comprising a second molded part wherein the second molded part comprises a second plurality of fibers, the second molded part partially infused with a second resin, and a joining region, the joining region comprising at least a portion of first plurality of fibers and at least a portion of second plurality of fibers, the at least a portion of first plurality of fibers and the at least a portion of second plurality of fibers substantially adjacent and infused with a third resin.

An aircraft notification system, the aircraft notification system having a processor and a memory communicatively connected to the processor, the memory containing instructions configuring the processor to receive aircraft angle data from a blended wing body aircraft (BWB) having a main body and a wing with no clear demarcation between the wings and the main body along a leading edge of the aircraft, determine an aircraft orientation as a function of the aircraft angle data, wherein the aircraft orientation comprises at least a pitch angle of the BWB while the BWB is in contact with a ground surface, transmit the aircraft orientation to an aircraft display system and visually display the aircraft orientation through the aircraft display system.

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 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.

In another aspect, a method for fueling an aircraft, the method including storing liquified gas fuel using a fuel tank, wherein the fuel tank is configured to store liquified gas fuel, fueling an aircraft using a fuel line. Fueling the aircraft may additionally include the fuel tank with liquified gas fuel to a desired level, wherein a desired level comprises fuel for a plurality of flights plus reserves. Filling may also include removing the fuel line as a function of the desired level. The method may additionally include venting the fuel tank using a vent line in fluid connection to the fuel tank. The fuel tank may then be prepared for flight as a function of a desired level. Finally, the method includes flying a plurality of flights using the aircraft.

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.

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 having one or more cross aisles extending along a lateral axis, wherein a shape of the passenger cabin is asymmetrical about a lateral axis, more than one passenger bays located within the passenger cabin, wherein each of the more than one passenger bays are separated by at least one cross aisle of the one or more cross aisles and one or more lavatories situated outside the more than one passenger bays and substantially adjacent to a perimeter of the passenger cabin, wherein each of the one or more lavatories are linked to one cross aisle of the one or more cross aisles.

A system is provided for an aircraft (20). This aircraft system includes an aircraft (20) and an air system (32). The airframe (22) includes a body (26) and a vane (54) connected to the body (26). The vane (54) projects spanwise away from the body (26) to a vane tip (62). The vane extends longitudinally between a leading edge (66) and a trailing edge (68). The vane (54) extends laterally between a first vane side (70A) and a second vane side (70B). The air system (32) includes a circuit inlet (88), a circuit outlet (90A) and an air circuit (86). The circuit inlet (88) is arranged with the body (26) and laterally offset from the vane (54). The circuit outlet (90A) is arranged with the vane (54). The air circuit (86) extends within the airframe (22) from the circuit inlet (88) to the circuit outlet (90A).

Aircraft control systems and methods include accessing data corresponding to a yaw moment command, computing a control effector adjustment command for one or more control effectors, and adjusting the one or more control effectors of the aircraft to implement the control effector adjustment command. The control effector adjustment command includes deflection adjustments for two control surfaces of the aircraft that are spaced apart on a wing of the aircraft along a transverse direction. The two control surfaces of the aircraft deflect in opposite directions to implement the control effector adjustment command.