379results about "Wing shapes" patented technology

An airfoil having: a composition gradient defining a first coefficient of thermal expansion and a second coefficient of thermal expansion that differs from the first coefficient of thermal expansion; and a thermoelectric junction operationally coupled to the composition gradient, wherein the composition gradient is formed of either of a plurality of dissimilar metals or of plastic with fillings or fibers.

The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.

A hydrogen aircraft includes: an airframe including a fuselage and a wing; at least one propulsion system fixed to the airframe; a pressurized chamber disposed inside the fuselage; a pressure bulkhead that is disposed at a rear part of the pressurized chamber and has strength to withstand pressurization of the pressurized chamber; a hydrogen tank that is disposed in an accommodation section and stores liquid hydrogen, the accommodation section being installed behind the pressure bulkhead, outside the pressurized chamber, and inside the fuselage; and a supply line that supplies the liquid hydrogen stored in the hydrogen tank to the propulsion system.

Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.

The invention provides a displacement vortex generator and a position regulation and control method, and belongs to the field of active flow control equipment. The VG comprises a belt, a belt guide rail, a belt bearing, a sliding block, a supporting column, a triangular VG body, a guide rail supporting block, a limiting groove, a body connecting plate and a motor. The belt is arranged on the belt guide rail and is driven by the motor; the sliding block is arranged on the belt, is in an inverted concave shape and is connected with the body connecting plate through the supporting column, and the VG bodies are fixed to the two ends of the body connecting plate. The belt guide rail is arranged on the guide rail supporting block, and the sliding block can penetrate through the limiting groove. The motor is controlled to drive the belt to drive the sliding block and the VG body to move, and accurate adjustment of the position of the vortex generator body is achieved. The position of the vortex generator is automatically adjusted according to changes of the incoming flow wind speed and the attack angle, the optimal pneumatic effect is kept under different working conditions, the pneumatic performance and the power generation efficiency of the wind turbine blade are remarkably improved, and the negative influence of the front edge roughness can be effectively weakened.

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 aircraft wing includes a main wing and a high lift assembly which includes a high lift body and a connection assembly movably connecting the high lift body to the main wing, such that the high lift body is movable between retracted and extended positions. The connection assembly includes primary and secondary connectors mountable to and engageable with the main wing via primary and secondary mount profiles, respectively. The primary connector is rotatable relative to the primary mount profile and at least one of the connection assembly and the main wing to configure the primary connector and mount profile between a decoupled configuration in which the primary connector may be moved into so as to be engaged with, and removed from so as to be disengaged from, the primary mount profile, and a locked configuration wherein movement between the primary mount profile and the secondary mount profile is restricted.

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 airfoil for an aircraft having an airfoil geometry. The airfoil geometry includes an upper surface and a lower surface, the upper and lower surfaces are in accordance with Cartesian coordinate values of X and Y. The Cartesian coordinate values of X and Y are non-dimensional values from 0 to 1 convertible to dimensional values by multiplying the Cartesian coordinate values of X and Y by a chord length of the airfoil. The upper surface and the lower surface form an enclosed airfoil shape. The aircraft is a supersonic aircraft, and the airfoil has a thickness-to-chord ratio of about 10%.

Four or more rotors installed on an aircraft include: a pair of first rotors that are left / right symmetrically arranged in front of a front wing about a position overlapping the central axis of a fuselage in plan view; and a pair of second rotors that are left / right symmetrically arranged between the front wing and a rear wing about a position overlapping the central axis of the fuselage in a plan view. The distance between the fuselage and the second rotors in the width direction is longer than the distance between the fuselage and the first rotors in the width direction.

Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.

An aircraft designed for vertical take-off and landing (VTOL) and fixed wing flight. The aircraft's structure includes a streamlined fuselage, forward swept wing and a canard, featuring a configuration of propulsors symmetrically embedded along the aircraft's longitudinal center of gravity and tilting propellers on the forward swept wingtips. Additionally, the fuselage includes doors to the propulsor ducts that can be opened for vertical flight and closed for forward flight.

The present invention provides an extreme STOL airplane comprising: a fuselage and a wing having port and starboard wing sections. Each wing section has a body with top and bottom surfaces, leading and trailing edges, and a span, i.e., the distance between a wing section tip and root connected to the fuselage, and flap coves. Aerodynamic elements integrated into the wing sections include Fowler flaps, having leading and trailing edges and a span, flap tracks, wherein the flap tracks are external to the wing section body, extend aftward beyond the trailing edge of the wing section, and are configured to enable the Fowler flaps to rotate or deflect and to translate or extend and retract, Frise ailerons, wherein the Frise ailerons are located outboard of the Fowler flaps, and spoilerons located over the leading edge of the Fowler flaps when the flaps are in the fully extended position.

The present invention provides an extreme STOL airplane comprising: a fuselage and a wing having port and starboard wing sections. Each wing section has a body with top and bottom surfaces, leading and trailing edges, and a span, i.e., the distance between a wing section tip and root connected to the fuselage, and flap coves. Aerodynamic elements integrated into the wing sections include Fowler flaps, having leading and trailing edges and a span, flap tracks, wherein the flap tracks are external to the wing section body, extend aftward beyond the trailing edge of the wing section, and are configured to enable the Fowler flaps to rotate or deflect and to translate or extend and retract, Frise ailerons, wherein the Frise ailerons are located outboard of the Fowler flaps, and spoilerons located over the leading edge of the Fowler flaps when the flaps are in the fully extended position.

Principles described herein allow for wings to be optimized for aerodynamic and structural efficiency while reducing planform compromises required to address wing tip stall problems. All-moving outboard wings allow the outboard wing local angle of attack to be changed relative to the inner wing region to avoid tip stall at high aircraft angles of attack, such as that which is required for low-speed flight. During high-speed cruise flight, at low aircraft angle of attack, the outboard wing local angle of attack can be increased to achieve an ideal elliptical lift distribution.

The invention provides a wave rider capable of vertically ascending and descending, and belongs to the technical field of wide-speed-range aircrafts, the wave rider specifically comprises a front edge shock wave generating surface, a central fuselage and sweepback wings located on the two sides of the central fuselage, the two sweepback wings are provided with mounting holes penetrating through the upper surface and the lower surface of the wave rider, and lift fans are mounted in the mounting holes; the lift fans are embedded into the mounting holes and used for providing vertical lift force for the wave rider, the axes of the lift fans are parallel to the vertical axis of the wave rider, and the lift fans on the two sweepback wings are symmetrically distributed on the two sides of the central fuselage. According to the treatment scheme, the vertical lifting capacity is provided for the wave rider, and the high-speed flight aerodynamic performance is considered.

The invention discloses a wide-speed-range variant high-speed aircraft aerodynamic layout, and belongs to the technical field of aircrafts, the wide-speed-range variant high-speed aircraft aerodynamic layout comprises a fuselage, the front end of the fuselage is provided with a drag reduction rod, the rear end is provided with a thrust vectoring nozzle, the left and right sides are symmetrically provided with triangular sweepback wings, and the top is provided with a supporting structure; a high-pressure capturing wing is arranged on the top of the supporting structure. The shock wave separation effect of the drag reduction rod is combined with the high-pressure capture and reflection shock wave induction mechanism of the high-pressure capture wings, so that the aircraft can achieve effective drag reduction and lift augmentation effects in different flight states, and the lift-drag ratio and adaptability of the high-speed blunt cone aircraft are remarkably improved.

An airfoil for a rotor blade includes an airfoil body having a leading edge, a trailing edge opposite the leading edge, an upper surface and a lower surface opposite the upper surface. wherein the airfoil body, in cross-section, has a profile defined by a chord length, a maximum thickness at a midpoint of the chord length, and an s-shaped camber line.

A craft comprises a hull, a wing, a hydrofoil, and a control system. The wing is configured to generate upwards aero lift as air flows past the wing to facilitate wing-borne flight of the craft. The hydrofoil is configured to generate upwards hydrofoil lift during a first mode of operation as water flows past the hydrofoil to facilitate hydrofoil-borne movement of the craft through the water. While the craft is hydrofoil-borne, the control system is configured to determine the upwards aero lift generated by the wing. The control system is further configured to control the hydrofoil to generate downwards hydrofoil lift to counteract the upwards aero lift generated by the wing that maintains the hydrofoil at least partially submerged in the water while the determined upwards aero lift is below a threshold lift.

A wing structure is disclosed having a first span portion including a depth that reduces in a spanwise outward direction, and a second span portion outboard of the first span portion and having a substantially uniform spanwise depth D3. The second span portion may be non-tapered, and may include parallel fore and aft spar portions. In some embodiments the non-tapered portion supports a movable wing tip device. A wing assembly and an aircraft are also disclosed.

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.

An aircraft apparatus is disclosed that has a fuselage; and a wing coupled to the fuselage, where the wing comprises a port outboard wing section and a starboard outboard wing section; where each of the port outboard wing section and the starboard outboard wing section comprise at least one of: curved leading edges of varying radii and curved trailing edges of varying radii.

Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.

An aircraft designed to provide sustained G forces, with a relatively high steady angle of attack maneuverability using less thrust by balancing thrust and drag to sustain a high turn rate with dual low thrust engines using novel wing and fuselage designs. The aircraft includes a wing oriented laterally relative to the fuselage, at least one horizontal tail surface extending laterally from the fuselage and positioned rearward of the fixed wing, and at least one vertical tail surface extending upward from the fuselage. The first and second engines are mounted to the fuselage at locations positioned vertically below the fixed wing.

A vertical / short takeoff and landing aircraft includes a pair of ducted lift / thrust fans that are rotatably movable between a first vertical lift position and a second horizontal thrust position. The lift / thrust fans cantilever from a fuselage of the aircraft, forward of the aircraft's wings. A downwardly exhausting, ducted lift fan is disposed within the aircraft's fuselage, aft of the aircraft's pitch axis. A power plant, disposed within the fuselage, is coupled with the lift / thrust fans and the lift fan by a transmission system. The lift / thrust fans and lift fan are positioned with respect to one another to be triangulated about the aircraft's center of gravity and the aircraft's center of lift.

The invention provides an air-breathing aircraft for long-term flight in an upper atmosphere, and relates to the technical field of aircrafts in the upper atmosphere, the air-breathing aircraft comprises an aircraft body, the aircraft body is provided with an air-breathing electric propulsion system, the outer contour of the aircraft body is cylindrical, and an air inlet channel is arranged in the center of the aircraft body; the air inlet channel comprises a gradually-shrinking conical inlet pipeline, an inwards-concave gradually-shrinking compression pipeline, a cylindrical ionization acceleration pipeline and a gradually-expanding conical outlet pipeline which are sequentially arranged from front to back. The solar cell wings are arranged on the outer side of the aircraft body, the solar cell wings are forward-swept trapezoidal wings, and the solar cell wings can supply power to the air suction type electric propulsion system; the problem that in the prior art, technical defects exist in the aerodynamic configuration design of how to achieve thrust and resistance balance of an aircraft flying for a long time in the upper atmosphere is solved.

An unmanned aerial vehicle comprises: a fuselage (1) containing a nose fairing (2) and a load compartment (6), a front and a rear wings (3, 7) attached to the fuselage (1), a front camera (15) and a sighting camera (16) mounted to the fuselage (1), an engine with a propeller (14) mounted on the rear of the fuselage (1), a communication module with an antenna (17) mounted on the fuselage (1). The front wing (3) contains two height rudders (4) and two vertical fins (5) at its ends, the rear wing (7) contains ailerons (8). The unmanned aerial vehicle additionally contains a keel (11) with a directional rudder (12) and an altimeter (18). Said rear wing (7) additionally contains two consoles (9) at its ends, made with the possibility of attaching to it in the process of assembling the UAV. The said fuselage (1) containing the nose fairing (2) and a load compartment (6) is made of flat plywood sheets.

Leading edge slotted blade row. The invention relates to a blade row (120) comprising at least one blade (120) having at least one leading edge slot (200) delimited by two lateral slot surfaces (210). A radius of curvature (RBA1) at the leading edge (BA) of a first profile (P1) located between said two lateral slot surfaces (210) is greater than a radius of curvature (RBA2) at the leading edge (BA) of a second profile (P2) adjacent to the at least one slot (200). Figure for the abstract: Fig. 5A.