15 results about "Elevon" patented technology

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a tailstock type overwater vertical take-off and landing fixed-wing unmanned aerial vehicle which can float and park on the water surface, can vertically take off to leave the water and is switched into a fixed-wing mode for cruising and level flight. The unmanned aerial vehicle comprises a four-rotor support buoy and a wing body fusion body fixed to the upper portion of the four-rotor support buoy, small wing type buoys are arranged on wing tips of the two sides of the wing body fusion body respectively, and lifting ailerons capable of deflecting up and down are arranged on the rear edges of wings on the two sides of the wing body fusion body respectively. And four motor rotor propeller propelling devices are uniformly arranged at the tip part of the four-rotor bracket buoy.

The systems, methods, and other embodiments described herein relate to controlling the elevons of an aircraft to stabilize the fuselage of a free-wing aircraft. In one embodiment, the system includes a processor and a memory storing machine-readable instructions. When an instruction is executed by the processor, the processor 1) measures the fuselage pitch attribute of the aircraft, 2) measures the wing pitch angle of the wing assembly, and 3) controls the angles of the elevons of the wing assembly based on the fuselage pitch attribute and the wing pitch angle, so that the fuselage and wing assembly of the aircraft rotate independently of each other and freely around the pitch axis of the aircraft.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and / or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

The invention relates to the technical field of small unmanned aerial vehicles, and discloses a vertical take-off and landing composite wing unmanned aerial vehicle based on flying wing layout, the vertical take-off and landing composite wing unmanned aerial vehicle comprises a fuselage, wings are fixedly connected to the exteriors of the two sides of the fuselage, vertical tails are fixedly connected to the exteriors of the wings, and mounting columns are fixedly connected to the interiors of one sides of the wings; the exterior of the mounting column is provided with double reverse propellers, the exterior of the fuselage is provided with an optical take-off and landing auxiliary module, the interiors of the wings are rotatably connected with lifting ailerons, the upper surfaces of the lifting ailerons are fixedly connected with mounting blocks I, and the exteriors of the mounting blocks I are rotatably connected with telescopic rods; and a second mounting block is rotationally connected to the outer portion of the telescopic rod, the bottom end of the second mounting block is mounted on the upper surface of the wing, and a supporting mechanism is mounted at the foot point. The lifting ailerons with the increased area are arranged on the rear edges of the wings, so that the unmanned aerial vehicle can quickly and stably complete vertical and horizontal attitude conversion in a narrow space.

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a front wing for an unmanned aerial vehicle, which comprises a front wing body used for being connected to a fuselage of the unmanned aerial vehicle, and further comprises a lifting aileron connected to the leeward side of the front wing body through a flexible connecting piece, the lifting aileron is used for being regulated and controlled by the lifting aileron control device to conduct pitching deflection, so that in the flight process of the unmanned aerial vehicle, the lifting aileron is regulated and controlled through the lifting aileron control device to conduct pitching deflection, and the flight attitude of the unmanned aerial vehicle is controlled. According to the unmanned aerial vehicle lifting aileron, the lifting aileron and the front wing body are flexibly connected through the flexible connecting piece, the flexible connecting piece limits the moving position of the lifting aileron, meanwhile, the connecting rigidity of the lifting aileron and the front wing body is weakened, and the operability of the unmanned aerial vehicle lifting aileron is improved.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and / or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

An aircraft (10) comprising: a port swept wing (14B) and a starboard swept wing (14A), each swept wing having an inner wing section (26A) comprising an integrated payload fuselage (20) and an outer wing section (30A) 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 the sweep angle of each outer wing section is lower than the sweep angle of the corresponding inner wing section; a central region (12) where the port swept wing meets the second swept wing; a port transition region (23A) where the port inner wing section meets the port outer wing section; a starboard transition region (23B) where the starboard inner wing section meets the starboard outer wing section; at least one rear spar on each wing, in which each rear spar is disposed close to a trailing edge (22A) of the wing to carry loads along the respective wing; one or more elevons (34A) or ailerons on each outer wing section; and one or more roll spoilers (32A) on each inner wing section.

Aircraft with a fuselage (12) and two wings (14, 16) arranged on opposite sides of the fuselage (12), wherein the wings (14, 16) each comprise at least one ducted propeller (22, 24) and each comprise at least one adjustable elevon (40, 42, 44, 46), wherein the ducted propellers (22, 24) are activatable at least in a vertical flight phase and the elevons (40, 42, 44, 46) are pivotable about a rotational axis (D) at least between a first position and a second position, wherein the elevons (40, 42, 44, 46) in the second position enclose a larger angle (a) to a horizontal plane than in the first position, wherein the elevons (40, 42, 44, 46) are adjusted to the second position in the vertical flight phase.

The present disclosure relates to an aircraft comprising two or more propulsion devices and a fuselage integrated with a pair of wings to constitute a hybrid wing (BWB) structure wherein the orientation of the fuselage and the pair of wings changes as the aircraft transitions from a vertical attitude to a horizontal attitude. Further, each wing of the pair of wings includes a lower winglet and an upper winglet that are identical and connected to each other at the wingtip. The aircraft also includes a plurality of elevons that are controlled by two or more propellers associated with the two or more propulsion devices.

Systems, methods, and other embodiments described herein relate to controlling aircraft elevons to stabilize a free-wing aircraft fuselage. In one embodiment, a system includes a processor and a memory storing machine-readable instructions. The instructions, when executed by the processor, cause the processor to 1) measure a fuselage pitch attribute of an aircraft, wherein a fuselage and wing assembly of the aircraft freely rotate about a pitch axis of the aircraft independently of one another, 2) measure a wing pitch angle of the wing assembly, and 3) control an angle of an elevon of the wing assembly based on the fuselage pitch attribute and the wing pitch angle.

A fluid flow-driven generator (1) for generating energy from a flow of liquid or gas that comprises a fluid-driven device (3, 4) comprising at least one movable foil (41) that has an adjustable angle of attack, a sensor (24) for sensing a magnitude of a dynamic environmental or structural factor that is indicative of a dynamic load on the fluid-driven device, and a governor (21) for controlling the angle of attack of the foil according to the magnitude of the factor to moderate the drag on the foil in the flow. This allows the ratio of the power coefficient Cp of the generator to the drag on the foil to be optimised, increasing the capacity factor of the generator. The fluid-driven device may comprise a fluid-driven flapping mechanism that undergoes reciprocal motion in the flow. Alternatively, or additionally, the governor may be configured to control the amplitude of the reciprocal motion according to the magnitude of the factor. Also disclosed is a passive or semi-passive fluid-driven flapping mechanism that comprises a swing arm (3) having a hydrofoil pivoted on a fulcrum (43) at a distal end (38) thereof, and at least one elevon (42) pivoted to the hydrofoil for movement between two opposite angled states relative to the hydrofoil. An elevon angle control mechanism (50, 55, 80) is arranged to invert the angle of the elevon at the end of each stroke of the swing arm, causing automatic reversal of the pitch of the hydrofoil. The angle of the elevon may be adjusted according to the magnitude of the factor automatically to control the angle of attack of the hydrofoil

The utility model belongs to the technical field of aircraft manufacturing, and discloses an elevator positioning tool which comprises a cross beam and a plug block, the cross beam is provided with a plurality of positioning assemblies, the positioning assemblies are matched to enable the cross beam to be positioned relative to a horizontal stabilizer of an empennage, and one end of the cross beam extends to the lower portion of the edge of an elevator and is provided with a supporting piece. An inspection gap is formed between the supporting piece and the skin of the elevator; the plug block is in lap joint with the supporting piece and is contained in the inspection gap. Wherein the plug block has various height sizes. The deviation range of the elevator can be judged and adjusted by observing and adjusting the gaps between the elevator and the plug blocks with different heights, then the elevator is positioned within the allowable error range near the zero position, the positioning precision of the elevator is improved, meanwhile, the elevator positioning tool is simple in structure and convenient to operate, the labor cost of elevator positioning can be reduced, and the working efficiency is improved. The assembling efficiency is improved, and efficient and high-quality assembling is achieved.

The present invention relates to a vertical takeoff and landing control method for a distributed-power tandem-wing UAV, belonging to the technical field of UAV flight control. The tandem-wing UAV comprises an inner ring power unit and an outer ring power unit disposed on the leading edges of the front and rear wings; elevons are symmetrically hinged to the trailing edges of both ends of the rear wing; and the front and rear wings are connected by a connecting assembly to form a tandem wing with a spatial height difference. The control method includes controlling the jump takeoff, transition flight, cruising flight, and vertical landing phases by distributing throttle amounts between the inner ring power unit and the outer ring power unit during the jump takeoff, cruising flight, and vertical landing phases. A continuous climb transition method is employed during the transition phase, and after the transition is completed, the flight state is controlled to transition to a cruising level flight state. The present invention enables the tandem-wing UAV to perform large-angle jump takeoff and autonomous 90-degree vertical landing. Furthermore, a control distribution design for the UAV's distributed power is implemented to improve energy utilization and extend flight time.

Systems, methods, and other embodiments described herein relate to controlling aircraft elevons to stabilize a free-wing aircraft fuselage. In one embodiment, a system includes a processor and a memory storing machine-readable instructions. These instructions, when executed by the processor, cause the processor to: 1) measure a fuselage pitch property of the aircraft wherein the fuselage and wing assemblies of the aircraft are free to rotate independently of each other about a pitch axis of the aircraft; 2) measuring a wing pitch angle of the wing assembly; and 3) controlling the angle of the lifting aileron of the wing assembly based on the fuselage pitch attribute and the wing pitch angle.

The invention provides a method and device for determining the clamping stagnation angle of a lifting aileron and analyzing the influence of the lifting aileron, and belongs to the technical field of aircraft pneumatic and operation stability control. The method comprises the steps that the clamping stagnation angle of the lifting aileron is determined according to the use requirement of the lifting aileron of an aircraft within the normal use range, and the influence of the lifting aileron is analyzed; the using requirements of the lifting aileron of the aircraft in the normal using range comprise the lifting aileron skewness required by the aircraft in the normal flight in the air to reach the preset steady-state overload in a using envelope and the lifting aileron skewness when the aircraft reaches the preset pitch angle speed at the initial climbing speed of full-engine work; and calculating and analyzing the longitudinal maneuvering capability of the clamping stagnation state and calculating and analyzing the rolling maneuvering capability of the clamping stagnation state based on the clamping stagnation angle. According to the method, for an unconventional layout aircraft, the clamping stagnation angle of the clamping stagnation of the lifting aileron serving as the composite control surface can be accurately evaluated, so that the influence of the clamping stagnation of the lifting aileron on the flight quality and the flight safety can be effectively analyzed.