9 results about "Elevon" patented technology

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.

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.

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

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.