33results about "Microlight aircrafts" patented technology

The present invention discloses a dual-motor coaxial different-direction dual-propeller structure of an electric paramotor. The structure comprises a cylindrical mounting shaft with a central hole inside, wherein a first brushless motor is fixedly sleeved on the mounting shaft; a first blade assembly is rotationally sleeved on the mounting shaft; a second brushless motor is fixedly sleeved on the mounting shaft; a second blade assembly is rotationally sleeved on the mounting shaft; the first blade assembly is in transmission connection with the first brushless motor; the second blade assembly is in transmission connection with the second brushless motor; and during flight, the first brushless motor and the second brushless motor respectively drive the first blade assembly and the second blade assembly to rotate in opposite directions.

The invention pertains to an autonomous aerial vehicle capable of vertical takeoff and equipped with a parafoil wing, which is used in various fields such as military, civil, agricultural, surveillance, and exploration in the aviation sector. The invention particularly concerns an autonomous aerial vehicle with a parafoil wing, where the entire parafoil wing is folded and stored inside a compartment, and vertical takeoff is achieved with its multiple motor structure; subsequently transitioning to efficient flight by deploying the parafoil wing in the air.

The disclosure pertains to a battery-powered personal flying apparatus comprising a body structure adapted to support and detachably couple user thereto, and a pair of wings rotationally coupled to opposite sides of the body structure. The wings preferably comprise at least a humerus portion and radius portion. The radius portion is configured to rotate relative to the humerus and, during use, the wings mimic the motion of bird flight. The disclosure further pertains to a method of facilitating human flight using the personal flying apparatus comprising the steps of maintaining the user's torso and legs in an inline and generally horizontal position, moving a pair of wings having a humerus rotatably coupled to a radius simultaneously through a wing flight pattern, and repeating the wing fight pattern to maintain flight of the user.

The invention pertains to an autonomous aerial vehicle capable of vertical takeoff and equipped with a parafoil wing, which is used in various fields such as military, civil, agricultural, surveillance, and exploration in the aviation sector. The invention particularly concerns an autonomous aerial vehicle with a parafoil wing, where the entire parafoil wing is folded and stored inside a compartment, and vertical takeoff is achieved with its multiple motor structure; subsequently transitioning to efficient flight by deploying the parafoil wing in the air.

The present invention relates to a precision landing unmanned aerodynamic parachute, which comprises a fuselage and a ram-air parachute. A first servo and a second servo are arranged at the rear end of the fuselage and are respectively connected to a first rocker arm and a second rocker arm. The ram-air parachute is connected to the ends of the first rocker arm and the second rocker arm. The ram-air parachute is simultaneously fixed on both sides of the fuselage frame. The fuselage is loaded with traveling wheels, which include a steering wheel, a first directional wheel and a second directional wheel, and are arranged in a three-point manner. The fuselage is loaded with a plurality of brushless motors, which provide the main power at the front end of the fuselage and the reverse thrust auxiliary power at the rear end of the fuselage through connecting propellers. A navigation and control system is carried on the fuselage, which specifically includes a flight controller and a GPS positioning device, a vision-assisted positioning device and a barometric altimeter electrically connected thereto. A power supply system is also included. The present invention has reverse thrust assistance, can greatly reduce the turning radius of the unmanned power parachute and improve the landing accuracy, and improve the accuracy of the power parachute.

A personal flying apparatus comprising a body structure adapted to support and detachably couple a user thereto; and a pair of wings rotationally coupled to opposite sides of the body structure and powered by a battery, the body structure comprises a torso portion and a leg portion; the leg portion being hingedly coupled to the torso portion; the torso portion comprising a harness configured to hold a user. The leg support comprises a pair of leg struts configured to be coupled to a user's legs; the leg struts being free to move independent of one another. The leg struts allow the user to move their legs relative to the torso portion, independently from each other, allowing the athlete to run during take off.

This present invention relates to the field of aircraft and discloses an aircraft and a method for connecting a canard to an arm. The connection method is used to couple a canard and an arm. The canard comprises a coupling insertion portion, which comprises a plurality of fixing portions. The arm comprises an arm insertion cavity, and an insertion opening is provided at one end of the arm insertion cavity. The coupling insertion portion is configured to be inserted into the arm insertion cavity through the insertion opening and is fixed within the arm via the fixing portions. In the present invention a detachable structure is enabled between the canard and the arm, allowing the position of the center of lift to be adjusted by exchanging canards featuring different designs, thereby adapting to aircraft cabins with different centers of gravity.

The disclosure pertains to a battery-powered personal flying apparatus comprising a body structure adapted to support and detachably couple user thereto, and a pair of wings rotationally coupled to opposite sides of the body structure. The wings preferably comprise at least a humerus portion and radius portion. The radius portion is configured to rotate relative to the humerus and, during use, the wings mimic the motion of bird flight. The disclosure further pertains to a method of facilitating human flight using the personal flying apparatus comprising the steps of maintaining the user's torso and legs in an inline and generally horizontal position, moving a pair of wings having a humerus rotatably coupled to a radius simultaneously through a wing flight pattern, and repeating the wing fight pattern to maintain flight of the user.

A parafoil aircraft is used as a field treatment delivery vehicle. Advantages are a relatively low airspeed to facilitate timed spraying over target areas of the field, ability to control flight to be close to the crop canopy, ability to carry a heavy cargo of treatment agent, short take-off and landing distance, and, unlike copter aircraft, limited turbulence caused by the parafoil aircraft that can interfere with targeted spraying over the field.

Disclosed herein is a helicopter flight support device for emergency situations. The helicopter flight support device includes a motor that causes a threaded shaft to rotate, which is coupled to the underside of a helicopter. This causes an outer support device and an inner support device to deploy until they form a wing-like configuration. The interior of the wing includes a plurality of support cables for tensioning the wing. The helicopter flight support device also includes upper and lower support cables mounted on the ends of the wing to provide horizontal stability.

The application discloses a large-delivery-ratio soft-wing unmanned aerial vehicle, the lower part of the wing parachute is provided with at least two groups of front and rear connected sling belts, each of the sling belts is provided with a pre-delivery hanging point and a post-delivery hanging point, the sling cabin is provided with a pre-delivery connecting point and a post-delivery connecting point corresponding to each of the pre-delivery hanging point and the post-delivery hanging point, the pre-delivery connecting point corresponding to the pre-delivery hanging point is connected through a pre-delivery connecting rope, the post-delivery connecting point corresponding to the post-delivery hanging point is connected through a post-delivery connecting rope, the pre-delivery connecting rope is shorter than the post-delivery connecting rope, and the pre-delivery connecting rope can be disconnected from the pre-delivery connecting point after the task load is delivered. The application realizes the synchronous movement of the sling cabin hanging point and the sling cabin gravity center after the task load is delivered, reduces the flight angle of attack, and has the capacity of delivering large-size and large-weight loads.

The invention relates to a reserve parachute for a paragliding aircraft, comprising: - a reserve canopy, - suspension lines connected to the reserve canopy, - a tether (15) connected to the suspension lines at one end and configured to be connected to a harness of the glider in its installed state at the other end, characterized in that the tether (15) is made of bundles (20) of polyamide fiber strands (22), the bundles (20) of polyamide fiber strands (22) having heat-shrinkable polyamide fibers, the bundles (20) of polyamide fiber strands (22) being assembled into a tether (15). Figure for the abstract: [Fig. 3]

Aircraft wing profile (1), connecting the lower surface (15) and the upper surface (13) of the wing (1) for separating the wing (1) into cells, characterized in that it comprises a flexible, supporting sheet cut into a streamlined shape giving the cross-section of the wing (1) when deployed, at least one reinforcing wire fixed at least at points to the flexible sheet, the reinforcing wire extending between the connection zone of the profile (17) to the upper surface (13) and the connection zone of the profile (17) to the lower surface (15), such that the reinforcing wire opposes its tensile strength to the stresses exerted between the lower surface (15) and the upper surface (13) during the flight of the aircraft. Figure for the abbreviation: Fig. 2

The invention relates to a transport method for transporting a load (50) by means of a paraglider (20) with a transport device (23) comprising a lifting device (24) with a connecting element (25) and a coupling means (26). It has at least the following steps: A receiving position (AP) of the load (50) is approached by means of the paraglider (20). The coupling means (26) is coupled to the load (50) before or during the approach. A lifting force exerted on the load (50) by means of the connecting element (25) is adjusted until the receiving position (AP) is reached, in which the paraglider (20) is located substantially vertically above the load (50). The lifting force is regulated by means of the lifting device (24) so ​​that it is equal to or greater than the weight of the load (50) in the receiving position (AP). Furthermore, the invention includes a paraglider control unit (30) and a paraglider (20).

The disclosure pertains to a harness for battery-powered personal flying apparatus. The harness comprises a pair torso struts hingedly coupled to a pair of leg braces which allow the legs to move independently of each other. The harness further includes extension rods coupled at a first end to the torso struts. The extension rods are coupled at a second end thereof to skis. The extension rods and skis being moveable between a standing position and an in-flight position. Said extension rods and skis configured to allow the harness to be independently supported in such a way that a user could step into or out of the harness from a generally upright position.

A canopy attachment assembly comprising at least one yoke, wherein the at least one yoke comprises at least two connection points; a canopy line system, configured to be securable to the at least one yoke in use via at least two connectors, wherein each of the at least two connectors is configured to fit exclusively into a predetermined one of the at least two connection points in the at least one yoke, such that the canopy line system is securable to the at least one yoke in one orientation only.

The invention relates to an electrical lift aid (1) for a paraglider (GS) comprising a harness (GZ) for supporting a pilot (P), wherein the lift aid (1) comprises a thrust motor (50) having a rotor (52), a spacer element (10) for spacing the thrust motor (50) behind the pilot (P) in the direction of flight (FR), a number of thrust rods (60) and at least two rotary joints (20, 30, 30'), wherein the thrust rods (60) are pivotally mounted on a first end (10v) of the spacer element (10) close to the pilot by means of a first rotary joint (20), and wherein the thrust motor (50) is pivotally mounted on a second end (10h) of the spacer element (10) at a distance from the pilot by means of a second rotary joint (30, 30'). The invention also relates to a method for achieving a gliding flight phase (III) with an electrical lift aid (1).

A motorized propeller-driven paragliding propulsion system comprising a wing, lines, a harness (2) mounted on a rigid frame (3) which carries a pilot (1) positioned in front of the frame (3) and creating a turbulence zone (6) behind him, characterized in that two propellers are directly driven by two identical electric motors powered by a battery, controlled by an electronic flight controller, rotating in opposite directions and maintained in the same vertical plane, offset by a rearward offset at the rear of the frame (3) and laterally offset by two lateral offset arms anchored by a central fitting at the rear of the frame (3) so that the airflow processed by the propellers is not impacted by the turbulence zone (6). Figure for the abbreviation: Fig. 1

A compact fixed wing aircraft which may be folded or partially disassembled for ease of storage or transport. The aircraft engine(s) may telescopically slide into the fuselage for ease of transport or storage. The aircraft may feature two engines powering separate propellers in a coaxial counter-rotating propeller assembly. The aircraft may feature manufacturing improvements including load bearing truss structures cut from single sheets or plates of metals, the use of high strength metals, or the use of solid polymer sheets as a surface covering.

The utility model relates to the technical field of aviation, and particularly provides a folding wing with a mixed structure and an aircraft comprising the wing. The hybrid structure folding wing comprises a folding wing leading edge beam assembly, a rigid telescopic supporting rod, a folding wing trailing edge beam, a rigid sliding connecting rod, a rotating sleeve assembly and a wing root supporting beam, the front end of the rigid sliding connecting rod is hinged to one of hinge points of a main beam short rod and a secondary beam short rod of the wing leading edge beam assembly, and the rear end of the rigid sliding connecting rod is hinged to the other of hinge points of the main beam short rod and the secondary beam short rod of the wing root supporting beam. The rear end of the rotating sleeve assembly is in sliding connection with the rotating sleeve assembly, and the rotating sleeve assembly comprises a locking device. Under the acting force of the wing folding / unfolding device, the wings can be unfolded / folded in parallel in the vertical direction of the longitudinal axis of the aircraft body, the fixed wings are formed after the wings are unfolded, lift force can be provided for the aircraft, corresponding loads can be borne, the size and the area of the wings are reduced by multiple times after the wings are folded, and storage and transportation are convenient.

The invention relates to a flying apparatus (100) comprising a main structure of airframe or fuselage (20) and a rotative wing surface (10), the rotation of the rotative wing surface (10) allowing stabilizing the apparatus (100) during taking-off, landing and displacing through the air. The fuselage (20) hangs from the rotative wing surface (10) around a hanging point, allowing the rotative wing surface (10) and the fuselage (20) be moveable independently with respect to each other and the rotative wing surface (10) is configured as a disc with a concave surface, being orientable in order to manoeuvre the apparatus (100), and comprising one or a plurality of orientable elements (11) acting as security and secondary command and control surfaces, orienting the apparatus (100) in desired directions. The flying apparatus (100) of the invention comprises a main structure of airframe or fuselage (20) and a rotative wing surface (10): the wing surface (10) can overwrap at least partially the structure of the fuselage (20) in order to improve the aerodynamic performance. In the flying apparatus (100) according to the invention, the airframe or fuselage (20) and the rotative wing surface (10) are rotatable around any of three rotational axis (X, Y and / or Z), independently to each other.

The invention relates to a transport method for transporting a load (50) by means of a paraglider (20) with a transport device (23) that comprises a lifting device (24) with a connecting element (25) and a coupling means (26). Said method comprises at least the following steps: a pick-up position (AP) of the load (50) is approached by means of the paraglider (20), the coupling means (26) is coupled to the load (50) before or during the approach, and a lifting force exerted on the load (50) by means of the connecting element (25) is adapted until the pick-up position (AP) is reached in which the paraglider (20) is located substantially perpendicularly above the load (50). In the process, the lifting force is adjusted by means of the lifting device (24) such that, in the pick-up position (AP), the lifting force is greater than or equal to a weight force of the load (50). The invention further comprises a paraglider control unit (30) and a paraglider (20).

Paraglider tow release with a simple attachment and release mechanism characterized by The principle is to use a sleeve (2) over a milled part (1) as a fastening and release mechanism. This very simple mechanism is the fundamental idea behind our trailing pawl. The special design ensures that a release is always guaranteed, regardless of the prevailing release conditions (different pull angles of the tow rope and under load or without load).

The present invention relates to a paraglider canopy and a paraglider including the same. The paraglider canopy according to an embodiment of the present invention includes an upper wing (210), a lower wing (220) disposed below the upper wing and spaced apart from the upper wing, a plurality of air cells (230) each formed independently between the upper wing and the lower wing, and an air inlet (240) formed in a leading edge of the upper wing and the lower wing to allow outside air to enter each of the plurality of air cells (230), wherein the leading edge of the upper wing and the lower wing may be formed of tubercles (212).

There is disclosed a rotorcraft comprising: an array of lift devices supported at a structure; a first group of the lift devices configured to generate thrust in a first common direction; a second group of the lift devices being tilted or tiltable relative to the first group of devices so as to generate thrust in at least a second common direction; and a flight control system.

The application discloses a method for improving glide ratio of a ram-wing parachute, and belongs to the technical field of ram-wing parachutes. The glide performance of the ram-wing parachute is improved by changing the shape of the parachute cloth through a mechanism method. The shape memory alloy is adopted. After the ram-wing parachute inlet parachute cloth is unfolded, the resistance wire is heated, the shape memory alloy wire props up the cover cloth at the leading edge cutout, and the shape memory alloy wire restores to a shape capable of cutting off the ram-air inlet. The leading edge air inlet is in a closed state. The method can solve the adverse effect of the ram-wing parachute leading edge air inlet on the glide performance of the ram-wing parachute, and improve the aerodynamic performance of the ram-wing parachute.

To provide methods and apparatus for recovering an unmanned aerial vehicle (UAV) with a kite.SOLUTION: The apparatus for recovering a UAV 120 during flight includes a tether 108, a tensioner 110 operatively coupled to the tether, and a kite 116 operatively coupled to the tether to support the tether for recovery of the UAV.SELECTED DRAWING: Figure 1

A parafoil aircraft is used as a field treatment delivery vehicle. Advantages are a relatively low airspeed to facilitate timed spraying over target areas of the field, ability to control flight to be close to the crop canopy, ability to carry a heavy cargo of treatment agent, short take-off and landing distance, and, unlike copter aircraft, limited turbulence caused by the parafoil aircraft that can interfere with targeted spraying over the field.