45results 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.

A paraglider controller for controlling a paraglider drive, in particular an electric ascent aid, for a paraglider. The paraglider controller comprises a UI connection interface for sending and / or receiving user commands comprising a voice signal. Optionally, the ascent aid control further comprises a flight data interface for receiving flight data. Furthermore, the ascent aid control comprises an evaluation unit for evaluating received user commands and optionally flight data, wherein a user signal is output via the UI connection interface and / or a control signal is output via a control interface. An input and / or an output of user commands is thereby carried out using the UI connection interface by means of the speech signal.

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 disclosure discloses a landing aid for a parachutist, in particular for a tandem jump or landing with heavy equipment, having an air bag, which protects the parachutist during landing, wherein the air bag has an inflow opening through which air can flow into the air bag in order to fill it by means of the airstream. It is provided that the landing aid comprises a spring element, by means of which the inflow opening is held in the correct position with respect to the air flow and / or an unpacking process of the air bag is supported.

The utility model discloses a paraglider control handle which comprises a cross rod, a first through hole is formed in the middle of the upper surface of the cross rod, a connecting rope is connected into the first through hole in a sliding mode, a hook is fixedly connected to one end of the connecting rope, and a connecting ring is movably connected to the top of the outer surface of the hook. According to the paraglider control handle, through the arrangement of the first through hole, the hook, the connecting ring, the stud, the nut and the hand rope, the stud penetrates through the first through hole, so that the connecting rope is connected with the cross rod, then the nut is in threaded connection with the outer surface of the stud, the trapezoidal ring is installed, and a paraglider rope is connected with the hook through the connecting ring; rapid installation of the paraglider handle and the rope is achieved, the convenience of assembly and disassembly is improved, the hand rope is wound around the outer surface of the trapezoidal ring, the phenomenon that a tightening mark is caused to the hand in the using process is avoided, a flight person can select to grab the hand rope or the cross rod for operation according to the requirement in the flying process, and the using requirement is met.

The utility model discloses an intelligent deformation double-wing-head vertical take-off and landing aircraft, and relates to the technical field of aircrafts. The intelligent transformation double-wing-head vertical take-off and landing aircraft comprises an aircraft body, vertical take-off and landing mechanisms, folding and unfolding mechanisms and at least two wing heads, and the vertical take-off and landing mechanisms are arranged on the two sides of the aircraft body and used for driving the aircraft body to take off and land vertically; the folding and unfolding mechanism is arranged at the top of the machine body; the at least two wing heads are separably arranged on the folding and unfolding mechanism, the at least two wing heads are distributed at intervals in the vertical direction, and the folding and unfolding mechanism is used for folding or unfolding the wing heads. According to the intelligent transformable double-wing-head vertical take-off and landing aircraft, the aircraft body takes off and lands vertically, so that the aircraft does not need to slide during take-off, and the requirement for a flight site is not high; when the aircraft breaks down, the wing heads can provide lift force for the aircraft body and buffer the aircraft body, so that the aircraft body slowly descends in a gliding state, safe falling of the aircraft body is guaranteed, and direct crash of the aircraft body is avoided.

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 present invention provides a rotor assembly and a single-rotor moving device for reducing counter-torque. The rotor assembly is arranged on a single-rotor aircraft. The rotor assembly includes a blade assembly, a reverse transmission assembly and a motor. The motor includes a stator and a rotor. The rotor rotates relative to the stator. The reverse transmission assembly is connected to the blade assembly and the rotor respectively. The rotor drives the blade assembly to rotate. The rotor and the blade assembly rotate synchronously in the opposite direction. With the above structure, during the movement of the single-rotor moving device, the motor drives the blade to rotate. During the operation of the motor, the rotation of the rotor will also cause counter-torque to act on the stator. The rotor and the blade rotate synchronously in the opposite direction, so that the direction of the counter-torque brought by the rotor rotation is opposite to the direction of the counter-torque brought by the rotor. The two sets of counter-torque forces offset each other, which can reduce the counter-torque brought by the rotor, thereby reducing the energy consumption of the body for balancing the counter-torque output.

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 coaxial electric paramotor for long-duration paraglider flights relates to the field of: equipment for fitting in or to aircraft; flight suits; parachutes; arrangement or mounting of power plants or propulsion transmissions in aircraft. The claimed solution is designed to allow an economical and simple use of energy for making long-duration paraglider flights without significant vibrations and torque and with a low level of noise. The proposed coaxial paramotor can be used by individuals and organizations for transportation. The essence of the utility model described herein lies in the use of a coaxial configuration of counter-rotating propellers, the diameter of which is significantly greater than those typically used in paramotors, together with the use of brushless electric motors or coaxial reduction gears.

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.