58results about "Microlight aircrafts" patented technology

The invention relates to a flight state system (20) for ascertaining a flight state of a paraglider (50, 50′) which comprises a canopy (51) with two canopy ends (52) and which carries a load (53) during intended use. Thereby, the flight state system comprises a sensor arrangement (S1, S2, S3) for ascertaining a first distance (d1) between the canopy ends (52) and / or at least a second distance (d2, d3) between a canopy end (52) and the load (53). Furthermore, the flight state system comprises an evaluation unit (37) which ascertains the flight state using the first distance (d1) and / or the second distances (d2, d3). The invention further relates to an evaluation system and / or control system (40), a paraglider (50, 50′) and a method for ascertaining a flight state of a paraglider (50, 50′).

The invention discloses a double-motor coaxial different-direction double-paddle structure of an electric paraglider, which comprises a cylindrical mounting shaft with a middle hole inside, and a first brushless motor, a first paddle component, a second brushless motor and a second paddle component are fixedly sleeved on the mounting shaft in sequence; the first paddle assembly is in transmission connection with the first brushless motor, the second paddle 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 paddle assembly and the second paddle assembly to rotate in opposite directions.

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.

There is provided an improved weight-shift control flexible wing aircraft and improved systems and methods for recovering or preventing a spiral dive or a stall of a weight-shift control flexible wing aircraft. The aircraft including a frame; a wing assembly defining a flexible sail extending from port to starboard sides of the vehicle, the flexible wing assembly comprising: a wing keel extending from fore to aft ends of the wing assembly; a pair of wings, wherein each side of said pair of wings has a strut coupled to and extending away from the wing keel and defines a leading edge and a trailing edge when the wing assembly is moved though air, wherein the trailing edge of each side of said pair of wings is configured for actuable reversible billowing in at least a portion along a length of the trialing edge.

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.

A paragliding harness (14) comprising a seat (16), a backrest (17), two paragliding wing attachment points, and a reserve harness connection device (1) for the harness (14) intended to be connected to a reserve parachute (13), characterized in that the reserve harness connection device (1) comprises: two reserve risers (3) attached to the harness (14) laterally on either side of the seat (16), at or above the paragliding wing attachment points, and an automatic system for righting the pilot upon deployment of the reserve parachute, comprising two righting lines (7), each attached to the backrest (17) or to the lateral periphery of the backrest (17) and to one of the reserve risers (3). Figure for the abstract: 1

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 provides a power flying wing capable of vertically taking off and landing, which relates to the technical field of aircrafts, aims to solve the problem that a power flying wing in the prior art cannot vertically take off and land, and comprises a propeller assembly, a traction arm, a support frame, a left flying wing and a right flying wing, the left flying wing and the right flying wing are symmetrically arranged on the left side and the right side of the supporting rack and rotationally connected with the supporting rack, the propeller assembly is connected to the top end of the traction arm, and the bottom end of the traction arm is rotationally connected with the top end of the supporting rack. When the power wind-moving wings vertically take off and land, the propeller assemblies rotate to be in a horizontal state through the traction arms, and when the power wind-moving wings horizontally fly, the propeller assemblies rotate to be in an inclined state through the traction arms. According to the power flying wing capable of vertically taking off and landing, vertical taking off and landing of the power flying wing are achieved, a runway is not needed, and flying is more convenient.

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.

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.

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 invention relates to the technical field of aircrafts, and discloses an aircraft and a canard and arm connecting method thereof. The canard and arm connecting method is used for coupling a canard and an arm, the canard comprises a coupling insertion part, and the coupling insertion part comprises a plurality of fixing parts; the vehicle arm comprises a vehicle arm insertion cavity, an insertion opening is formed in one end of the vehicle arm insertion cavity, and the coupling insertion part can be inserted into the vehicle arm insertion cavity through the insertion opening and is fixed in the vehicle arm through the fixing part. According to the method for connecting the canards and the arms, the canards and the arms form a detachable structure, and the position of the lift center can be adjusted by replacing the canards of different styles so as to adapt to aircraft cabins of different gravity centers.

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 invention relates to a connection device for an electrical (11) or electronic device in a paragliding aircraft (100), comprising: - two terminals on a harness (5) in which the user (U) is seated, configured to be connected to a power supply (50), - at least two terminals on the wing (1), configured to be connected to electrical (11) or electronic devices on the wing (1), characterized in that it further comprises at least two suspension lines (31, 33), each with a conductive line electrically connecting one terminal on the harness (5) to one terminal on the wing (1). Figure for the abstract: Fig. 1

The present invention provides a detachable portable parafoil powered propulsion device and a method for using the same. The detachable portable parafoil powered propulsion device comprises two symmetrical propulsion units, wherein the propulsion units comprise a bottom guide plate, a top cover plate, a jet thruster, a motor, a propeller and a locking structure. The present invention solves the control response lag problem of a traditional powered parafoil and the problem that a cloth umbrella-shaped structure may be folded in a crosswind or a strong wind and cannot maintain a wing shape.

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 present invention relates to a delta wing flight simulator that comprises a structure (1) with a base (41) and two collapsible arches (42, 43) that can be collapsed by means of actuators hinged on the base (41), according to perpendicular axes that are coplanar and perpendicular to each other, and joined by a sliding crosshead (44), located at the intersection of both arches (42, 43); a pilot support (2) joined to the crosshead (44); a delta wing bar (3) or triangle joined to the crosshead (44) that is located in front of the support (2); a sensor controller (4) for controlling movement of the support (2); a control system (6) that acts on the digital simulation and operates the actuators based on the simulated flight parameters and the pilot's movements detected by the controller (4); and a display system for the pilot.

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 utility model discloses a combined aircraft which comprises an aircraft body, a rotor wing flight mechanism, a delta wing mechanism and a propelling mechanism, and the rotor wing flight mechanism is used for generating first aerodynamic force for vertical take-off and landing of the aircraft body; the unfolded delta wing mechanism is used for generating second aerodynamic force of the fuselage, the folded delta wing mechanism can be separated from the fuselage to accelerate the fuselage, and the propelling mechanism provides forward flight power for the fuselage. The first aerodynamic force generated by the rotor wing flight mechanism is used for vertically lifting the aircraft and switching the flight attitude; when the aircraft is switched to the low-altitude flight state, the delta wing mechanism is unfolded to generate second aerodynamic force for the aircraft body, stable lift force can be provided for the aircraft body, and therefore the endurance time is prolonged, and meanwhile the aircraft can be matched with the propelling mechanism to fly forwards. In addition, the delta wing mechanism in a separated and folded state can reduce the air resistance of the combined aircraft, and the rotor wing flight mechanism can realize rapid flight in a short time, so that more flight requirements are met.

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]