A vertical takeoff and landing fixed-wing aircraft comprises a fuselage and semicircular wings (2) symmetrically distributed relative to the fuselage on the left and on the right. Propellers (3) rotating around the axial directions of the semicircular wings are disposed in the semicircular wings. The semicircular wings are symmetrically disposed on the left side and the right side of the fuselage, the propellers rotating around the axial directions of the semicircular wings are disposed in the semicircular wings, and the semicircular wings and the propellers integrally rotate around the axis perpendicular to the fuselage; an unmanned aerial vehicle vertically takes off and lands, hovers and cruises by adjusting the attitudes of the semicircular wings and the propellers, thereby reducing the duration of flight of the unmanned aerial vehicle; by replacing traditional fixed wings with the semicircular wings, the volume and the weight of the unmanned aerial vehicle are reduced, the loading capacity and the flexibility of the unmanned aerial vehicle are improved, the operation of the unmanned aerial vehicle is stable, and the aerodynamic performance of the unmanned aerial vehicle is good.
An unmanned aerial vehicle tabletop crossing training system. The system comprises: a first starting point and a first ending point, wherein a plurality of levels are provided between the first starting point and the first ending point, each level respectively comprising a processor, an infrared diffuse-reflection type sensor, an LED light and a communication module; an output end of the infrared diffuse-reflection type sensor is connected to an input end of the processor; an output end of the processor is connected to an input end of the LED light; and the processor is connected to the communication module. By means of the unmanned aerial vehicle application solution provided by the system, the system can not only improve the flight operation skill of a consumer, but is also safe, interesting and challenging, can detect a training result in real time by means of a scoring and ranking list function, is very convenient and has a wide application range, and can be widely applied to the field of unmanned aerial vehicles.
Disclosed is an unmanned aerial vehicle safe house, comprising a safe house body (1), and a protection roof (2) covering the top end of the safe house body (1), wherein the safe house body (1) comprises several door leaves (10), the several door leaves (10) being successively end-to-end connected to form a polygonal structure, and a hinge portion (11) being provided between any two adjacent door leaves (10), so as to enable the two adjacent door leaves (10) to be hinged to each other, and one of the hinging portions (11) being a latch hinge, so that the two adjacent door leaves (10) corresponding to the latch hinge are in a detachable hinge connection. The unmanned aerial vehicle safe house has a simple structure and is very easy to assemble and disassemble.
E06B 3/48 - Battants reliés par leurs bords, p.ex. battants repliables
E04H 17/16 - Clôtures construites en éléments rigides, p.ex. avec des panneaux de fil de fer supplémentaires ou avec des poteaux utilisant des éléments préfabriqués genre panneaux, p.ex. châssis en fil métallique
4.
UNMANNED AERIAL VEHICLE TRAINING BARRIER WITH OBSTACLES
Disclosed is an unmanned aerial vehicle training barrier with obstacles, comprising a main body, wherein the main body comprises a casing, a bottom portion and a fan blade, the fan blade is arranged above the bottom portion, the bottom portion is provided with an electric motor, the bottom portion is further mounted with an infrared diffuse reflection sensor for detecting whether the unmanned aerial vehicle has passed the barrier, and the electric motor is connected to the fan blade; and the casing is fixedly connected to the bottom portion. In the unmanned aerial vehicle training barrier with obstacles provided by the present invention, by designing the combination of the sensor and the fan blade, when the training begins, the fan blade rotates, increasing the fun and difficulty in the training. When the unmanned aerial vehicle overcomes the rotating impediment of the fan blade and passes through the barrier, the sensor detects the corresponding information. The present invention is very convenient, improves the user experience, and is broadly applicable in the field of unmanned aerial vehicles.
Disclosed is an unmanned aerial vehicle training barrier, comprising a main body, wherein the main body comprises a bottom portion (1), and an infrared diffuse reflection sensor (2) is mounted on the bottom portion. By providing the sensor on the bottom portion of the barrier to detect whether the unmanned aerial vehicle has passed the barrier, the unmanned aerial vehicle training barrier is very convenient and fast, has a simple design structure and low costs, small size and many style variations, and can be broadly applied in the field of unmanned aerial vehicles.
Disclosed is a fixed-wing unmanned aerial vehicle which takes off and lands vertically, comprising a body (1), a wing (2) fixedly arranged on the body (1) and an empennage fixedly arranged at the tail of the body (1), and further comprising two pairs of auxiliary wings (3), wherein the two pairs of auxiliary wings (3) are rotatably arranged at side ends of the body (1), the two pairs of auxiliary wings (3) are respectively arranged at a front end and a rear end, with respect to the wing (2), of the body (1), each pair of the auxiliary wings (3) is symmetrically arranged on two sides of the body (1), and at the positions corresponding to the two pairs of auxiliary wings (3), on the body (1) are provided accommodation grooves (10) for accommodating the two pairs of auxiliary wings (3) when a fixed wing is in flight. The unmanned aerial vehicle which takes off and lands vertically has the advantage of it being convenient to take in and extend the auxiliary wings (3), has a good flight performance and is convenient to package and transport.
Disclosed are an infrared sensing apparatus and an unmanned aerial vehicle timing system applying the apparatus. The apparatus comprises: a sensing frame (1) through which an unmanned aerial vehicle can pass, wherein one side of the sensing frame (1) is provided with an infrared receiver (31), and the other side opposite same is provided with an infrared transmitter (32); the sensing frame (1) is provided with a circuit board (5); the circuit board (5) is provided with a controller and a communication module; and the sensing frame (1) is provided with indicator lights (2). The system comprises: at least two infrared sensing apparatuses and a display screen. By means of arranging the infrared receiver (31) and the infrared transmitter (32) on two opposite sides of the sensing frame (1), the passing through of an unmanned aerial vehicle can be detected and is indicated by means of the indicator lights (2). The structure of the apparatus is simple, and there is no need to arrange a response unit on the unmanned aerial vehicle, thus reducing the load of the unmanned aerial vehicle. The apparatus is convenient to use. In addition, by means of communication between several sensing frames (1), timing can be carried out for an unmanned aerial vehicle racing competition, and the time is displayed by means of a display screen.
G07C 1/28 - Enregistrement ou indication de l'heure d'un événement ou d'un temps écoulé, p.ex. horodateurs pour la main-d'œuvre en rapport avec des jeux ou des sports indiquant la durée du jeu
A63B 71/06 - Dispositifs indicateurs ou de marque pour jeux ou joueurs
A game device based on an unmanned aerial vehicle, the device comprising an unmanned aerial vehicle, a remote controller, a detection device, and a ground control station. The unmanned aerial vehicle is installed with an infrared emission module, and the detection device is installed with an infrared receiving module. The unmanned aerial vehicle continuously sends an infrared signal during flight. When the unmanned aerial vehicle passes by the detection device under the control of the remote controller, the sent infrared signal thereof is detected by the detection device and delivered to the ground control station for computation, thus providing an entertainment game related to an unmanned aerial vehicle.
A vertical take-off and landing aircraft having fixed wings, comprising a fuselage (100), wings (210) symmetrically distributed relative to the fuselage (100), and vertical tails (310) vertically connected to the wings (210) and symmetrically distributed relative to the fuselage (100). Rotors (410) are arranged on the wings (210) and the vertical tails (310), and at least the rotors (410) on the vertical tails (310) rotate independently. The aircraft has the advantages of both an aircraft having fixed wings and a helicopter, and may carry out vertical take-off and landing, thus reducing the requirements for a site, and at the same time, the speed, journey and load capacity thereof are greatly improved. In addition, the flight mode is switched by means of the inclination of the whole fuselage (100), so that the aircraft has a low level of technical difficulty, a simple structure, good stability and is simple to operate in comparison to an aircraft having revolving wings.
B64C 27/26 - Giravions complexes, c. à d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
A modularized driving component and a combined model. The modularized driving component comprises power modules (10) and a control module (20) that are independently separable. The power modules (10) are used for generating a driving force. The control module (20) is used for supplying energy to the power modules (10) and controlling the power modules (10). The power modules (10) are detachably connected to the control module (20) via a connecting structure and, relying on the connecting structure, the direction of the driving force generated by the power modules (10) is adjustable. As such, different numbers of the power modules (10) and the control module (20) can be combined freely, or, the power modules (10), the control module (20), and other modules can be freely combined to form different combined models, thus implementing functional expansion; in addition, any module can be replaced directly when malfunctioned, thus aiding the extension of the service life of the combined model, and simplifying repair steps.
An integrated power multi-axis unmanned aerial vehicle, which comprises an internal combustion engine, an electric motor, an electricity storage unit, and an electric drive unit. The internal combustion engine is employed to drive an electric generator to generate electricity so as to provide power to the electric drive unit and the electricity storage unit. Because the energy density ratio of a fuel is high, the employment of electricity for driving the aerial vehicle in flight obviates the need for a complex mechanical structure, thus reducing the weight of the aerial vehicle. The organic combination of fuel-electricity integrated power supply mode greatly extends the range of the unmanned aerial vehicle; at the same time, a cooling fan is provided, and the electric generator can be cooled by the cooling fan, thus preventing the electric generator from being damaged due to overheating. In sum of the above, the integrated power multi-axis unmanned aerial vehicle implements stable, reliable, long-range flight of the unmanned aerial vehicle and is broadly applicable in the technical field of unmanned aerial vehicles.
A battery fixing and mounting structure for a battery self-dismounting unmanned aerial vehicle comprises an unmanned aerial vehicle mainly body (1) and a battery cover (2). A battery chamber (10) used for accommodating a battery (4) is formed in the bottom of the unmanned aerial vehicle mainly body (1). A hinged connection hole is formed in one side of the battery chamber (10). A hinged connection pillar matching the hinged connection hole is disposed on one corresponding side on the battery cover (2). The hinged connection pillar is hingedly connected in the hinged connection hole and enables the battery cover (2) to be hingedly connected onto the unmanned aerial vehicle mainly body (1). A battery cover female buckle is disposed on the other side of the battery chamber (10) distant from the hinged connection hole, and a battery cover male buckle (21) matching the battery cover female buckle is disposed on a free end of the battery cover (2). The battery cover male buckle (21) can tightly button up the battery cover female buckle on the unmanned aerial vehicle mainly body (1) and limits the battery (4) in the battery chamber (10), and the battery cover male buckle (21) and/or the battery cover female buckle are/is members the shapes of which can be changed. The battery fixing and mounting structure for a battery self-dismounting unmanned aerial vehicle has the advantages: the battery fixing and mounting structure has a simple structure, is easy to implement, can protect the safety of the unmanned aerial vehicle mainly body, and can effectively prolong the service of the unmanned aerial vehicle, and the like.
B64C 1/32 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés Éléments de fuselage séparables ou largables facilitant l'évacuation de secours
B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
13.
TOOL-FREE STRUCTURE FOR FAST REPLACEMENT AND MOUNTING OF EXTERNAL MODULE TO UNMANNED AERIAL VEHICLE
A tool-free structure for fast replacement and mounting of an external module to an unmanned aerial vehicle comprises an unmanned aerial vehicle main body (1) and an external module (2). The external module (2) can be detachably mounted on the unmanned aerial vehicle main body (1) by means of a fast dismounting assembly. The fast dismounting assembly comprises a sliding rail (31) mounted on the unmanned aerial vehicle main body (1). The external module (2) is provided with a U-shaped sliding groove (32) for matching the sliding rail (31) and capable of moving on the sliding rail (31). An end portion of the sliding rail (31) is provided with a one-side button bayonet (33). The external module (2) is provided with a one-side button (34) matching the one-side button bayonet. The one-side button (34) can be fastened on the one-side button bayonet (33) and can tightly fasten the external module (2) to the unmanned aerial vehicle main body (1). The tool-free structure for fast replacement and mounting of an external module to an unmanned aerial vehicle has the advantages of being convenient to dismount and mount, being flexible in application, and having a nice appearance of the whole machine.
A fastening structure for fast dismounting and replacement of an arm of a multi-shaft unmanned aerial vehicle and for uniform force bearing comprises an unmanned aerial vehicle main body (1) and a detachable arm assembly (2). The unmanned aerial vehicle main body (1) and the detachable arm assembly (2) are electrically connected in a pluggable manner. The unmanned aerial vehicle main body (1) is provided with a frame connecting head (3), the detachable arm assembly (2) is provided with an arm connecting head (4) matching the frame connecting head (3), and the frame connecting head (3) and the arm connecting head (4) are detachably connected and connect the unmanned aerial vehicle main body (1) and the detachable arm assembly (2) as a whole. The fastening structure for fast dismounting and replacement of an arm of a multi-shaft unmanned aerial vehicle and for uniform force bearing has the advantages of being convenient to dismount and mount, high in connecting strength and being capable of effectively reducing the size and the like, which are not available on the existing products.
A method for controlling a laser radar based micro unmanned aerial vehicle (UAV), comprising: collecting real time laser ranging information; performing UAV pose calculation, synchronous positioning, map building and dynamic route planning according to the laser ranging information so as to generate a motor driving signal to control flight of the UAV. A system for controlling a laser radar based micro unmanned aerial vehicle (UAV), comprising: a UAV flight control module, a laser ranging radar module and a motor. The method and system introduce to the civil domain the key technology of autonomous navigation of a UAV in a low-altitude complex environment, thereby improving navigation reliability in a low -altitude complex environment while reducing hardware cost. The method and system are widely used in the technical field of UAVs.
An unmanned aerial vehicle having a linked folding structure, comprising a vehicle base (100), and a plurality of vehicle arms (200) and landing gear (300) distributed along the perimeter of the vehicle base (100), and also comprising connecting rods (400), the number of vehicle arms (200) being the same as the number of landing gear (300), the tail end of the vehicle arms (200) being provided with a first rotating structure, a second rotating structure being arranged on the side of the first rotating structure toward the head end of the vehicle arm (200), the tail end of the landing gear (300) being provided with a third rotating structure, a fourth rotating structure being arranged on the side of the third rotating structure toward the head end of the landing gear (300), the vehicle arms (200) and the landing gear (300) being hinged to the vehicle base (100) by means of the second and the fourth rotating structures respectively, and the connecting rods (400) being hinged to the vehicle arms (200) and the landing gear (300) by means of the first and the third rotating structures respectively to form a connecting mechanism, the connecting mechanism having a folded state and an opened state, and being able to switch between the two states; the overall volume of the present unmanned aerial vehicle can be reduced by means of folding, facilitating storage and transport of the unmanned aerial vehicle; and rapid switching of the unmanned aerial vehicle from a folded state to an opened state can be implemented.
An adaptive variable-pitch propeller, and aircraft. The propeller comprises a main shaft (1), blades (2), a rotorhead (3), a spring (4), blade fasteners (5), connecting rods (6), and a connecting rod securing member (7). The rotorhead (3) is sleeved on and connected to the main shaft (1), and slidable along the same. The connecting rod securing member (7) is mounted to an end portion of the main shaft (1). The spring (4) is arranged between the rotorhead (3) and the connecting rod securing member (7). The blade fasteners (5) have one end fixed to one of the blades (2), and the other end rotatably connected to the rotorhead (3). The connecting rods (6) are rotatably connected to the connecting rod securing member (7) and the blade fasteners (5). The blade fasteners (5) can drive the blades (2) to slide along the main shaft (1) together with rotorhead (3) as an integral body, and are driven, during the sliding motion, by the connecting rods (6) to rotate with respect to the rotorhead (3), such that angles of the blades (2) with respect to the rotation plane are changed, and the spring (4) can have deformation along with the axial motion of the rotorhead (3). The adaptive variable-pitch propeller can adaptively change the propeller pitch along with the change of a flying speed, thus enabling an aircraft to have superior efficiency across different speeds. The adaptive variable-pitch propeller achieves automated pitch variation by means of a mechanical structure, eliminating a need of a control system or an additional drive device.
A multi-purpose unmanned aerial vehicle and a control system. The unmanned aerial vehicle comprises a main control module, a camera, an infrared emission unit, an infrared reception unit, a GPS module, a 24 GHZ wireless transmission module, a memory, and a flight driving module. The control system comprises a multi-purpose unmanned aerial vehicle, a VR helmet, a remote control, and a mobile intelligent terminal. The multi-purpose unmanned aerial vehicle is separately connected to the VR helmet and the remote control, and implements, by the remote control and the VR helmet, location tracking, tracking shot, and unmanned aerial vehicle interaction functions, thereby resolving the problems in which a conventional unmanned aerial vehicle product only has a single function, lacks compatibility, and causes resource wastes owing to being exclusively used for one function. The multi-purpose unmanned aerial vehicle and the control system are widely applicable to the field of remote-controlled unmanned aerial vehicles.
An unmanned aerial vehicle, comprising a central processing unit, an infrared transmitting unit and an infrared receiving unit. An output end of the central processing unit is connected to an input end of the infrared transmitting unit, and the output end of the infrared receiving unit is connected to the input end of the central processing unit. The unmanned aerial vehicle system comprises the unmanned aerial vehicle and a remote control device for controlling the unmanned aerial vehicle, and the remote control device is connected to the unmanned aerial vehicle via a wireless signal. Further provided is an unmanned aerial vehicle-based spatial battle method in which, by adding ID information of the unmanned aerial vehicle in an infrared signal, a firing error ratio in an infrared battle can be reduced. For an operator, in addition to aerial photography and the experience of flight, one or more unmanned aerial vehicles can participate in a simulated air battle shooting game, improving enjoyment of the unmanned aerial vehicle.
A small unmanned aerial vehicle with a rotary body comprises a body (1) provided with an inside-installed power supply and a control system. The body is provided with two oppositely arranged rotor propellers (2) and two oppositely arranged hinges (3). A rotary shaft of the rotor propeller is parallel to the horizontal plane. Wings (4) are hinged on the hinges. The rotary shaft of the hinge is at an angle of 7 ° to 11 ° to the horizontal plane and at an angle of 60 ° to the axis of the corresponding wing. Each wing is provided with a limit mechanism that allows the axis of the wing to remain parallel to the horizontal plane when the wing is in a stationary state. The unmanned aerial vehicle has relatively high mobility and relatively strong endurance.
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