09 - Appareils et instruments scientifiques et électriques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
39 - Services de transport, emballage et entreposage; organisation de voyages
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Aviation drive trains; electric motors for aircraft. Computer hardware and software for aircraft; electricity
storage apparatus for aircraft. Motor vehicles by land, air, water or rail; air vehicles;
the aircraft; military drones; civilian drones; aerial drone
(not toy); photo drones; small remote-controlled camera
drones; delivery drones; aeronautical installations,
machinery and equipment; space vehicles. Transport of persons and goods by means of aircraft;
transportation and delivery services by air; rental of
aircraft. Custom manufacturing of aircraft; custom construction of
machines in the field of aircraft. Software as a service [SaaS] in the aviation sector.
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
39 - Services de transport, emballage et entreposage; organisation de voyages
Produits et services
Motor vehicles by land, air, water or rail, namely, electrically powered aircraft and electric vertical take-off and landing drones and aircraft; Air vehicles, namely, electrically powered aircraft and electric vertical take-off and landing drones and aircraft; aircraft; Military drones; Civilian drones; Aerial Drones not being toys; Photo drones; Small remote-controlled camera drones; Delivery drones; Aeronautical installations, machinery and equipment, namely, structural parts for aircraft, aircraft fuselages, undercarriage aircraft parts, propellers for aircraft, airfoils for aircraft; Space vehicles Transport of persons and goods by means of aircraft; transportation and delivery of goods by air; rental of aircraft
09 - Appareils et instruments scientifiques et électriques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
28 - Jeux, jouets, articles de sport
39 - Services de transport, emballage et entreposage; organisation de voyages
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Electric drive units, other than for land vehicles; Motors, electric, other than for land vehicles. Computer hardware and software for land vehicles, aircraft and water vehicles; Electricity storage apparatus for land vehicles, aircraft and water vehicles. Electrically powered motor vehicles by land, air, water or rail; Drones; Aeronautical installations, machinery and equipment; Space vehicles; Electric drive units for land vehicles. Sporting articles and equipment, especially electrically driven paragliders, electrically driven surf boards and electrically driven hydrofoils for surfing. Transport of persons and goods by means of aircraft; Transportation and delivery services by air; Rental of land vehicles, aircraft and water vehicles. Customization of land vehicles, aircraft and water vehicles; Custom construction of machines in the field of land vehicles, aircraft and water vehicles. Software as as Service [SaaS] in the field of land vehicles, aircraft and water vehicles; Technical research in the field of land vehicles, aircraft and water vehicles; Engineering services in the field of land vehicles, aircraft and water vehicles; Certification [quality control] in the field of land vehicles, aircraft and water vehicles.
A method of measuring airflow velocity using an integrated heating airspeed tube where the integrated heating airspeed tube has a tube body and a heating component. The tube body is provided with a heating cavity, the heating component is located inside the heating cavity, and the heating component and the tube body are integrally formed. The heating component and at least two static pressure air inlet channels are physically separate but overlap in a lengthwise directly within a horizontal portion of the airspeed tube. The tube body integrally forms the static pressure air inlet channel, the dynamic pressure air inlet channel, the heating cavity, the dynamic pressure air inlet hole, and the static pressure air inlet hole as a unitary one-piece structure.
A method to test a power system and an avionics equipment of an unmanned aerial vehicle (UVA) including providing a support component, a power system load-bearing component, an avionics equipment load-bearing component, a jacking component and a roller component. The method further includes providing a plurality of power system load-bearing components that are fixedly arranged on the support components, respectively, and each power system load-bearing component is configured to carry the power system of a UAV; the avionics equipment load-bearing component is fixedly arranged on the support component, and the avionics equipment load-bearing component is configured to bear the avionics equipment of the UAV; the output end of the jacking component is fixedly connected to the bottom end of the support component.
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G01R 1/04 - Boîtiers; Organes de support; Agencements des bornes
G01R 31/00 - Dispositions pour tester les propriétés électriques; Dispositions pour la localisation des pannes électriques; Dispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
8.
Method of testing an unmanned aerial vehicle (UAV) using a test bench
A method to test an unmanned aerial vehicle (UAV) using a support component, a universal rotating component, a fixed component and a return component. The method further includes wherein the universal rotating component slides along the Z direction and is arranged on the support component, and one end of the universal rotating component can rotate in a universal way relative to the other end of the universal rotating component. The fixed component is connected to one end of the universal rotating component, and the fixed component is configured to fix the UAV. One end of the return component is connected to the support component, the other end is connected to the other end of the universal rotating component, and the return component is configured to drive the universal rotating component and the fixed component to reset.
A method to transport a battery for an unmanned aerial vehicle using a battery transport box, the box having a box body shell and an upper cover. The unmanned aerial vehicle battery transport box further having a heat dissipating device and a heating device. When the temperature in the box body is lower than the lower limit of the set temperature range, the heating device heats the box body. When the temperature in the box body is higher than the upper limit of the set temperature range, the heat dissipating device dissipates heat of the box body. The temperature in the box body is adjusted by the heating device and the heat dissipating device.
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B60L 50/64 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant de la puissance de propulsion fournie par des batteries ou des piles à combustible utilisant de l'énergie fournie par des batteries - Détails de construction des batteries spécialement adaptées aux véhicules électriques
B60L 58/27 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des batteries pour la commande de la température des batteries par chauffage
09 - Appareils et instruments scientifiques et électriques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
39 - Services de transport, emballage et entreposage; organisation de voyages
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Aviation drive trains; electric motors for aircraft. Computer hardware and software for aircraft; electricity storage apparatus for aircraft. Motor vehicles by land, air, water or rail; Air vehicles; The aircraft; Military drones; Civilian drones; Aerial Drone (not toy); Photo drones; Small remote-controlled camera drones; Delivery drones; Aeronautical installations, machinery and equipment; Space vehicles. Transport of persons and goods by means of aircraft; transportation and delivery services by air; rental of aircraft. Customization of aircraft; custom construction of machines in the field of aircraft. Software as a service [SaaS] in the aviation sector.
11.
Method of flight control in a vertical takeoff and landing aerial vehicle with angled propellers
A method of flight control including having a vertical takeoff and landing aerial vehicle that has a plurality of lift propellers disposed on two linear support pieces, and there are two vertical stabilizers disposed at the rear of the two linear support pieces. A rotating shaft of each lift propeller from among the multiple lift propellers outwards forms an angle of 5 degrees to 15 degrees relative to a vertical plane of the aerial vehicle perpendicular to a horizontal plane of the aerial vehicle. The aerial vehicle of the present disclosure improves the heading axis control capacity of the aerial vehicle and reduces the restriction to the design size of the aerial vehicle.
A method of balanced charging that includes the use of a plurality of charging modules, each of which independently charges a battery unit and is provided with a positive port and a negative port with independent functions; the positive port is connected with the positive port of the battery unit corresponding to the charging module, and the negative port is connected with the negative port of the battery unit corresponding to the charging module.
An unmanned aerial vehicle (UAV) test bench, which falls within the technical field of UAV test, comprising a support component, a universal rotating component, a fixed component and a return component: the universal rotating component slides along the Z direction and is arranged on the support component, and one end of the universal rotating component can rotate in a universal way relative to the other end of the universal rotating component. The fixed component is connected to one end of the universal rotating component, and the fixed component is configured to fix the UAV. One end of the return component is connected to the support component, the other end is connected to the other end of the universal rotating component, and the return component is configured to drive the universal rotating component and the fixed component to reset.
An experimental bench for an unmanned aerial vehicle (UAV) power system and avionics equipment, which relates to the technical field of UAV test, comprising a support component, a power system load-bearing component, an avionics equipment load-bearing component, a jacking component and a roller component. A plurality of power system load-bearing components are provided, and are fixedly arranged on the support components, respectively, and each power system load-bearing component is configured to carry the power system of a UAV; the avionics equipment load-bearing component is fixedly arranged on the support component, and the avionics equipment load-bearing component is configured to bear the avionics equipment of the UAV; the output end of the jacking component is fixedly connected to the bottom end of the support component.
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G01R 1/04 - Boîtiers; Organes de support; Agencements des bornes
G01R 31/00 - Dispositions pour tester les propriétés électriques; Dispositions pour la localisation des pannes électriques; Dispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
15.
VTOL fixed-wing drone with overlapping propellers attached to linear supports connecting fore and hind wings
A long-distance drone having a main body, a left hind wing, a right hind wing, a left forewing, and a right forewing. There is a left linear support connecting the left forewing to the left hind wing, and a right linear support connecting the right forewing to the right hind wing. A plurality of propellers are disposed on the left and the right linear supports.
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
An unmanned aerial vehicle (UAV), and specifically discloses a UAV transport box. The UAV transport box has a mounting frame, a box body, a driving device, and a control system. The box body has a bottom plate and a side plate, the bottom plate is fixedly installed on the mounting frame, the UAV is arranged on the bottom plate, and the side plate can be unfolded through the driving device, so that the side plate and the bottom plate are in the same plane to form an area which is large enough to provide a suitable take-off and landing platform for the UAV, and can realize the automatic opening and closing for the UAV transport box.
B65D 88/52 - Grands réceptacles pliables, c. à d. avec des parois articulées entre elles ou démontables
B60P 3/11 - Véhicules adaptés pour transporter, porter ou comporter des charges ou des objets spéciaux pour le transport de véhicules pour le transport d'avions
B65D 85/68 - Réceptacles, éléments d'emballage ou paquets spécialement adaptés à des objets ou à des matériaux particuliers pour machines, moteurs ou véhicules assemblés ou en pièces détachées
The disclosure provides a method of controlling the yaw of a fixed-wing UAV, with two propulsion propellers arranged parallel to each other and providing thrust for the UAV; A plurality of motors configured to drive the two propulsion propellers, wherein the thrust ratio provided by the two propulsion propellers is changed to generate asymmetric thrust which controls the active yaw of the UAV. The fixed-wing UAV provided by the disclosure improves the reliability of the thrust system and active yaw.
The disclosure provides a method of controlling the yaw of a fixed-wing UAV, with two traction propellers arranged parallel to each other and providing thrust for the UAV; A plurality of motors configured to drive the two traction propellers, wherein the thrust ratio provided by the two traction propellers is changed to generate asymmetric thrust which controls the active yaw of the UAV. The fixed-wing UAV provided by the disclosure improves the reliability of the thrust system and active yaw.
The disclosure provides a fixed-wing UAV, with two pull propellers or two push propellers arranged parallel to each other and providing thrust for the UAV. Wherein the thrust ratio provided by the two pull propellers or the two push propellers is changed to generate asymmetric thrust which controls the active yaw of the UAV.
An aircraft having a fuselage and a front landing gear; both sides of the rear bottom of the fuselage are fixedly connected with the rear landing gear; one end of the front landing gear is rotatably connected to the front bottom of the fuselage. When the front landing gear rotates to the first position, the second position and the third position, the connecting line between the end of the front landing gear away from the fuselage and the end of the rear landing gear away from the fuselage intersects with the plane, where the fuselage is located, on the side close to the front of the fuselage, parallel to and intersect on the side close to the rear of the fuselage.
A vertical takeoff and landing (VTOL) UAV having a UAV main body, two rear landing gears and two front landing gears; the two rear landing gears are fixedly connected to both sides of the rear bottom of the UAV main body, respectively; the two front landing gears are rotatably connected to both sides of the front bottom of the UAV main body, respectively. One end of the front landing gear away from the UAV main body is provided with a locating block. Rotating the front landing gear enables the locating block mounted on the front landing gear to get close to or away from the UAV main body.
An unmanned aerial vehicle's (UAV) take-off and landing platform. It includes a driving device, a bottom plate, a movable plate and a tractor. The tractor is connected to the front end of a bearing platform, and the tractor can drive the bearing platform to move; the bearing platform comprises the bottom plate and the movable plate. The movable plate has a first side plate, a second side plate and a third side plate. The first side plate and the second side plate are symmetrically arranged on both sides of the bottom plate, and the third side plate is arranged at the tail end of the bottom plate. The movable plate movably connects with the bottom plate and can move relative to the bottom plate with the drive of the driving device, so that the bearing platform can switch between the folded state and the unfolded state.
B64F 1/22 - Installations au sol ou installations pour ponts d'envol des porte-avions pour la manœuvre des aéronefs
B60P 3/11 - Véhicules adaptés pour transporter, porter ou comporter des charges ou des objets spéciaux pour le transport de véhicules pour le transport d'avions
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
23.
UNMANNED AERIAL VEHICLE AND CONTROL METHOD THEREOF
The present invention discloses an unmanned aerial vehicle and a control method thereof. The unmanned aerial vehicle includes a control module, motor arms, a plurality of lift motors and lift propellers. The control module is used to preset a correspondence between two ends of each motor arm and the corresponding lift motors; the control module is used to control each lift motor to be initiated; the control module is also used to determine whether a lift motor fails, determine a target lift motor and a target position if so, and adjust the power of other lift motors in all the lift motors corresponding to the target position apart from the target lift motor. The present invention improves the flight stability and safety of the unmanned aerial vehicle.
A UAV with vertical takeoff and landing (VTOL) function. having a plurality of lift propellers; a cabin engaged with a plurality of lift propellers; a water propulsion system engaged with the cabin to push the cabin in a forward direction when the cabin is at least partially immersed in water; at least one water inlet engaged with the water propulsion system; the cabin is a cargo hold or a passenger cabin. The UAV provided by the disclosure can realize vertical takeoff and landing in the water area, and fly, drive and navigate freely in the whole area.
A method of navigating an UAV over water with vertical takeoff and landing (VTOL) function. The UAV having a plurality of lift propellers; a cabin engaged with a plurality of lift propellers; a water propulsion system engaged with the cabin to push the cabin in a forward direction when the cabin is at least partially immersed in water; at least one water inlet engaged with the water propulsion system; the cabin is a cargo hold or a passenger cabin. The UAV provided by the disclosure can realize vertical takeoff and landing in the water area, and fly, drive and navigate freely in the whole area.
A method of navigating a detached cabin of an UAV over water. The UAV having a plurality of lift propellers; a cabin engaged with a plurality of lift propellers; a water propulsion system engaged with the cabin to push the cabin in a forward direction when the cabin is at least partially immersed in water; at least one water inlet engaged with the water propulsion system; the cabin is a cargo hold or a passenger cabin. The UAV provided by the disclosure can realize vertical takeoff and landing in the water area, and fly, drive and navigate freely in the whole area.
A vertical takeoff and landing unmanned aerial vehicle and a cooling system for the unmanned aerial vehicle. Heat dissipation in an arm of an unmanned aerial vehicle is achieved by providing a forward-facing opening at the front end of each of a left linear support and a right linear support of the unmanned aerial vehicle, thereby achieving the purposes of lowering temperature in the arm and protecting equipment in the arm.
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]
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant climatisé
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
Produits et services
Motor vehicles by land, air, water or rail; Air vehicles; The aircraft; Military drones; Civilian drones; Aerial Drone (not toy); Photo drones; Small remote-controlled camera drones; Delivery drones; Aeronautical installations, machinery and equipment; Space vehicles.
A vertical takeoff and landing aerial vehicle, including a plurality of lift propellers. A rotating shaft of each lift propeller from among the multiple lift propellers outwards forms an angle of 5 degrees to 15 degrees relative to a vertical plane of the aerial vehicle perpendicular to a horizontal plane of the aerial vehicle. The aerial vehicle of the present disclosure improves the heading axis control capacity of the aerial vehicle and reduces the restriction to the design size of the aerial vehicle.
An amphibious drone having a fuselage, a linear support, a wing and a take-off and landing device. The take-off and landing device is on the lower surface of the linear support or the wing. The take-off and landing device has a buoyancy unit and a power device, and the power device is capable of generating thrust to push the buoyancy unit to move. The take-off and landing device can be on the lower surface of the drone, and realizes the water support of the drone by symmetrically providing the take-off and landing device. At the same time, the take-off and landing device is further provided with a power device for pushing the drone to be started. The amphibious drone can take off and land by relying on the take-off and landing device, which can be disassembled to adapt to different usage conditions.
An unmanned aerial vehicle battery transport box having a box body shell and an upper cover. The unmanned aerial vehicle battery transport box further having a heat dissipating device and a heating device. When the temperature in the box body is lower than the lower limit of the set temperature range, the heating device heats the box body. When the temperature in the box body is higher than the upper limit of the set temperature range, the heat dissipating device dissipates heat of the box body. The temperature in the box body is adjusted by the heating device and the heat dissipating device.
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B60L 50/64 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant de la puissance de propulsion fournie par des batteries ou des piles à combustible utilisant de l'énergie fournie par des batteries - Détails de construction des batteries spécialement adaptées aux véhicules électriques
B60L 58/27 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des batteries pour la commande de la température des batteries par chauffage
The disclosure provides a fixed wing UAV, with two propulsion propellers arranged parallel to each other and providing thrust for the UAV, or two traction propellers arranged parallel to each other and providing thrust for the UAV; A plurality of motors configured to drive the two propulsion propellers or the two traction propellers respectively, wherein the thrust ratio provided by the two propulsion propellers or the thrust ratio provided by the two traction propellers is changed to generate asymmetric thrust which controls the active yaw of the UAV. The fixed wing UAV provided by the disclosure improves the reliability of the thrust system and active yaw.
A balanced charging device and a charging system used to solve the technical problem of too long charging time of the balanced charging device. The balanced charging device comprises a plurality of charging modules, each of which independently charges a battery unit and is provided with a positive port and a negative port with independent functions; the positive port is connected with the positive port of the battery unit corresponding to the charging module, and the negative port is connected with the negative port of the battery unit corresponding to the charging module. The charging system includes the balanced charging device. The balanced charging device and charging system provided by the disclosure are used for charging a plurality of battery units in series.
A UAV with vertical takeoff and landing (VTOL) function having a plurality of lift propellers; a cabin engaged with a plurality of lift propellers; a water propulsion system engaged with the cabin to push the cabin in a forward direction when the cabin is at least partially immersed in water; at least one water inlet engaged with the water propulsion system; the cabin is a cargo hold or a passenger cabin. The UAV provided by the disclosure can realize vertical takeoff and landing in the water area, and fly, drive and navigate freely in the whole area.
A vertical takeoff and landing aerial vehicle and a cooling system for the aerial vehicle. The vertical takeoff and landing aerial vehicle comprises at least one air inlet provided on the top side of a linear support below a lift propeller, and at least one air outlet provided on the linear support. In the vertical takeoff and landing stage of the aerial vehicle provided by the disclosure, airflow generated by rotation of a lift propeller forms a rapid-flowing spatial flow field, which can achieve efficient heat dissipation of a motor and an electronic speed controller in an arm; and in the vertical takeoff and landing unmanned aerial vehicle provided by the utility, the takeoff weight of the unmanned aerial vehicle cannot be increased, power consumption of airborne equipment cannot be increased, and interior space of the arm cannot be occupied.
A vertical takeoff and landing aerial vehicle. A left linear support and a right linear support of the unmanned aerial vehicle are respectively provided with a first group of multiple lift propellers and a second group of lift propellers, and the aerial vehicle is provided with a left dorsal fin and a right dorsal fin. By arranging a plurality of lift propellers, a left dorsal fin, and a right dorsal fin on the vertical takeoff and landing aerial vehicle provided by the disclosure, the aerial vehicle is higher in stability in the flight process.
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 27/28 - Giravions complexes, c. à d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec hélices propulsives de déplacement pouvant pivoter pour agir comme rotors de sustentation
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
A long-distance drone is disclosed having a canard wing configuration with a cabin attached to a left main wing and a right main wing. There is a left forewing and a right forewing connected together to form a single-piece forewing. There is a left linear support connecting the left forewing to the left main wing, and a right linear support connecting the right forewing to the right main wing. A plurality of propellers is disposed on the left and the right linear supports.
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 39/04 - Aéronefs non prévus ailleurs à fuselages ou poutres de queue multiples
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]
B64C 11/46 - Aménagements ou caractéristiques de construction des hélices multiples
B64D 31/00 - Commande des groupes moteurs; Leur disposition
A vertical takeoff and landing aerial vehicle, which comprises a plurality of lift propellers respectively arranged at the top sides of a left linear support and a right linear support, and a left additional lift propeller and a right additional lift propeller respectively arranged on the bottom sides of the left linear support and the right linear support. According to the aerial vehicle provided by the disclosure, the takeoff and landing power of the aerial vehicle is effectively improved and the maximum take-off weight and effective load of the aerial vehicle are improved by using multiple groups of lift motors on the aerial vehicle.
A vertical takeoff and landing aerial vehicle and a cooling system for the aerial vehicle. Heat dissipation in an arm of an aerial vehicle is achieved by installing a fan in a hollow interior of each of a left linear support and a right linear support of the aerial vehicle, thereby achieving the purposes of lowering temperature in the arm and protecting equipment in the arm.
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
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]
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
B64C 11/00 - Hélices, p.ex. du type caréné; Caractéristiques communes aux hélices et aux rotors pour giravions
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
A UAV landing platform having movable covers to securely store/maintain/charge a UAV. The UAV may be launched from the landing platform, and the landing platform can have visual indicators to guide the landing of the UAV back onto the landing platform. There can be an optional mechanism to self-adjust/self-level the landing surface such that a UAV can safely land onto the landing platform even when the landing platform is on a traveling vehicle.
The present invention discloses a multi-rotor aircraft with a multi-axis misalignment layout, which comprises a frame, a plurality of upper power sources, a plurality of lower power sources, a plurality of upper propellers, and a plurality of lower propellers. The plurality of upper propellers are provided at intervals and are connected to the upper part of the frame through the plurality of upper power sources. The plurality of lower propellers are provided at intervals and are connected to the lower part of the frame through the plurality of lower power sources. In the vertical projection direction of the frame, the plurality of upper propellers and the plurality of lower propellers are staggered. The upper propellers and the lower propellers are staggered so that the pitch between the upper propellers and the lower propellers is large.
An integrated heating airspeed tube and an unmanned aerial vehicle where the integrated heating airspeed tube has a tube body and a heating component. The tube body is provided with a heating cavity, the heating component is located inside the heating cavity, and the heating component and the tube body are integrally formed. The unmanned aerial vehicle includes the integrated heating airspeed tube as described above. The integrated heating airspeed tube and the unmanned aerial vehicle are heated in the tube body through the heating component, so that the heating removes liquid, effectively preventing liquid from blocking the integrated heating airspeed tube, and meeting the using requirements in severe weather. At the same time, the integrated heating structure design is higher in reliability and is not easy to cause operation failure, and saves the assembly cost.
A landing platform and method for an unmanned aerial vehicle (UAV), and a charging system. A landing platform (100) for a UAV (101) is provided with a movable cover (105), so as to safely store/maintain/charge the UAV (101). The UAV (101) can be launched from the landing platform (100), and the landing platform (100) may be provided with visual indicators (111, 112, 113, 114, 115) for guiding the UAV (101) to land back on the landing platform (100). An optional mechanism may exist to automatically adjust/automatically level a landing surface (106), such that even when the landing platform (100) is located on a traveling tool, the UAV (101) can still safely land on the landing platform (100).
A visual positioning system, an unmanned aerial vehicle, and a method for self-detecting the position of an unmanned aerial vehicle. The visual positioning system (709) comprises a lens module (702), a matching module (703), a translation module (704) and a sensor module (705); the unmanned aerial vehicle (100) has a body (101), the body (101) has a lower side (1011), and the lens module (702) is provided on the lower side (1011); the lens module (702) has a wide field of view, and captures a series of images (I) of a region under the unmanned aerial vehicle (100) over time during flight; the matching module (703) compares features in each image (I) of the series of images (I), so as to derive first data (D1); and the translation module (704) translates the first data (D1) into positioning data. Said visual positioning system enables the unmanned aerial vehicle to obtain additional/alternative positioning information.
A vertical takeoff and landing (VTOL) fixed-wing aircraft having overlapping propellers and low handing vertical stabilizers disposed on the rear end of the aircraft.
A long-distance drone is disclosed having a canard body style with a main body, a left main wing, a right main wing, a left forewing, and a right forewing. The left forewing is attached to the main body forward of the left main wing, and the right forewing is attached to the main body forward of the right main wing. There is a left linear support connecting the left forewing to the left main wing, and a right linear support connecting the right forewing to the right main wing. A plurality of propellers are disposed on the left and the right linear supports.
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
28 - Jeux, jouets, articles de sport
Produits et services
Vehicles and means of transport; unmanned air and space
vehicles; air vehicles; military drones; civilian drones;
drones with cameras; freight drones; search and rescue
drones; vertical take-off and landing drones; surveillance
drones; delivery drones. Drones [toys].
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
28 - Jeux, jouets, articles de sport
Produits et services
Vehicles and means of transport, namely, drones, helicopters, and propeller-driven aircraft; unmanned air vehicles, namely, drones, helicopters, propeller-driven aircraft, and space vehicles; air vehicles, namely, drones, helicopters, and propeller-driven aircraft; military drones; civilian drones; drones with cameras; freight drones; search and rescue drones; vertical take-off and landing drones; surveillance drones; delivery drones Toy drones
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
28 - Jeux, jouets, articles de sport
Produits et services
Air and space vehicles; Drones; Military drones; Civilian drones; Camera drones; Cargo Drones; Search and rescue drones; VTOL Drones; Survillance Drones; Delivery drones. Drones [toys].
a) of the first radiator (142) so as to discharge the heat sent from the first radiator (142) out of the motor (100) while the turbine (144) is rotating. The radiating device is simple in structure, and solves the problem of heat discharging of the large power brushless DC motor.
