KR20170036297A - Unmanned Aerial Vehicle, Base Station, Unmanned Aerial System and Control Method thereof - Google Patents

Unmanned Aerial Vehicle, Base Station, Unmanned Aerial System and Control Method thereof Download PDF

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Publication number
KR20170036297A
KR20170036297A KR1020150135282A KR20150135282A KR20170036297A KR 20170036297 A KR20170036297 A KR 20170036297A KR 1020150135282 A KR1020150135282 A KR 1020150135282A KR 20150135282 A KR20150135282 A KR 20150135282A KR 20170036297 A KR20170036297 A KR 20170036297A
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South Korea
Prior art keywords
landing
wireless power
unmanned aerial
aerial vehicle
power transmission
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KR1020150135282A
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Korean (ko)
Inventor
김정호
김동현
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한국과학기술원
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Priority to KR1020150135282A priority Critical patent/KR20170036297A/en
Publication of KR20170036297A publication Critical patent/KR20170036297A/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/06—Undercarriages fixed
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/52—Skis or runners
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/007—Helicopter portable landing pads
    • H02J17/00—
    • B64C2201/066—

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Charge And Discharge Circuits For Batteries Or The Like (AREA)

Abstract

The unmanned aerial vehicle system of the present invention includes at least one unmanned airplane and a base station provided as a landing area for the at least one unmanned airplane. A plurality of first landing concave and convex structures are formed on the surface of the landing pad of the base station and a second landing concave and convex structures are formed on the bottom of the landing skid of each of the at least one UAV . Here, each of the plurality of first landing concave and convex structures is a cone-shaped landing protrusion, and the second landing concave-convex structure is preferably a hopper-shaped landing groove for accommodating a cone shape.

Description

Technical Field [0001] The present invention relates to an unmanned aerial vehicle, a base station, an unmanned aerial vehicle,

The present invention relates to an unmanned aerial vehicle, a base station, an unmanned aerial vehicle, and a control method thereof. More particularly, the present invention relates to a unmanned aerial vehicle, a base station, an unmanned aerial vehicle ≪ / RTI >

Unmanned aircrafts, drone, are expected to increase due to the development of unmanned aircraft technology and the increase in demand. Various types of high performance unmanned aerial vehicles are being developed and released. With the development of the technology of the unmanned aerial vehicle such as this, it is expected that it will be possible to use the technology which is increasingly used in the future in everyday life. Among them, UAV is expected to be a substitute for a task that is difficult for a person to perform or a task that takes a long time.

However, in case of conventional UAV, if you use battery, you have a limited flight time. If you choose wired charging method, it will be dangerous to charge in a harsh environment.

In the conventional drone charging method, one dron is charged to one charging platform or a specific position. And it is difficult to develop a remote control or automatic landing technology because the landing should be induced to accurately align to the charging position.

In addition, since the conventional drone charging platform or landing pad is provided on a flat surface, there is a problem that the dron may shake or move in a landing state in a moving body such as a vehicle or a ship or in a vibration place.

1. Publication No. 2013-0020437 2. Published patent 2013-0122715 3. Patent No. 1489641 4. Patent No. 1527210 5. US Patent 9,041,254 6. US Patent 9,004,396 7. US Patent Publication 2015/0069968 8. U.S. Published Patent Application 2014/0032034

SUMMARY OF THE INVENTION It is an object of the present invention to provide an unmanned aerial vehicle, a base station, an unmanned aerial vehicle system and a control method thereof, which are created to solve the problems of the prior art as described above.

It is another object of the present invention to provide a unmanned aerial vehicle, a base station, an unmanned aerial vehicle system and a control method thereof that can maintain a safe landing state even if there is vibration or movement, and is easy to install on a moving object such as a vehicle or a ship.

It is another object of the present invention to provide a UAV, a base station, an unmanned aerial vehicle, and a control method thereof, which can simultaneously charge a plurality of high-speed wireless batteries.

Another object of the present invention is to provide a base station, an unmanned aerial vehicle system, and a control method thereof, in which a plurality of unmanned aerial vehicles having different models or different sizes and shapes can be easily taken off and landed.

It is to be understood, however, that the present invention is not limited to the above-described embodiments and various modifications may be made without departing from the spirit and scope of the invention.

In order to accomplish one aspect of the present invention, an unmanned aerial vehicle system according to exemplary embodiments includes at least one unmanned airplane and a base station provided as a landing area for the at least one unmanned airplane. A plurality of first landing concave and convex structures are formed on the surface of the landing pad of the base station and a second landing concave and convex structures are formed on the bottom of the landing skid of each of the at least one UAV . Here, each of the plurality of first landing concave and convex structures is a cone-shaped landing protrusion, and the second landing concave-convex structure is preferably a hopper-shaped landing groove for accommodating a cone shape. Of course, the first and second landing concavo-convex structures may be formed in opposite shapes.

In the embodiment of the present invention, each of the landing protrusions is provided with a wireless power transmission coil, and each landing slot may be provided with a wireless power reception coil. Therefore, the wireless power transmission coil and the wireless power reception coil are automatically aligned by the engagement of the landing groove with the landing groove upon landing.

In an embodiment of the present invention, each of the first landing concavo-convex structures may be provided with a landing sensor. Here, the landing sensor may be configured as any one of a pressure sensor, a magnetic sensor, an inductive current sensor, an induced voltage sensor, or a proximity sensor.

In the embodiment of the present invention, it is preferable that an electromagnetic wave shielding layer is formed on the upper surface of the landing skid facing the bottom surface.

In the exemplary embodiment of the present invention, the base station includes a plurality of wireless power transmitters connected to each of a plurality of wireless power transmission coils, a plurality of wireless power transmitters connected to the plurality of landing sensors, And a control unit for grouping the power transmission coils and the wireless power transmission units into a landing group and activating the wireless power transmission unit of the landing group to control wireless transmission of electric energy to the landed unmanned aerial vehicle. Here, each of the plurality of wireless power transmission units may be configured to be one of a magnetic induction type or a self-resonance type.

In an embodiment of the present invention, the UAV includes a plurality of wireless power receivers connected to each of a plurality of wireless power receiving coils, and a charging unit charging the battery with electric energy supplied from a plurality of wireless power receiving units.

In another embodiment of the present invention, the base station includes a landing pad having a size capable of landing a plurality of unmanned aerial vehicles, a plurality of landing protrusions protruding conically on the surface of the landing pad, A plurality of transmission coils, a plurality of landing sensors installed on each of the plurality of landing projections, a plurality of wireless power transmission units connected to each of the plurality of transmission coils, and a plurality of landing sensors And a control unit for grouping the transmission coils and the wireless power transmission units corresponding to the landing sensors located therein into a landing group and activating the wireless power transmission units of the landing group to control the supply of electric energy to the landed unmanned airplane .

The UAV of another embodiment of the present invention includes a flying body and a landing skid installed at a lower end of the flying body. A plurality of hopper-shaped landing grooves are formed on the bottom surface of the landing skid so as to be engaged with the landing protrusions, respectively. The landing skid includes a plurality of wireless power receiving coils formed in each of the landing grooves, a plurality of wireless power receiving units connected to each of the wireless power receiving coils, and a plurality of wireless power receiving units, .

The control method of the unmanned aerial vehicle system according to the embodiment of the present invention monitors whether or not the unmanned airplane is landed through a plurality of landing sensors and corresponds to the landing sensors that are operated in conjunction with the landing operation of the unmanned airplane among the plurality of landing sensors The wireless power transmission coils and the wireless power transmission units are grouped into one landing group, the wireless power transmission unit of the landing group is activated to transmit electric energy, the completion of charging of the unmanned airplane is monitored, Terminating the transmission operation of the wireless power transmission units of the landing group, and releasing the landing group.

The unmanned aerial vehicle system according to the present invention can simultaneously charge drones of different sizes in one base station. Since landing pads and landing skids use a contact method similar to "LEGO BLOCK", they do not require precise alignment with the drones for charging, so the base station can be installed on a variety of moving vehicles such as moving trucks, buses, and ships . In addition, the protruding spike-structured wireless power transmission coils are advantageous against contamination due to foreign matter, and even if several UAVs need to be charged at the same time, simultaneous charging is possible. . Faster charging times can be controlled using multiple coil systems in the pike. And the landing skid's ferrite electromagnetic shielding layer can shield the electromagnetic interference (EMI) to the drone during wireless charging to protect against flight failure or damage.

However, the effects of the present invention are not limited to the above-mentioned effects, and may be variously expanded without departing from the spirit and scope of the present invention.

1 is a bird's-eye view of a preferred embodiment of the unmanned aerial vehicle according to the present invention.
2 is a view for explaining a contact state between a base station and a landing skid in a drones landing zone;
3 is a view for explaining another arrangement position of the landing sensor;
4 is a block diagram of a preferred embodiment of a wireless aviation system according to the present invention;
5 is a flowchart for explaining a preferred embodiment of a control method of the unmanned aerial vehicle system according to the present invention.

For the embodiments of the invention disclosed herein, specific structural and functional descriptions are set forth for the purpose of describing an embodiment of the invention only, and it is to be understood that the embodiments of the invention may be practiced in various forms, The present invention should not be construed as limited to the embodiments described in Figs.

The present invention is capable of various modifications and various forms, and specific embodiments are illustrated in the drawings and described in detail in the text. It is to be understood, however, that the invention is not intended to be limited to the particular forms disclosed, but on the contrary, is intended to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the invention.

The terms first, second, etc. may be used to describe various components, but the components should not be limited by the terms. The terms may be used for the purpose of distinguishing one component from another. For example, without departing from the scope of the present invention, the first component may be referred to as a second component, and similarly, the second component may also be referred to as a first component.

It is to be understood that when an element is referred to as being "connected" or "connected" to another element, it may be directly connected or connected to the other element, . On the other hand, when an element is referred to as being "directly connected" or "directly connected" to another element, it should be understood that there are no other elements in between. Other expressions that describe the relationship between components, such as "between" and "between" or "neighboring to" and "directly adjacent to" should be interpreted as well.

The terminology used in this application is used only to describe a specific embodiment and is not intended to limit the invention. The singular expressions include plural expressions unless the context clearly dictates otherwise. In the present application, the terms "comprise", "having", and the like are intended to specify the presence of stated features, integers, steps, operations, elements, components, or combinations thereof, , Steps, operations, components, parts, or combinations thereof, as a matter of principle.

Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. Terms such as those defined in commonly used dictionaries should be construed as meaning consistent with meaning in the context of the relevant art and are not to be construed as ideal or overly formal in meaning unless expressly defined in the present application .

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. The same reference numerals are used for the same constituent elements in the drawings and redundant explanations for the same constituent elements are omitted. Hereinafter, an unmanned aerial vehicle or an unmanned aerial vehicle is called a dragon.

FIG. 1 is a perspective view of a preferred embodiment of the unmanned aerial vehicle according to the present invention, and FIG. 2 is a view for explaining a contact state of a base station and a landing skid in a drones landing zone.

Referring to the drawings, the unmanned aerial vehicle system 10 includes a base station 100 and a drone 200.

A plurality of first landing concave and convex structures 120 are formed on the surface of the landing pad 110 of the base station 100. Each of the first landing concave-convex structures 120 may be constituted by a landing protrusion 122 of a spike shape in the form of a cone, a truncated cone or a cone. The landing protrusion 122 is provided with a wireless power transmission coil 124 and a landing sensor 126. The landing sensor 126 may be disposed at the apex of the landing protrusion 122. [ The landing sensor 126 may be configured as any one of a pressure sensor, a magnetic sensor, an inductive current sensor, an induced voltage sensor, or a proximity sensor. For example, when a pressure sensor is used, the load of the drone 200 can be sensed.

The drones 200 include a main body 210 and a landing skid 220. The landing skid 220 is plate-shaped, the second landing concavo-convex structures 230 are formed on the bottom surface, and the electromagnetic wave shielding layer 240 is formed on the opposite surface. Each of the second landing concave and convex structures 230 may be configured as a hopper-shaped landing groove 232 into which a plurality of first landing concave and convex structures 120 are inserted. A wireless power receiving coil 234 is provided on a side wall constituting the landing groove 232.

It is preferable that the wireless power transmission coil 124 and the wireless power reception coil 234 are arranged to face each other at a position where they are almost in an interviewed state in the case of the magnetic induction method. The wireless power transmission coil 124 and the wireless power reception coil 234 may be spaced apart to some extent in the case of the self resonance method.

The electromagnetic wave shielding layer 240 may be formed of a ferrite material or may have a conductive pattern structure capable of shielding electromagnetic waves generated during wireless charging. Therefore, the electromagnetic wave shielding layer 240 is positioned between the main body 210 and the landing skid 220 to protect the flight circuit installed in the main body 210 from electromagnetic waves.

3 is a view for explaining another arrangement position of the landing sensor. 3 differs from FIG. 2 in that the landing sensor 126 is not disposed at the vertex of the landing protrusion 122 but is disposed in the landing pad 120 between the landing protrusions 122.

The landing sensor 126 may be constituted by an induction current sensor or an induced voltage sensor based on mutual inductance formed between the wireless power transmission coil 124 and the wireless power reception coil 234 in addition to a separate pressure sensor.

Although the first landing concavo-convex structure 120 is described as being the landing protrusion 122 and the second landing concavo-convex structure 230 as the landing groove 232 in the above-described embodiment, Also, in the present invention, the first and second landing concavo-convex structures are not only cones, shapes and hopper shapes, but also polygonal or polygonal prism shapes and corresponding inclined grooves. That is, a concavo-convex structure in which alignment is automatically induced along the inclined surface without precise alignment is sufficient. The landing skid on the landing pad of the present invention is automatically aligned by the concave-convex coupling, and the landing skid can be stably maintained without moving even to external pressure such as vibration or wind.

Fig. 4 shows a block configuration of a preferred embodiment of a wireless aviation system according to the present invention.

Referring to the drawings, a base station 100 of a wireless aviation system 10 has a landing area capable of taking-off and landing of a plurality of drones 200A and 200B. The base station 100 of the wireless aviation system 10 includes a plurality of wireless power transmitters 130-11 to 130-1m 130-21 to 130-2n, a plurality of landing sensors 126-11 to 126-1m ) 126-21 to 126-2n, and a control unit 140. [ The wireless power transmission units 130-11 to 130-1m 130-21 to 130-2n may include a power source, a power adjustment circuit, a matching circuit, a transmission coil 124, and the like. A plurality of wireless power transmission units 130-11 to 130-1m 130-21 to 130-2n and a plurality of landing sensors 126-11 to 126-1m : 1. The control unit 140 is connected to the plurality of landing sensors 126-11 to 126-1m (126-21 to 126-2n). The control unit 140 groups the wireless power transmission coils and the wireless power transmission units corresponding to the landing sensors located in the landing zone of the landing skid into a landing group, activates the wireless power transmission unit of the landing group, And controls the wireless transmission of energy.

The drone 200A includes m radio power receiving units 250-11 to 250-1m, a charging unit 260, and an air circuit unit 270. [ The drone 200B includes n wireless power receiving units 250-21 to 250-2n, a charging unit 260, and an air circuit unit 270. [ The charging unit 260 receives the electric energy received from the m wireless power receiving units 250-11 to 250-1m to charge the battery. The electric energy charged in the battery is supplied to the power supply of the flight circuit unit 270. Each of the wireless power receiving units 250-11 to 250-1m may include a receiving coil, a matching circuit, and a power adjusting unit.

The drone 200A includes m wireless power transmitters 130-11 to 130-1m and m landing sensors 126-11 to 126-1 m disposed in the landing zone of the landing pad of the base station 100, And the drones 200B correspond to the n wireless power transmission units 130-21 to 130-2n and the n landing sensors 126-21 to 126-2m. Each of the m radio power receiving units 250-11 to 250-1m of the drone 200A corresponds to each of the m radio power transmitting units 130-11 to 130-1m at a ratio of 1: Each of the n wireless power receiving units 250-21 to 250-2m corresponds to each of the n wireless power transmitting units 130-21 to 130-2m at a ratio of 1: 1.

5 is a flowchart for explaining a preferred embodiment of the control method of the unmanned aerial vehicle system of the present invention.

Referring to FIG. 5, the controller 140 of the base station 100 monitors whether or not the drones 200A land on the landing pad 110 through the landing sensors (S102). When the drones 200A land in the landing zone, m landing sensors 126-11 through 126-1m located in the landing zone sense whether the drones 200A land or not, and provide them to the controller 140. [ The control unit 140 groups the m landing sensors 126-11 to 126-1m sensing the landing into the landing group G1 (S104). The control unit 140 then transmits the m wireless power transmission units 130-11 to 130-1m corresponding to m landing sensors 126-11 to 126-1m belonging to the landing group G1 in a 1: Grouping them into a group G1 (S106) and activating the m wireless power transmitters 130-11 to 130-1m of the G1 group to transmit the multiple wireless powers to the drones 200A. The drones 200A receive the multiplexed wireless power through the m wireless power receivers 250-11 to 250-1m. When charging is completed in the drone 200A, the charging completion signal is transmitted to the base station 100 through a communication method such as Bluetooth. The control unit 140 monitors completion of charging of the drones 200A (S110). If the charging is not completed in step S110, it is monitored whether the drones are taken off (S112). If the drones are maintained in the landing state, step S108 is continued.

If the charging is completed or the charging is not completed in step S110, if the drones are taken off in step S112, the controller 140 terminates or stops the transmission operation of the m wireless power transmitters 130-11 to 130-1m of the G1 group (S114). Then, the control unit 140 cancels the grouping of the landing group G1 (S116).

When the drone 200B lands on the landing pad, the n landing sensors 126-21 through 126-2n located in the landing zone are grouped into the landing group G2 as described above, Grouping the n wireless power transmitters 130-21 to 130-2m corresponding to the landing sensors 126-21 to 126-2n in the 1: 1 group into the group G2 and transmitting the n wireless powers And activates the transmitting units 130-21 to 130-2n to transmit the multiplexed wireless power to the drones 200B.

Even when the drone 200A and the drone 200B land at the same time, the control unit 140 can individually group the G1 group and the G2 group and control the wireless charging by the multiple wireless power transmission for each group.

It will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the spirit or scope of the invention as defined in the following claims. It can be understood that it is possible.

10: unmanned aerial vehicle system 100: base station
110: landing pad 120: first landing concave and convex structure
122: Landing protrusion 124: Wireless power transmission coil
126: Landing sensor 130: Wireless power transmission unit
140: control unit 200: unmanned airplane, drones
210: main body 220: landing skid
230: second landing concave / convex structure 232: landing groove
234: wireless power receiving coil 240: electromagnetic wave shielding layer
250: wireless power receiver 260:
270: flight circuit

Claims (12)

An unmanned aerial vehicle system comprising at least one unmanned aerial vehicle and a base station provided as a landing area for the at least one unmanned aerial vehicle,
A plurality of first landing concavo-convex structures are formed on a surface of the landing pad of the base station,
Wherein the landing skid of each of the at least one unmanned aerial vehicle has a second landing concavo-convex structure coupled to the first landing concavo-convex structures. The unmanned aerial vehicle system according to claim 1, wherein each of the plurality of first landing concavo-convex structures is a cone-shaped landing projection, and the second landing concavo-convex structure is a hopper-shaped landing groove for accommodating the cone shape. [3] The apparatus of claim 2, wherein each of the landing protrusions is provided with a wireless power transmission coil, and each of the landing slots is provided with a wireless power receiving coil, An unmanned aerial vehicle system in which a wireless power receiving coil is automatically aligned. The unmanned aerial vehicle system according to claim 1, wherein each of the first landing concavo-convex structures includes a landing sensor. 5. The unmanned aerial vehicle system according to claim 4, wherein the landing sensor is one of a pressure sensor, a magnetic sensor, an inductive current sensor, an induced voltage sensor or a proximity sensor. The unmanned aerial system according to claim 1, wherein an electromagnetic wave shielding layer is formed on an upper surface of the landing skid facing the bottom surface of the landing skid. 5. The base station of claim 4,
A plurality of wireless power transmission units connected to each of the plurality of wireless power transmission coils, wireless power transmission coils connected to the plurality of landing sensors and corresponding to landing sensors located in a landing zone of the landing skid, And a control unit for grouping the power transmission units into a landing group and activating the wireless power transmission unit of the landing group to control wireless transmission of electric energy to the landed unmanned airplane. 8. The unmanned aerial vehicle system according to claim 7, wherein each of the plurality of wireless power transmission units comprises one of a magnetic induction type and a self-resonance type. 5. The method of claim 4, wherein the unmanned aircraft
A plurality of wireless power receiving units connected to each of the plurality of wireless power receiving coils and a charging unit charging the battery with electric energy supplied from the plurality of wireless power receiving units. A base station of an unmanned aerial vehicle system provided with a landing area for at least one unmanned aerial vehicle,
A landing pad having a size capable of landing a plurality of unmanned aerial vehicles;
A plurality of landing protrusions protruding in a conical shape on a surface of the landing pad;
A plurality of transfer coils provided on each of the plurality of landing protrusions;
A plurality of landing sensors provided on each of the plurality of landing protrusions;
A plurality of wireless power transmitters coupled to each of the plurality of transmit coils; And
Grouping the transmission coils and the wireless power transmission units corresponding to the landing sensors located in the landing zone of the unmanned airplane among the plurality of landing sensors into a landing group, activating the wireless power transmission units of the landing group, And a control unit for controlling supply of electric energy to the base station of the unmanned aerial system. An unmanned aircraft landing on a base station having a plurality of landing protrusions protruding conically on a surface of a landing pad,
Flight body; And
And a landing skid installed at a lower end of the flying body,
A plurality of hopper-shaped landing grooves are formed on the bottom surface of the landing skid,
A plurality of wireless power receiving coils formed in each of the landing grooves;
A plurality of wireless power receivers connected to each of the wireless power receiving coils; And
And a charging unit charging the battery with the electric energy received through the plurality of wireless power receiving units. A control method of an unmanned aerial vehicle system having a base station provided as a landing area of at least one unmanned aerial vehicle
Monitoring the landing of the UAV through a plurality of landing sensors,
Grouping the wireless power transmission coils and the wireless power transmission units corresponding to the landing sensors sensed in conjunction with the landing operation of the UAV among the plurality of landing sensors into one landing group,
Activating a wireless power transmission unit of the landing group to transmit electrical energy,
Monitoring completion of charging of the unmanned air vehicle,
When the charging operation is completed by the monitoring operation, the transmission operation of the wireless power transmission units of the landing group is terminated,
And releases the landing group.



KR1020150135282A 2015-09-24 2015-09-24 Unmanned Aerial Vehicle, Base Station, Unmanned Aerial System and Control Method thereof KR20170036297A (en)

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CN107943084A (en) * 2017-12-12 2018-04-20 江西理工大学 A kind of trailing type electromagnetic interference system and method for civilian multi-rotor unmanned aerial vehicle
CN108725820A (en) * 2018-04-08 2018-11-02 北京领航智能科技发展有限公司 Unmanned plane automatic charging platform
CN109353492A (en) * 2018-09-28 2019-02-19 李模萍 A kind of method of rising and falling of vehicle orientation rate controlling V-arrangement sliding slot
CN111404239A (en) * 2020-04-28 2020-07-10 上海交通大学 A porous charging panel of antiskid for unmanned aerial vehicle descending charges
RU2765726C1 (en) * 2021-03-31 2022-02-02 Федеральное государственное бюджетное учреждение науки Институт проблем морских технологий Дальневосточного отделения Российской академии наук (ИПМТ ДВО РАН) Device for automatic fixation of a helicopter-type unmanned aerial vehicle on the landing pad of an unmanned vessel with contactless transmission of electricity to charge batteries
WO2022158660A1 (en) * 2021-01-20 2022-07-28 울산과학기술원 Drone charging station and method for operating same
WO2023124434A1 (en) * 2021-12-31 2023-07-06 蜂巢航宇科技（北京）有限公司 Multi-rotor dronebox

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