Unmanned aerial vehicle

Abstract

The purpose of the present invention is to suppress an increase in the weight of a drone while being able to carry a necessary amount of fuel. The drone includes: a drone body; and the cargo unit is detachably arranged on the unmanned aerial vehicle main body. The unmanned aerial vehicle main body comprises an unmanned aerial vehicle body; the generator supplies power to the unmanned aerial vehicle body; and a first tank for accommodating fuel of the generator. The cargo unit comprises: a second tank for accommodating the fuel of the generator; and a cargo holding part for holding the cargo to be conveyed.

Description

Technical Field

[0001] The invention relates to an unmanned aerial vehicle (UAV) equipped with a fuel tank. Background Art

[0002] A drone is an unmanned aircraft that is remotely operated or autonomously operated without a pilot on board. An example of such an unmanned aircraft is the one described in Patent Document 1 below.

[0003] Patent document 1 discloses an unmanned helicopter equipped with a fuel supply device, which includes: a main tank that delivers fuel to the engine via a main pump; and a sub-tank that replenishes fuel to the main tank via a sub-pump, and controls the drive of the aircraft based on the fuel remaining levels in the main tank and the sub-tank.

[0004] Previous technical literature

[0005] Patent Literature

[0006] Patent Document 1: Japanese Patent Application Laid-Open No. 2002-166895 Summary of the Invention

[0007] Technical issues to be solved by the invention

[0008] To increase the range of a drone, it's necessary to increase the number of fuel tanks or increase their capacity, as described in Patent Document 1. However, increasing the number of fuel tanks or increasing their size increases the weight of the drone without the fuel, leading to worse fuel efficiency. Furthermore, for drones used for purposes such as cargo delivery with a predetermined flight path, carrying more fuel than necessary can worsen fuel efficiency. Therefore, it is desirable to improve fuel efficiency by reducing the weight of the drone while enabling it to carry the required amount of fuel optimized for cargo weight and flight distance.

[0009] The present invention has been made to solve the above-mentioned problems, and an object of the present invention is to provide an unmanned aerial vehicle (UAV) capable of carrying a necessary amount of fuel while suppressing an increase in the weight of the UAV.

[0010] Means for solving technical problems

[0011] The drone of the present invention for achieving the above-mentioned purpose comprises: a drone body; and a cargo unit, which is detachably arranged on the drone body, wherein the drone body includes: a drone body, which is electrically driven to fly; a generator, which supplies power to the drone body; and a first tank, which is used to accommodate fuel for the generator; and the cargo unit includes: a second tank, which is used to accommodate fuel for the generator; and a cargo holding portion, which is used to hold the cargo to be transported.

[0012] Effects of the Invention

[0013] According to the drone of the present invention, it is possible to suppress an increase in the weight of the drone while being able to carry a necessary amount of fuel. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a schematic diagram showing the drone according to the first embodiment.

[0015] Figure 2 This is a schematic diagram showing the state where the cargo unit is unloaded from the drone body.

[0016] Figure 3 This is a schematic diagram showing a modified example in which a plurality of cargo units are installed on a drone.

[0017] Figure 4 This is a schematic diagram showing a drone according to a second embodiment.

[0018] Figure 5 This is a schematic diagram showing the generator and fuel supply system.

[0019] Figure 6 This is a schematic diagram showing a drone according to a third embodiment. DETAILED DESCRIPTION

[0020] The following describes in detail preferred embodiments of the present invention with reference to the accompanying drawings. The present invention is not limited to these embodiments and, when multiple embodiments exist, also includes configurations combining the various embodiments. Furthermore, the constituent elements in the embodiments include those readily apparent to those skilled in the art, substantially identical elements, and so-called equivalent elements.

[0021] <Drone>

[0022] Figure 1 This is a schematic diagram showing the drone according to the first embodiment.

[0023] like Figure 1 As shown, the drone 10 includes: a drone body 11; and a cargo unit 12 that is detachably mounted on the drone body 11. The drone 10 is a cargo delivery drone. The drone 10 can carry cargo CA loaded in the cargo unit 12 mounted on the drone body 11 and fly, and deliver the loaded cargo CA to a destination. The drone 10 is in a state where the cargo unit 12 is mounted on the drone body 11 (see FIG. 1 ). Figure 1 ) and the state where the cargo unit 12 is separated from the drone body 11 (refer to Figure 2 ) can fly in any state.

[0024] <Drone main body structure>

[0025] like Figure 1 As shown, the drone body 11 includes: a drone body 21 that is electrically driven to fly; a generator 22 that supplies power to the drone body 21; and a first tank 23 for containing fuel for the generator 22.

[0026] The drone body 21 is comprised of an electric drone device. It includes multiple rotors 21a and electric motors 21b that drive each rotor 21a. The drone body 21 incorporates a battery (battery), a communications unit, a position information acquisition unit utilizing a satellite positioning system, an attitude information acquisition unit utilizing an accelerometer and gyroscope, a camera, and a control unit for controlling these components. The electric motor 21b is driven by power supplied by the battery and / or a generator 22. Thus, the drone body 11 is a hybrid device combining the power sources of the battery and the generator 22. The drone body 21 is capable of both remote control via the communications unit and autonomous flight along a pre-set path via the position information acquisition unit.

[0027] A plurality of rotors 21 a are provided on the upper surface side of the drone body 21 , and a landing gear 24 , a generator 22 , and a first tank 23 are provided on the lower surface side of the drone body 21 .

[0028] The generator 22 is fixed to the bottom surface of the drone body 21 via a bracket. The generator 22 is, for example, a gas turbine generator. A gas turbine generator is a combination of a rotating electric machine (electrical generator) and a gas turbine. The gas turbine generator rotates the turbine using high-temperature gas generated by the combustion of a mixture of fuel supplied to the combustor and compressed air supplied from the compressor. The rotation of the turbine then drives the rotating electric machine, generating electricity.

[0029] The first tank 23 is provided on the side of the generator 22. The first tank 23 is a container for storing fuel supplied to the generator 22. The fuel is a liquid fuel and can be a petroleum-based fuel such as kerosene. The first tank 23 is fluidically connected to the fuel pump 25 of the generator 22. The fuel pump 25 supplies the fuel in the first tank 23 to the generator 22. In addition, the generator 22 is configured so that when the cargo unit 12 is mounted on the drone body 11, the fuel is supplied from the second tank 41 described later rather than the first tank 23 to generate electricity. That is, when the cargo unit 12 is separated from the drone body 11, or when the fuel in the second tank 41 is empty, the generator 22 generates electricity by supplying fuel from the first tank 23.

[0030] A connecting portion 31a for connecting the cargo unit 12 to the drone body 11 is provided on the bottom surface of the generator 22. The connecting portion 31a is configured to be mechanically coupled and disconnected from the connecting portion 31b of the cargo unit 12. By coupling the connecting portion 31a and the connecting portion 31b, the cargo unit 12 is secured (mounted) to the drone body 11. By disconnecting the connecting portion 31a and the connecting portion 31b, the cargo unit 12 can be detached from the drone body 11.

[0031] like Figure 1 and Figure 2 As shown, the drone body 11 further includes a loading and unloading mechanism 30 for switching between the drone body 11 and the cargo unit 12. The loading and unloading mechanism 30 includes an actuator that drives a connecting portion 31a, switching between connecting portions 31a and 31b. The loading and unloading mechanism 30 can be remotely operated through the control unit of the drone body 21, and can also perform automated loading and unloading operations based on a program.

[0032] <Cargo unit structure>

[0033] like Figure 1 As shown, the cargo unit 12 includes a second tank 41 for storing fuel for the generator 22 and a cargo holding portion 42 for holding cargo to be transported. The cargo unit 12 has a chassis 40 on which the second tank 41 and the cargo holding portion 42 are mounted, and a connection portion 31b is provided on the upper surface.

[0034] The second tank 41 is disposed on the upper portion of the chassis 40. The second tank 41 is a container for storing fuel supplied to the generator 22. The volume of the second tank 41 can be greater than that of the first tank 23. The second tank 41 can be connected to the fuel pump 25 via the connection portion 31b. Specifically, when the connection portion 31a is coupled to the connection portion 31b, the second tank 41 is fluidically connected to the fuel pump 25.

[0035] The cargo holding portion 42 is disposed at the lower portion of the chassis 40 (ie, below the second tank 41). The cargo holding portion 42 is a storage space of a predetermined volume capable of storing cargo CA.

[0036] <Use of drones>

[0037] The following describes the basic functions of the drone 10. Figure 1 As shown, when using the drone 10, a user at a base places fuel corresponding to the weight of the cargo CA and the flight distance to the destination of the cargo CA in the second tank 41, places the cargo CA on the cargo holding portion 42, and mounts the cargo unit 12 on the drone body 11. Furthermore, the first tank 23 is filled with a full amount of fuel.

[0038] Drone 10 flies along a pre-set flight path from base to destination. Because cargo unit 12 is attached to drone body 11, fuel from second tank 41 is supplied to generator 22. In other words, drone 10 uses fuel from second tank 41 to fly from base to destination.

[0039] After the drone 10 arrives at the destination, the cargo unit 12 is disconnected from the drone body 11 by the loading and unloading mechanism 30. Figure 2 As shown, drone 10 detaches cargo unit 12, allowing flight using only drone main body 11. Since cargo unit 12 is detached from drone main body 11, fuel from first tank 23 is supplied to generator 22. In other words, drone 10 uses fuel from first tank 23 during the return trip from the destination to base. During the return trip, drone 10's weight is reduced by an amount equivalent to the weight of cargo unit 12, resulting in improved fuel consumption. Consequently, drone 10 can fly from the destination to base using only the fuel stored in first tank 23, which has a smaller volume than second tank 41.

[0040] <Modification of the first embodiment>

[0041] The drone 10 of the first embodiment can include a plurality of cargo units 12 each including a second tank 41 and a cargo holding portion 42. Figure 3 In the example shown, drone 10 includes five cargo units 12A to 12E. This drone 10 is operated as follows. Drone 10 attaches cargo unit 12A and uses the fuel in cargo unit 12A's second tank 41 to fly from base to destination A. Drone 10 detaches cargo unit 12A, attaches cargo unit 12B, and uses the fuel in cargo unit 12B's second tank 41 to fly from destination A to destination B. Drone 10 detaches cargo unit 12B, attaches cargo unit 12C, and uses the fuel in cargo unit 12C's second tank 41 to fly from destination B to destination C. Similarly, cargo units 12D and 12E are used to fly from destination C to destination D and from destination D to destination E, respectively. Finally, drone 10 detaches cargo unit 12E and returns to base from destination E, using only the drone main body 11 and the fuel in the first tank 23.

[0042] Figure 4 1 is a schematic diagram showing a drone 10A according to a second embodiment. Components having the same functions as those in the first embodiment are denoted by the same reference numerals, and detailed descriptions thereof are omitted.

[0043] like Figure 4As shown, the generator 22 of the drone 10A includes a first fuel pump 51 that supplies fuel to the generator 22, replacing the fuel pump 25 of the first embodiment. The cargo unit 12 of the drone 10A is connected to the drone body 11 and is positioned below the first fuel pump 51. The cargo unit 12 includes a second fuel pump 52 that supplies fuel from the second tank 41 to the first fuel pump 51.

[0044] Furthermore, the first tank 23 is positioned within the drone body 11 to hold fuel above the inlet of the first fuel pump 51. Specifically, since the fuel level within the first tank 23 is positioned above the inlet of the first fuel pump 51, the fuel within the first tank 23 is supplied to the first fuel pump 51 via a head difference. Meanwhile, since the second tank 41 is positioned below the first fuel pump 51, fuel must be pumped from the second tank 41 to the first fuel pump 51. Therefore, in the second embodiment, the fuel in the second tank 41 is supplied to the generator 22 in two stages: via the second fuel pump 52 and the first fuel pump 51.

[0045] Since the first fuel pump 51 does not need to pump fuel, it can be a smaller and lighter pump than the fuel pump 25 of the first embodiment. Since the second fuel pump 52 is provided on the cargo unit 12, when the cargo unit 12 is separated from the drone body 11, the weight of the drone body 11 is reduced by the weight of the second fuel pump 52.

[0046] Figure 5 It is a schematic diagram showing the generator 22 and the fuel supply system.

[0047] Generator Structure

[0048] like Figure 5 As shown, the generator 22 includes a rotating electrical machine 61 and a gas turbine 62 connected to the rotating electrical machine 61. The rotating electrical machine 61 includes a rotor portion 61a and a stator portion 61b. The gas turbine 62 includes a compressor 62a, a combustor 62b, and a turbine 62c. The compressor 62a, the turbine 62c, and the rotor portion 61a of the rotating electrical machine 61 are connected by a rotating shaft 63 so as to rotate integrally.

[0049] The compressor 62a is driven by the rotating shaft 63 to rotate, compressing air and supplying high-temperature, high-pressure compressed air to the combustor 62b. The combustor 62b supplies fuel gas to the compressed air to generate a mixed gas, which is then combusted to produce high-temperature, high-pressure combustion gas. The turbine 62c rotates due to the expansion of the combustion gas, thereby driving the rotating shaft 63. The rotating motor 61 generates electricity by rotating the rotor 61a relative to the stator 61b via the rotating shaft 63. The electricity generated by the rotating motor 61 is supplied to the drone body 21.

[0050] <Structure of the fuel supply system>

[0051] The generator 22 is equipped with a control valve 64. The control valve 64 controls the flow rate of fuel supplied to the generator 22 from the first fuel pump 51 and discharges the remaining fuel into the first tank 23. Specifically, the discharge port of the first fuel pump 51 is connected to the fuel nozzle of the burner 62b via the control valve 64. The first fuel pump 51 discharges fuel at a predetermined high pressure for injecting the fuel into the burner 62b. The control valve 64 is also connected to the first tank 23 via the return flow path 71 and delivers the remaining fuel to the first tank 23. The inlet of the first fuel pump 51 is connected to the first tank 23 and the connection portion 81a via a branched inlet flow path 72.

[0052] The first tank 23 is connected to the inlet flow path 72 and the return flow path 71. Furthermore, the first tank 23 has an overflow flow path 73 connected to the second tank 41. When fuel exceeding the upper limit of the first tank 23 is supplied from the return flow path 71 to the first tank 23, the excess fuel is discharged to the overflow flow path 73. The overflow flow path 73 is connected to the connection portion 82a.

[0053] The second tank 41 is connected to the connection portion 82b via the overflow connection passage 75. Furthermore, the second tank 41 of the cargo unit 12 is connected to the inlet of the second fuel pump 52 via the supply flow passage 74. The discharge port of the second fuel pump 52 is connected to the connection portion 81b. The second fuel pump 52 discharges fuel at a predetermined low pressure for drawing the fuel in the second tank 41 to the first fuel pump 51.

[0054] By connecting the drone body 11 and the cargo unit 12, the connectors 81a and 82a are fluidically connected to the corresponding connectors 81b and 82b, respectively. This allows fuel from the second tank 41 to be supplied to the burner 62b via the second fuel pump 52, the first fuel pump 51, and the control valve 64. A check valve 77 is provided in the inlet flow path 72 between the first tank 23 and the first fuel pump 51, and the discharge pressure of the second fuel pump 52 is higher than the delivery pressure from the first tank 23 (equivalent to the head difference). Therefore, while the second fuel pump 52 is supplying fuel, fuel is not supplied from the first tank 23, and fuel is preferentially supplied from the second tank 41 rather than the first tank 23.

[0055] The remaining fuel discharged from the control valve 64 returns to the first tank 23 via the return flow path 71, the first tank 23, and the overflow flow path 73. Thus, when the cargo unit 12 is attached to the drone body 11, the fuel storage amount of the first tank 23 is maintained at a full level.

[0056] When the drone body 11 is separated from the cargo unit 12, the connections 81a and 82a are closed. In this state, the fuel in the first tank 23 is supplied to the first fuel pump 51 via the inlet flow path 72, and the supplied fuel is supplied from the first fuel pump 51 to the burner 62b via the control valve 64.

[0057] The remaining configuration of the drone 10A according to the second embodiment is the same as that of the drone 10 according to the first embodiment, and therefore description thereof will be omitted.

[0058] Figure 6 1 is a schematic diagram showing a drone 10B according to a third embodiment. Components having the same functions as those in the first embodiment are denoted by the same reference numerals, and detailed descriptions thereof are omitted.

[0059] like Figure 6 As shown, the drone 10B further comprises: a starting unit 13, which is independent of the cargo unit 12 (refer to Figure 4 ) and can be detachably mounted on the drone body 11.

[0060] The starting unit 13 is a unit for starting the generator 22. The starting unit 13 is provided with auxiliary equipment 13a for starting the gas turbine generator.

[0061] The auxiliary equipment 13a may include, for example, an igniter, an exciter, a starting power supply, and a voltage converter. The igniter is a device that uses sparks generated by discharge to ignite the burner 62b of the generator 22 (see Figure 5 ) ignites the mixture in the exciter. The exciter supplies a discharge voltage to the igniter. The starting power supply, for example, includes a capacitor for storing power for the exciter. The voltage converter, for example, includes a DC-DC converter for converting the output voltage of the starting power supply into the input voltage of the exciter.

[0062] After the generator 22 (gas turbine generator) is started by the auxiliary equipment 13a, the gas turbine 62 (refer to Figure 5 ) until the drone 10 stops, it can continue operating by fuel supply without the need for auxiliary equipment 13a. Therefore, the starting unit 13 only needs to be attached to the drone body 11 when starting the generator 22. After the generator 22 starts, the starting unit 13 can be detached from the drone body 11. In the third embodiment, after the generator 22 starts, it continues operating until the drone 10 returns to the base via the destination.

[0063] like Figure 6As shown, the starting unit 13 may include, in addition to the auxiliary equipment 13a, a third tank 13b containing starting fuel and a backup battery 13c for replacing the battery mounted on the drone body 21.

[0064] In the third embodiment, when the user at the base sets out from the drone 10B, he first attaches the starting unit 13 to the drone body 11 to start the generator 22. After the generator 22 starts, the user detaches the starting unit 13 from the drone body 11 and places the cargo unit 12 (see FIG. 1 ) holding the cargo CA. Figure 4 ) is mounted on the drone body 11. Furthermore, the drone 10B flies from the base to the destination. The backup battery 13c is mounted on the starting unit 13, which provides great convenience when replacing the battery in the drone body 21 during the drone 10B's departure.

[0065] The remaining configuration of the drone 10B according to the third embodiment is the same as that of the drone 10 according to the first embodiment, and therefore description thereof will be omitted.

[0066] The drone involved in the first embodiment includes: a drone body 11; and a cargo unit 12, which is detachably arranged on the drone body 11, and the drone body 11 includes: a drone body 21, which is electrically driven to fly; a generator 22, which supplies power to the drone body 21; and a first tank 23, which is used to accommodate fuel for the generator 22, and the cargo unit 12 includes: a second tank 41, which is used to accommodate fuel for the generator 22; and a cargo holding part 42, which is used to hold the cargo CA to be transported.

[0067] According to the first embodiment, the drone can fly using the fuel stored in the second tank 41 while the cargo unit 12 is attached to the drone body 11. Therefore, by storing the required amount of fuel, optimized based on the total weight of the cargo unit 12 and the flight distance to the destination of the cargo CA, in the second tank 41, the drone can fly on the outbound leg to the destination. Furthermore, when the cargo unit 12 is detached from the drone body 11, the drone can fly using the fuel stored in the first tank 23. Therefore, the drone can detach the cargo unit 12 from the drone body 11 at the destination and fly the return leg from the destination to the base using only the drone body 11. When the cargo unit 12 is detached from the drone body 11, the total weight of the cargo unit 12, including the weight of the cargo CA and the weight of the second tank 41, is removed from the drone 10. As a result, fuel consumption on the return leg is less than that on the outbound leg, allowing the size of the first tank 23 and the amount of fuel stored therein to be reduced accordingly. The improvement in the fuel efficiency of the drone 10 achieved by reducing the size of the first tank 23 and the amount of fuel contained therein can be achieved both when attaching and detaching the cargo unit 12. As a result, it is possible to minimize the weight increase of the drone 10 while still being able to carry the necessary amount of fuel.

[0068] Furthermore, according to the drone of the first embodiment, the cargo CA and fuel (fuel in the second tank 41) can be pre-loaded in the cargo unit 12 independently of the drone body 11. Therefore, simply by attaching the cargo unit 12 to the drone body 11, the cargo CA can be loaded and the fuel in the second tank 41 can be refilled. This further reduces the time required for flight preparation.

[0069] The drone according to the second embodiment is the drone according to the first embodiment, wherein the generator 22 is configured to preferentially supply fuel from the second tank 41 rather than the first tank 23 to generate electricity when the cargo unit 12 is attached to the drone body 11. This allows the generator 22 to generate electricity using the fuel in the second tank 41 of the cargo unit 12 during the outbound flight to the destination. After the cargo unit 12 is separated from the drone body 11 at the destination, the generator 22 can generate electricity using the fuel in the first tank 23 of the drone body 11 during the return flight from the destination to the base. This facilitates optimizing the fuel load and prevents unnecessary large amounts of fuel from being carried. By reducing the fuel load, the weight of the drone 10 can be reduced, thereby improving the drone's fuel efficiency.

[0070] The drone according to the third embodiment is the drone according to the first or second embodiment, wherein the generator 22 includes a first fuel pump 51 for supplying fuel to the generator 22, and the cargo unit 12 is disposed below the first fuel pump 51 while connected to the drone body 11. The cargo unit 12 further includes a second fuel pump 52 for supplying fuel from the second tank 41 to the first fuel pump 51. Thus, by mounting the second fuel pump 52 for pumping fuel from the second tank 41 on the cargo unit 12, it can be separated from the drone body 11. As a result, the weight of the drone body 11 can be reduced compared to a case where the fuel pump is provided on the drone body 11. This reduction in weight of the drone body 11 improves fuel efficiency, thereby further reducing the size and weight of the first tank 23.

[0071] The drone according to the fourth embodiment is the drone according to the third embodiment, in which the first tank 23 is located in the drone body 11 to hold fuel above the inlet of the first fuel pump 51. This allows the fuel in the first tank 23 to be supplied to the first fuel pump 51 by utilizing the head difference. Consequently, the weight of the drone body 11 can be further reduced compared to a case where a pump for pumping fuel from the first tank 23 is provided on the drone body 11.

[0072] The drone according to the fifth embodiment is the drone according to the third or fourth embodiment, wherein the generator 22 further includes a control valve 64 for controlling the flow rate of fuel supplied to the generator 22 from the first fuel pump 51 and discharging excess fuel into the first tank 23. The first tank 23 has an overflow channel 73 connected to the second tank 41. Thus, excess fuel due to flow control is first discharged from the control valve 64 into the first tank 23, and then, when the first tank 23 is full, is discharged from the first tank 23 into the second tank 41. Therefore, during outbound flight with the cargo unit 12 attached to the drone body 11, the first tank 23 can be maintained full. Consequently, when the cargo unit 12 is detached from the drone body 11 and only the fuel in the first tank 23 is used for power generation and flight, flight can commence with the first tank 23 fully filled.

[0073] The drone according to the sixth embodiment is the drone according to any one of the first to fifth embodiments, wherein the drone body 11 further includes a loading and unloading mechanism 30 for switching between the drone body 11 and the cargo unit 12. This mechanism can easily shorten the time required for loading and unloading operations compared to manual loading and unloading operations between the drone body 11 and the cargo unit 12. Furthermore, the cargo unit 12 can be safely loaded and unloaded without stopping the generator 22, eliminating the need to stop and restart the generator 22.

[0074] The drone according to the seventh embodiment is the drone according to any of the first to sixth embodiments, equipped with multiple cargo units 12 each including a second tank 41 and a cargo holder 42. This allows not only an operation method in which the cargo units 12 are detached from the drone body 11 at a destination and returned to base, but also a single drone body 11 can be used in a variety of ways by replacing multiple cargo units 12. For example, by sequentially replacing cargo units 12 at multiple destinations, a single drone body 11 can be used to sequentially transport cargo CA to multiple destinations. This operation method allows the drone 10 to fly along a flight path that would not be achievable using only the fuel carried by a single cargo unit 12 (second tank 41).

[0075] The drone according to the eighth embodiment is the drone according to any one of the first to seventh embodiments, further comprising a starting unit 13 detachably mounted on the drone body 11, independent of the cargo unit 12, for starting the generator 22. This allows the starting unit 13, required for starting the generator 22, to be detached from the drone body 11. Consequently, the weight of the drone body 11 can be effectively reduced compared to a case where the auxiliary equipment 13a required for starting the generator 22 is mounted on the drone body 11. This reduced weight of the drone body 11 improves fuel efficiency, thereby enabling the first tank 23 to be made smaller and lighter.

[0076] In the above embodiment, the generator 22, the first tank 23, and the cargo unit 12 are provided on the lower side of the drone body 21. However, the rotor 21a may be provided on the lower side of the drone body 21, and the generator 22, the first tank 23, and the cargo unit 12 may be provided on the upper side of the drone body 21. Furthermore, multiple cargo units 12 may be mounted on the drone body 11.

[0077] The above-described method of operating the drone 10 is merely an example and is not limited to the above-described embodiment. As can be seen from the above-described embodiment, various operational methods can be achieved by combining flight with the cargo unit 12 attached to the drone body 11 and flight with the cargo unit 12 detached from the drone body 11.

[0078] Explanation of symbols

[0079] 10, 10A, 10B - UAV, 11 - UAV body, 12, 12A, 12B, 12C, 12D, 12E - cargo unit, 13 - starting unit, 21 - UAV body, 22 - generator, 23 - first tank, 30 - loading and unloading mechanism, 42 - cargo holding unit, 51 - first fuel pump, 52 - second fuel pump, 64 - control valve, 73 - overflow flow path.

Claims

1. A drone comprising: A drone body; and a cargo unit, detachably mounted on the drone body, The drone body includes: The drone body is electrically driven to fly; a generator for supplying power to the drone body; and The first tank is used to contain the fuel of the generator, The cargo unit comprises: a second tank for containing fuel for the generator; and The cargo holding portion is used to hold the cargo to be transported.

2. The drone according to claim 1, wherein: The generator is configured to generate electricity by preferentially supplying fuel from the second tank rather than the first tank when the cargo unit is mounted on the drone body.

3. The drone according to claim 2, wherein: The generator includes a first fuel pump for supplying fuel to the generator. The cargo unit is arranged below the first fuel pump in a state connected to the drone body. The cargo unit further includes a second fuel pump that supplies the fuel in the second tank to the first fuel pump.

4. The drone according to claim 3, wherein: The first tank is provided to store fuel at a position above the inlet of the first fuel pump in the drone body.

5. The drone according to claim 3 or 4, wherein: The generator further includes a control valve that controls the flow rate of fuel supplied from the first fuel pump to the generator and discharges excess fuel to the first tank. The first tank has an overflow flow path connected to the second tank.

6. The drone according to any one of claims 1 to 3, wherein: The drone body further includes a loading and unloading mechanism for switching loading and unloading between the drone body and the cargo unit. 7 . The drone according to claim 1 , comprising a plurality of the cargo units, each of the cargo units including the second tank and the cargo holding portion.

8. The drone according to any one of claims 1 to 3, further comprising: A starting unit is independent of the cargo unit and is detachably arranged on the drone body, and is used to start the generator.

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