Flying device

Abstract

To provide a flying device capable of effectively operating an engine during flight.SOLUTION: A flying device 10 is a device that floats in the air by means of thrust generated by the rotation of a rotor 14. The flying device 10 includes a machine body 19, an engine 30, a tank 27, and an electric component 28. An internal space 29 of the machine body 19 is partitioned into a first space 291 and a second space 292 by the tank 27. The engine 30 is disposed in the first space 291. The electric component 28 is disposed in the second space 292.SELECTED DRAWING: Figure 5

Description

[Technical Field]

[0001] The present invention relates to a flying device, and more particularly to a flying device having a tank on its fuselage. [Background technology]

[0002] Conventionally, there have been known unmanned flying devices capable of flying in the air. Such flying devices are capable of flying in the air by using the thrust of a rotor that rotates around a vertical axis.

[0003] Examples of application fields for such flying devices include transportation, surveying, and photography. When a flying device is used in such fields, it is equipped with surveying and photography equipment. By using the flying device in such fields, it is possible to fly the flying device in areas where humans cannot enter, and transport, photograph, and survey such areas. Inventions related to such flying devices are described in, for example, Patent Document 1 and Patent Document 2.

[0004] In a typical flying device, the rotor rotates using power supplied from a storage battery installed in the flying device. However, because the amount of energy supplied by the storage battery is not always sufficient, flying devices equipped with an engine have also emerged to achieve continuous flight over long periods of time. In such flying devices, the driving force of the engine rotates a generator, and the rotor is driven by the power generated by the generator. A flying device with this configuration is also called a series-type hybrid drone because the engine and generator are connected in series along the path through which energy is supplied from the power source to the rotor. Using such a flying device for photography and surveying enables wide-area photography and surveying. An example of a flying device equipped with an engine is described in Patent Document 3. Parallel-type hybrid drones, in which the main rotor is mechanically rotated by the driving force of the engine and the sub-rotor is rotated by a motor, are also gradually emerging. [Prior art documents] [Patent documents]

[0005] [Patent Document 1] Japanese Patent Application Laid-Open No. 2012-51545 [Patent Document 2] Japanese Patent Application Laid-Open No. 2014-240242 [Patent Document 3] Japanese Patent Application Laid-Open No. 2011-251678 Summary of the Invention [Problem to be solved by the invention]

[0006] However, in the above-mentioned conventional flight devices, there is room for improvement in terms of the engines mounted on the flight devices.

[0007] Specifically, when the engine operates, the air surrounding the engine heats up. Therefore, if the heated air is sent into the engine's combustion chamber, the engine's operating efficiency decreases. To solve this problem, installing a duct to take in air from a distance to be supplied to the engine would complicate the overall configuration of the flight device and make it difficult to reduce the overall weight of the flight device. Furthermore, if electrical equipment such as a battery or inverter is installed near the engine inside the body of the flight device, the engine could overheat the electrical equipment, causing the electrical equipment to become unstable.

[0008] The present invention has been made in view of the above circumstances, and an object of the present invention is to provide a flight device that can operate an engine effectively during flight. [Means for solving the problem]

[0009] The flying device of the present invention is a flying device that floats in the air by the thrust generated by the rotation of a rotor, and is characterized in that it comprises an airframe, an engine, a tank, and electrical equipment, and the internal space of the airframe is divided into a first space and a second space by the tank, the engine is arranged in the first space, and the electrical equipment is arranged in the second space.

[0010] In addition, in the flight device of the present invention, when the airframe is viewed from above, the tank divides the internal space into the first space and the second space.

[0011] In addition, in the flight device of the present invention, the tank has a communication part that connects the first space and the second space.

[0012] In addition, in the flight device of the present invention, the communication section is a concave portion formed by partially recessing the upper surface of the tank downward.

[0013] In addition, in the flying device of the present invention, the engine has an engine main body, an air intake section that takes in air from the outside, and a supply air duct section that supplies air from the air intake section to the engine main body, and the supply air duct section extends from the first space to the second space through the communication section, and the air intake section is arranged in the second space.

[0014] In the flight device of the present invention, the tank is a fuel tank that stores fuel to be supplied to the engine.

[0015] In addition, in the flight device of the present invention, the tank has an outlet portion through which the fluid is taken out to the outside and a bottom portion, and the bottom portion is inclined downward toward the outlet portion. [Effects of the Invention]

[0016] The flying device of the present invention is a flying device that floats in the air using thrust generated by the rotation of a rotor, and is characterized in that it comprises an airframe, an engine, a tank, and electrical equipment, and the interior space of the airframe is divided into a first space and a second space by the tank, with the engine disposed in the first space and the electrical equipment disposed in the second space. According to the flying device of the present invention, by disposing the engine in the first space and the electrical equipment in the second space, the tank can insulate the engine from the electrical equipment. Therefore, even if the engine generates heat during flight, the electrical equipment will not overheat and can operate stably.

[0017] In addition, in the flight device of the present invention, when the airframe is viewed from above, the tank divides the internal space into the first space and the second space. According to the flight device of the present invention, for example, the first space can be formed on the rear side of the airframe, and the second space can be formed on the front side of the airframe. Therefore, the engine can be stored in the first space formed on the rear side, and electrical equipment can be stored in the second space formed on the front side.

[0018] In addition, in the flight device of the present invention, the tank has a communication part that connects the first space and the second space. According to the flight device of the present invention, some of the engine components can be disposed in the second space via the communication part.

[0019] In addition, in the flight device of the present invention, the communication section is a concave section formed by partially recessing the upper surface of the tank downward. According to the flight device of the present invention, by making the communication section a concave section, the communication section can be formed with a simple configuration. Furthermore, by forming the communication section as a recess in the upper surface of the tank, it is possible to prevent the communication section from obstructing the flow of fluid inside the tank.

[0020] In addition, in the flight device of the present invention, the engine has an engine main body, an air intake section that takes in air from the outside, and a supply air duct section that supplies air from the air intake section to the engine main body, the supply air duct section extending from the first space to the second space through the communication section, and the air intake section being disposed in the second space. According to the flight device of the present invention, relatively low-temperature air present in the second space can be supplied to the combustion chamber of the engine main body via the air intake section and the supply air duct section. This allows for increased engine output.

[0021] In addition, in the flight device of the present invention, the tank is a fuel tank that stores fuel to be supplied to the engine. According to the flight device of the present invention, the fuel tank can function as a heat insulator that separates the first space from the second space. Therefore, the first space and the second space can be insulated without the need for a dedicated heat insulator.

[0022] In addition, in the flight device of the present invention, the tank has an outlet section through which the fluid is taken out and a bottom section, and the bottom section is inclined downward toward the outlet section. According to the flight device of the present invention, by having the bottom section inclined downward toward the outlet section, even if the airborne vehicle tilts, the fluid such as fuel stored in the tank can flow down the bottom section and collect at the outlet section. [Brief explanation of the drawings]

[0023] [Figure 1] 1 is a perspective view showing a flying device according to an embodiment of the present invention; [Figure 2] 1 is a top view showing a flying device according to an embodiment of the present invention; [Figure 3] 1 is a side view showing a flying device according to an embodiment of the present invention. [Figure 4] 1 is a perspective view showing a flying device according to an embodiment of the present invention; [Figure 5] 1 is a perspective view showing the fuselage and the interior of a flying device according to an embodiment of the present invention. [Figure 6A] FIG. 2 is a perspective view showing a fuel tank of the flying device according to the embodiment of the present invention. [Figure 6B] FIG. 2 is a side view showing a fuel tank of the flying device according to the embodiment of the present invention. [Figure 7] FIG. 2 is a perspective view showing an engine of a flying device according to an embodiment of the present invention. [Figure 8] FIG. 2 is a cross-sectional view showing an engine of a flying device according to an embodiment of the present invention. [Figure 9] 1 is a connection diagram showing a flying device according to an embodiment of the present invention; DETAILED DESCRIPTION OF THE INVENTION

[0024] Hereinafter, an embodiment of the present invention will be described in detail with reference to the drawings. In the following description, the left-right direction refers to the left-right direction when the flight device 10 is viewed from the rear. In addition, in the following description, the same components are generally designated by the same reference numerals, and repeated explanations will be omitted.

[0025] FIG. 1 is a perspective view of the flight device 10. FIG. 2 is a top view of the flight device 10. FIG. 3 is a side view of the flight device 10. The flight device 10 is also called a drone, and more specifically, a hybrid drone. Furthermore, in the following description, the front refers to the front side in the direction of travel of the flight device 10, and the rear refers to the rear side in the direction of travel of the flight device 10. Furthermore, in the following description, the side away from the aircraft 19 may be referred to as the outside, and the side approaching the aircraft 19 may be referred to as the inside.

[0026] FIG. 1 is a perspective view of a flight device 10. The flight device 10 is a device that floats in the air using thrust generated by the rotation of a rotor 14. The flight device 10 mainly comprises an airframe 19, an engine 30, a tank 27, and electrical equipment 28. Here, the engine 30, the tank 27, and the electrical equipment 28 are not shown because they are covered by a cover 17. The engine 30, the tank 27, and the electrical equipment 28 will be described later with reference to FIG. 4 and other figures. The flight device 10 also has an arm 12, a motor 21, a rotor 14, and the like.

[0027] 1 to 3, the flight device 10 is an engine-equipped drone equipped with an engine 30 (described later) that flies using energy generated by operating the engine 30. A series hybrid drone or a parallel hybrid drone can be used as the flight device 10. In a series hybrid drone, the engine 30 drives a generator 16 (described later), and a motor 21 powered by the generator 16 rotates a rotor 14 (described later). A parallel hybrid drone has a mechanical drive system that mechanically rotates another rotor 14 using the engine 30, in addition to an electrical drive system that rotates the rotor 14 using the motor 21.

[0028] The airframe 19 is the main body that supports the engine 30 and other components that make up the flight device 10, and is made of synthetic resin, metal, or a composite material of these. Here, the airframe 19 is covered by the cover 17, so it does not appear in FIG. 1.

[0029] The cover 17 is a plate made of synthetic resin and is configured to cover the fuselage 19, engine 30, etc., which will be described later. The cover 17 has a cover upper surface portion 171, cover side surface portions 172, and a removal portion 273. The cover upper surface portion 171, cover side surface portions 172, and cover lower surface portion 173 may be continuous as a single unit, or each may be a separate plate-like member. The cover upper surface portion 171 is configured to cover the fuselage 19 from above. The cover side surface portions 172 are configured to cover the cover 17 from the sides, i.e., the front, right, rear, and left. The cover lower surface portion 173 is configured to cover the fuselage 19 from below.

[0030] The rotors 14 generate thrust for the airframe 19 to float by rotating. Here, multiple rotors 14 are arranged. Specifically, a total of six rotors 14 are arranged on the front left, front right, right side, rear right, rear left, and left side. Figure 1 etc. shows the outer periphery of the rotation range of the rotors 14. In reality, the rotors 14 are made up of two or four propeller-like members.

[0031] The engine 30 generates power to rotate the rotor 14. In Fig. 1, the engine 30 is built into the airframe 19 and is not shown. The engine 30 is built into the airframe 19 and generates energy to rotate the rotor 14 at a predetermined rotational speed.

[0032] A plurality of arms 12 extend from the body 19 toward the periphery. The arms 12 are members that extend in a generally rod-like shape toward the front left, front right, right side, rear right, rear left, and left side. In this example, a total of six arms 12 are provided.

[0033] The motor 21 rotates the rotor 14 using electric power generated when an engine 30 (described later) operates a generator 16. The motor 21 is disposed at the tip of each arm 12. In this example, the motor 21 is disposed on the underside of the tip of the arm 12, and the rotor 14 is installed below the motor 21.

[0034] The legs 15 are support members that extend downward from the bottom of the fuselage 19. When the flight device 10 is in a landing state, the lowest parts of the legs 15 come into contact with the ground surface.

[0035] The exhaust section 13 is a section through which exhaust gas generated by the operation of the engine 30 is discharged to the outside. The exhaust section 13 is also called a muffler.

[0036] Although not shown here, the flight device 10 has a cooling mechanism for cooling the engine 30. This cooling mechanism has a radiator (not shown) attached to the arm 12, and cools the engine 30 by circulating a cooling fluid between the radiator and the engine 30.

[0037] 4 is a perspective view of the flight device 10. The airframe 19 is composed of arm-like members assembled to form a roughly hexagonal shape when viewed from above. Inside the airframe 19, components such as an engine 30, a tank 27, and electrical equipment 28 are housed. These components are covered by the cover 17 shown in FIG. 1.

[0038] FIG. 5 is a perspective view showing the fuselage 19 of the flight device 10 and its interior.

[0039] The internal space 29 is an area inside the fuselage 19. The internal space 29 has a shape resembling a flattened hexagonal prism. The internal space 29 is a space covered by the cover 17 shown in FIG. 1 and other figures. Although the internal space 29 is covered by the cover 17, it communicates with the outside through a gap formed in the cover 17. Therefore, as the flight device 10 flies, the internal space 29 is ventilated with outside air through this gap. Therefore, even if the engine 30 generates heat during flight of the flight device 10, the air in the internal space 29 is ventilated, preventing the inside of the internal space 29 from becoming excessively hot.

[0040] The internal space 29 of the airframe 19 is divided by the tank 27 into a first space 291 and a second space 292. Specifically, when the airframe 19 is viewed from above, the tank 27 divides the internal space 29 into the first space 291 and the second space 292. Therefore, in the internal space 29, the portion rearward of the tank 27 is the first space 291, and the portion forward of the tank 27 is the second space 292.

[0041] The tank 27 is, for example, a fuel tank 271 that stores fuel such as gasoline to be supplied to the engine 30. The fuel tank 271 is made of synthetic resin with a hollow structure and has an elongated shape along the left-right direction. In the front-rear direction, the fuel tank 271 is disposed approximately in the center of the internal space 29. Specifically, in the front-rear direction, the rear surface of the fuel tank 271 is disposed approximately in the center of the internal space 29. In addition, in the left-right direction, the width of the fuel tank 271 is approximately the same as the width of the internal space 29. The tank 27 having such a shape can partition the internal space 29. In this embodiment, the tank 27 functions as a fuel container that stores fuel, as well as a partition member that partitions the internal space 29, and as an insulating member that insulates the first space 291 and the second space 292.

[0042] The first space 291 accommodates the engine 30, the generator 16, and the like.

[0043] The engine 30 has an engine main body 34, a supply air duct 26, and an air intake section 25. The air intake section 25 is a section that takes in air from the outside to be supplied to a combustion chamber 48 (described later) of the engine main body 34. The air intake section 25 has a filter that captures dust contained in the taken-in air. The supply air duct 26 is a tubular member that connects the combustion chamber 48 of the engine main body 34 with the air intake section 25. The supply air duct 26 is a tubular member that extends along the front-to-rear direction and passes through a communication section 35 of a fuel tank 271. In other words, the supply air duct 26 extends from a first space 291 to a second space 292, penetrating the communication section 35, which is a partial recess in the fuel tank 271.

[0044] A generator 16 is attached to the engine 30. The generator 16 has a generator 161 and a generator 162. As described below, the engine 30 has a first engine section 40 and a second engine section 41 disposed opposite each other. The generators 161 and 162 are rotationally driven by the first engine section 40 and the second engine section 41, respectively, thereby generating electricity. The generator 16 is disposed between the engine main body section 34 and the fuel tank 271. With this configuration, the generator 16 can insulate the engine main body section 34 and the fuel tank 271, which become hot during operation. Therefore, fuel such as gasoline stored in the fuel tank 271 can be prevented from overheating during operation of the engine main body section 34.

[0045] The electrical equipment 28 is disposed in the second space 292. The electrical devices constituting the flight device 10 are used as the electrical equipment 28. Specifically, the electrical equipment 28 includes a power converter 281 and a battery 282. The electrical equipment 28 housed in the second space 292 is insulated from the engine main body 34 by the fuel tank 271. Therefore, even if the engine 30 generates heat while the flight device 10 is flying, the electrical equipment 28 is prevented from overheating due to the heat generated. Furthermore, the second space 292 is disposed forward of the first space 291. Therefore, while the flight device 10 is flying, air present in the first space 291 that has been overheated by the engine 30 is prevented from flowing into the second space 292. This also prevents the air inside the second space 292 from overheating.

[0046] When the engine 30 is operating during flight of the flight device 10, air is supplied to the combustion chamber 48 of the engine main body 34 (described later) via the air intake section 25 and the supply air duct section 26. The air taken in from the air intake section 25 is present in the second space 292. As described above, the engine main body 34, which is disposed in the first space 291, is insulated from the air present in the second space 292 by the fuel tank 271. Therefore, the air present in the second space 292 is at a lower temperature than the air present in the first space 291, which is heated by the engine 30. Furthermore, during flight of the flight device 10, outside air is constantly taken into the second space 292 through the gap formed in the cover 17 described above. Furthermore, in the direction of travel of the flight device 10, the second space 292 is disposed further forward than the first space 291. Therefore, when the flight device 10 flies forward, hot air from the first space 291 rarely enters the second space 292. Therefore, the air in the second space 292, which is at a relatively low temperature, is sent to the combustion chamber 48 (described later) of the power conversion unit 281 via the air intake unit 25 and the supply air passage unit 26. This increases the combustion efficiency in the combustion chamber 48, and improves the operating efficiency of the engine 30.

[0047] 6A is a perspective view showing the fuel tank 271 of the flight device 10. FIG. 6B is a side view showing the fuel tank 271 of the flight device 10.

[0048] 6A and 6B, as described above, fuel tank 271 has a flat shape in the front-to-rear direction. Fuel tank 271 mainly includes tank main body 272, supply portion 275, removal portion 273, bottom portion 274, and communication portion 35.

[0049] The tank main body 272 occupies the majority of the fuel tank 271 and is made of a hollow synthetic resin plate.

[0050] The supply part 275 is a generally cylindrical part formed on the left side of the upper surface of the tank main body 272. The supply part 275 connects the inside and outside of the tank main body 272. The supply part 275 is normally closed by a cap, which can be removed when refueling, etc. Fuel such as gasoline is supplied to the tank main body 272 via the supply part 275.

[0051] The outlet portion 273 is a substantially cylindrical portion formed in the approximate center of the bottom surface of the tank main body 272. The outlet portion 273 connects the inside and outside of the tank main body 272. Fuel such as gasoline stored in the tank main body 272 is transported from the outlet portion 273 to the engine 30 via a conduit (not shown).

[0052] The bottom surface 274 is the bottom surface of the tank main body 272. The bottom surface 274 slopes downward toward the removal portion 273. Specifically, because the removal portion 273 is disposed approximately in the center of the tank main body 272 in the left-right direction, the bottom surface 274 presents an inclined surface that slopes downward toward the center in the left-right direction. With this configuration, even if the fuel tank 271 tilts while the flight device 10 is flying, the fuel stored inside the tank main body 272 can flow along the bottom surface 274 toward the removal portion 273.

[0053] Referring to FIG. 6B, the communication portion 35 is a concave portion formed by partially recessing the upper surface of the tank 27 downward. As described above, referring to FIG. 5, the communication portion 35 is a portion that connects the first space 291 and the second space 292. The supply air duct 26 of the engine 30 shown in FIG. 5 is disposed in the communication portion 35. By forming the communication portion 35 in this shape, it is possible to prevent the communication portion 35 from obstructing the flow of fuel inside the tank main body 272. Here, the communication portion 35 may be a portion recessed leftward on the right side of the tank main body 272, a portion recessed rightward on the left side of the tank main body 272, or a portion recessed upward on the bottom side of the tank main body 272. Furthermore, the communication portion 35 may be formed as a portion that penetrates approximately the center of the tank main body 272.

[0054] FIG. 7 is a perspective view showing the engine 30 of the flight device 10. As shown in FIG.

[0055] The engine 30 has a first engine block 32 and a second engine block 33. The first engine block 32 and the second engine block 33 are made of cast metal such as aluminum and form the outer shell of the engine 30. As will be described later, components of a first engine section 40 are disposed inside the first engine block 32. Components of a second engine section 41 are disposed inside the second engine block 33. The first crankshaft 42 and the second crankshaft 45 extend to the outside from the side surfaces of the first engine block 32 and the second engine block 33, respectively.

[0056] FIG. 8 is a cross-sectional view showing the engine 30 of the flight device 10.

[0057] The engine 30 has a first engine section 40 and a second engine section 41. The first engine section 40 and the second engine section 41 are disposed opposite each other. Furthermore, the respective members of the first engine section 40 are housed in a first engine block 32, and the respective members of the second engine section 41 are housed in a second engine block 33.

[0058] The first engine section 40 has a first piston 43 that reciprocates, a first crankshaft 42 that converts the reciprocating motion of the first piston 43 into rotational motion, and a first connecting rod 44 that rotatably connects the first piston 43 and the first crankshaft 42.

[0059] The second engine section 41 has a second piston 46 that reciprocates, a second crankshaft 45 that converts the reciprocating motion of the second piston 46 into rotational motion, and a second connecting rod 47 that rotatably connects the second piston 46 and the second crankshaft 45.

[0060] The first piston 43 of the first engine section 40 and the second piston 46 of the second engine section 41 share a combustion chamber 48. In other words, the first piston 43 and the second piston 46 reciprocate inside a single, communicating cylinder 49. Therefore, the first engine section 40 and the first piston 43 simultaneously stroke toward the center, thereby reducing the stroke amount and achieving a high expansion ratio of the mixed gas in the combustion chamber 48. Referring to FIG. 6A , an air-fuel mixture consisting of fuel stored in a fuel tank 271 and air taken in from the air intake section 25 is introduced into the combustion chamber 48.

[0061] Although not shown here, the engine 30 has a volume space formed therein that communicates with the combustion chamber 48, and a spark plug is disposed in this volume space. The combustion chamber 48 also has an intake port and an exhaust port, not shown here, so that an air-fuel mixture containing a fuel such as gasoline is introduced into the combustion chamber 48 from the intake port, and the exhaust gas after combustion is discharged from the combustion chamber 48 to the outside via the exhaust port.

[0062] The engine 30 is formed by joining and fastening a first engine block 32 and a second engine block 33. That is, the internal space of the first cylinder block 50 and the internal space of the second cylinder block 51 are connected to each other to form a combustion chamber 48, which is a cylinder 49. A first piston 43 reciprocates within the first cylinder block 50, and a second piston 46 reciprocates within the internal space of the second cylinder block 51.

[0063] FIG. 9 is a connection diagram showing the connection configuration of the flight device 10.

[0064] The flight device 10 mainly includes an arithmetic and control unit 31, an engine 30, a generator 16, a battery 282, a power conversion unit 281, a motor 21, and a rotor 14.

[0065] The arithmetic and control unit 31 has a CPU, ROM, RAM, etc., and controls the behavior of each device constituting the flight device 10 based on inputs from various sensors and controllers (not shown here). The arithmetic and control unit 31 also includes a flight controller that controls the rotation speed of each rotor 14 based on inputs from the various sensors.

[0066] The engine 30 operates based on an input signal from the arithmetic and control unit 31, and generates energy for the flight device 10 to fly. The specific configuration of the engine 30 is as described with reference to Fig. 7 and the like.

[0067] The generator 16 is a device that generates electric power using the driving force of the engine 30, and includes a generator 161 and a generator 162. The generator 161 is driven by the first engine section 40 of the engine 30 described above. The generator 162 is driven by the second engine section 41 of the engine 30 described above.

[0068] The battery 282 is interposed between the generator 16 and the power conversion unit 281. The battery 282 is charged by the generator 16. The power discharged from the battery 282 is supplied to the power conversion unit 281, which will be described later, and the like.

[0069] The power conversion units 281 are provided corresponding to the individual motors 21 and rotors 14. The power conversion units 281 may be a converter and inverter that converts AC power supplied from the generator 16 to DC power and then converts it to AC power of a predetermined frequency. Furthermore, the power conversion units 281 may be an inverter that converts DC power supplied from the battery 282 to a predetermined frequency.

[0070] The motors 21 are provided corresponding to the individual rotors 14. Each of the motors 21 rotates at a predetermined speed by power supplied from the power conversion unit 281.

[0071] The following is a brief description of the operation of the flight device 10. The flight device 10 is operated in landing mode, takeoff mode, hovering mode, ascending / descending mode, and horizontal movement mode.

[0072] In the landing state, the flight device 10 is on the ground. In this state, the engine 30 is not running and the rotor 14 is not rotating.

[0073] In takeoff, the flight device 10 lifts off the ground surface due to the thrust generated by the rotation of the rotor 14 .

[0074] In the hovering state, the flight device 10 rotates the motors 21 and rotors 14 using the driving force generated by the engine 30 based on instructions from the arithmetic and control unit 31, causing the flight device 10 to float at a predetermined position in the air. At this time, each rotor 14 rotates based on instructions from the arithmetic and control unit 31. The arithmetic and control unit 31 controls each power conversion unit 281 to maintain the predetermined rotational speed of each motor 21 and rotor 14 so that the flight device 10 can maintain a predetermined altitude and attitude.

[0075] In the ascent / descent state, the flight device 10 ascends or descends by controlling the rotation speed of each motor 21 and rotor 14. In this case, the calculation and control unit 31 controls each power conversion unit 281 to maintain the predetermined rotation speed of each motor 21 and rotor 14 so that the flight device 10 can maintain a predetermined altitude and attitude.

[0076] In the horizontal movement state, the arithmetic and control unit 31 controls each power conversion unit 281 to control the rotation speed of each motor 21 and rotor 14, thereby tilting the flight device 10. In this case, the arithmetic and control unit 31 also controls the driving state of the engine 30 to rotate the rotor 14 at a predetermined speed.

[0077] Although the embodiments of the present invention have been described above, the present invention is not limited to these and can be modified within the scope of the present invention. In addition, the above-described embodiments can be combined with each other.

[0078] For example, with reference to Figure 6A etc., a fuel tank 271 has been exemplified as tank 27, but tanks that store other objects may also be used as tank 27. Specifically, the object stored in tank 27 may be a liquid, such as a pesticide. Furthermore, the object stored in tank 27 may be a portion of a cooling fluid circulating between a radiator and an engine.

[0079] 5, fuel tank 271 does not necessarily have to divide internal space 29 in the front-rear direction. Fuel tank 271 may divide internal space 29 in the left-right direction or in the up-down direction. [Explanation of symbols]

[0080] 10 Flight equipment 12 Arm 13 Exhaust section 14 rotors 15 Legs 16. Generator 161 Generator 162 Generator 17 Cover 171 Top of cover 172 Side of cover 173 Underside of cover 19 aircraft 21 Motor 25 Air supply section 26 Supply air passage section 27 Tank 271 Fuel Tank 272 Tank body 273 Removal section 274 Bottom part 275 Supply section 28 Electrical equipment 281 Power conversion unit 282 Battery 29 Interior Space 291 1st space 292 2nd space 30 Engine 31 Calculation control unit 32 No. 1 engine block 33 No. 2 engine block 34 Engine body 35 Communication part 40 First Engine Section 41 Second Engine Section 42 No. 1 crankshaft 43 First piston 44 First connecting rod 45 No. 2 crankshaft 46 Second piston 47 Second connecting rod 48 Combustion chamber 49 cylinders 50 No. 1 cylinder block 51 Second cylinder block

Claims

1. It is a flying device that floats in the air using the thrust generated by the rotation of the rotor. The aircraft comprises a body, an engine, a tank, and electrical equipment, The internal space of the aircraft body is divided into a first space and a second space by the tank, the engine is disposed in the first space, The flying device is characterized in that the electrical equipment is arranged in the second space.

2. 2. The flight device according to claim 1, wherein, when the airframe is viewed from above, the tank divides the internal space into the first space and the second space.

3. 2. The flight device according to claim 1, wherein the tank has a communication part that connects the first space and the second space.

4. 4. The flight device according to claim 3, wherein the communication portion is a concave portion formed by partially recessing the upper surface of the tank downward.

5. the engine has an engine main body, an air intake section that takes in air from the outside, and a supply air duct section that supplies air from the air intake section to the engine main body, the supply air passage portion extends from the first space to the second space through the communication portion, 4. The flying device according to claim 3, wherein the air supply section is disposed in the second space.

6. 4. The flight device according to claim 3, wherein the tank is a fuel tank that stores fuel to be supplied to the engine.

7. The tank has an outlet portion through which the fluid is taken out to the outside and a bottom portion, 2. The flight device according to claim 1, wherein the bottom surface is inclined downward toward the outlet.

Images