Flight device

Abstract

To provide an aircraft that allows for easy attachment of work equipment to the aircraft. [Solution] The machine comprises a body, a plurality of rotors 19 provided on the body, and a drive source 30 that drives at least a portion of the plurality of rotors 19. The machine has a main body that holds the drive source 30 inside, and skids, the skids having mounting parts 60 to which working devices can be attached.

Description

Technical Field

[0007]

[0001] The present invention relates to a flying device such as a multicopter.

Background Art

[0002] For example, as described in Patent Document 1, it has been devised to perform work by a work device while moving the work device using a flying device.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0008] In the present invention, the skid has left and right contact portions that make contact with the ground, vertical extension portions that extend upward from each of the left and right contact portions, and horizontal extension portions that are provided across the left and right vertical extension portions, and the mounting portion is preferably provided on the horizontal extension portion.

[0009] With this configuration, the lateral extension and mounting sections are positioned away from the ground, making it possible to position the work device at a height that facilitates attachment work to the mounting section. Therefore, by moving the work device closer to the mounting section, it becomes possible to easily attach the work device to the aircraft.

[0010] In the present invention, it is preferable that the mounting portion is provided on the lower surface of the lateral extension portion.

[0011] With this configuration, when the work device is moved below the lateral extension section, the mounting section is positioned above the work device. If the distance between the work device and the mounting section is short in this configuration, the work device can be easily attached to the aircraft.

[0012] In the present invention, it is preferable that the mounting portion is positioned below the main body portion.

[0013] In this configuration, the work equipment is attached below the heavier main body of the flight device. As a result, the main body and the work equipment are positioned in a straight line extending vertically, making it possible to create a configuration that is less prone to losing balance.

[0014] In the present invention, the mounting portion is provided with a towing portion capable of winding up and unwinding a long towing body, and it is preferable that the mounting portion is attached to the long towing body by attaching the work device to it and winding up the long towing body to attach the work device.

[0015] With this configuration, even if the distance between the work device and the mounting part is long, the work device can be easily attached to the aircraft by using the towing part.

[0016] In the present invention, it is preferable that the mounting portion is located laterally inward from both ends of the lateral extension portion in the left-right direction of the machine body.

[0017] This configuration creates a space enclosed by a lateral extension and a longitudinal extension. Furthermore, the mounting section is located within this space. Therefore, by moving the work device into this space, it becomes possible to position the work device close to the mounting section, making it easy to attach the work device to the aircraft.

[0018] In the present invention, it is preferable that a plurality of mounting portions are provided, and that each mounting portion is positioned so as not to overlap with the drive source in a plan view.

[0019] Generally, power sources are heavy, and the positional relationship between such power sources and work devices can cause imbalances. A configuration with multiple mounting points allows for adjustment of the work device's position relative to the power source using these multiple points. Furthermore, by positioning the multiple mounting points in locations that do not overlap with the power source in a plan view, the distance between the mounting points can be increased, allowing for adjustment of the work device's position relative to the power source over a wider range.

[0020] In the present invention, the vehicle is provided with an engine as the driving source and a fuel tank for storing fuel to be supplied to the engine, and it is preferable that at least a portion of each mounting portion overlaps with the fuel tank in a plan view.

[0021] According to this configuration, the working device is attached below the heavy fuel tank of the flying device. As a result, the fuel tank and the working device are linearly positioned in the vertical direction, and it is possible to achieve a configuration in which the balance is not easily disrupted.

[0022] In the present invention, it is preferable that the working device is attached to the attachment portion via a long member.

[0023] According to this configuration, even if the distance between the working device and the attachment portion is large, it is possible to easily attach the working device to the flying device using the long member.

[0024] In the present invention, it is preferable that the plurality of attachment portions are arranged so as to be located at the same height position, and the working device is supported so as to be located below the plurality of attachment portions and to overlap with the space surrounded by the plurality of attachment portions in plan view.

[0025] According to this configuration, since the working device is supported by the plurality of attachment portions located at the same height position, for example, it is possible to easily and suitably support the working device, such as keeping the working device horizontal by simply using wires of the same length.

Brief Description of the Drawings

[0026] [Figure 1] It is a plan view of the flying device. [Figure 2] It is a side view of the flying device. [Figure 3] It is a bottom view of the flying device. [Figure 4] It is a side view showing the configuration of the main body portion, the connecting member, the skid, and the attachment portion (weight attachment portion). [Figure 5] It is a perspective view showing the configuration of the attachment portion and the weight attachment portion. [Figure 6] It is a view showing the configuration of the attachment portion and the weight attachment portion. [Figure 7]This is a front view showing the configuration of the transport cart. [Figure 8] This is a side view showing the configuration of the transport cart. [Modes for carrying out the invention]

[0027] Embodiments for carrying out the present invention will be described with reference to the drawings. In the following description, unless otherwise specified, the direction of arrow F in the figures is "forward", the direction of arrow B is "backward", the direction of arrow L is "left", and the direction of arrow R is "right". Also, the direction of arrow U in the figures is "up", and the direction of arrow D is "down".

[0028] [Overall configuration of the flying device] The following describes the flight device of this embodiment. As shown in Figures 1 and 2, the flight device includes a main body 1, two sets of first arm sections 11, four sets of second arm sections 21, two sets of main rotors 19 (corresponding to the "rotors" of the present invention), four sets of sub-rotors 20 (corresponding to the "rotors" of the present invention), skids 29, two sets of engines 30 (corresponding to the "drive sources" of the present invention), a fuel tank 50, two sets of radiators 63, and the like.

[0029] [Main Unit Configuration] As shown in Figures 3 and 4, the main body 1 includes an upper horizontal frame 2, a lower horizontal frame 3, an upper joint 4, a lower joint 5, a vertical frame 6, and frames 9 and 10.

[0030] The main body 1 is provided with eight round pipe-shaped upper horizontal frames 2 and eight round pipe-shaped lower horizontal frames 3. Each of the upper horizontal frames 2 and lower horizontal frames 3 is set to the same length. The ends of the upper horizontal frames 2 are connected to each other by eight upper joints 4. The ends of the lower horizontal frames 3 are connected to each other by eight lower joints 5.

[0031] Two round pipe-shaped frames 9 are connected along the front-to-back direction to the lower horizontal frame 3. Two round pipe-shaped frames 10 are connected along the left-to-right direction to the lower horizontal frame 3 and frame 9.

[0032] Eight round pipe-shaped vertical frames 6 are connected across the upper joint section 4 and the lower joint section 5. The engine 30 is held in the space enclosed by the upper horizontal frame 2, the lower horizontal frame 3, and the vertical frames 6 inside the main body section 1.

[0033] [Configuration of the first arm] As shown in Figures 1 and 2, two sets of first arm portions 11, one on the right and one on the left, are provided on the main body portion 1.

[0034] As shown in Figures 2 and 4, the first arm section 11 has two round pipe-shaped upper frames 12, two round pipe-shaped lower frames 13, a flat plate-shaped support plate 14, and two flat plate-shaped connecting plates 15. The upper frames 12 and lower frames 13 are connected to the support plate 14, and the connecting plate 15 is connected across the upper frames 12 and lower frames 13.

[0035] In the right first arm section 11, the upper frame 12 is connected to the front and rear upper joint sections 4 of the right upper horizontal frame 2 of the main body section 1, and the lower frame 13 is connected to the front and rear lower joint sections 5 of the right lower horizontal frame 3 of the main body section 1.

[0036] In the left first arm section 11, the upper frame 12 is connected to the front and rear upper joint sections 4 of the left upper horizontal frame 2 of the main body section 1, and the lower frame 13 is connected to the front and rear lower joint sections 5 of the left lower horizontal frame 3 of the main body section 1.

[0037] The right and left first arm sections 11 extend outward from the main body section 1 in opposite directions in a plan view. The upper frame 12 is configured to be slightly longer than the lower frame 13, and the support plate 14 is positioned at the same height as the lower horizontal frame 3 of the main body section 1 in a side view. As will be described later, the right and left main rotors 19 are attached to the support plate 14.

[0038] [Configuration of the second arm] As shown in Figures 1 and 2, four sets of second arm sections 21 are provided on the main body section 1: right front and right rear, left front and left rear.

[0039] As shown in Figures 2 and 4, the second arm section 21 has two round pipe-shaped upper frames 22, two round pipe-shaped lower frames 23, a flat plate-shaped support plate 24, two flat plate-shaped connecting plates 25, and one round pipe-shaped support frame 26.

[0040] The upper frame 22 and the lower frame 23 are connected to the support plate 24, and the connecting plate 25 is connected across the upper frame 22 and the lower frame 23.

[0041] In the right front and right rear second arm sections 21, the upper frame 22 is connected to the front and rear upper joint sections 4 of the right front and right rear upper transverse frame 2 of the main body section 1, and the lower frame 23 is connected to the front and rear lower joint sections 5 of the right front and right rear lower transverse frame 3 of the main body section 1.

[0042] In the left front and left rear second arm sections 21, the upper frame 22 is connected to the front and rear upper joint sections 4 of the left front and left rear upper transverse frame 2 of the main body section 1, and the lower frame 23 is connected to the front and rear lower joint sections 5 of the left front and left rear lower transverse frame 3 of the main body section 1.

[0043] The right front second arm portion 21 is provided on the upper lateral frame 2 and lower lateral frame 3 of the main body portion 1, which are located in front of the right first arm portion 11. The right rear second arm portion 21 is provided on the upper lateral frame 2 and lower lateral frame 3 of the main body portion 1, which are located behind the right first arm portion 11.

[0044] The left front second arm portion 21 is provided on the upper horizontal frame 2 and lower horizontal frame 3 of the main body portion 1, which are located in front of the left first arm portion 11. The left rear second arm portion 21 is provided on the upper horizontal frame 2 and lower horizontal frame 3 of the main body portion 1, which are located behind the left first arm portion 11.

[0045] As shown in Figure 1, the right front and left rear second arm portions 21 extend outward from the main body portion 1 in opposite directions in a plan view.

[0046] As will be described later, the right front and right rear sub-rotors 20 and the left front and left rear sub-rotors 20 are attached to the ends of the support frame 26.

[0047] [Main rotor and sub-rotor configuration] As shown in Figures 1 to 3, right and left main rotors 19 are provided. The main rotors 19 are rotatably mounted on the ends (support plates 14) of the first arm section 11 around an axis P1 in the vertical direction, and are rotationally driven by the power of the engine 30. The rotational drive of the main rotors 19 generates lift, which is necessary for the aircraft to float.

[0048] As shown in Figures 1 and 2, in each of the four sets of second arm sections 21 (right front and right rear, left front and left rear), an electric motor 27 is mounted upward on the upper part of the end of the support frame 26, and a sub-rotor 20 is attached to the drive shaft (not shown) of the electric motor 27. An electric motor 28 is mounted downward on the lower part of the end of the support frame 26, and a sub-rotor 20 is attached to the drive shaft (not shown) of the electric motor 28.

[0049] In the four sets of sub-rotors 20, the upper and lower sub-rotors 20 are rotated in opposite directions around the axis P2 aligned with the vertical direction of the electric motors 27 and 28. The rotational drive of the sub-rotors 20 generates lift for attitude control of the main body 1. Attitude control of the main body 1 by the sub-rotors 20, and the lift generated by the main rotor 19, enables forward and backward flight, right and left flight, right and left turns, etc.

[0050] As the main rotor 19 is driven to rotate around the axis P1, two sets of circular rotation surfaces A1 are formed by the rotational trajectory of the main rotor 19. As the sub-rotor 20 is driven to rotate around the axis P2, four sets of circular rotation surfaces A2 are formed by the rotational trajectory of the sub-rotor 20.

[0051] The rotation surface A1 of the main rotor 19 is larger in diameter than the rotation surface A2 of the sub-rotor 20. The rotation surfaces A2 of the right front and right rear sub-rotors 20 are located in front of and behind the rotation surface A1 of the right main rotor 19. The rotation surfaces A2 of the left front and left rear sub-rotors 20 are located in front of and behind the rotation surface A1 of the left main rotor 19.

[0052] [Configuration of connecting members] As shown in Figures 2 and 4, below the main body 1, there are connecting members 16 that connect the main body 1 and the skid 29 before and after the connection. The main body 1 and the connecting members 16 constitute the aircraft body of the flight device (hereinafter referred to as "aircraft A").

[0053] The front and rear connecting members 16 each have a round pipe-shaped horizontal frame 17 and a round pipe-shaped connecting frame 18.

[0054] The horizontal frame 17 has a wider width than the main body 1. The horizontal frame 17 includes a first horizontal frame 17a located in the center, and right and left second horizontal frames 17b connected to both ends of the first horizontal frame 17a by horizontal internal joints 41.

[0055] The first horizontal frame 17a is configured to extend along the left-right direction of the aircraft A.

[0056] As shown in Figure 1, the right and left second transverse frames 17b are configured to be located further outward in the front-rear direction than they are located laterally in the left-right direction of the aircraft A. In other words, the second transverse frame 17b of the front connecting member 16 is located further forward as it is laterally outward, and the second transverse frame 17b of the rear connecting member 16 is located further back as it is laterally outward. With this configuration, the central portion (first transverse frame 17a) of the transverse frame 17 is located further inward in the front-rear direction of the aircraft A compared to the left and right ends.

[0057] As shown in Figures 1, 2, and 4, the connecting frame 18 is provided to extend diagonally downward so as to be located lower laterally outward from the lower joint portion 5 of the main body 1 when viewed in the front-rear direction of the aircraft A. The laterally outward end of the connecting frame 18 is connected to both ends of the lateral frame 17 by the lateral outer joint portions 42. Similar to the second lateral frame 17b, the connecting frame 18 is configured to be located further outward in the front-rear direction of the aircraft A as it moves laterally outward from the aircraft A in the left-right direction. In other words, the connecting frame 18 of the front connecting member 16 is located further forward as it moves laterally outward, and the connecting frame 18 of the rear connecting member 16 is located further back as it moves laterally outward.

[0058] With the above configuration, the connecting member 16 is configured to be symmetrical on the left and right sides of the aircraft A, and to have a trapezoidal shape when viewed from the front and rear of the aircraft A. With this configuration, the connecting member 16 extends from the main body 1 in the left and right directions of the aircraft A, and is positioned laterally outward on the side where the skid 29 is located in the left and right directions of the aircraft A. In other words, the connecting member 16 is configured to be wider on the side where the skid 29 is located in the left and right directions of the aircraft A.

[0059] The lower end portion of the connecting member 16 is provided with a lateral inner connecting portion 43 and a lateral outer connecting portion 44 for connecting the connecting member 16 and the skid 29. The lateral inner connecting portion 43 and the lateral outer connecting portion 44 are made of round pipe-shaped members.

[0060] The lateral internal connection portion 43 is configured to extend in the vertical direction. The upper end of the lateral internal connection portion 43 is connected to the lower part of the lateral internal joint portion 41. The lateral internal connection portion 43 is positioned to penetrate the skid 29 in the vertical direction and is fixed to the skid 29 by welding or the like.

[0061] The upper portion of the horizontal internal joint 41 is provided with a vertical connecting member 45 that connects the horizontal internal joint 41 to the lower joint 5 of the main body 1. In this embodiment, the front and rear vertical frames 6 penetrate the lower joint 5 and extend below the lower joint 5. The portions of the front and rear vertical frames 6 below the lower joint 5 are configured as the vertical connecting member 45. With this configuration, the vertical connecting member 45 is configured to connect the main body 1 to the location where the horizontal internal connection 43 of the connecting member 16 is located. The horizontal internal connection 43 is located in a position that overlaps with the location where the connecting member 16 and the main body 1 are connected in a plan view.

[0062] The lateral external connection portion 44 is configured to extend in the vertical direction. The lateral external connection portion 44 is located laterally outward from the connection point (lower joint portion 5) between the connecting member 16 and the main body portion 1 in the left-right direction of the aircraft body A, and is located at the outermost lateral end of the connecting member 16. The lateral internal connection portion 43 is located laterally inward from the lateral external connection portion 44 in the left-right direction of the aircraft body A. The upper end of the lateral external connection portion 44 is connected to the lateral external joint portion 42. The lower end of the lateral external connection portion 44 is fixed to the skid 29 by welding or the like, connecting the connecting member 16 and the skid 29.

[0063] [Skid configuration] As shown in Figures 2 and 3, the skid 29 has left and right contact points 51 that make contact with the ground, front and rear longitudinal extensions 52 that extend upward from the left and right contact points 51, front and rear lateral extensions 53 that are provided across the left and right longitudinal extensions 52, and left and right front and rear connecting points 54 that connect the front and rear lateral extensions 53.

[0064] As shown in Figure 3, the front and rear lateral extensions 53 are bent at the left-right central portion 53c, which is the central part of the lateral extension 53 in the left-right direction of the aircraft body A. The left-right central portion 53c is located closer to the center in the front-rear direction of the aircraft body A than the upper connection portion 55, which is the connection point between the longitudinal extension 52 and the lateral extension 53. In other words, the front and rear lateral extensions 53 are configured to move further apart from each other as they move laterally outward. With this configuration, the longitudinal extension 52 and the lateral extension 53 are located outside the rotation trajectory (rotation plane A1) of the main rotor 19 in a plan view.

[0065] As shown in Figure 2, the lateral extension 53 is composed of a frame body that extends in the left-right direction of the aircraft body A. The lateral extension 53 is configured to extend horizontally when viewed in the front-rear direction of the aircraft body A, and the height position of the left-right central portion 53c of the lateral extension 53 and the height position of the upper connecting portion 55 are at the same height. Reinforcing members 55s are provided at both ends of the lateral extension 53, extending across the vertical extension 52 and the lateral extension 53.

[0066] Each of the front-rear and left-right longitudinal extensions 52 is composed of a frame body extending downward from both ends (upper connection parts 55) of the lateral extension 53. The longitudinal extensions 52 are positioned so that they are located further outward towards the bottom in the front-rear and left-right directions of the aircraft A (see Figures 7 and 8). The lower connection part 56, which is the connection point between the longitudinal extension 52 and the ground contact part 51, is located laterally outward from the upper connection part 55 in the left-right direction of the aircraft A.

[0067] The left and right ground contact points 51 are each composed of pipe-shaped members extending along the front-rear direction of the aircraft body A. The left and right ground contact points 51 are located at the lower ends of the longitudinal extension 52 and are positioned laterally outward from the upper connection point 55 in the left-right direction of the aircraft body A.

[0068] As shown in Figure 3, the left and right front and rear connecting sections 54 are made of round pipe-shaped members that extend in the front-rear direction of the aircraft body A. The left and right front and rear connecting sections 54 are connected to a point that is located outward in the left-right direction of the aircraft body A from the point where the lateral inward connecting section 43 of the front and rear longitudinal extension section 52 is fixed.

[0069] [Configuration of the mounting section] As shown in Figures 3 and 4, the skid 29 has a mounting section 60 to which a working device (not shown) can be attached. Here, the working device may be, but is not limited to, a seeding device for sowing seeds in the field, a fertilizer application device for supplying fertilizer to seedlings planted in the field, a pesticide application device for supplying herbicides or other chemicals to the field, or a camera for photographing the field.

[0070] In this embodiment, four mounting portions 60 are provided. As shown in Figures 5 and 6, each mounting portion 60 has a mounting plate-shaped member 61 made of a plate-shaped material. The mounting plate-shaped member 61 is fixed by welding or the like to the lower end portion of a lateral internal connection portion 43 that is provided to penetrate the skid 29 in the vertical direction.

[0071] The mounting portion 60 has a bolt Ba to which a work device can be attached. A bolt hole 61h for attaching a work device is formed in the central part of the mounting plate-shaped member 61, through which the bolt Ba can be inserted. The bolt Ba is fixed to the mounting plate-shaped member 61 by being fastened with a nut while inserted through the bolt hole 61h for attaching a work device. In this embodiment, the bolt Ba to which the work device can be attached is an eye bolt with a ring at its head. The bolt Ba is configured to allow attachment of a work device using a hook or the like.

[0072] As shown in Figures 4 to 6, each mounting portion 60 is provided on the lower surface of the lateral extension portion 53 of the skid 29 and is positioned below the main body portion 1. Furthermore, the mounting portions 60 are located laterally inward from both ends of the lateral extension portion 53 in the front-rear and left-right directions of the aircraft A, and are located inside the upper connection portion 55.

[0073] The four mounting parts 60 (mounting plate-shaped members 61) are arranged to be at the same height.

[0074] With the above configuration, the work device is supported so as to be located below the four mounting parts 60 and in a position that overlaps with the space surrounded by the four mounting parts 60 in a plan view.

[0075] [Weight mounting configuration] As shown in Figures 4 to 6, the aircraft is equipped with a weight attachment section 60W that allows for adjustment of the center of gravity by attaching weights W.

[0076] The mounting plate-shaped member 61 is formed in a substantially rectangular shape, and weight bolt holes Wh are formed at the four corners of the mounting plate-shaped member 61, through which bolts Bw for fixing the weight W can be inserted. The bolts Bw are inserted into the weight bolt holes Wh and fastened with nuts to fix them to the mounting plate-shaped member 61. The weight W is attached to the mounting plate-shaped member 61 using the four bolts Bw. In other words, the mounting plate-shaped member 61 and the bolts Bw constitute the weight mounting section 60W.

[0077] With the above configuration, the mounting plate-shaped member 61 is configured to allow the work device and the weight W to be attached. In other words, the weight mounting section 60W also serves as the mounting section 60.

[0078] In this embodiment, as described above, the working device is attached to the ring of the bolt Ba, which is an eyebolt, and the weight mounting portion 60W is located above the mounting position of the working device (the ring of the bolt Ba) in the mounting portion 60.

[0079] As shown in Figure 3, the mounting portion 60 and the weight W attached to the mounting portion 60 are positioned so as not to overlap with the engine 30 in a plan view. Furthermore, the weight W attached to the mounting portion 60 and the weight mounting portion 60W is positioned so that at least a portion of it overlaps with the fuel tank 50 in a plan view, and is positioned at a height lower than the height of the fuel tank 50.

[0080] [Configuration of the transport cart] As shown in Figures 7 and 8, the flying device is equipped with a transport trolley 70 configured to transport the flying device. The transport trolley 70 has wheels 71, a trolley body 72 supported by the wheels 71, and a support part 73 that supports the flying device.

[0081] The wheels 71 are configured to rotate freely, and the transport cart 70 can be moved manually by an operator using the wheels 71.

[0082] The bogie body 72 is constructed by combining multiple metal frames. In this embodiment, as shown in Figures 7 and 8, the frames are combined to form the edges of a cube, thereby constructing the bogie body 72 in a cubic shape. The wheels 71 are provided on the underside of the bogie body 72. As shown in Figure 7, the width of the bogie body 72 in the left-right direction is shorter than the distance between the left and right longitudinal extensions 52 and the distance between the left and right ground contact portions 51 of the skid 29 of the aircraft device.

[0083] The support portion 73 is fixed to the upper surface of the trolley body 72. In this embodiment, the support portion 73 is a manual jack that can lift and operate the flying device by being configured to extend and retract in the height direction. The support portion 73 has a connecting portion 73c at its upper end that is configured to be connected to the flying device. The connecting portion 73c is configured to be movable in the height direction. By moving the connecting portion 73c closer to and further away from the flying device, it is possible to switch between a supported state that supports the flying device and an unsupported state that does not support the flying device. Note that Figure 7 shows the transport trolley 70 in the unsupported state, and Figure 8 shows the transport trolley 70 in the supported state.

[0084] In the unsupported state, the connecting portion 73c is located at a lower height than the lateral extension portion 53. By operating the support portion 73 to the supported state and changing the height of the connecting portion 73c, it is configured to be connectable to the lateral extension portion 53. With this configuration, the support portion 73 is configured to support the lateral extension portion 53, which is the portion of the flight device above the ground contact portion 51.

[0085] When the support portion 73 is in the supporting position, the contact portion 51 of the skid 29 is located higher than the contact position of the wheel 71 and is lifted off the ground. When in the supporting position, the aircraft can be moved manually by an operator using the wheel 71.

[0086] [Another embodiment] The following are examples of alternative embodiments that modify the above embodiments.

[0087] (1) In the above embodiment, the skid 29 was described as having a configuration comprising left and right ground contact portions 51 that make contact with the ground, front and rear longitudinal extension portions 52 that extend upward from each of the left and right ground contact portions 51, front and rear lateral extension portions 53 that are provided across the left and right longitudinal extension portions 52, and left and right front and rear connecting portions 54 that connect the front and rear lateral extension portions 53. However, the present invention is not limited to the above embodiment. For example, the skid 29 may have a configuration comprising one longitudinal extension portion 52 and one lateral extension portion 53 located in the central part in the front-rear direction of the aircraft body A.

[0088] (2) In the above embodiment, the connecting member 16 was provided so as to extend from the main body 1 in the left-right direction of the aircraft A when viewed in the front-rear direction of the aircraft A, and was configured to be located laterally outward on the side where the skid 29 is located. However, the present invention is not limited to the above embodiment. For example, the connecting member 16 may have the same width as the main body 1 when viewed in the front-rear direction of the aircraft A, or the connecting member 16 may be configured so that its width becomes narrower on the side where the skid 29 is located when viewed in the front-rear direction of the aircraft A.

[0089] (3) In the above embodiment, a configuration in which a lateral inner connecting portion 43 and a lateral outer connecting portion 44 for connecting the connecting member 16 and the skid 29 are provided was described as an example, but the present invention is not limited to the above embodiment. For example, the configuration may consist of only the lateral inner connecting portion 43 of the lateral inner connecting portion 43 and the lateral outer connecting portion 44, or the configuration may consist of only the lateral outer connecting portion 44 of the lateral inner connecting portion 43 and the lateral outer connecting portion 44.

[0090] (4) In the above embodiment, the mounting portion 60 was described as having a bolt Ba to which a work device can be attached, but the present invention is not limited to the above embodiment. For example, the mounting portion 60 may be provided with a towing portion that can wind up and unwind a long towing body, and the mounting portion 60 may be configured to attach a work device to a long towing body and then wind up the long towing body to attach the work device. Alternatively, the work device may be attached to the mounting portion 60 via a long body such as a wire.

[0091] (5) In the above embodiment, each mounting portion 60 is provided on the lower surface of the lateral extension portion 53 of the skid 29, and is located laterally inward from both ends of the lateral extension portion 53 in the front-rear and left-right directions of the aircraft body A, and is located inward from the upper connecting portion 55. Furthermore, the four mounting portions 60 (mounting plate-shaped members 61) are arranged to be at the same height. However, the present invention is not limited to the above embodiment. For example, the mounting portion 60 may be provided on the longitudinal extension portion 52 of the skid 29, and may also be located laterally outward from both ends of the lateral extension portion 53 in the front-rear and left-right directions of the aircraft body A. Furthermore, the four mounting portions 60 (mounting plate-shaped members 61) may be arranged to be at different heights. Also, there may be three or fewer mounting portions 60, or five or more.

[0092] (6) In the above embodiment, the weight mounting portion 60W was described as also serving as the mounting portion 60, but the present invention is not limited to the above embodiment. For example, the mounting portion 60 and the weight mounting portion 60W may be configured as separate parts.

[0093] (7) In the above embodiment, the front and rear lateral extensions 53 are bent at the left and right central portions 53c, and the left and right central portions 53c are located closer to the center in the front-rear direction of the aircraft A than the upper connecting portion 55. However, the present invention is not limited to the above embodiment. The front and rear lateral extensions 53 may not be bent at the left and right central portions 53c. For example, the front and rear lateral extensions 53 may each be curved from the upper connecting portion 55 located at one end of the lateral extension 53 to the upper connecting portion 55 located at the other end, so that the left and right central portions 53c are located closer to the center in the front-rear direction of the aircraft A than the upper connecting portion 55.

[0094] (8) In the above embodiment, the transport trolley 70 was described as having a configuration in which it is equipped with freely rotating wheels 71, but the present invention is not limited to the above embodiment. For example, the transport trolley 70 may be equipped with drive wheels or crawlers driven by a motor or the like instead of the freely rotating wheels 71.

[0095] (9) In the above embodiment, the support portion 73 was described as a manual jack, but the present invention is not limited to the above embodiment. For example, the support portion 73 may be a hydraulic jack or an air jack.

[0096] (10) In the above embodiment, the support portion 73 was described as supporting the lateral extension portion 53 of the skid 29 of the aircraft when in the support state, but the present invention is not limited to the above embodiment. For example, the support portion 73 may be configured to support the longitudinal extension portion 52 of the skid 29 of the aircraft when in the support state.

[0097] Furthermore, the configurations disclosed in the above embodiments (including other embodiments, the same applies hereinafter) can be applied in combination with configurations disclosed in other embodiments, as long as no inconsistencies arise. In addition, the embodiments disclosed herein are illustrative, and the embodiments of the present invention are not limited thereto, and can be modified as appropriate without departing from the object of the present invention. [Industrial applicability]

[0098] This invention can be used in flying devices. [Explanation of Symbols]

[0099] 1: Main body 19: Main rotor (rotor) 20: Sub-rotor (rotor) 29: Skid 30: Engine (power source) 50: Fuel tank 51: Grounding part 52: Longitudinal extension 53: Lateral extension part 60: Mounting part A: Aircraft

Claims

1. The aircraft and, Multiple rotors provided on the aforementioned aircraft, The system includes a drive source that drives at least a portion of the multiple rotors, The aircraft comprises a main body that holds the drive source internally, and skids. The skid is an aircraft having a mounting portion to which a work device can be attached.

2. The skid has left and right contact points that make contact with the ground, vertical extensions extending upward from each of the left and right contact points, and horizontal extensions provided across the left and right vertical extensions. The flight device according to claim 1, wherein the mounting portion is provided on the laterally extended portion.

3. The flight device according to claim 2, wherein the mounting portion is provided on the lower surface of the lateral extension portion.

4. The flight device according to claim 3, wherein the mounting portion is positioned below the main body portion.

5. The mounting portion is provided with a towing unit capable of winding up and unwinding a long towing body. The flight device according to claim 1, wherein the mounting portion is attached to the towing elongated body by attaching the working device to it and winding up the towing elongated body to attach the working device.

6. The flight device according to claim 2, wherein the mounting portion is located laterally inward from both ends of the lateral extension portion in the left-right direction of the aircraft.

7. Multiple mounting parts are provided, The flight device according to claim 1, wherein each of the aforementioned mounting parts is positioned in a location that does not overlap with the drive source in a plan view.

8. The engine provided as the drive source, The system includes a fuel tank for storing fuel to be supplied to the engine, The flight device according to claim 7, wherein at least a portion of each of the aforementioned mounting portions overlaps with the fuel tank in a plan view.

9. The flight device according to claim 8, wherein the work device is attached to the mounting portion via a long body.

10. Multiple mounting parts are arranged to be located at the same height. The flight device according to claim 7, wherein the working device is supported so as to be located below the plurality of mounting parts and in a position that overlaps with the space surrounded by the plurality of mounting parts in a plan view.

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