Flight device

Abstract

In an aircraft that transmits power from a water-cooled engine to a rotor via a transmission shaft, thereby rotating the rotor with the engine's power, the radiator is configured to ensure sufficient heat exchange. [Solution] The system includes an arm portion 11 extending outward from the main body portion 1, and a rotor 19 attached to the arm portion 11. A transmission shaft 60 is provided along the arm portion 11, spanning from the main body portion 1 to the rotor 19, and transmits power from the engine 30 to the rotor 19. A radiator 63 is attached to the arm portion 11 so as to be located above the transmission shaft 60 and along the rotation plane A1 of the rotor 19.

Description

Technical Field

[0001] The present invention relates to the configuration of a cooling system for a flying device such as a multicopter.

Background Art

[0002] An example of a flying device is disclosed in Patent Document 1. In Patent Document 1, a plurality of arm portions extend radially from the main body portion, and a rotor that generates lift is provided on each of the arm portions. The entire flying device is configured by the main body portion and the plurality of arm portions.

[0003] In Patent Document 1, an engine, a generator driven by the engine, and a battery that stores the generated electric power are provided in the main body portion, and an electric motor that rotationally drives the rotor is provided in the arm portion, and the electric motor operates by the power of the battery.

Prior Art Documents

Patent Documents

[0004]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0005] In a relatively large flying device, it is conceivable to transmit the power of the engine to the rotor by a transmission shaft and rotationally drive the rotor by the power of the engine. In a flying device that rotationally drives a rotor by the power of an engine, when a water-cooled engine is provided, it is necessary to configure the heat exchange in the radiator that generates the cooling water of the engine to be sufficiently performed.

[0006] The present invention aims to provide a configuration for an aircraft that transmits power from a water-cooled engine to a rotor via a transmission shaft, thereby rotating the rotor using the engine's power, in which sufficient heat exchange occurs in the radiator. [Means for solving the problem]

[0007] The flying device of the present invention comprises a main body, an engine provided in the main body, an arm extending outward from the main body, a rotor attached to the arm, a transmission shaft provided along the arm and spanning from the main body to the rotor, for transmitting power from the engine to the rotor, and a radiator for generating cooling water for the engine, wherein the radiator is located above the transmission shaft and is attached to the arm so as to be aligned with the rotational surface of the rotor.

[0008] According to the present invention, an engine is provided in the main body, an arm extends outward from the main body, and a rotor is attached to the arm. A transmission shaft is provided along the arm, spanning from the main body to the rotor, and the engine's power is transmitted to the rotor via the transmission shaft. As the rotor rotates, the air near the rotor flows from above, through the interior and periphery of the rotor's rotating surface, and down to the rotor. Since the arm extends outward from the main body, the areas above and below the arm are easily left open, allowing for a natural upward-to-downward airflow associated with the rotor's rotation.

[0009] According to the present invention, the radiator is mounted on an arm along the rotational plane of the rotor and is located above the transmission shaft that transmits engine power to the rotor. Because the radiator is mounted on the arm, it is positioned closer to the rotor, making it easier for the airflow from above to below, caused by the rotor's rotation, to hit the radiator. By positioning the radiator along the rotor's rotation plane, the upward-to-downward airflow associated with the rotor's rotation is more likely to strike the radiator perpendicularly. By positioning the radiator above the drive shaft, the drive shaft is less likely to obstruct the upward-to-downward airflow generated by the rotor's rotation as it hits the radiator. This allows for sufficient heat exchange in the radiator, resulting in more efficient engine cooling and improved flight performance of the aircraft.

[0010] In the present invention, it is preferable that the radiator is located between the upper and lower portions of the arm portion when viewed from the side.

[0011] According to the present invention, the radiator is provided at a position between the upper and lower portions of the arm, and within the vertical range of the arm, thereby enabling a compact configuration of the radiator and the arm.

[0012] In the present invention, it is preferable that the transmission shaft is located between the radiator and the lower portion of the arm when viewed from the side.

[0013] According to the present invention, when the radiator is located between the upper and lower portions of the arm, the transmission shaft is located between the radiator and the lower portion of the arm, thereby positioning the radiator above the transmission shaft. As a result, in addition to the radiator, the transmission shaft is located within the vertical range of the arm section, allowing the radiator, transmission shaft, and arm section to be configured compactly.

[0014] In the present invention, it is preferable that the radiator is provided across one portion and the other portion of the arm in a direction perpendicular to the longitudinal direction of the arm portion when viewed in plan.

[0015] According to the present invention, the radiator is provided across one and the other portion of the arm in a direction perpendicular to the longitudinal direction of the arm in a plan view, and does not protrude significantly laterally from the arm, so the radiator and the arm are configured compactly.

[0016] In the present invention, it is preferable that the radiator is provided in a position between the upper and lower portions of the arm in a side view, and extends across one portion of the arm and the other portion in a direction perpendicular to the longitudinal direction of the arm in a plan view.

[0017] According to the present invention, the radiator is located inside the arm section, resulting in a compact configuration for both the radiator and the arm section. According to the present invention, since the radiator is installed inside the arm portion, the radiator is protected by the arm portion, thus preventing damage to the radiator.

[0018] In the present invention, it is preferable that the radiator, the arm portion, and the transmission shaft are located above the rotational surface, and that in a plan view, the radiator and the rotational surface overlap.

[0019] According to the present invention, the rotation planes of the radiator and the rotor overlap in a plan view, which allows the airflow from above to below due to the rotor's rotation to sufficiently hit the radiator. This is advantageous in that it ensures sufficient heat exchange in the radiator and is advantageous in improving the flight performance of the aircraft.

[0020] According to the present invention, the radiator, the arm portion, and the transmission shaft are positioned above the rotation plane of the rotor, so that the air near the lower surface of the radiator and the air near the portion of the transmission shaft located below the radiator are drawn downward by the rotor.

[0021] Thus, even if floating substances such as paper scraps adhere to the lower surface portion of the radiator or the transmission shaft, the floating substances are sucked downward and discharged by the rotor, so that it is possible to prevent the floating substances from adhering to the lower surface portion of the radiator or the transmission shaft, which is advantageous in terms of enabling sufficient heat exchange in the radiator and improving the flight performance of the flying device.

[0022] In the present invention, it is preferable that the radiator overlaps with the engine in a side view seen from a direction along the longitudinal direction of the arm portion.

[0023] According to the present invention, since the radiator is provided at the same height as the engine, the hoses and pipes for circulating the cooling water across the radiator and the engine are likely to be short, so that the structure can be simplified.

[0024] In the present invention, it is preferable that a fuel tank is provided below the engine and the radiator is provided above the fuel tank in a side view.

[0025] According to the present invention, the fuel tank is provided below the engine, the low center of gravity of the main body portion is achieved, and the fuel tank is less likely to interfere with the upward-to-downward flow of air accompanying the rotation of the rotor, which is advantageous in terms of improving the flight performance of the flying device.

[0026] According to the present invention, since the radiator is provided at a position higher than the fuel tank provided below the engine, a state where the radiator is provided at the same height as the engine can be obtained without difficulty, and the radiator, the engine, and the fuel tank are arranged in a well-balanced manner, which is advantageous in terms of improving the flight performance of the flying device.

Brief Description of the Drawings

[0027] [Figure 1] It is a plan view of a flying device. [Figure 2] It is a left side view of a flying device. [Figure 3]This is a plan view of the flight device with the second arm folded. [Figure 4] This is a left side view of the flight device with the second arm folded. [Figure 5] This is a plan view of the main body, the first arm, and the second arm. [Figure 6] This is an exploded plan view of the main body, the first arm, and the second arm. [Figure 7] This is a rear view of the disassembled main body, first arm, and second arm. [Figure 8] This is a plan view showing the interior of the main body. [Figure 9] This is a left side view showing the inside of the main unit. [Figure 10] This is a rear view showing the inside of the main unit. [Figure 11] This is a perspective view of the fuel tank. [Figure 12] This is a front view showing the drive structure of the main rotor. [Figure 13] This is a plan view showing the drive structure of the main rotor. [Modes for carrying out the invention]

[0028] Figures 1 to 13 show the flying device, where F indicates forward, B indicates backward, U indicates upward, D indicates downward, R indicates right, and L indicates left.

[0029] (Overall configuration of the flying device) 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, four sets of sub-rotors 20, skids 29, two sets of engines 30 (see Figures 8 and 9), a fuel tank 50, two sets of radiators 63, and the like.

[0030] (Configuration of main body 1) As shown in Figures 5, 6, and 7, 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 7, 8, 9, and 10.

[0031] Eight round pipe-shaped upper horizontal frames 2 and eight round pipe-shaped lower horizontal frames 3 are provided, and 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 by eight upper joints 4, so that the upper horizontal frames 2 and the upper joints 4 are formed in a regular octagon shape in plan view. Two round pipe-shaped frames 7 are connected to the upper joints 4 along the left-right direction, and two round pipe-shaped frames 8 are connected to the frames 7 along the front-back direction.

[0032] The ends of the lower horizontal frame 3 are connected by eight lower joints 5, so that the lower horizontal frame 3 and the lower joints 5 are formed in a regular octagon shape in plan view. Two round pipe-shaped frames 9 are connected to the lower horizontal frame 3 along the front-to-back direction. Two round pipe-shaped frames 10 are connected to the lower horizontal frame 3 and the frames 9 along the left-to-right direction.

[0033] Eight round pipe-shaped vertical frames 6 are provided, and these vertical frames 6 are connected across the upper joint section 4 and the lower joint section 5. The upper horizontal frame 2, the lower horizontal frame 3, and the vertical frames 6 constitute the main body 1, which is a regular octagonal cube in plan view.

[0034] In the main body 1, the regular octagon formed by the upper horizontal frame 2 and the upper joint 4, and the regular octagon formed by the lower horizontal frame 3 and the lower joint 5, are both regular octagons of the same size. The upper joint 4 and the lower joint 5 are located on the same circumscribed circle (not shown) in plan view, and the main body 1 has a point-symmetrical shape in plan view. The regular octagon formed by the lower horizontal frame 3 and the lower joint 5 of the main body 1 aligns with the rotation surface A1 of the main rotor 19 (see Figure 1) and the rotation surface A2 of the sub-rotor 20 (see Figure 1), which will be described later.

[0035] (Skid 29 configuration) As shown in Figures 2 and 7, trapezoidal front and rear connecting members 16 are provided in a front view. The connecting member 16 has one round pipe-shaped horizontal frame 17 and two round pipe-shaped connecting frames 18. The horizontal frame 17 has a wider width than the main body 1, and the connecting frames 18 are connected to both ends of the horizontal frame 17 and extend diagonally upward.

[0036] In the main body 1, the front and rear vertical frames 6 extend downward through the lower joint 5. The lower end of the front vertical frame 6 of the main body 1 is connected to the horizontal frame 17 of the front connecting member 16, and the upper end of the connecting frame 18 of the front connecting member 16 is connected to the lower joint 5 of the front lower horizontal frame 3 of the main body 1.

[0037] The lower end of the rear vertical frame 6 of the main body 1 is connected to the horizontal frame 17 of the rear connecting member 16, and the upper end of the connecting frame 18 of the rear connecting member 16 is connected to the lower joint portion 5 of the rear lower horizontal frame 3 of the main body 1. The skid 29 is connected to the lower part of the front and rear connecting members 16, and is connected to the lower part of the main body 1 via the front and rear connecting members 16.

[0038] (Configuration of the first arm section 11) As shown in Figures 5, 6, and 7, two sets of first arm portions 11, one on the right and one on the left, are provided on the main body portion 1.

[0039] 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.

[0040] 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.

[0041] 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.

[0042] As shown in Figure 5, the right and left first arm sections 11 extend outward from the main body section 1 in opposite directions in a plan view. As shown in Figures 2 and 7, the upper frame 12 is configured to be slightly longer than the lower frame 13. As shown in Figures 2 and 4, the support plate 14 is located 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 (see Figures 1 and 2) are attached to the support plate 14.

[0043] (Configuration of the second arm section 21) As shown in Figures 5, 6, and 7, 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.

[0044] The second arm section 21 includes 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.

[0045] 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. The support frame 26 is attached to the support plate 24 in a foldable manner, as will be described later. The second arm portion 21 is configured to be longer than the first arm portion 11.

[0046] 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.

[0047] As a result, the right 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 on the front side (one side) of the right first arm portion 11. The right 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 on the rear side (the other side) of the right first arm portion 11.

[0048] 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.

[0049] As a result, 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 on the front side (one side) 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 on the rear side (the other side) of the left first arm portion 11.

[0050] The right front and left rear second arm portions 21 extend outward from the main body portion 1 in opposite directions when viewed from above.

[0051] The upper and lower lateral frames 2 and 3 at the front of the main body 1, located between the right front and left front second arm portions 21, do not have the first arm portion 11 and the second arm portion 21. The upper and lower lateral frames 2 and 3 at the rear of the main body 1, located between the right rear and left rear second arm portions 21, do not have the first arm portion 11 and the second arm portion 21.

[0052] As shown in Figures 5, 6, and 7, the upper frame 22 and the lower frame 23 are configured to be the same length. As shown in Figures 2 and 4, the support plate 24 is located at an intermediate height between the upper frame 22 and the lower horizontal frame 3 of the main body 1 in a side view, and is positioned higher than the support plate 14 of the first arm 11. As will be described later, the right front and right rear sub-rotors 20 (see Figures 1 and 2) and the left front and left rear sub-rotors 20 (see Figures 1 and 2) are attached to the ends of the support frame 26.

[0053] (Configuration of main rotor 19 and sub-rotor 20) As shown in Figures 1 and 2, the right and left main rotors 19 are provided. As will be described later, the main rotor 19 is mounted on the end of the first arm section 11 (support plate 14) so ​​as to be rotatable around an axis P1 in the vertical direction, and is rotationally driven by the power of the engine 30 (see Figures 8 and 9). The rotational drive of the main rotor 19 generates a lift force that supports the main body section 1.

[0054] 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. The sub-rotor 20 is detachable from the drive shafts of the electric motors 27 and 28.

[0055] 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 turns and left turns, etc.

[0056] 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.

[0057] 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.

[0058] (Folding configuration of the second arm section 21) - 1 As shown in Figures 5, 6, and 7, in each of the four sets of second arm portions 21 (front right and rear right, front left and rear left), the portion of the support frame 26 closest to the first arm portion 11 is attached to the support plate 24 so as to be able to swing around the axis P3 in the vertical direction.

[0059] The state shown in Figures 5, 6, and 7 is one in which the upper frame 22, lower frame 233, and support frame 26 are arranged in a straight line in a plan view, and the support frame 26 is connected to the support plate 24 by bolts 67. In the state shown in Figures 5, 6, and 7, the flight described above takes place.

[0060] When an operator transports the aircraft on the cargo bed of a transport vehicle (not shown), the operator performs the following operations. In this case, the operator may remove the main rotor 19 and sub-rotor 20 in advance.

[0061] As shown in Figure 3, the worker removes all bolts 67 (see Figure 5) from the support frame 26 of the second arm section 21. The operator swings the support frame 26 of the right front second arm section 21 around the axis P3 towards the rear, where the right front sub-rotor 20 is closer to the right main rotor 19. The operator swings the support frame 26 of the right rear second arm section 21 around the axis P3 forward, so that the right rear sub-rotor 20 is closer to the right main rotor 19.

[0062] The operator swings the support frame 26 of the left front second arm section 21 around the axis P3 towards the rear, where the left front sub-rotor 20 is closer to the left main rotor 19. The operator swings the support frame 26 of the left rear second arm section 21 around the axis P3 forward, so that the left rear sub-rotor 20 is closer to the left main rotor 19.

[0063] The worker attaches a jig (not shown) across the support frame 26 of the right front second arm section 21 and the support frame 26 of the right rear second arm section 21 to fix the support frame 26 of the right front second arm section 21 and the support frame 26 of the right rear second arm section 21 together.

[0064] The worker attaches a jig (not shown) across the support frame 26 of the left front second arm section 21 and the support frame 26 of the left rear second arm section 21 to fix the support frame 26 of the left front second arm section 21 and the support frame 26 of the left rear second arm section 21 together. In this manner, the worker folds the second arm section 21.

[0065] The worker loads the aircraft onto the cargo bed of the transport vehicle in the aforementioned state. In this case, the worker removes the main rotor 19 from the first arm section 11 and the sub-rotor 20 from the second arm section 21, depending on the transport conditions. After the flying device is loaded onto the transport vehicle's cargo bed, the worker prevents the second arm section 21 from swaying up and down by attaching a columnar jig (not shown) across the jig attached to the support frame 26 of the second arm section 21 and the floor of the transport vehicle's cargo bed.

[0066] (Folding configuration of the second arm section 21) - 2 As shown in Figure 3, let's assume that a tangent line L1 is assumed to extend from the front of the rotation plane A1 of the right main rotor 19 to the front of the rotation plane A1 of the left main rotor 19. Let's also assume that a tangent line L2 is assumed to extend from the rear of the rotation plane A1 of the right main rotor 19 to the rear of the rotation plane A1 of the left main rotor 19.

[0067] The axis P3 of the second arm section 21 is located outward from the rotation plane A1 of the main rotor 19 in a plan view, and is located on the side of the first arm section 11 with respect to the tangents L1 and L2. The upward exhaust section 43 (see Figures 8 and 9), which is the rear end of the exhaust pipe 40 of the engine 30 described later, is located on the side of the main body section 1 with respect to the tangent L2 in a plan view.

[0068] As shown in Figures 3 and 4, when the second arm portion 21 is folded (the support frame 26 is oscillated), the electric motors 27 and 28 are positioned above the rotation surface A1 of the main rotor 19 in a side view, and further from the main body portion 1 than the gear mechanism 57 (see Figures 12 and 13), which will be described later, in a plan view, and enter the interior of the rotation surface A1 of the main rotor 19.

[0069] When the second arm section 21 is folded (by the swinging operation of the support frame 26), the support frame 26 of the second arm section 21 and the rotational surface A2 of the sub-rotor 20 come into contact with the tangents L1 and L2 in a plan view. In a plan view, most of the support frame 26 and most of the rotational surface A2 of the sub-rotor 20 overlap with the rotational surface A1 of the main rotor 19.

[0070] As a result, when the second arm section 21 is folded (by the swinging operation of the support frame 26), all parts of the flight device, including the main body section 1, the first arm section 11 and the second arm section 21, the skids 29, the main rotor 19 and the sub-rotor 20, and the exhaust pipe 40, are positioned between tangent lines L1 and L2 in a plan view.

[0071] (Engine 30 configuration) - 1 As shown in Figures 8, 9, and 10, the two sets of engines 30 are of the inline four-cylinder type, and the output shafts 30a are mounted laterally along the left-right direction. A common cylinder head 30c is provided between the two sets of engines 30, and the two sets of engines 30 are connected to each other via the cylinder head 30c and mounted side by side, front to back.

[0072] In the previous engine 30, the output shaft 30a is located on the right side of the engine 30, and the flywheel 30b is located on the left side of the engine 30. In the later engine 30, the output shaft 30a is located on the left side of the engine 30, and the flywheel 30b is located on the right side of the engine 30.

[0073] The front engine 30 is attached to the front frame 9 of the main body 1 (see Figures 5 and 6) via a bracket 31. The rear engine 30 is attached to the rear frame 9 of the main body 1 (see Figures 5 and 6) via a bracket 31. In this way, both the front and rear engines 30 are attached to the main body 1.

[0074] In a plan view, the engine 30 is located inside the regular octagon formed by the upper horizontal frame 2 and upper joint 4 of the main body 1, and inside the regular octagon formed by the lower horizontal frame 3 and lower joint 5 of the main body 1.

[0075] In a side view, the engine 30 is located below the regular octagon formed by the upper horizontal frame 2 and upper joint 4 of the main body 1. In a side view, the engine 30 overlaps with the regular octagon formed by the lower horizontal frame 3 and lower joint 5 of the main body 1, and the lower part of the engine 30 extends downward from the regular octagon formed by the lower horizontal frame 3 and lower joint 5 of the main body 1 in a side view.

[0076] (Engine 30 configuration) - 2 As shown in Figures 8, 9, and 10, the intake manifold 32 is located on the upper part of the cylinder head 30c of the engine 30, and the air cleaner 33 is attached to the right side of the intake manifold 32.

[0077] The battery 34 is mounted on the lower horizontal frame 3 and the front frame 9 at the front of the main body 1, and is located in front of the engine 30. The control device 35 is mounted on the lower horizontal frame 3 at the right rear of the main body 1. A coolant pump 36 is mounted on the bottom of the engine 30. An oil pump 37, which circulates the lubricating oil for the engine 30, is also mounted on the bottom of the engine 30.

[0078] A generator (not shown) driven by the engine 30 is provided in the main body 1, and the power from the generator charges the battery 34. The power from the battery 34 is supplied to the control device 35, which in turn supplies power to the electric motors 27 and 28, causing the electric motors 27 and 28 to operate.

[0079] The intake manifold 32 and air cleaner 33, battery 34 and control device 35, coolant pump 36 and oil pump 37 are located, in a plan view, inside the regular octagon formed by the upper horizontal frame 2 and upper joint 4 of the main body 1, and inside the regular octagon formed by the lower horizontal frame 3 and lower joint 5 of the main body 1.

[0080] The intake manifold 32, air cleaner 33, battery 34, and control device 35 are located in a side view between the regular octagon formed by the upper horizontal frame 2 and upper joint 4 of the main body 1 and the regular octagon formed by the lower horizontal frame 3 and lower joint 5 of the main body 1. In a side view, the cooling water pump 36 and the oil pump 37 are located below the regular octagon formed by the lower horizontal frame 3 and lower joint 5 of the main body 1.

[0081] (Configuration of engine 30, exhaust pipe 40 and muffler 38) - 1 As shown in Figures 8, 9, and 10, the exhaust pipe 40 extends from the engine 30. The exhaust pipe 40 has four first lateral exhaust sections 41, one second lateral exhaust section 42, one upward exhaust section 43, and an exhaust port 44.

[0082] Four first lateral exhaust sections 41 of the exhaust pipe 40 extend rearward from the cylinder head 30c of the engine 30 and merge. One second lateral exhaust section 42 of the exhaust pipe 40 extends rearward from the merging section of the first lateral exhaust sections 41.

[0083] The first lateral exhaust portion 41 and the second lateral exhaust portion 42 of the exhaust pipe 40 are located in a side view between the regular octagon formed by the upper lateral frame 2 and upper joint portion 4 of the main body 1 and the regular octagon formed by the lower lateral frame 3 and lower joint portion 5 of the main body 1 (the vertical width of the main body 1).

[0084] Behind the confluence of the first horizontal exhaust section 41 of the exhaust pipe 40, a rectangular frame (horizontal section) is provided, which is composed of an upper horizontal frame 2 and a lower horizontal frame 3 at the rear of the main body 1, and right and left vertical frames 6. The second horizontal exhaust section 42 of the exhaust pipe 40 protrudes rearward from the aforementioned rectangular frame (horizontal section).

[0085] The upward-facing exhaust portion 43 of the exhaust pipe 40 extends upward from the second lateral exhaust portion 42, and the exhaust port 44 of the exhaust pipe 40 is provided at the upper end of the upward-facing exhaust portion 43. The aforementioned rectangular frame portion (lateral portion) through which the second lateral exhaust portion 42 of the exhaust pipe 40 passes does not have a first arm portion 11 (see Figure 1) or a second arm portion 21 (see Figure 1).

[0086] (Configuration of engine 30, exhaust pipe 40 and muffler 38) - 2 As shown in Figures 8, 9, and 10, in the aforementioned rectangular frame (horizontal section) where the first arm section 11 and the second arm section 21 are not provided, the right and left support members 39 are connected across the upper horizontal frame 2 and the lower horizontal frame 3 at the rear of the main body section 1.

[0087] In a side view, the support member 39 is composed of the upper horizontal frame 2 and lower horizontal frame 3 and the right and left vertical frames 6 at the rear of the main body 1, and is bent so as to protrude rearward (outward) from the rectangular frame (horizontal part).

[0088] The muffler 38 is provided on the second lateral exhaust portion 42 of the exhaust pipe 40, and is located between the right and left support members 39 and attached to the support members 39. The exhaust pipe 40 and the muffler 38 are attached to the main body 1 via the support members 39.

[0089] The second lateral exhaust portion 42 of the exhaust pipe 40 and the front part of the muffler 38 are located between the rear upper lateral frame 2 and the rear lower lateral frame 3 of the main body 1 in a side view, and overlap with the rear upper lateral frame 2 and the rear lower lateral frame 3 of the main body 1 in a plan view.

[0090] The second lateral exhaust portion 42 of the exhaust pipe 40 and the front portion of the muffler 38 are located between the right and left vertical frames 6 at the rear of the main body 1 in a plan view, and overlap with the right and left vertical frames 6 at the rear of the main body 1 in a side view.

[0091] (Fuel tank 50 configuration) - 1 As shown in Figures 9, 10, and 11, the fuel tank 50 is located below the engine 30. The fuel tank 50 has a first part 51, a second part 52, and a third part 53, and is constructed by welding aluminum plates together.

[0092] The first portion 51 of the fuel tank 50 is formed in a long, slender shape that extends forward and backward along the regular octagon formed by the lower transverse frame 3 and lower joint 5 of the main body 1 when viewed from the side. The regular octagon formed by the lower transverse frame 3 and lower joint 5 of the main body 1 is aligned with the rotation surface A1 of the main rotor 19 (see Figure 1) and the rotation surface A2 of the sub-rotor 20 (see Figure 1).

[0093] The second portion 52 of the fuel tank 50 is formed by extending upward from the front of the first portion 51. The third portion 53 of the fuel tank 50 is formed by extending upward from the rear of the first portion 51.

[0094] The mounting member 46 is connected to the right and left frames 9 of the main body 1 (see Figures 5 and 6) and extends downward from the frames 9. The mounting member 46 is connected to the portion between the second portion 52 and the third portion 53 of the first portion 51 of the fuel tank 50, and the fuel tank 50 is connected to the main body 1 via the mounting member 46.

[0095] When the fuel tank 50 is connected to the main body 1, the fuel tank 50 is located between the front connecting member 16 and the rear connecting member 16 in a side view, and is positioned higher than the skid 29.

[0096] As shown in Figure 9, the second portion 52 of the fuel tank 50 is located below the battery 34. The third portion 53 of the fuel tank 50 is located below the first lateral exhaust portion 41 and the second lateral exhaust portion 42 of the exhaust pipe 40. The cooling water pump 36 and oil pump 37 of the engine 30, and the flywheel 30b of the engine 30, are positioned above between the second part 52 and the third part 53 of the fuel tank 50.

[0097] (Fuel tank 50 configuration) - 2 As shown in Figures 9 and 11, a fuel pump 45 is located inside the first portion 51 of the fuel tank 50, at the bottom of the first portion 51, and fuel from the fuel tank 50 is supplied to the engine 30 by the fuel pump 45. A round pipe-shaped support member 47 is connected across the upper and lower parts of the first portion 51 of the fuel tank 50, and the support member 47 is located on the front and rear sides of the fuel pump 45.

[0098] The pipe member 48 is attached across the upper left portion of the second portion 52 of the fuel tank 50 and the upper left portion of the third portion 53 of the fuel tank 50, and the pipe member 48 is located to the left and outward of the engine 30 and battery 34. The air inside the fuel tank 50 circulates through the pipe member 48 across the second portion 52 and the third portion 53 of the fuel tank 50.

[0099] A pipe joint 49 is provided in the middle of the pipe member 48, and a long, slender pipe-shaped breather section 54 is provided on the pipe joint 49 and extends upward. Outside air enters the second section 52 and the third section 53 of the fuel tank 50 via the breather section 54 and the pipe member 48. The air in the second section 52 and the third section 53 of the fuel tank 50 is discharged to the outside via the breather section 54 and the pipe member 48.

[0100] A refueling section 55 for supplying fuel to the fuel tank 50 is provided on the upper left side of the second section 52 of the fuel tank 50 and extends upward from the second section 52 of the fuel tank 50. The refueling section 55 is provided near the pipe member 48 and is located to the left and outward of the battery 34.

[0101] A guide pipe member 56 is installed across the upper part of the lubrication section 55 and the pipe joint section 49. External air enters the lubrication section 55 via the breather section 54, pipe member 48, and guide pipe member 56. The air in the lubrication section 55 is discharged to the outside via the breather section 54, pipe member 48, and guide pipe member 56.

[0102] (Drive structure of main rotor 19) As shown in Figures 12 and 13, right and left gear mechanisms 57, each housing a bevel gear (not shown), are attached to the support plate 14 of the first arm section 11. A drive shaft 57a protrudes downward from the gear mechanism 57, and an input shaft 57b protrudes from the gear mechanism 57 toward the engine 30. The main rotor 19 is attached to the drive shaft 57a. The main rotor 19 is detachable from the drive shaft 57a of the gear mechanism 57.

[0103] The output shaft 30a of the front engine 30 protrudes laterally outward to the right from the engine 30, and the right transmission shaft 60 is connected across the output shaft 30a of the front engine 30 and the input shaft 57b of the right gear mechanism 57.

[0104] The output shaft 30a of the rear engine 30 protrudes laterally outward to the left from the engine 30, and the left transmission shaft 60 is connected across the output shaft 30a of the rear engine 30 and the input shaft 57b of the left gear mechanism 57.

[0105] The power from the engine 30 is transmitted via the transmission shaft 60 to the input shaft 57b of the gear mechanism 57, and the main rotor 19 is rotationally driven by the drive shaft 57a of the gear mechanism 57 around the axis P1 in the vertical direction of the gear mechanism 57.

[0106] As shown in Figure 8, a transmission belt 68 is attached across the output shaft 30a of the front engine 30 and the flywheel 30b of the rear engine 30. The rotational speeds of the front engine 30 and the rear engine 30 are synchronized by the transmission belt 68, causing the right and left main rotors 19 to rotate at the same speed.

[0107] The rotating surface A1 of the main rotor 19 follows a regular octagon formed by the lower transverse frame 3 and lower joint 5 of the main body 1 in a side view. The rotating surface A1 of the main rotor 19 is located below the first arm 11 and the transmission shaft 60 in a side view, and below the bearing 59 and disc coupling 70, which will be described later. The end of the rotating surface A1 of the main rotor 19 on the side of the main body 1 is located near the upper transverse frame 2 and lower transverse frame 3 on the right (left) side of the main body 1 in a plan view.

[0108] (Configuration of the transmission shaft 60) As shown in Figures 12 and 13, the transmission shaft 60 is divided into a first shaft portion 61 and a second shaft portion 62, and the first shaft portion 61 and the second shaft portion 62 are connected by a disc coupling 70. The first shaft portion 61 and the second shaft portion 62 are the same length, but the outer diameter D2 of the second shaft portion 62 is set to a larger value than the outer diameter D1 of the first shaft portion 61.

[0109] A support member 58 is attached to the lower frame 13 of the first arm portion 11, and a bearing 59 is attached to the support member 58. One portion of the first shaft portion 61 of the transmission shaft 60 is connected to the output shaft 30a of the engine 30 via a disc coupling 71.

[0110] One portion of the second shaft portion 62 of the transmission shaft 60 is connected to the first shaft portion 61 of the transmission shaft 60 via a disc coupling 70. The other portion of the second shaft portion 62 of the transmission shaft 60 is connected to the input shaft 57b of the gear mechanism 57 via a disc coupling 72.

[0111] The other portion of the first shaft portion 61 of the transmission shaft 60 is supported by a bearing 59, and the portion of the first shaft portion 61 of the transmission shaft 60 near the disc coupling 70 is supported by the bearing 59.

[0112] The transmission shaft 60 (first shaft portion 61 and second shaft portion 62, disc coupling 70), the bearing 59, and the disc coupling 72 are located in a plan view between the front upper frame 12 and the rear upper frame 12 of the first arm portion 11. The transmission shaft 60 (first shaft portion 61 and second shaft portion 62, disc coupling 70), the bearing 59, and the disc coupling 72 are located between the upper frame 12 and the lower frame 13 of the first arm portion 11 in a side view.

[0113] (Radiator 63 configuration) As shown in Figures 1 and 3, right and left radiators 63 are provided to generate coolant for the engine 30, and the radiators 63 are attached to the first arm portion 11 as described below.

[0114] As shown in Figures 12 and 13, a bracket 64 is mounted upward near the support member 58 in the front lower frame 13 and rear lower frame 13 of the first arm section 11. The radiator 63 is attached to the bracket 64 and, via the bracket 64, is attached to the first arm section 11 (front lower frame 13 and rear lower frame 13). A hose 65 connects the radiator 63 to the coolant pump 36 (see Figure 9). A hose 66 connects the radiator 63 to the engine 30.

[0115] The radiator 63 is positioned laterally along the rotation plane A1 of the main rotor 19, above the transmission shaft 60 (first shaft portion 61 and second shaft portion 62, disc coupling 70) and bearing 59. In a plan view, the radiator 63 is located inside the rotation plane A1 of the main rotor 19 and overlaps with the rotation plane A1 of the main rotor 19.

[0116] In a side view, the radiator 63 is located between the upper frame 12 and the lower frame 13 of the first arm portion 11, and in a plan view, it spans the front upper frame 12 (lower frame 13) and the rear upper frame 12 (lower frame 13) of the first arm portion 11.

[0117] The transmission shaft 60 (first shaft portion 61 and second shaft portion 62, disc coupling 70) and bearing 59 are located in a position between the radiator 63 and the lower frame 13 of the first arm portion 11, as seen from the side. The radiator 63 is positioned between the upper frame 12 and the lower frame 13 of the first arm portion 11 in a side view. As a result, in a side view from the left-right direction, which is along the longitudinal direction of the first arm portion 11, the radiator 63 overlaps with the engine 30 and is positioned higher than the fuel tank 50.

[0118] (First alternative embodiment of the invention) The radiator 63 may be mounted on the upper frame 12 of the first arm portion 11, and in a side view, it may be positioned between the upper frame 12 of the first arm portion 11 and the transmission shaft 60.

[0119] (Second alternative embodiment of the invention) The radiator 63 may be mounted on the upper frame 12 of the first arm portion 11 such that, in a side view, it is positioned above the upper frame 12 of the first arm portion 11.

[0120] (Third alternative embodiment of the invention) The drive shaft 57a of the gear mechanism 57 may be positioned upward, and the main rotor 19 (rotation surface A1) attached to the drive shaft 57a of the gear mechanism 57 may be positioned above the first arm portion 11.

[0121] (Correspondence with claims) - 1 The first arm section 11 corresponds to the arm section. The main rotor 19 corresponds to the rotor. The upper frame 12 corresponds to the upper part of the arm section. The lower frame 13 corresponds to the lower part of the arm section.

[0122] The front upper frame 12 and front lower frame 13 correspond to one portion of the arm in a direction perpendicular to the longitudinal direction of the arm. The rear upper frame 12 and rear lower frame 13 correspond to the other portion of the arm in a direction perpendicular to the longitudinal direction of the arm.

[0123] (Correspondence with claims) - 2 The system comprises a main body 1, an engine 30 provided on the main body 1, an arm portion (first arm portion 11) extending outward from the main body 1, and a rotor (main rotor 19) attached to the arm portion (first arm portion 11). A transmission shaft 60 is provided along the arm portion (first arm portion 11) extending from the main body portion 1 to the rotor (main rotor 19), and transmits power from the engine 30 to the rotor (main rotor 19). A radiator 63 is provided to generate coolant for the engine 30. The radiator 63 is mounted on the arm portion (first arm portion 11) so as to be located above the transmission shaft 60 and along the rotational plane A1 of the rotor (main rotor 19).

[0124] (Correspondence with claims) - 3 The radiator 63 is located in a position between the upper part (upper frame 12) and the lower part (lower frame 13) of the arm portion (first arm portion 11) when viewed from the side. The transmission shaft 60 is located in a side view between the radiator 63 and the lower part (lower frame 13) of the arm section (first arm section 11).

[0125] In a plan view, the radiator 63 is provided across one portion (upper frame 12, lower frame 13) and the other portion (upper frame 12, lower frame 13) of the arm portion (first arm portion 11) in a direction perpendicular to the longitudinal direction of the arm portion (first arm portion 11).

[0126] The radiator 63 is positioned between the upper portion (upper frame 12) and the lower portion (lower frame 13) of the arm portion (first arm portion 11) in a side view, and is provided across one portion (upper frame 12, lower frame 13) and the other portion (upper frame 12, lower frame 13) of the arm portion (first arm portion 11) in a direction perpendicular to the longitudinal direction of the arm portion (first arm portion 11).

[0127] (Correspondence with claims) - 4 The radiator 63, the arm section (first arm section 11), and the transmission shaft 60 are located above the rotational surface A1. In a plan view, the radiator 63 and the rotational surface A1 overlap.

[0128] In a side view, taken from a direction along the longitudinal direction of the arm portion (first arm portion 11), the radiator 63 overlaps with the engine 30. A fuel tank 50 is located below the engine 30. The radiator 63 is located above the fuel tank 50 in a side view. [Industrial applicability]

[0129] This invention can be applied to flying devices. [Explanation of symbols]

[0130] 1. Main body 11. First arm section (arm section) 12 Upper frame (upper part) (one part) (other part) 13 Lower frame (lower part) (one part) (other part) 19 rotors 30 Engine 50 Fuel Tank 60 transmission shaft 63 Radiator A1 Rotation plane

Claims

1. The main body and The engine provided in the main body, An arm portion extending outward from the main body portion, A rotor attached to the aforementioned arm portion, A transmission shaft is provided along the arm portion, extending from the main body portion to the rotor, and transmits the power of the engine to the rotor. The system is equipped with a radiator that generates coolant for the engine, An aircraft in which the radiator is mounted on the arm portion such that it is located above the transmission shaft and is aligned with the rotational plane of the rotor.

2. The flight device according to claim 1, wherein the radiator is located between the upper and lower portions of the arm in a side view.

3. The flight device according to claim 2, wherein the transmission shaft is located in a position between the radiator and the lower portion of the arm in a side view.

4. The flight device according to claim 1, wherein the radiator is provided across one portion and the other portion of the arm in a direction perpendicular to the longitudinal direction of the arm in a plan view.

5. The flight device according to claim 1, wherein the radiator is provided in a position between the upper and lower portions of the arm in a side view, and extends across one portion and the other portion of the arm in a direction perpendicular to the longitudinal direction of the arm in a plan view.

6. The radiator, the arm portion, and the transmission shaft are located above the rotation surface. The flying device according to claim 1, wherein the radiator and the rotating surface overlap in a plan view.

7. The flight device according to claim 1, wherein the radiator overlaps with the engine in a side view taken from a direction along the longitudinal direction of the arm portion.

8. A fuel tank is provided below the engine, The aircraft according to claim 7, wherein the radiator is located above the fuel tank in a side view.

Images