Work vehicle

Abstract

To enable fuel supply to a fuel tank to be performed with no hindrance in a work vehicle in which a loading space is provided on an upper part of a machine body.SOLUTION: A work vehicle includes: a loading space 2 provided in an upper part of a machine body 1 and in which a cargo can be placed; a fuel tank 37 provided in a lower part of an outer peripheral part 21 of the loading space 2; and an engine 23 that is provided in further downward than the fuel tank 37 and generates power for driving a travel device by fuel supplied from the fuel tank 37.SELECTED DRAWING: Figure 4

Description

[Technical Field]

[0001] The present invention relates to a work vehicle having a loading platform mounted on the upper part of the vehicle body. [Background technology]

[0002] The work vehicle disclosed in Patent Document 1 has an engine mounted on a body supported by a traveling device, and the engine drives a hydraulic pump, which in turn operates a hydraulic motor using hydraulic oil from the hydraulic pump to drive the traveling device. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Application Laid-Open No. 2018-103681 Summary of the Invention [Problem to be solved by the invention]

[0004] The work vehicle in Patent Document 1 is proposed to be used as a work vehicle for transporting cargo by providing a relatively large loading platform on top of the vehicle body. When providing a loading platform on top of the vehicle body, it is necessary to configure it so that fuel can be replenished to the fuel tank without any problems.

[0005] SUMMARY OF THE INVENTION An object of the present invention is to provide a structure for a work vehicle having a loading platform on top of the vehicle body, which allows for uninterrupted refueling of the fuel tank. [Means for solving the problem]

[0006] The work vehicle of the present invention comprises a body supported by a traveling device, a loading platform provided on the top of the body and capable of carrying cargo, a fuel tank provided below the outer periphery of the loading platform, and an engine provided below the fuel tank and using fuel supplied from the fuel tank to generate power for driving the traveling device. the fuel tank is provided below one end of the loading platform in a direction along the traveling direction of the vehicle, the engine is provided below a position on the loading platform that is closer to the one end than the center of the traveling direction of the vehicle, and a hydraulic oil tank is provided on the vehicle at the other end of the traveling direction of the vehicle. There are.

[0007] According to the present invention, when a loading platform is provided on top of the machine body supported by the traveling gear, the fuel tank is provided below the outer periphery of the loading platform, rather than below the center of the loading platform. This allows the fuel tank to be refueled without being affected by the loading platform, even if the loading platform is large, thereby improving the workability of refueling. Since the engine is located below the fuel tank, fuel is smoothly supplied from the fuel tank to the engine, and there are fewer cases where the fuel supply from the fuel tank to the engine is cut off.

[0008]

[0009] When a work vehicle with a loading platform on top of the vehicle moves forward (or backward) on a slope or on very uneven ground, there is a risk that the vehicle may roll over sideways. According to the present invention, a fuel tank is provided on the outer periphery of the loading platform below one end in the direction of travel of the vehicle, and an engine is provided on the vehicle below a position on the loading platform closer to the one end than the center of the vehicle in the direction of travel. This reduces the possibility that the fuel tank or engine will collide with the ground if the aircraft rolls over, preventing damage to the fuel tank or engine due to the aircraft rolling over.

[0010] If the forward end of the vehicle is defined as the front end of the vehicle and the front end of the loading platform, and the reverse end of the vehicle is defined as the rear end of the vehicle and the rear end of the loading platform, the fuel tank is provided below the front of the loading platform and the engine is provided at the front of the vehicle, or the fuel tank is provided below the rear of the loading platform and the engine is provided at the rear of the vehicle.

[0011] According to the present invention, the fuel tank and the engine are positioned relatively close to each other, so that the fuel supply pipe from the fuel tank to the engine can be relatively short. This allows for a simple fuel supply system from the fuel tank to the engine, and simplifies the structure. For example, even if the work vehicle is traveling on a slope or on very uneven ground and tilts significantly, the fuel supply from the fuel tank to the engine is less likely to be cut off.

[0012]

[0013] According to the present invention, the hydraulic oil tank is provided at the other end of the aircraft in the direction along the aircraft's traveling direction, and the engine and the hydraulic oil tank are provided on one side and the other side along the aircraft's traveling direction. This improves the weight balance in the direction of travel of the vehicle, thereby improving the running performance of the work vehicle.

[0014] In the present invention, it is preferable that a muffler into which the engine exhaust is sent is provided in a section between the engine and the hydraulic oil tank, and that an exhaust section that discharges the engine exhaust downward from the muffler is provided in the muffler.

[0015] According to the present invention, when the engine and hydraulic oil tank are installed on one side and the other side in the direction along the vehicle's travel direction, the muffler can be positioned by effectively utilizing the space between the engine and the hydraulic oil tank, which is advantageous in terms of making the work vehicle more compact. According to the present invention, the exhaust portion of the muffler allows the engine exhaust to be discharged downward from the muffler, thereby suppressing the scattering of the engine exhaust.

[0016] In the present invention, it is preferable that the battery be provided at the other end of the aircraft in the direction along the aircraft's traveling direction, and at a position farther from the center of the aircraft than the hydraulic oil tank.

[0017] When comparing the engine and the hydraulic oil tank, the engine is often heavier than the hydraulic oil tank, so there is room for improvement in terms of improving the weight balance in the direction of travel of the aircraft. According to the present invention, the battery is provided at the other end of the aircraft in the direction along the aircraft's traveling direction (the end where the hydraulic oil tank is provided), so that the engine is provided at one end of the aircraft in the direction along the aircraft's traveling direction, and the hydraulic oil tank and battery are provided at the other end of the aircraft in the direction along the aircraft's traveling direction. This further improves the weight balance in the direction of travel of the vehicle, which is advantageous in terms of improving the running performance of the work vehicle.

[0018] According to the present invention, when the battery is provided at the other end in the direction along the aircraft's traveling direction (the end where the hydraulic oil tank is provided), the battery is provided at a position farther from the center of the aircraft than the hydraulic oil tank. This allows the battery to be replaced with less influence from the hydraulic oil tank, improving the workability of battery replacement.

[0019] In the present invention, it is preferable that an oil cooler that cools the hydraulic oil in the hydraulic oil tank is provided at one end of the aircraft in the direction along the aircraft's traveling direction, and at a position farther from the center of the aircraft than the engine.

[0020] According to the present invention, an oil cooler is provided at one end (the end on the engine side) of the aircraft in the direction of travel of the aircraft, and is provided at a position farther from the center of the aircraft than the engine. This allows the oil cooler to be more easily exposed to outside air without being affected by the engine, thereby improving the cooling performance of the oil cooler.

[0021] In the present invention, it is preferable that a cooling fan for introducing cooling air into the engine is provided at a portion of the engine facing the oil cooler.

[0022] According to the present invention, in an air-cooled engine having a cooling fan, the cooling fan faces the oil cooler. This makes it easier for outside air to be introduced into the engine as cooling air by the cooling fan through the oil cooler, which is advantageous in terms of improving the cooling performance of the oil cooler.

[0023] The work vehicle of the present invention comprises a body supported by traveling devices, a loading platform provided on the top of the body and capable of carrying cargo, a fuel tank provided below the outer periphery of the loading platform, and an engine provided below the fuel tank and using fuel supplied from the fuel tank to generate power for driving the traveling devices, the fuel tank being provided below one end of the loading platform in a direction along the traveling direction of the body, and the engine being provided below a position on the loading platform closer to the one end than the center of the traveling direction of the body, An operating member support frame is provided that protrudes outward from the other end of the loading platform in the direction along the traveling direction of the vehicle, and an operating member is supported by the operating member support frame. do.

[0024] According to the present invention, the operating member is provided on the opposite side of the loading platform from the fuel tank and engine, so that the worker can operate the operating member without being affected by the fuel tank and engine, thereby improving the operability of the operating member.

[0025] The work vehicle of the present invention comprises a body supported by a traveling device, a loading platform provided on the upper part of the body and capable of carrying cargo, a fuel tank provided below the outer periphery of the loading platform, and an engine provided below the fuel tank and using fuel supplied from the fuel tank to generate power for driving the traveling device, The fuel tank is provided with a fuel filler port that is positioned on the outer side of the aircraft body relative to the outer periphery of the loading platform. do.

[0026] According to the present invention, for example, when refueling a fuel tank from a fuel transport tank, the fuel tank's filler port is located further outward from the aircraft than the outer periphery of the loading platform, which reduces the likelihood of the transport tank interfering with the loading platform, which is advantageous in terms of improving the workability of refueling.

[0027] In the present invention, it is preferable that a cover be provided that can be operated between a closed position that covers the fuel filler opening and an open position that opens the fuel filler opening.

[0028] According to the present invention, by operating the cover to the closed position, it is possible to prevent foreign matter from adhering to the filler opening of the fuel tank. When refueling the fuel tank, by operating the cover to the open position, fuel can be smoothly refueled through the filler opening of the fuel tank. [Brief explanation of the drawings]

[0029] [Figure 1] FIG. [Figure 2] FIG. [Figure 3] FIG. [Figure 4] FIG. [Figure 5] FIG. [Figure 6] FIG. [Figure 7] FIG. DETAILED DESCRIPTION OF THE INVENTION

[0030] Figures 1 to 7 show remotely controlled and autonomously traveling work vehicles, and in Figures 1 to 7, F indicates the forward direction, B indicates the backward direction, U indicates the upward direction, D indicates the downward direction, R indicates the right direction, and L indicates the left direction.

[0031] (Overall configuration of the work vehicle) As shown in Figures 1 and 2, a machine body 1 is provided, and a loading platform 2 is provided on top of the machine body 1. Wheels 3 for running (corresponding to running devices) are provided on the right front, left front, right rear, and left rear of the machine body 1, and the machine body 1 is supported by the four wheels 3.

[0032] (Wheel support structure) As shown in Figure 1, at the right front, left front, right rear, and left rear of the aircraft body 1, a first support arm 4 is supported so as to be swingable back and forth around an axis P1 along the left-right direction, and a second support arm 5 is supported below the first support arm 4 so as to be swingable up and down around an axis P2 along the left-right direction.

[0033] A steering member 6 is supported on the end of the first support arm 4 so as to be swingable left and right about an axis P3 extending in the up-down direction, and the wheel 3 is supported on the steering member 6. A freely rotatable auxiliary wheel 7 is supported on the second support arm 5 at the position of axis P2.

[0034] A double-acting hydraulic cylinder 8 is connected between the machine body 1 and the lower part of the first support arm 4, and when the hydraulic cylinder 8 is operated to extend or retract, the first support arm 4 is operated to swing back and forth relative to the machine body 1.

[0035] A double-acting hydraulic cylinder 9 is connected between the upper part of the first support arm 4 and the second support arm 5, and when the hydraulic cylinder 9 is extended or retracted, the second support arm 5 is swung up and down relative to the first support arm 4.

[0036] A double-acting hydraulic cylinder (not shown) is connected between the second support arm 5 and the steering member 6, and by extending and contracting the hydraulic cylinder, the steering member 6 is steered left and right relative to the second support arm 5. A hydraulic motor (not shown) is provided on the steering member 6, and the wheels 3 are driven to rotate in the forward and reverse directions by the hydraulic motor.

[0037] As the wheels 3 are driven to rotate in the forward and reverse directions, the machine body 1 travels forward and backward (moves forward and backward), and the forward direction (forward) and backward direction (backward) are directions that follow the direction in which the machine body 1 is traveling. By steering the steering member 6 (wheels 3), the vehicle 1 can make right and left turns, move diagonally forward (diagonally backward) in parallel, make pivot turns, and perform super-pivot turns. The four sets of first support arms 4 and second support arms 5 are each independently operated to swing back and forth and up and down, thereby keeping the machine body 1 horizontal even on slopes or rough ground.

[0038] (Aircraft configuration) As shown in Figures 3 to 6, right and left frames 10 are arranged along the front-to-rear direction, and frame 11 along the left-to-right direction is connected across the right and left frames 10. Frame 12 is connected to the front and rear parts of the underside of frame 10 and extends downward from frame 10. Right and left frames 13 are connected across the lower parts of the front and rear frames 12 and are arranged below frame 10 along the front-to-rear direction.

[0039] The front and rear frames 14, which are U-shaped when viewed from the front, are connected across the front portions of the right and left frames 13 and across the rear portions of the right and left frames 13. A frame 15 extending in the left-right direction is connected across the right and left portions of the lower parts of the frames 14, and the right and left frames 16 extending in the front-to-rear direction are connected across the front and rear frames 15. As shown in FIG. 1 , right and left side panels 17 are connected across the front and rear frames 14. The vehicle body 1 is composed of the frames 10 to 16, the side panels 17, etc.

[0040] An attachment portion 18, which is shaped like an inverted channel when viewed from the front, is connected to the front and rear of the right frames 10, 13 and is also connected to the front and rear of the left frames 10, 13. The first support arm 4 described above is supported by the attachment portion 18 so as to be swingable back and forth around an axis P1.

[0041] (Loading platform configuration) As shown in Figures 3 to 6, right and left frames 19 are connected to the front-to-rear middle portion of frame 10, and right and left frames 20 extending in the front-to-rear direction are connected between front and rear mounting portions 18 and frames 19.

[0042] A frame 21 (corresponding to the outer periphery) configured in a square shape in a plan view is provided, and the frame 21 is connected across the right and left frames 20. A square flat plate 22 having approximately the same size as the frame 21 in a plan view is connected to the frame 21. The loading platform 2 is configured with the frame 21 and the flat plate 22, and luggage can be placed on the loading platform 2.

[0043] 1 and 2, right and left covers 39 are provided on the right and left sides of the outer periphery of the loading platform 2. Right and left covers 40 are provided on the right and left sides of the front part of the outer periphery of the loading platform 2, and right and left covers 41 are provided on the right and left sides of the rear part of the outer periphery of the loading platform 2.

[0044] 1 and 2, the above-described configuration provides a vehicle body 1 supported by wheels 3 (traveling devices). A loading platform 2 is provided on top of the vehicle body 1 and is capable of carrying luggage.

[0045] (Configuration of engines installed on the aircraft) 3, 4, and 5, the engine 23 is supported on the front of the frame 16 (the front of the vehicle body 1) and is provided between the right and left side plates 17 (see FIG. 1). The engine 23 generates power to drive the wheels 3, as will be described later.

[0046] The engine 23 is an air-cooled type provided with a cooling fan 23a, which is provided at the front of the engine 23. An output shaft 23b protrudes rearward from the engine 23, and a fan 26 is attached to the output shaft 23b of the engine 23.

[0047] When the cooling fan 23a of the engine 23 is driven to rotate, outside air in front of the engine 23 is introduced as cooling air into the engine 23, thereby cooling the engine 23. When the fan 26 is driven to rotate by the output shaft 23b of the engine 23, high-temperature air near the engine 23 passes between the right and left side panels 17 and is discharged toward the rear of the aircraft body 1.

[0048] (Configuration of fuel tanks installed on the aircraft) 3 to 6, right and left mounting brackets 36 are provided on the front end of the frame 13, and a fuel tank 37 is attached to the mounting brackets 36. A fuel supply pipe 38 is connected between the fuel tank 37 and a carburetor (not shown) of the engine 23.

[0049] The fuel tank 37 is located above the engine 23, below the left and right center of the front end of the cargo bed 2, between the covers 40, and below the front part of the outer periphery of the cargo bed 2.

[0050] 3 to 7, right and left U-shaped frames 45 are connected across the front ends of frames 10, 13. Frame 45 is provided between fuel tank 37 and right cover 40, and between fuel tank 37 and left cover 40, and protrudes forward of fuel tank 37 in side view.

[0051] 1, 2, and 7, the right and left covers 42 are connected to the frame 45, and the cover 43 is connected across the lower parts of the right and left frames 45. The cover 44 is supported by the right and left frames 45 so as to be swingable about an axis P4 extending in the left-right direction.

[0052] The state shown in Figures 1 and 2 is when the cover 44 is operated to the closed position, and the front, right and left sides, top and bottom of the fuel tank 37 are covered and protected by the covers 42, 43, 44 and the frame 45.

[0053] As shown in FIG. 7, when cover 44 is opened forward, the top of fuel tank 37 is opened and fuel filler port 37a provided at the front of the top of fuel tank 37 is also opened, allowing the operator to fill fuel through fuel filler port 37a of fuel tank 37.

[0054] With the above configuration, as shown in FIGS. 3 to 7, the fuel tank 37 is provided below the frame 21 (outer periphery) of the bed 2. The engine 23 is provided below the fuel tank 37 and generates power for driving the wheels 3 (traveling device) using fuel supplied from the fuel tank 37.

[0055] A fuel tank 37 is provided below one end of the loading platform 2 in the direction along the traveling direction of the machine body 1. An engine 23 is provided below a position on one end side of the center of the platform 2 in the traveling direction of the machine body 1.

[0056] The fuel tank 37 is provided with a fuel filler opening 37a that is arranged on the outer side of the body 1 relative to the frame 21 (outer periphery) of the loading platform 2. A cover 44 is provided which can be operated between a closed position where it covers the filler opening 37a of the fuel tank 37 and an open position where it opens the filler opening 37a of the fuel tank 37.

[0057] (The hydraulic pump, hydraulic oil tank, muffler, and battery mounted on the aircraft) 3, 4, and 5, the hydraulic pump 24 is provided on the right side of the engine 23 and is supported on the front part of the frame 16 (the front part of the aircraft body 1). A transmission belt 25 is attached between the output shaft 23b of the engine 23 and the hydraulic pump 24, and the hydraulic pump 24 is driven by the engine 23.

[0058] The hydraulic oil tank 27 is supported at the rear of the frame 16 (at the rear of the aircraft body 1). A muffler 46 is provided between the engine 23 and the hydraulic oil tank 27 along the left-right direction and is supported by the frame 16. A battery 48 is supported at the rear end of the frame 16 and is provided rearward of the hydraulic oil tank 27 and the rear frame 14.

[0059] An exhaust pipe 47 extends from the engine 23, passing between the engine 23 and the transmission belt 25, and is connected to the left part of the muffler 46. An exhaust section 46a of the muffler 46 extends downward from the lower part of the right part of the muffler 46. Exhaust from the engine 23 is sent to the muffler 46 via the exhaust pipe 47 and is discharged downward from the exhaust section 46a of the muffler 46.

[0060] The engine 23 , hydraulic pump 24 , transmission belt 25 , fan 26 , muffler 46 and hydraulic oil tank 27 are provided between the right and left side plates 17 , and the battery 48 is provided behind the hydraulic oil tank 27 .

[0061] As described above, when the fan 26 is driven to rotate, the hot air near the engine 23 passes between the right and left side panels 17 and is discharged toward the rear of the aircraft 1. In addition, the hot air near the hydraulic pump 24, muffler 46, hydraulic oil tank 27, and battery 48 is also discharged toward the rear of the aircraft 1.

[0062] With the above configuration, as shown in FIGS. 3, 4 and 5, the hydraulic oil tank 27 is provided at the other end of the aircraft 1 in the direction along the traveling direction of the aircraft 1 (opposite the engine 23 and fuel tank 37). A muffler 46 to which the exhaust gas from the engine 23 is sent is provided in the area between the engine 23 and the hydraulic oil tank 27, and an exhaust section 46a is provided in the muffler 46 to discharge the exhaust gas from the engine 23 downward from the muffler 46. The battery 48 is provided at the other end of the aircraft 1 in the direction along the aircraft 1's travel direction (opposite the engine 23 and fuel tank 37), and at a position farther from the center of the aircraft 1 than the hydraulic oil tank 27.

[0063] (Configuration of hydraulic oil supply system from hydraulic pump to hydraulic cylinder and hydraulic motor) 3 to 6, a hydraulic oil pipe 28 extends forward from the left lateral side of the hydraulic oil tank 27, passes on the left side and front side of the engine 23, and is connected to the hydraulic pump 24. A hydraulic oil distribution unit 29 is supported by the frame 11 and provided above the engine 23, and a hydraulic oil pipe 31 extends upward from the hydraulic pump 24 and is connected to the hydraulic oil distribution unit 29.

[0064] Two control valve units 30 are supported on the right frame 13, and two control valve units 30 are supported on the left frame 13, and a hydraulic oil pipe 32 is connected between the hydraulic oil distribution section 29 and the control valve units 30.

[0065] The oil cooler 33 is supported on the front end of the frame 16 (the front end of the fuselage 1) and is provided in front of the engine 23 (cooling fan 23a). As described above, when the cooling fan 23a of the engine 23 is driven to rotate and outside air in front of the engine 23 is introduced into the engine 23 as cooling air, the outside air is likely to be introduced into the engine 23 through the oil cooler 33.

[0066] A hydraulic oil pipe 34 is connected between the hydraulic oil distribution section 29 and the oil cooler 33. A hydraulic oil pipe 35 runs along the right side of the engine 23 and connects between the hydraulic oil tank 27 and the oil cooler 33.

[0067] When the hydraulic pump 24 is driven by the engine 23, hydraulic oil in a hydraulic oil tank 27 is sucked into the hydraulic pump 24 via a hydraulic oil pipe 28, and the hydraulic oil in the hydraulic pump 24 is supplied to a hydraulic oil distribution section 29 via a hydraulic oil pipe 31. The hydraulic oil supplied to the hydraulic oil distribution section 29 is supplied to a control valve unit 30 via a hydraulic oil pipe 32, and is supplied from the control valve unit 30 to the hydraulic cylinders 8 and 9 and the hydraulic motor shown in FIG.

[0068] A support frame 50 (corresponding to an operating member support frame) is provided at the rear of the rear frame 11 and the frame 21, and protrudes rearward from the rear frame 11 and the frame 21. An operating lever 49 (corresponding to an operating member) is supported by the support frame 50, and the control valve unit 30 is operated by operating the operating lever 49.

[0069] The hydraulic cylinders 8, 9 and hydraulic motor are operated by hydraulic oil from the control valve unit 30, causing the first support arm 4 to swing back and forth relative to the machine body 1, the second support arm 5 to swing up and down relative to the first support arm 4, the steering member 6 to steer left and right relative to the second support arm 5, and the wheels 3 to rotate in the forward and reverse directions.

[0070] The hydraulic oil returning from the hydraulic cylinders 8, 9 and the hydraulic motor, as well as excess hydraulic oil, is supplied from the hydraulic oil distribution section 29 to the oil cooler 33 via a hydraulic oil pipe 34, and the hydraulic oil cooled in the oil cooler 33 returns to the hydraulic oil tank 27 via a hydraulic oil pipe 35.

[0071] With the above configuration, as shown in Figures 4, 5, and 6, the oil cooler 33 that cools the hydraulic oil in the hydraulic oil tank 27 is provided at one end of the aircraft 1 in the direction along the aircraft 1's traveling direction, and at a position farther from the center of the aircraft 1 than the engine 23. A cooling fan 23 a that introduces cooling air into the engine 23 is provided at a portion of the engine 23 facing the oil cooler 33 . A support frame 50 (operating member support frame) is provided that protrudes outward from the other end of the loading platform 2 in the direction along the traveling direction of the machine body 1. An operating lever 49 (operating member) is provided that is supported by the support frame 50 (operating member support frame).

[0072] (First Alternative Embodiment of the Invention) The fuel tank 37 may be provided below the left-right center of the rear end of the cargo bed 2, between the covers 41, and below the rear of the frame 21 (periphery) of the cargo bed 2. In this configuration, the engine 23, hydraulic pump 24, and oil cooler 33 are preferably provided at the rear of the aircraft 1, with the oil cooler 33 being provided rearward of the engine 23. The hydraulic oil tank 27 and battery 48 are preferably provided at the front of the aircraft 1, with the battery 48 being provided forward of the hydraulic oil tank 27. The support frame 50 is preferably provided at the front of the loading platform 2 and protrudes forward from the loading platform 2, and the operating lever 49 is preferably supported by the support frame 50.

[0073] (Second Alternative Embodiment of the Invention) The mounting bracket 36 may be connected to the frame 21, and the fuel tank 37 may be attached to the mounting bracket 36. According to this configuration, the fuel tank 37 is supported by the frame 21 (bed 2).

[0074] (Third Alternative Embodiment of the Invention) The fuel tank 37 may be provided below the front right or front left part of the frame 21 (outer periphery) of the cargo bed 2, or below the rear right or rear left part of the frame 21 (outer periphery) of the cargo bed 2.

[0075] (Fourth Alternative Embodiment of the Invention) The fuel tank 37 may be provided below the right front part of the frame 21 (periphery) of the cargo bed 2, the right rear part, or the right front-rear center part. The fuel tank 37 may be provided below the left front part, the left rear part, or the left central part between the front and rear of the frame 21 (periphery) of the cargo bed 2.

[0076] (Fifth Alternative Embodiment of the Invention) In the configurations shown in FIGS. 1 to 7, (first modified embodiment of the invention) to (fourth modified embodiment of the invention), the fuel tank 37 may be provided at a position slightly lower than the loading platform 2.

[0077] (Sixth Alternative Embodiment of the Invention) When the engine 23 is provided at the front of the airframe 1, the engine 23 may be provided slightly rearward of the front end of the airframe 1 (closer to the center in the traveling direction of the airframe 1). When the engine 23 is provided at the rear of the airframe 1, the engine 23 may be provided slightly forward of the rear end of the airframe 1 (closer to the center in the traveling direction of the airframe 1). With the above-described configuration, the engine 23 is provided below a position on one end side of the center of the platform 2 in the traveling direction of the machine body 1.

[0078] (Seventh Alternative Embodiment of the Invention) Instead of driving the wheels 3 using hydraulic oil from the hydraulic pump 24 driven by the engine 23, the power of the engine 23 may be transmitted directly to the wheels 3 via a transmission shaft (not shown) or a transmission chain (not shown). Instead of the wheels 3, a crawler type traveling device (not shown) may be provided. [Industrial Applicability]

[0079] The present invention can be applied to work vehicles that are suitable for traveling on uneven or sloping work ground, and can also be applied to work vehicles that can accommodate a worker. [Explanation of symbols]

[0080] 1 aircraft 2 Cargo bed 3 Wheels (running gear) 21 Frame (periphery) 23 Engine 23a Cooling fan 27 Hydraulic oil tank 33 Oil cooler 37 Fuel Tank 37a Fuel filler 44 Cover 46 Muffler 46a Exhaust section 48 Battery 49 Operating lever (operating member) 50 Support frame (operating member support frame)

Claims

1. a machine body supported by a running gear; a loading platform provided on the upper part of the aircraft body and capable of carrying luggage; a fuel tank provided below the outer periphery of the loading platform; an engine that is provided below the fuel tank and generates power for driving the traveling device using fuel supplied from the fuel tank, the fuel tank is provided below one end of the loading platform in a direction along the traveling direction of the aircraft body, the engine is provided below a position on the platform closer to the one end than the center of the vehicle's traveling direction, A work vehicle in which a hydraulic oil tank is provided at the other end of the vehicle body in a direction along the vehicle body's traveling direction.

2. a muffler into which exhaust gas from the engine is delivered is provided between the engine and the hydraulic oil tank; 2. The work vehicle according to claim 1, wherein the muffler is provided with an exhaust section that discharges exhaust gas from the engine downward from the muffler.

3. 3. A work vehicle as described in claim 1 or 2, wherein the battery is provided at the other end of the vehicle body in the direction of travel of the vehicle body and at a position farther from the center of the vehicle body than the hydraulic oil tank.

4. 2. The work vehicle according to claim 1, wherein an oil cooler that cools the hydraulic oil in the hydraulic oil tank is provided at one end of the vehicle body in the direction of travel of the vehicle body and at a position farther from the center of the vehicle body than the engine.

5. 5. A work vehicle according to claim 4, wherein a cooling fan for introducing cooling air into the engine is provided at a portion of the engine facing the oil cooler.

6. A machine body supported by a running device; a loading platform provided on the upper part of the aircraft body and capable of carrying luggage; a fuel tank provided below the outer periphery of the loading platform; an engine that is provided below the fuel tank and generates power for driving the traveling device using fuel supplied from the fuel tank, the fuel tank is provided below one end of the loading platform in a direction along the traveling direction of the aircraft body, the engine is provided below a position on the platform closer to the one end than the center of the vehicle's traveling direction, an operating member support frame protruding outward from the other end of the loading platform in the direction along the traveling direction of the vehicle; A work vehicle provided with an operating member supported by the operating member support frame.

7. A machine body supported by a running device; a loading platform provided on the upper part of the aircraft body and capable of carrying luggage; a fuel tank provided below the outer periphery of the loading platform; an engine that is provided below the fuel tank and generates power for driving the traveling device using fuel supplied from the fuel tank, A work vehicle in which the fuel tank is provided with a fuel filler port that is positioned further outward from the outer periphery of the loading platform than the vehicle body.

8. 8. The work vehicle according to claim 7, further comprising a cover operable to a closed position that covers the fuel filler opening and an open position that opens the fuel filler opening.

Images