JPS625374Y2 - - Google Patents

Description

[Detailed description of the invention] This invention arranges the engine and the driving section in parallel in the lateral direction of the vehicle body, arranges the engine with the crankshaft protruding outward from the lateral side of the vehicle body, and moves the cargo platform using a fluid pressure actuator. The present invention relates to a transport vehicle that is configured to be able to swing up and down, has an engine and a transmission transmission interlocked, and is configured to drive front wheels and rear wheels from the transmission transmission via a transmission shaft.

A transverse engine type transport vehicle, in which the engine and driving section are installed side by side, with the longitudinal direction of the engine facing the width direction of the aircraft, has the engine installed with the longitudinal direction facing the longitudinal direction of the aircraft. Compared to the vertical engine type, the loading platform can be moved much closer to the front of the fuselage where the engine and operating section are located, which has the advantage of shortening the longitudinal length of the fuselage.

In the case of such a transport vehicle, when the loading platform is made to be able to swing up and down to enable dumping and dumping of cargo, fluid pressure is used as the driving source for the up and down swing, but it is relatively difficult to drive the operating pump. Since a high rotational force is required, this pump is generally installed at the end of the crankshaft of the engine, or at the end of an intermediate shaft one step below the crankshaft and parallel to the crankshaft.

However, in such conventional means, the engine is placed next to the operating section, so the width of the machine body must be set longer to accommodate the space for installing the pump, which is a problem, especially for small-sized machines. Another disadvantage is that the side of the aircraft where the engine is installed becomes heavy and lacks stability. Furthermore, the piping system from the pump to the actuator requires a large detour around the engine, taking into account the effects of heat and vibration, which requires a large amount of installation space and requires special installation. It also requires additional structure, making it even larger, and has the drawback of being difficult to assemble.

The present invention was devised in view of the above-mentioned drawbacks of the conventional structure, and the object is to provide a transport vehicle that has a narrow vehicle width, can be downsized, and is highly stable.

Next, embodiments of the present invention will be described based on the drawings.

A driving section 3 and a driving section 4 are provided at the front of the machine base, which is equipped with a pair of left and right wheels 1, 1, 2, 2 in a drivable manner at the front and rear, respectively, and a loading platform 5 is provided behind them.
is provided so as to be able to swing up and down about an axis P located at the rear end by a pair of left and right hydraulic cylinders 6, thereby forming a transport vehicle that is capable of dumping and discharging cargo.

A drive system for the front and rear wheels 1, 2 and the fluid pressure cylinder 6 is configured by an engine 8 arranged in parallel with the seat 7 of the driving section 3 in the lateral direction of the vehicle body, and interlocked with the engine 8 via a bevel gear mechanism 9. A transmission transmission transmission 10, a fluid pressure pump 11 interlocked with the engine 8 via the bevel gear mechanism 9, and a cylinder control device 12 equipped with a fluid storage tank and a control valve are provided in the drive unit 4, respectively. Gear transmission 1
0, the front wheels 1 and the rear wheels 2 are interlocked and connected by a differential mechanism 13 that interlocks the left and right wheels, and a transmission shaft 14 that interlocks the differential mechanism 13 and the transmission transmission 10, Both 6 and 11 are connected so that the cylinder 6 is driven by the pump 11.

The driving unit 4 is constructed by disposing the engine 8 with the crankshaft 8a protruding laterally and outwardly of the vehicle body, and with the transmission transmission 10 located below the rear side of the engine 8 and approximately at the center of the left and right sides of the vehicle body. , in order to interlock the crankshaft 8a and the input shaft 10a of the transmission transmission 10, which extends in the longitudinal direction of the aircraft, the engine 8 is installed on the rear side of the engine 8 and above the transmission transmission 10.
A counter shaft K is provided which is substantially parallel to the crankshaft 8a of the engine 8, and one end side of the counter shaft K is interlocked with the crankshaft 8a of the engine 8 via a belt transmission mechanism A. In the middle of the process, a bevel gear 9 of a bevel gear mechanism 9 for changing the direction for transmitting power from the engine 8 to the transmission transmission 10 is installed.
a, 9b, the output shaft 9c of the bevel gear mechanism 9 and the input shaft 10a of the transmission transmission 10 are interlocked via a belt transmission mechanism B, and the power from the engine 8 is transferred to the transmission transmission 1.
Further, the pump 11 of the fluid pressure cylinder 6 of the loading platform 5 is connected to the end of the counter shaft K on the operating unit 3 side, and the bevel gear mechanism 9 for changing the transmission direction and the By distributing the pump 11 to the left and right above the transmission transmission 10, the driving part 4 itself becomes compact, the transmission structure between the driving parts equipment is simplified, and the left and right weight of the vehicle body is well balanced. We have taken care to make this possible.

Note that the fluid pressure cylinder 6 can be changed to a fluid pressure motor combined with a link mechanism for swinging the loading platform, and these are collectively referred to as the fluid pressure actuator 6.

In summary, the present invention provides the above-mentioned transport vehicle with the transmission transmission 10 being connected to its input shaft 1.
0a facing in the longitudinal direction of the aircraft, the engine 8 is located at the lower rear side of the engine 8 and at the center in the width direction of the aircraft. A counter shaft K is provided above, which is substantially parallel to the crankshaft 8a of the engine 8, and one end side of the counter shaft K is interlocked with the crankshaft 8a of the engine 8 via a transmission mechanism A. A bevel gear mechanism 9 for changing the direction for transmitting the power from the engine 8 to the transmission transmission 10 is provided midway on the engine 8 side of K, and the output shaft 9c of the bevel gear mechanism 9 and the transmission transmission transmission 10 are connected to each other. The input shaft 10a and the transmission mechanism B
The countershaft K is configured to transmit power from the engine 8 to the transmission transmission mechanism in conjunction with each other via a
It is characterized in that the pump 11 of the fluid pressure actuator 6 of the loading platform 5 is connected.

That is, the pump 11 is placed behind the engine 8 and laterally in parallel with the bevel gear mechanism 9 for changing the transmission direction, and is also placed on the driving section 3 side. Compared to other cases, the required installation space in the longitudinal direction of the machine body can be significantly shortened, and the loading platform 5 can be brought much closer to the front side of the machine body where the driving section and engine are located.

Furthermore, compared to the conventional structure described at the beginning, the width of the aircraft body can be made significantly smaller, making it possible to shorten the aircraft width both in the longitudinal and lateral directions, which greatly contributes to miniaturization.

In addition, the piping system between the pump 11 and the fluid actuator 6 can be easily arranged in a straight line over the shortest distance, so compared to the conventional structure, it does not require an unnecessarily large installation space and does not require any special mounting structure. This has the advantage of further reducing the size and making assembly easier.

Furthermore, the left-right balance of the aircraft is much more stable than when the driving section, engine, and pump are arranged side by side in that order, and stable running performance can be obtained despite the smaller size.

In addition, since the pump is linked to the counter shaft K equipped with the bevel gear mechanism 9, which is hardly slowed down by the crankshaft 8a, its full potential can be demonstrated, and the platform can be vertically oscillated efficiently. That is.

Note that although reference numerals are written in the claims section of the utility model registration for convenience of comparison with the drawings, the present invention is not limited to the structure of the attached drawings by such entry.

[Brief description of the drawings]

The drawings show an embodiment of the transport vehicle according to the present invention, with FIG. 1 being an overall side view, and FIG. 2 being a rear view showing the main parts.
FIG. 3 is a side view showing the main parts. 1...Front wheel, 2...Rear wheel, 3...Driving section,
5... Loading platform, 6... Actuator, 8... Engine, 8a... Crankshaft, 9a, 9b...
...bevel gear, 9c...output shaft, 10...mission, 10a...input shaft, 11...pump, A,
B...Transmission mechanism, K...Counter shaft.

Claims (1)

[Scope of utility model registration request] The engine 8 and the driving section 3 are arranged in parallel in the lateral direction of the vehicle body, and the engine 8 is arranged with the crankshaft 8a protruding outward laterally of the vehicle body,
The loading platform 5 is configured to be vertically swingable by a fluid pressure actuator 6, and is connected to an engine 8 and a transmission transmission 10.
In the transport vehicle configured to drive the front wheels 1 and the rear wheels 2 from the transmission transmission shaft 14 through the transmission shaft 14, the transmission transmission transmission 10 is configured such that the input shaft 10a thereof is directed in the longitudinal direction of the aircraft body. at the lower rear side of the engine 8 in a state where the
It is arranged at the center in the width direction of the fuselage, and is located on the rear side of the engine 8 and the transmission transmission 1.
A counter shaft K is provided above the crankshaft 8a of the engine 8, and one end side of the counter shaft K is interlocked with the crankshaft 8a of the engine 8 via a transmission mechanism A. A bevel gear mechanism 9 for changing direction for transmitting power from the engine 8 to the transmission transmission 10 is provided midway on the engine 8 side of the counter shaft K, and an output shaft 9c of the bevel gear mechanism 9 and the transmission transmission transmission mechanism 9 are provided. 10 input shafts 1
0a through a transmission mechanism B to transmit the power from the engine 8 to the transmission transmission transmission mechanism. A transport vehicle characterized in that a pump 11 of a pressure actuator 6 is connected.