JP2009149132A - Engine inclination device for monorail carrier - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To solve the problem that a large machine body becoming an obstruct of maintenance/inspection and conveying ability cannot be made to light weight and miniaturization in a monorail carrier mounted with a 4-cycled gasoline engine traveling on the monorail installed on a rapid inclination ground of ascending/descending with large height difference. <P>SOLUTION: The engine inclination device for the monorail carrier has an intermediate shaft 1 becoming a turning center just above the engine 10 and a fuel tank 11 is constituted on an upper part. Thereby, shaking of the engine by movement of the fuel in the fuel tank at stopping is prevented from being amplified. It is made to the most main characteristic that the engine inclination device is made to an engine inclination device with light weight and miniaturization in which inclination of the engine is restricted to turning of a range of 15° of ascending/descending not affecting to function of the engine. <P>COPYRIGHT: (C)2009,JPO&INPIT

Description

  The present invention relates to a single rail transporter that can easily correct the attitude of an engine.

Among the devices that correct the engine inclination of a single rail transporter, the engine inclination device senses only the necessary information about the inclination of the rail installed on the slope with the inclination sensor, and the engine along the inclination of the rail. Since there is an advantage that the posture can be corrected in accordance with the allowable tilt range, it is practically used as a tilt control for a four-cycle gasoline engine.
The practical engine tilting device shown in Patent Document 1 is equipped with a fuel tank at an upper position of the engine and further has a rotation center above it, and an intermediate shaft is provided at the rotation center. The pulleys are provided at both ends of the intermediate shaft, the belt is stretched from the engine output shaft pulley to the pulley on one end side of the intermediate shaft, and the belt is stretched from the other end pulley to the input side pulley of the speed reducer. For this reason, belt covers are required on both sides of the aircraft, and there is a drawback that inspection and maintenance becomes complicated.
In addition, since the center of rotation is configured to be far away from the center of gravity of the engine, in order to keep the engine level, a large space is required in the front and rear, resulting in a drawback that the body becomes large.

  Further, when the aircraft is stopped from starting, the force caused by the movement of the fuel in the fuel tank amplifies the shake due to the inertial force of the engine mass.

  In the case of the invention of Patent Document 2, the engine rotation center is configured below the engine, and the engine is rotated by the electric cylinder. Switches that detect the inclination of the engine are required, and there are problems such as high costs and problems with durability of electrical components.

As an improvement measure, the present invention provides a center of rotation immediately above the engine, an intermediate shaft at the center of rotation, a fuel tank at the top, an idle pulley at one end of the intermediate shaft, By stretching a belt from the engine output pulley to the idle pulley and from the idle pulley to the reducer input shaft pulley to concentrate these power transmission mechanisms on one side of the fuselage and to limit the rotation range of the engine to a minimum We propose a simple, single-rail transporter with a lightweight, small engine attitude correction function that eliminates the electrical components for rotation and is simple, durable with little engine and fuel tank runout.
JP 2003-182565 A Japanese Patent No. 3932013

  The problem to be solved is that if a gasoline engine that needs to be equipped with an engine tilting device is installed in a single-rail transporting machine that runs on a single-rail running on a steep slope with a large elevation difference, maintenance inspection In addition, a large aircraft that hinders transportation capacity cannot be reduced in size and weight.

  The present invention has a rotation center immediately above the engine, and a fuel tank is formed on the upper part to prevent the engine from shaking due to the movement of the fuel, and the engine tilt does not affect the function of the engine. The most important feature is that it is a lightweight and small engine tilting device limited to motion.

  Since the engine tilting device of the single rail transporter of the present invention has the center of rotation immediately above the engine on the center of gravity line of the engine and the fuel tank installed in the engine, the engine runout caused by the movement of the fuel is generated. There is an advantage that it is possible to prevent the engine and the fuel tank from rotating in a range that does not affect the function of the engine in a small occupied space.

  There is a center of rotation directly above the engine, and a fuel tank is formed on the top to prevent the engine from shaking due to fuel movement, and the tilt of the engine is limited to a range that does not affect the function of the engine. The purpose of the above was achieved, and the engine tilting device of the single-rail transporter was made smaller and lighter without impairing the running performance of the 4-cycle gasoline engine.

1 to 4 show an embodiment of an engine tilting device of a single rail transporter. FIG. 1 is a left side view of the traveling direction of an engine tilting device of a single rail transporter that travels on a horizontal single rail, and FIG. 2 is a traveling direction of an engine tilting device of a single rail transporter that travels on a climbing single rail. FIG. 3 is a left side view toward the traveling direction of the engine tilting device of the single-rail transporter that travels on a single rail having a descending slope, and FIG. 4 is a traveling direction of the engine tilting device of the single-rail transporting device. The back is shown.
FIG. 5 shows a magnitude L1 of the shake between the engine and the fuel tank by a schematic diagram on the left side in the advancing direction immediately above the center of gravity line of the engine and when the center of rotation is below the fuel tank. 6 shows a magnitude L2 of the shake between the engine and the fuel tank by a schematic diagram on the left side in the traveling direction when the center of rotation is above the fuel tank and the center of rotation is above the fuel tank. .
1 is an intermediate shaft, 2 is an idle pulley, 3 is an engine output pulley, 4 is an engine belt, 5 is an engine tension pulley, 6 is a centrifugal clutch, 7 is an input belt, and 8 is a deceleration. Machine input pulley, 9 is an input tension pulley, 10 is an engine, 11 is a fuel tank, 12 is an intermediate shaft support frame, 12a is an intermediate shaft support frame (left), 12b is an intermediate shaft support frame (right) ), 13 is a stopper (front), 14 is a stopper (rear),
Details of the codes are shown in the “Description of codes” section below.

  The present invention has a rotation center immediately above the engine, and a fuel tank is formed on the upper part to prevent the engine from shaking due to the movement of the fuel, and the engine tilt does not affect the function of the engine. Limited to motion.

An intermediate shaft 1 is provided immediately above the engine cylinder head on the center of gravity of the engine, and the left and right sides of the intermediate shaft 1 are pivotally supported by intermediate shaft support frames (left 12a) (right 12b). The intermediate shaft support frame (left) (right) is fastened to the power vehicle frame.
An engine support plate (left 18a) and an engine support plate (right 18b) are inserted inside the intermediate shaft support frame (left 12a) and the intermediate shaft support frame (right 12b) so as to be rotatable with respect to the intermediate shaft 1. The left side of the engine, the right side of the engine, and the bottom side of the engine are fastened to the engine support plates 18a and 18b, respectively.

A fuel tank 11 is disposed above the intermediate shaft 1 provided immediately above the engine cylinder head on the center of gravity of the engine 10, and the fuel tank 11 is fastened to the engine 10 with the intermediate shaft 1 interposed therebetween. 10 and the fuel tank 11 rotate around the intermediate shaft 1.

  An idle pulley 2 is rotatably attached to the left of the intermediate shaft 1. An engine belt 4 is stretched around the engine output pulley 3, and the center portion of the engine belt is fixedly stretched by an engine tension pulley 5. Further, the input belt 7 is stretched from the idle pulley 2 to the reduction gear input pulley 8, and the vicinity of the reduction gear input pulley 8 is automatically tensioned by the input tension pulley 9.

  A reduction gear 19 is fastened to the power vehicle frame 15, and a stopper (rear 14) that stops the rotation when the engine tilts forward by about 15 degrees is provided at the center of the power vehicle frame 15, A bumper frame 16 connected to the power vehicle frame is provided with a stopper (front 13) that stops rotation when the engine tilts backward about 15 degrees.

  Power is transmitted from the engine output pulley 3 to the idle pulley 2 and from the idle pulley to the reducer input pulley 8, and the rail slope climbs 15 with the intermediate shaft 1 as the center of rotation in the range of 15 degrees forward lean to 15 degrees forward of the engine. In the range from 15 degrees to 15 degrees, there is an effect of automatically maintaining the level. In this range, the rotating engine output pulley 3, the centrifugal clutch 6, and the engine tension pulley 5 are arranged so as not to interfere with the non-rotating input belt 7, the speed reducer input pulley 8, and the input tension pulley 9. .

In the case of a normal single-rail transporter, it is common to set a rail up to 45 degrees and climb up and down. However, the allowable inclination limit of the 4-cycle gasoline engine is set to about 30 degrees forward and backward. Therefore, the basic function of the 4-cycle gasoline engine is not affected by correcting the inclination of the allowable engine inclination range of plus 15 degrees to minus 15 degrees by rotating the engine.
Therefore, in the range of 45 degrees above and below 15 degrees of rail inclination climbing and descending, the engine is 15 degrees forward leaning or 15 degrees backward leaning and is restricted by the stopper (rear 14) and the stopper (front 13). However, there is no problem with the engine function and it is possible to run.

The effect of providing the intermediate shaft 1 immediately above the cylinder head of the engine 10 and arranging the fuel tank 11 thereon will be described.
First, the vibration of the engine 10 at the time of stopping is greatly reduced, the airframe is stabilized, and the impact on the stopper and the like is eliminated. In the case of stopping in the forward direction, since the fuel tank 11 is located above the rotation center shown in FIG. 5, the fuel at the time of stopping moves forward in the fuel tank by the inertial force acting in the direction of FIG. 5F1. At this time, a force acts in the direction of FIG. 5F2 that stops the shake L1 of the engine 10.
On the other hand, the rotation center is shown by the schematic diagram shown in the attached FIG. 6 of this invention about the conventional single rail conveyance machine (patent document 1 case of FIGS. 1-3). In this case, the center of rotation of the engine of the single rail transporter is above the fuel tank. When the aircraft is stopped, if the engine turns within a range of 15 degrees up and down the rail, the swinging force due to the inertial force acting in the direction of FIGS. 6F1 and F2 is large, and the movement of the fuel in the fuel tank is in the direction of FIG. And acts as a force that amplifies the runout L2 of the engine in the direction of F2. Therefore, the runout L1 of the engine of the present invention shown in FIG. 5 is always smaller than the runout L2 of the engine having the center of rotation at the top of the fuel tank shown in FIG.
In the case of the present invention, even when the single-rail transporter travels on the rail, the engine rotates within the same range of 15 degrees up and down. However, since the occupied space is small, the size of the airframe can be reduced.
By limiting the rotation range to plus or minus 15 degrees, the idle pulley 2, the engine output pulley 3, the speed reducer input pulley 8, the engine belt 4, the input belt 7, the engine tension pulley 5, and the input tension pulley 9 are moved to the left side of the body. It became possible to concentrate on the. For this reason, the belt cover only needs to be on the left side, and maintenance inspection becomes easy.

  The present invention facilitates maintenance and inspection of a single rail transporter equipped with a versatile four-cycle gasoline engine, and rotates the engine with a four-cycle gasoline engine mounted on a tilt exceeding the allowable limit of tilt. It is intended to achieve a lightweight, low-cost single-rail transporter by tilting and correcting the posture to prevent engine trouble.

It is a left view toward the advancing direction which showed the implementation method of the engine inclination apparatus of a single rail transporter. Example 1 It is a left view toward the advancing direction which showed the implementation method of the engine tilting apparatus of the single rail conveyance machine which drive | works the climbing single rail. Example 1 It is a left view toward the advancing direction which showed the implementation method of the engine tilting device of the single rail conveyance machine which drive | works the single rail of a descending gradient. Example 1 It is a rear view toward the advancing direction which showed the implementation method of the engine tilting apparatus of a single rail conveying machine. Example 1 It is a left side schematic diagram toward the advancing direction which showed run-out of an engine and a fuel tank at the time of a stop of a single rail transportation machine which runs on a single rail. (Example 1 shows a case where the center of rotation is just above the center of gravity line of the engine and below the fuel tank.) When the center of rotation is above the fuel tank, it is a schematic diagram on the left side in the direction of travel showing the swing of the engine and the fuel tank when the single rail transporter is stopped. (Patent Document 1 shows the case where the center of rotation is located above the center of gravity line of the engine and above the fuel tank.)

Explanation of symbols

1 Intermediate shaft 2 Idle pulley 3 Engine output pulley 4 Engine belt 5 Engine tension pulley
6 Centrifugal clutch 7 Input belt 8 Reducer input pulley 9 Input tension pulley 10 Engine 11 Fuel tank 12 Intermediate shaft support frame 12a Intermediate shaft support frame (left)
12b Intermediate shaft support frame (right)
13 Stopper (front)
14 Stopper (rear)
15 Motor vehicle frame 16 Bumper frame 17 Drive wheel 18 Engine support plate 18a Engine support plate (left)
18b Engine support plate (right)
19 Reducer L1, L2 Fluctuation of engine and fuel tank F1 Direction of fuel movement F2 Direction of engine movement

Claims (3)

  The engine output is transmitted through the speed reducer, and the driving wheel provided on the final shaft of the speed reducer is configured to travel with thrust, and an intermediate shaft is provided at the top of the engine almost on the center of gravity line of the engine. Further, a fuel tank is disposed on the upper part of the intermediate shaft, and the engine and the fuel tank are configured to rotate about the intermediate shaft as a rotation center with respect to the traveling direction of the airframe. Engine tilting device.   The engine is automatically held horizontally when the forward / backward inclination of the aircraft is within the range of the set amount, and in the case of forward tilt of the aircraft exceeding the set amount, the engine is moved by the stopper (front) 13 at the set backward tilt position. 2. The engine tilting device for a single rail transporter according to claim 1, wherein the engine is stopped by a stopper (rear) 14 at a set forward tilt position when the aircraft is tilted backward. A belt is stretched from an engine output pulley to an idle pulley provided at one end of the intermediate shaft, and a belt is stretched from the idle pulley to a speed reducer input shaft pulley. 2. The engine output shaft, the intermediate shaft, and the speed reducer input shaft are arranged so that the speed reducer input pulley 8, the engine belt 4, the input belt 7, and the tension pulley 9 do not interfere with each other. An engine tilting device for a single rail transporter as described in 1.

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