JP4537989B2 - Engine tilting device for single rail conveyor - Google Patents

Description

  The present invention relates to a tilting device that maintains a posture within an allowable tilting range of an engine in a single rail transporter that travels on a rail laid on a steeply sloped ground.

  A single-rail transporter equipped with a 4-cycle gasoline engine has a drawback in that climbing and descending slopes are restricted because engine seizure occurs due to poor lubrication of the engine oil when the allowable inclination of the engine is exceeded. In order to solve this, even if the inclination of the rail changes, it is necessary to keep the engine within a horizontal or allowable inclination range. Since the single-rail transporter needs to rotate the engine back and forth with respect to the traveling direction, it can be rotated on an invention that forms the engine in a swing state (Patent Document 1) or on a support shaft that extends to the left and right attached to the frame. An invention (Patent Document 2) in which an engine base is supported by an arm attached to is generally disclosed. The invention of Patent Document 1 is an example of a single rail transporter with the engine in a swing state, and the invention of Patent Document 2 is an example of a single rail transporter supported by an arm that is rotatably provided. .

  However, in the example described in Patent Document 1, the rotation center of the engine is configured above the engine, and an intermediate shaft is provided at the rotation center to drive power from the engine to the counter shaft and from the intermediate shaft to the input shaft of the speed reducer. There was a need to communicate. For this reason, a shaft, a bearing, a bearing case, a pulley, a belt, and the like are newly required, and the frame for supporting the engine becomes complicated and the weight increases. For this reason, there is a drawback that it is inevitable that the cost is inevitably increased. In the case of the invention of Patent Document 2, the rotation center of the engine is configured below the engine, so that the output of the engine is transmitted to the input shaft of the speed reducer by a belt via an intermediate shaft provided at the rotation center. There was a defect similar to that of the invention of Patent Document 1 that the weight increased.

Since the single rail transporter climbs a steep slope, the increase in its own weight means that the transport weight is reduced, and its basic performance is greatly affected. This drawback is a major obstacle in terms of traveling on slopes in applications where a single-rail transporter transports people and cargo from the starting point to a destination with a large difference in altitude. Specifically, there are problems such as a decrease in speed when climbing, an increase in fuel consumption, and a hindrance to weight reduction that is characteristic of a single-rail transporter equipped with a 4-cycle gasoline engine. there were. Further, FIGS. 8 to 9 according to the invention of Patent Document 2 show an example in which the engine output shaft is the center of rotation, but a centrifugal clutch provided on the engine output shaft, and a pillow block outside the V-belt. In this case, the centrifugal clutch and V-belt, which are consumables, cannot be easily inspected and replaced, or the engine always moves forward and backward to maintain the level. There was a problem of shaking and shaking. Usually, the output shaft of a general-purpose engine is provided only on one side of the engine, and the length of the output shaft is not so long, so it is not easy to support the output shaft and provide a centrifugal clutch. It was.

As an improvement measure, the present invention does not take the conventional system in which an intermediate shaft is provided at the center of rotation and power is transmitted from the intermediate shaft to the counter shaft, and the engine has a structure in which maintenance and inspection of the centrifugal clutch and V-belt are easy. Power is transmitted from the output shaft to the input shaft of the reducer and the drive wheel of the final shaft via the V-belt with the output shaft as the rotation center, and durability is improved by limiting the rotation range of the engine to a minimum It was proposed to be light and small.
JP 2003-182565 A JP 2002-120716 A

  The present invention facilitates maintenance and inspection of a single rail transporter equipped with a versatile four-cycle gasoline engine, and intermittently rotates the mounted four-cycle gasoline engine to an appropriate angle according to the inclination. Therefore, it is intended to realize a lightweight, low-cost single rail transporter that prevents deterioration of the airframe and engine trouble due to wear of bearings and rollers.

  In the present invention, when a single-rail transporter travels on an inclined ground, the engine rotates around the output shaft of the engine so that it can travel within an inclination angle range that does not affect the basic performance of the engine at all times. The most important feature is that the vehicle can be made compact and the vehicle can be tilted while the center of gravity of the engine is near the center of rotation.

  The engine tilting device of the single-rail transporter is characterized in that, first of all, a pulley is provided outside the bearing (left) that supports the output shaft provided on the output shaft of the engine, and the output of the engine via the belt. Is transmitted to the input pulley of the speed reducer, and a single rail transporter configured to travel by obtaining thrust with the drive wheel provided on the final shaft of the speed reducer, the engine has an output shaft on the left and right sides of the engine base. A guide rail that traces a semicircular arc around the center is fastened, the guide rail is gripped by a plurality of rollers provided on the engine support frame, and is rotated in the direction of travel around the output shaft of the engine. By being configured to move, there is no need to provide an intermediate shaft, so that the weight can be reduced, and the belt hung on the pulley provided on the output shaft can be easily replaced.

  Second, a bearing (left) is provided on the engine output shaft, and a bearing (left) for supporting the engine output shaft is provided on the support shaft frame (left) fastened to the engine support frame fixed to the power vehicle frame. An engine support shaft that extends from the engine base and is fixed is provided on the right side surface on the center of the engine output shaft. The engine is rotatably supported by a support shaft frame (right) having a bearing (right) that supports the engine support shaft, and the engine is semicircular on the left and right sides of the engine base around the output shaft. A guide rail for drawing a trajectory is fastened, and the guide rail is held by a plurality of rollers provided on the engine support frame. A centrifugal clutch capable of engaging and disengaging power depending on the number of rotations is provided outside the bearing (left) of the engine output shaft so that power is transmitted to the input pulley of the speed reducer by a belt.

  Third, a guide rail that draws a semicircular arc around the output shaft is fastened to the left and right of the engine base, and the guide rail is gripped by a plurality of rollers provided on the engine support frame. The engine body is guided by the guide rail gripped by the roller and rotates around the output shaft, and when climbing or descending on a sloping ground, the engine is neutral, i.e. parallel or forward tilted with respect to the power vehicle frame. One of the three postures of backward tilt will be held.

  Fourth, the engine frame includes a neutral switch that detects that the rotating engine is substantially parallel to the rail, a forward limit switch that detects the forward tilt position of the engine, and a rearward tilt position of the engine. A tilt limit switch is provided for detection, and the motor vehicle frame is provided with a fuselage forward tilt switch and a fuselage tilt switch for detecting a certain degree of tilt in the front-rear direction. When the aircraft tilts forward, the front of the fuselage This is because the engine is electrically controlled to tilt backward by detection of the tilt switch, while the engine is electrically controlled to tilt forward by detection of the rear tilt switch when the aircraft tilts backward.

  An engine tilting device for a single rail transporter according to the present invention includes a plurality of rollers that are provided on an engine base with guide rails formed so as to draw a semicircular arc shape around an output shaft of the engine, and are rotatably provided on an engine support frame. The engine grips the guide rail, and the engine rotates about the engine output shaft along the locus of the guide rail. Therefore, since the distance between the output shaft and the reducer input shaft is constant regardless of the rotation of the engine, there is no need to provide an intermediate shaft, and power can be transmitted directly from the engine output shaft to the reducer input shaft with a V-belt. Thus, the power transmission efficiency is improved and the size can be reduced. Furthermore, with the engine output shaft as the center of rotation, the center of gravity movement is small even when the engine rotates greatly due to the situation where the aircraft is traveling, so the change in the load balance on the guide rollers and drive wheels of the power vehicle is small and durable. There is an advantage that the improvement of vibration and vibration can be reduced.

In addition, the shape of the guide rail provided on the engine base is formed so as to draw a semicircular arc shape with the output shaft of the engine as the center of rotation, and is held by a plurality of rollers, so the center of rotation is the engine output. On the axis. Therefore, the occupied space by the rotation of the engine is from the range of the distance from the center of the output shaft to the engine base provided in the engine body, so compared with the distance from the conventional swing-type rotation center to the end of the engine horizontal device The aircraft can be downsized because it is much smaller.

Since the engine is supported by a roller that grips a guide rail that draws a semicircular arc with the engine output shaft as the center of rotation, a bearing that supports the engine output shaft (left) and a support shaft and bearing on the right side of the engine (Right) can be downsized, and the bearing (left) can be configured inside the centrifugal clutch attached to the engine output shaft. The present invention has an advantage that a bearing (left) is formed inside the centrifugal clutch attached to the engine output shaft, so that inspection and replacement maintenance of the V-belt and the centrifugal clutch can be easily performed.

  The purpose is to prevent both deterioration of the rotating parts such as bearings and rollers and engine troubles due to wear by rotating the engine as few times as possible in the smallest possible space around the rotation axis of the engine. By configuring the engine tilting device with the minimum number of parts, weight reduction is not hindered, and there is no need to provide an intermediate shaft or the like, which is achieved without impairing power transmission efficiency.

  FIG. 1 is a side view of an embodiment of the apparatus of the present invention, FIG. 2 is a side view of the aircraft when climbing, FIG. 3 is a side view of the aircraft when descending, and FIG. FIG. 5 is a side view showing the positional relationship between the engine output shaft and the engine base at a time, FIG. 5 is a side view showing the positional relationship between the engine output shaft and the engine base in a head-down state when traveling on an inclined ground, and FIG. FIG. 9 is a front view in the direction of travel, FIG. 9 is a flowchart showing an operation for electrically controlling the inclination of the engine based on information from the traveling aircraft, and FIG. 10 is 45 degrees and 25 with respect to the horizontal ground. It is a schematic diagram which compares the inclination-angle of the engine of this invention straddled on the rail installed in the slope of the degree. 1 is an engine, 2 is an engine base, 3 is a guide rail, 4a is an engine tilt limit switch, 4b is an engine tilt neutral switch, 4c is an engine tilt limit switch, 5 is an electric cylinder, 6 is a cylinder receiver, and 7 is an output Shaft, 8 is a centrifugal clutch, 9 is a V belt, 10 is an input shaft, 11 is a reduction gear, 12 is a drive wheel, 13 is a motor vehicle frame, 14 is a start stop lever, 15 is a roller, 16 is a roller, and 17 is an engine Support shaft, 18a bearing (left), 18b bearing (right), 19a support shaft frame (left), 19b support shaft frame (right), 20 sensor box, 21 weight, 22 forward tilt Switch, 23 is a rear tilt switch, 24 is a stopper, 25 is a stopper, 26 is a recess into which the switch actuator is inserted, and 27 is an engine support frame. It is a non.

An engine support frame 27 is provided in front of the power vehicle frame 13, and support shaft frames (left) 19a are provided on the left and right sides of the engine support frame 27, respectively.
A support shaft frame (right) 19b is fastened. The support shaft frame (left) 19a is provided with a bearing (left) 18a to support the engine output shaft 7. The engine 1 is fastened to the engine base 2, and an engine support shaft 17 fixed to the engine base 2 is provided on the right side of the engine on the center of the output shaft 7. The engine support shaft 17 is pivotally supported by a bearing (right) 18b provided on a support shaft frame (right) 19b, and the engine base 2 and the engine 1 are integrally rotatable about the output shaft 7. ing.

  The left and right sides of the engine base 2 are fastened with semicircular arc guide rails 3 that draw a circular arc at the center of the output shaft 7, and the guide rails are mounted on the engine support frame 27 so as to be rotatable on each of the left and right sides. The rollers 15 and 16 are held from above and below and can be rotated about the output shaft 7. The left and right sides of the engine base 2 are fastened with semicircular arc guide rails 3 that draw a semicircular arc around the center of the output shaft, and the guide rails 3 are rotatably attached to the engine support frame 27. Since the four rollers 15 and 16 each hold the guide rail 3 from above and below, the engine 1 is configured to be rotatable about the output shaft. A centrifugal clutch 8 is attached to the outside of the bearing (left) 18a of the engine output shaft 7 so that power transmission is engaged and disengaged depending on the engine speed. The rotational force of the engine 1 is transmitted to the pulley provided on the speed reducer input shaft 10 of the speed reducer 11 by the belt 9 and travels by the drive wheels 12.

The electric cylinder 5 is provided to change the tilt position of the engine 1 and is rotatably attached to the engine base 2 at one end and a cylinder receiver 6 extending from the power vehicle frame 13 at the other end. The engine 1 and the engine base 2 are configured to tilt backward or forward about the engine output shaft 7 by the expansion and contraction of the electric cylinder 5.
In a four-cycle gasoline engine, an inclination of around 30 degrees is usually allowed. When this limit inclination angle is exceeded, the engine 1 rotates and the inclination of the engine is within an allowable value, so that it is possible to mount and use a four-cycle gasoline engine on a single rail carrier. For this reason, in this proposal, as a means for detecting the inclination of the airframe provided on the power vehicle frame 13, a pendulum type weight 21 is used to detect the forward inclination of the airframe when the inclination is about ± 25 degrees. A switch (front) 22 and a tilt switch (rear) 23 for detecting the rear tilt of the aircraft are configured to detect the tilt of the aircraft.

Next, control of the engine tilting device will be described with reference to the drawings.
As shown in FIG. 7, when the single rail transporter climbs the hill, the motor vehicle is tilted backward, but when tilted by about 25 degrees, the pendulum weight 21 in the sensor box 20 touches and the rear tilt switch 23 of the airframe is touched. Detect with.
The engine 1 is held in a state substantially parallel to the power vehicle (FIG. 1) until the power vehicle is tilted 25 degrees, but there is no problem in engine performance.
When the motor vehicle tilts beyond 25 degrees, the electric cylinder 5 contracts and the engine 1 takes a forward leaning posture (FIG. 2), and detects the tilt of the engine provided on the engine frame 13 along the engine base 2. The system is tilted forward to a position where the engine forward tilt limit switch 4c is operated and stopped. In the schematic diagram shown in FIG. 10, the tilting device of the present invention provided in the single rail transporter that runs on the rail 3 installed on the ground inclined at 25 degrees with respect to the horizontal ground, and 45 Compared to the tilting device of the present invention provided in a single-rail transporter traveling on a rail installed on a ground inclined at a degree, it travels on a rail installed on a 25-degree inclined ground. In this case, the engine 1 is tilted forward by about 25 degrees with respect to the power vehicle, and maintains a horizontal posture with respect to the ground. Similarly, in FIG. 10, in the tilting device of the present invention of the single rail transporter straddled on the rail 3 installed on the slope at 45 degrees with respect to the horizontal ground, the engine is about 25 degrees with respect to the motor vehicle. Since the vehicle is traveling while maintaining a forward tilt, the engine is controlled so that it does not rotate even when the inclination of the rail reaches 45 degrees. However, since this is an acceptable range, there is no problem in engine performance.

When the aircraft going uphill enters a trajectory of 25 degrees or less, and the aircraft rear tilt switch 23 provided in the sensor box 20 is turned OFF as shown in FIGS. The backward tilt start circuit works, the electric cylinder 5 is extended by the relay to rotate the engine 1 in the backward tilt direction, the engine tilt neutral switch 4b is actuated, the extension of the electric cylinder 5 is stopped, and the engine posture is the motor vehicle. It is held substantially parallel to the frame.

  As shown in FIG. 3, when the single-rail transporter descends with a head down, similarly, the pendulum weight 21 of the sensor box swings to contact the machine forward tilt switch 22, thereby extending the electric cylinder 5. The engine is tilted backward and stopped until the engine rearward tilt limit switch 4a of the device for detecting the tilt of the engine provided in the engine frame 13 is operated. As shown in FIG. 5, when the engine is tilted backward, the actuator of the engine tilt limit switch 4a enters the recess 26 provided in the engine base 2, and the engine tilt limit switch 4a is activated.

  As described above, the rotation of the engine 1 travels in a state substantially parallel to the motor vehicle frame, that is, in a state parallel to the rail, within the inclination of the rail plus or minus 25 degrees, and when the inclination is plus or minus 25 to 45 degrees. The engine travels with an attitude of 25 degrees before and after the power vehicle frame, that is, the engine is held at 20 degrees from the horizontal with respect to the horizontal plane. In other words, in the present invention, even if the inclination of the rail changes, the vehicle travels while maintaining any one of the three postures of parallel, forward tilt 25 degrees, and rearward tilt 25 degrees on the basis of the power vehicle frame. Compared with a cylinder that holds the engine horizontally, the minimum rotation can compensate for the shortcomings of a 4-cycle gasoline engine. For this reason, the tilting device of the present invention enables the manufacture of a single rail transporter that is lighter and smaller, and has the effect of ensuring the durability of the components of the 4-cycle gasoline engine.

The guide rail 3 provided on the left and right sides of the engine base 2 and the rollers 15 and 16 for holding the guide rail provided on the engine support frame 27 support the engine 1 and the engine base 2. The engine 1 is centered on the engine output shaft 7. It can be rotated. This prevents the engine from collapsing due to belt tension. Further, by configuring some of the plurality of rollers with an elastic body such as rubber, it is possible to absorb the vibration of the engine and improve the durability of the rotating device.

The engine tilting apparatus of the present invention achieves further weight reduction of a single-rail transporter equipped with a 4-cycle gasoline engine by attaching a tilting apparatus that rotates the engine around the center of the engine rotation axis, and travels on a steeply inclined land. Improved performance, installed a centrifugal clutch outside the bearing provided on the output shaft of the engine, facilitated maintenance, and maintained a parallel, 25 ° forward or 25 ° back position on the power vehicle frame. As a result, durability can be improved.
.

It is the horizontal side view which showed the implementation method of an engine tilting apparatus. Example 1 It is the engine forward inclination side view which showed the implementation method of the engine inclination apparatus. Example 1 It is an engine back tilt side view which showed the implementation method of an engine tilting apparatus. Example 1 It is the horizontal side view which showed the implementation method of the apparatus which inspects the inclination of the engine of an engine tilting apparatus. Example 1 It is the engine back inclination side view which showed the implementation method of the apparatus which inspects the inclination of the engine of an engine inclination apparatus. Example 1 It is the horizontal side view which showed the implementation method of the apparatus which detects the inclination of the airframe of an engine tilting apparatus. Example 1 It is the back tilt side view which showed the implementation method of the apparatus which detects the inclination of an airframe at the time of the back tilt of an engine tilting apparatus. Example 1 It is the front view of the airframe which showed the implementation method of the engine tilting device toward the advancing direction. Example 1 It is a flowchart which shows control of an engine tilting apparatus. Example 1 It is a schematic diagram which compares the inclination angle of the engine of this invention straddled on the rail installed in the 45 degree and 25 degree | times inclination ground with respect to the horizontal ground.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Engine 2 Engine base 3 Rail 4 Engine inclination switch 4a Engine backward limit switch 4b Engine inclination neutral limit switch 4c Engine forward limit switch 5 Electric cylinder 6 Cylinder support 7 Output shaft 8 Centrifugal clutch 9 V belt 10 Input shaft 11 Deceleration device 12 Drive Wheel 13 Power Car Frame 14 Start Stop Lever 15 Roller 16 Roller 17 Engine Support Shaft 18a Bearing (Left)
18b Bearing (Right)
19a Support shaft frame (left)
19b Support shaft frame (right)
20 Sensor box 21 Weight 22 Machine body forward tilt switch 23 Machine body rearward tilt switch 24 Stopper 25 Stopper 26 Concave part 27 where switch actuator enters 27 Engine support frame

Claims (1)

A pulley is provided outside the bearing (left) that supports the output shaft provided on the output shaft of the engine, and the engine output is transmitted to the input pulley of the reducer via the belt, and provided on the final shaft of the reducer. In a single rail conveyor configured to travel with drive wheels to obtain thrust,
A guide rail that draws a locus in a semicircular arc around the output shaft is fastened to the left and right of the engine base, and the guide rail is gripped by a plurality of rollers provided on the engine support frame, and rotated around the center of the engine output shaft. Has power transmission means directly from the output shaft,
  The bearing (left) that supports the engine output shaft is provided on the support shaft frame (left) fastened to the engine support frame fixed to the power vehicle frame, and extends from the engine base to the right side surface on the center of the engine output shaft. The bearing shaft (right) that supports the fixed engine support shaft is provided on the support shaft frame (right) fastened to the engine support frame, and the support shaft frame (left) fastened to the engine support frame and the support shaft frame (right) The engine is pivotally supported around the output shaft that is pivotally supported by the bearing provided in the
  The engine support frame includes an engine tilt neutral limit switch for detecting that the rotating engine is substantially parallel to the rail, a forward tilt limit switch for detecting the forward tilt position of the engine, and a reverse tilt position of the engine. A rearward tilt limit switch for detection is provided, and the power vehicle frame is provided with a forward tilt switch and a forward tilt switch for detecting a predetermined tilt in the longitudinal direction of the aircraft, and the engine is detected by detecting the forward tilt switch. An engine tilting apparatus, wherein the engine tilting apparatus is electrically controlled to tilt backward and is electrically controlled to tilt forward by detection of a rear tilt switch.

Images