JP3053245U - Speed control lever of tamping rammer - Google Patents

Abstract

(57) [Summary] [Problem] To close a cock by stopping the engine by operating the throttle lever after completing the work on a tamping rammer that may inadvertently turn the aircraft when moving and transporting the aircraft. The fuel supply path from the fuel tank to the engine and the pneumatic hole of the fuel tank are automatically closed without any need for operation, etc., and leakage of fuel is shut off, so that accidents due to fuel leakage can be prevented. Provide a speed control lever for tamping rammer. SOLUTION: A pair of curved elongated grooves 10 along a rotation direction are respectively provided at symmetrical positions around a rotation shaft hole 9 of a rotation plate 3 for a winding drum of a throttle adjustment wire having a lever 5 protruding from an outer peripheral surface thereof. The fixed plate 6 which is axially mounted on the rotary plate 3 via bolts 8 has a length corresponding to each of the curved elongated grooves 10 and 11 of the rotary plate 3. The fuel tank 16 and the carburetor 17 spaced apart along the direction, a pair of fuel opening / closing connection ports 14 and a pair of air opening / closing connection ports 15 communicating with an upper space in the fuel tank 16. An engine stop switch 7 operated by the lever 5 is provided at one end of the rotation range.

Description

[Detailed description of the invention]

[0001]

[Technical field to which the invention belongs]

 The present invention relates to a speed control lever of a tamping rammer used for compaction work on a pavement road surface, and more particularly, to an improvement of a speed control lever for operating a drive mechanism of the rammer.

[0002]

[Prior art]

 Conventionally, a tamping rammer used for compaction work on pavement roads converts the rotational force of the engine into vertical motion of the pedestal, and continuously beats the road with a pressing plate provided at the lower end of the pedestal. The structure of the fuselage is a vertically long overall shape with a heavy engine and fuel tank at the top, and pillars and compaction plates at the bottom, and the shape of the fuselage depends on the vertical motion. The airframe will stand in a forward-tilted position, as the squeezing plate is attached at an angle to the lower end of the pedestal so that forward movement can be obtained. For this reason, even when it is possible to stand while supporting the airframe with the compacting plate at the time of stoppage, it has the property of easily falling down due to a lateral force.

[0003] The tamping rammer is loaded on a truck bed and transported before and after the start of the work, and at the time of the transport, the tamping rammer stands up by the press platen as described above. Since the aircraft is likely to fall down from lateral forces in this state, it is necessary to secure the aircraft to the carrier with ropes so that the aircraft does not fall on the carrier during transportation. However, in many cases, it is troublesome to fix the aircraft on the bed with ropes, so the aircraft is often loaded sideways on the bed and transported.

[0004]

[Issues to be solved by the invention]

 As mentioned above, when transporting the rammer, if the aircraft is loaded sideways on the carrier and transported, the fuel will leak from the air pressure holes in the fuel tank and the carburetor, causing an accident due to a flash explosion. There is a risk.

[0005] In order to solve such a problem, the manufacturer should instruct the user that when transporting and moving the rammer, the aircraft should always be in an upright position without falling down. It is necessary, but as a manufacturer, regardless of the reason, in consideration of the case where the aircraft is turned over, even if the aircraft is turned over, even if the aircraft is turned over, fuel will be supplied from the air holes of the fuel tank and the carburetor. It is necessary to improve the structure to prevent leakage.

Conventionally, a device for preventing fuel from leaking from an air pressure hole or a carburetor of a fuel tank when an engine is turned over is known, for example, from Japanese Utility Model Laid-Open No. 4-34459. . However, these devices provide a cock between the fuel tank and the carburetor and close the cock to prevent fuel from leaking from the air pressure holes in the fuel tank and the carburetor. It is necessary to always close the cock before the cock is closed. If the engine is turned sideways without closing the cock, there is a problem that fuel leakage cannot be avoided.

[0007]

[Means for Solving the Problems]

 In this invention, for the tamping rammer that may inadvertently turn the aircraft when transporting the aircraft, the cock is deliberately closed when the aircraft has finished the work and stopped the engine by operating the throttle lever. The fuel supply path from the fuel tank to the engine and the air pressure holes in the fuel tank are automatically closed without any need for operation, etc., and fuel leakage is shut off. The purpose is to provide a speed control lever for a tamping rammer that can prevent accidents due to fuel leakage even if the aircraft is accidentally turned sideways.

The speed control lever of the tamping rammer according to the present invention includes, as specific means for that purpose, a rotary plate for a winding drum of a throttle adjustment wire having a lever protruding on the outer peripheral surface, and a mounting substrate on the rear surface and a surface on the front surface. A predetermined range of the outer periphery is annularly formed at a symmetrical position about the rotation shaft hole on the surface of the rotating plate which is in contact with the fixed plate and is rotatably mounted on a shaft via a bolt so as to be sandwiched between the fixed plate and the fixed plate. It has a pair of curved long grooves along the rotation direction surrounded by the packing, and on the back surface of the fixed plate that overlaps with the rotating plate, the back surface of the fixed plate is provided at a position corresponding to each curved long groove of the rotating plate. A pair of fuel opening / closing connection ports forming a fuel inlet from the fuel tank and a fuel outlet to the carburetor and a fuel outlet to the carburetor, and an air outlet to the fuel tank and a fuel outlet to the air outlet are formed. Form air inlet A pair of air opening / closing connection ports are provided, and when the lever is rotated, the rotating plate is connected to the fuel inlet of the fuel opening / closing connection port and the air outlet of the air opening / closing connection port by respective curved long grooves of the fixed plate. A stop switch of an engine operated by the lever is disposed at a position turned to an off angle.

[0009]

[Embodiment of the invention]

 The structure of the speed control lever for a tamping rammer according to the present invention will be described with reference to the embodiment shown in the drawings. As shown in FIGS. 1 and 2, the speed control lever is fixed to the upper operation handle 1 of the rammer and the like. A mounting board 2 for the throttle lever 5, a winding wire for a throttle lever adjustment wire 4 rotatably mounted on the mounting board 2, a rotating plate 3 for the drum, and a rotating plate 3 attached to the surface of the rotating plate 3. It is basically composed of a fixed plate 6 and an engine stop switch 7 attached to the operation handle 1 or the like and operated by operating the throttle lever 5.

The drum rotating plate 3 around which the throttle adjustment wire 4 is wound is disposed so as to be sandwiched between the mounting substrate 2 on the back surface and the fixed plate 6 on the front surface. Is mounted on a shaft so as to rotate within a predetermined range through a bolt 8 inserted so as to reach the mounting substrate 2 through the mounting board 2.

The rotating plate 3 has one end of a throttle adjusting wire 4 wound around and connected to the carburetor 16 of FIG. 5 at the other end, and a throttle on a part of the outer periphery. A lever 5 is provided in a protruding manner, and the speed adjustment and the stop of the engine can be operated by rotating the rotary plate 3 about the bolt 8 by the lever 5.

Further, on the surface of the rotary plate 3 which is in contact with the back surface of the fixed plate 6, a pair of curved portions along the rotation direction are provided at symmetrical positions around the rotary shaft hole 9 through which the bolt 8 passes. In addition to the provision of the elongated grooves 10 and 11, a cocoon-shaped annular concave groove 12 is provided in a predetermined area surrounding the curved elongated grooves 10 and 11, and the annular packing 13 is fitted into the concave grooves 12. ing.

On the other hand, the fixed plate 6 which is in contact with the surface of the rotating plate 3 has a curved long groove 10, 10 at a concentric position corresponding to the set angular position of each curved long groove 10, 11 on the rotating plate 3. A pair of fuel opening / closing connection ports 14 and a pair of similar air opening / closing connection ports 15 which are separated from each other on an axis along the length direction of 11 are provided.

The pair of fuel opening / closing connection ports 14 are used for introducing a fuel from a fuel tank 16 shown in FIG. 5 and a fuel inlet 14 a for sending the fuel introduced into the fuel inlet 14 a to a carburetor 17 of an engine. And a pair of air opening / closing connection ports 15, and an air outlet 15 a for introducing air into the upper space in the fuel tank 16, and guides air to the air outlet 15 a. And an air inlet 15b. A packing 18 is provided at the inner ends of the fuel inlet 14a and the air outlet 15a.

The rotary plate 3 can be rotated by a lever 5 within a range indicated by lines AA to BB in FIG. 3 with respect to the mounting board 2. As shown in FIG. 4, when the lever 5 is turned at the angle of the line AA, the fuel outlet 14b of the fuel opening / closing connection port 14 is connected to the curved long groove 10, so that the fuel is vaporized by the engine. Although the fuel can be sent to the fuel container 17, the fuel is supplied by the rotary plate 3 because the fuel inlet 14 a for introducing the fuel from the fuel tank 16 is separated from the curved long groove 10. It is shut off and does not flow in the direction of the vaporizer 17.

At this time, at the air opening / closing connection port 15, an air inlet 15 b for taking in air into the fuel tank 16 is connected to the curved elongated groove 11. Since the air outlet 15a for introducing air into the upper space in the tank 16 is separated from the curved elongated groove 11, the air is shut off by the rotating plate 3 and is not supplied into the fuel tank 16, and the air outlet 15a is not provided. The backflow of fuel due to is also prevented.

As shown in FIG. 3, when the lever 5 is rotated from the position of the line AA to the direction of the line BB, both the fuel outlet 14 b and the fuel inlet 14 a of the fuel opening / closing connection port 14 are curved. The fuel in the fuel tank 16 is introduced into the fuel inlet 14a and then sent out from the fuel outlet 14b through the curved elongated groove 10 to the carburetor 17 of the engine because the fuel is aligned with the elongated groove 10.

At that time, in the air opening / closing connection port 15, since both the air inlet 15 b and the air outlet 15 a coincide with the curved long groove 11, the air introduced from the air inlet 15 b passes through the curved long groove 11. Then, the fuel is introduced into the upper space in the fuel tank 16 from the air outlet 15a, and the state in which the fuel in the fuel tank 16 flows to the carburetor 17 through the fuel opening / closing connection port 14 is maintained.

The flow of fuel and air is maintained by setting the lever 5 within the range of the length of each of the curved elongated grooves 10 and 11. In the meantime, the engine throttle is adjusted by the change of the rotation angle of the lever 5, the throttle valve is opened to the maximum state at the angle of the line BB, and the idling state is at a position closer to the line BB than the line AA. Is held in. When the lever 5 is tilted to the position of the line AA as shown in FIG. 4, the lever 5 presses the engine stop switch 7 attached to the operation handle 1, so that the engine is stopped and at the same time the fuel inlet 14a is turned on. And the air outlet 15a is shut off to stop the fuel flow.

[0020]

[Effect of the invention]

 As described above, in the present invention, a pair of curved long grooves 10 along the rotation direction are provided at symmetrical positions around the rotation shaft hole 9 in the rotary plate 3 of the throttle adjustment wire 4 operated by the lever 5. , 11 are provided on the fixed plate 6 which is in contact with the rotary plate 3 at concentric positions corresponding to the curved elongated grooves 10, 11 of the rotary plate 3 along the longitudinal direction of the curved elongated grooves 10, 11, respectively. Since a pair of fuel opening / closing connection ports 14 and a similar pair of air opening / closing connection ports 15 which are separated from each other on the axis are provided, the engine stop switch 7 is operated separately from the operation of the lever 5 to adjust the engine speed. When the engine is stopped, the fuel inlet 14a of the fuel opening / closing connection port 14 and the air outlet 15a of the air opening / closing connection port 15 are shut off, so that the flow of fuel can be reliably stopped.

Therefore, according to the governing lever device of the present invention, the tamping rammer, which may inadvertently fall down when the aircraft is moved and transported, is operated by operating the throttle lever after the aircraft completes the work. As long as the fuel is stopped, the fuel supply path from the fuel tank to the engine and the air pressure holes in the fuel tank are automatically closed without the need to close the cock. Can be reliably shut off, and accidents due to fuel leakage can be prevented even if the aircraft is accidentally turned over during transport and transportation after work is completed.

The rotating plate 3 and the fixed plate 6 are pressure-bonded to each other on both front and back sides, and the annular packing 13 is placed in a predetermined range around a pair of curved elongated grooves 10 and 11 provided on the surface of the rotating plate 3. Since the back surface of the fixed plate 6 is pressed against the surface of the rotating plate 3 having the annular packing 13, fuel and air introduced into the curved elongated grooves 10 and 11 are sealed inside the annular packing 13 and Leakage can be reliably blocked. Further, two sets of connection ports having a separate function of a pair of fuel opening / closing connection ports 14 and a pair of air opening / closing connection ports 15 are provided at symmetric positions about the rotation shaft hole 9 of the rotating plate 3 and the fixed plate 6. Since the diameters of the rotating plate 3 and the fixed plate 6 are small, it is possible to contribute to the measurement of the entire apparatus.

[Brief description of the drawings]

FIG. 1 is a perspective view showing a configuration of a speed control lever according to the present invention.

FIG. 2 is a sectional view along the length direction of a lever.

FIG. 3 is a plan view of a lever showing a state of conduction of fuel and air during operation of the engine.

FIG. 4 is a plan view of a lever showing a shut-off state of fuel and air when the engine is stopped.

FIG. 5 is a circuit diagram showing the relationship between the speed control lever of the present invention, the fuel tank and the engine.

[Explanation of symbols]

1: upper operation handle, 2: mounting board, 3: rotating plate, 4: wire, 5: throttle lever, 6: fixed plate, 7: engine stop switch, 8: bolt,
9: rotary shaft hole 10, 11: curved long groove, 12: concave groove, 13: packing, 14: fuel opening / closing connection port,
14a: fuel inlet, 14b: fuel outlet, 15: air opening / closing connection port, 15a: air outlet, 15b: air inlet,
16: fuel tank, 17: vaporizer, 18: packing

Claims (1)

[Utility model registration claims] 1. A rotatable shaft via a bolt such that a rotary plate for a drum for winding a throttle adjusting wire having a lever protruding from an outer peripheral surface thereof is sandwiched between a mounting substrate on a back surface and a fixing plate on a surface. At a symmetrical position around the rotation shaft hole on the surface of the rotating plate that is attached and in contact with the fixed plate, each of the rotating plates has a pair of curved long grooves along a rotating direction surrounded by an annular packing around a predetermined range of the outer periphery. A fuel inlet from a fuel tank is provided at a position corresponding to each curved long groove of the rotating plate on a back surface of the fixed plate that overlaps with the rotating plate along a longitudinal direction of the curved long groove. And a pair of fuel opening and closing connection ports forming a fuel outlet to the carburetor, an air outlet into the fuel tank, and a pair of air opening and closing connection ports forming an air inlet to the air outlet. The rotating plate is connected to the fuel by the movement A stop switch of the engine operated by the lever is disposed at a position where the fuel inlet of the port and the air outlet of the air opening / closing connection port are turned to an angle which is displaced from each curved long groove of the fixing plate. Speed control lever for tamping rammer.