JPH0424131A - Direction indicator for working vehicle - Google Patents

Abstract

PURPOSE:To operate turn-on operation a direction indicator lamp in advance of a body direction change as well as to secure such a working vehicle that makes any possible danger avoidable even if this on-operation is forgotten by installing a direction indication control mechanism which automatically operates the direction indicator lamp into both on-off states corresponding to the detection body direction. CONSTITUTION:When a detection body direction by a detection mechanism 6 is a rectilinear sense, by way of example, all detection switches 12a, 12b come to 'on' or 'off', and both direction indicator lamps LW, RW come to off. If the detection body direction is, for example, right hand, the switch 12a and the left direction indicator lamp LW both come to 'on'. On the other hand, even if the detection body direction is, for example, a rectilinear sense and a direction indication control mechanism 18 outputs an 'off' operating signal, such a fact that the direction indicator lamps LW and RW is operated into ON preferentially by an operator 9a or 9b is made possible owing to each action of both OR circuits 7 and 8. In this connection, even if these operators 9a and 9b are turned off intact, the direction indicator lamp LW or RW at the side corresponding to the detection body direction is automatically turned on.

Description

[Detailed description of the invention] [Industrial application field] The present invention relates to a direction indicating device for a working vehicle.

[Conventional technology]

Conventionally, in work vehicles, it is preferable to turn on the direction indicator lights before changing the direction of the machine.
It was designed to be entered and operated by humans.

[Problem to be solved by the invention]

In the past, when changing the orientation of the aircraft, there were cases in which people forgot to turn on the direction indicator lights.

SUMMARY OF THE INVENTION An object of the present invention is to provide a work vehicle in which a direction indicator light can be turned on prior to changing the direction of the vehicle, and even if the turn signal lamp is forgotten to turn on, danger can be avoided.

[Means to solve the problem]

In order to achieve the purpose of the direction indicating device for a work vehicle according to the present invention, an artificial operating tool is provided for a pair of left and right direction indicating lights, and a detection mechanism is provided for detecting the orientation of the aircraft in which the aircraft direction device appears. and a direction indicator control mechanism that automatically operates the direction indicator light to an on state and an off state corresponding to the detected aircraft orientation based on the aircraft orientation detected by the detection mechanism, Giving priority to switching to the on state based on the operation of the operating tool over the switching operation by the direction indicating control mechanism, and giving priority to switching the direction indicator light to the on state based on the operation of the direction indicating control mechanism. The human operating tool and the direction indicating control mechanism are linked to the direction indicating light in a state where priority is given to the cutting operation by the human operating tool.

Although the manual operation tool may be constructed so that it can be manually returned to the cutting position, it is advantageous if the return operation is performed by automatic cutting means.

[For production]

By operating the manual operation tool at any time, such as when changing the orientation of the aircraft, even if the aircraft is traveling straight and the direction control mechanism is instructing a turning operation, the direction will be changed over the turning operation. The indicator light can be operated at any time.

Even if you forget to manually operate the direction indicator lights and change the orientation of the aircraft, the direction indicator control mechanism will automatically turn on based on the information from the detection mechanism, and the manual operation will be in the off position. However, the turn signal lights are turned on in priority.

If an automatic cut-off means is provided, even if the manual operating tool is operated to the ON position, it will not immediately return to the OFF position, and the turn signal will be turned ON or the turn signal will be turned ON even if the manual operating tool is in the ON position. Even if it is possible to check whether the operated direction indicator light is the correct one that matches the direction in which the aircraft should be heading, the manual control tool will not be forgotten to be returned to the off position after returning to the straight-ahead state. It will automatically return.

[Effects of the Invention] When changing the orientation of the aircraft, the direction indicator light can be turned on using the human operating tool prior to performing the steering operation. Furthermore, even if the manual operation is forgotten, the direction indicator lights will automatically turn on when the aircraft is turned, and the direction of the change in direction will be relatively reliably communicated to other vehicles, allowing safe driving. It became so.

Providing an automatic cut-off means makes it possible to confirm the operation by using the human operating tool as a display means, and also prevents forgetting to turn off the direction indicator light, making it possible to drive safely from these aspects as well.

[Example] Next, examples will be shown.

As shown in Fig. 4, the loading platform (3) is placed on the rear side of the crawler machine, which is equipped with a driving part (1) and a driving part (2) at the front part of the machine, by means of a dump cylinder (C). The truck is mounted so that it can be swung up and down around its axis, creating a transport vehicle capable of dumping a cargo platform.

As shown in FIG. 4, direction indicator lights (LW) and (RW) are attached to the left and right sides of the guard frame (4) located between the loading platform (3) and the driving section (1). And the first
As shown in the figure, two operation switches (LS) that enable manual operation of the turn signal lights (LW) and (RH),
(RS) to the pair of left and right steering levers (5a), (5
b), as well as direction indicator lights (LW),
A detection mechanism (6) that enables automatic operation of the (RW) is attached to the steering levers (5a) and (5b), and the direction indicator light (LW) (RW) is turned on prior to the aircraft direction change operation. The vehicle is configured so that the vehicle can be operated automatically, and the turn signal lights (LW) and (RW) can be turned on automatically even if the manual operation for this purpose is forgotten.

That is, as shown in Figure 2, the left steering lever (5a
) is the operation switch (LS) attached to the left direction indicator light (LW).
), and the operation switch (R5) attached to the right steering lever (5b) is connected to the right direction indicator light (RW), and the OR circuit (7
) or (8).

Both operation switches (LS) and (RS) are configured to be turned on by pushing the button-type operating tool (9a) or (9b) into the on position, and when the switch is turned on, the direction Indicator light (I
J) or (RW) is turned on to blink.

The detection mechanism (6) is connected to the steering lever (5) as shown in FIG.
Across a) and (5b) - book switch operating rod (10
) and also install the steering levers (5a) and (5b).
As the lever is swung around the axis (P), the lever operating force changes, and the adjustment interposed between the steering levers (5a) and (5b) and the switch operating rod (10) changes. Core type bearing (11
), and the positional relationship of the two bearings (11) (11) (11), the switch operating rod (10) comes into contact with the detection switches (12a) and (12b) to turn on and operate the detection switches. It is configured to be turned off remotely from the switches (12a) and (12b). That is,
The aircraft direction device (13) is configured to direct the aircraft by driving and stopping the left and right crawler traveling devices (A) and (A) using the steering levers (5a) and (5b). In this case, the aircraft orientation device (13) detects the orientation of the aircraft based on the operating positions of the steering levers (5a) and (5b), and the detection results are transmitted by the detection switches (12a) and (12b). It is configured to be electrically extracted. In other words, as shown in FIGS. 3(a), (d), and (ne), all the steering levers (5a) and (5b) are in the neutral position (N), the forward position (F), or the reverse position (R).
), when the straight-ahead direction appears, it is detected and both detection switches (12a) and (12b) are turned on or off. And Figure 3 (1+)
, (c), one of the steering levers (5)
When a) or (5b) is in the neutral position 1f (N) and the other steering lever (5b) or (5a) is in the forward position (F), when leftward or rightward direction appears, it is detected and either One of the detection switches (12a) or (12b) is turned on.

The OR circuits (7) and (8), one OR circuit (7)
an AND circuit (14) and a N07 circuit (1
5), the other OR circuit (8) is detected by the switch (12a)
AND circuit (16) and N07 circuit (17) linked to both or one of (12b) and (12b), the direction indicator light (L-) is set based on the orientation of the aircraft detected by the detection mechanism (6).
A direction indication control mechanism (18) is configured to automatically operate the (RW) and (RW). That is, the detection mechanism (6)
When the detected aircraft direction is straight ahead, both the detection switches (12a) and (12b) are turned on and off, causing both direction indicator lights (LW), (
RW) is cut.

If the orientation of the aircraft detected by the detection mechanism (6) is to the left, the detection switch (12a) is turned on, the left direction indicator light (open) is turned on, and the detection mechanism (6)
If the aircraft is facing right, the detection switch (
12b) is turned on, the right direction indicator light (4)
is entered.

Even if the orientation of the aircraft detected by the detection mechanism (6) is straight ahead and the direction control mechanism (18) is outputting a turning operation signal,
Priority is given to switching the direction indicator lights (LW) and (RW) to ON using the operating tools (9a) or (9b), and operating tools (9a) and (9b) are in the OFF position (
OFF>, press the operation switch (LS) and (RS)
) is outputting a turning operation signal, the direction indication control mechanism (18) has priority over this and outputs the turn signal light (LW) and (R
Each of the switching operations of W) to ON is an OR circuit (7
) and (8), even if the aircraft direction device (13) is operated to show the straight ahead direction, the direction indicator light (Lll) is activated by the operating tools (9a) and (9b).
l) and (RW) can be input and operated. and,
Even if the operating tools (9a) and (9b) are left in the off position (OFF), when the aircraft direction device (13) is operated to the leftward or rightward direction, the direction instruction control mechanism (engine 8) is activated. Due to this action, the direction indicator light (LW) or (RW) on the side corresponding to the orientation of the aircraft detected by the detection mechanism (6) is automatically turned on.

As shown in FIG. 2, the detection switch (12a) and (12
b) A pair of electromagnetic two-seater operating tools (
By attaching one of the operating tools (19a) of 19a) and (19b) so as to act on the operating switch (LS), and attaching the other operating tool (19b) so as to act on the operating switch (IIIS). This is to prevent forgetting to return the operation switches (LS) and (R5) that were operated to turn them on and turn them off.

That is, when the operating tools (9a) and (9b) are operated to the entry position, they maintain the entry position by self-holding action in order to maintain the direction indicator light (LW) or (RW) in the entry position. , When the aircraft direction device (13) is operated and the detection switch (12a) or (12b) is turned on, the switch operation tool (9a) or (9b) turns on the operation switch (LS) to energize by turning on the detection switch. Alternatively, by switching (RS) to OFF, the operating tool (9a) or (9b) is returned to the OFF position. In other words, even if the operating tools (9a) and (9b) are operated to the on position prior to changing the orientation of the aircraft, the switch operating tools (9a) or (9b) restore them to the off position when the orientation of the aircraft is changed. When it is operated and the aircraft returns to straight ahead, it is in the cut position.

[Another Embodiment] The present invention can also be applied to a work vehicle having a wheel-type traveling device configured to perform swing steering operation of the traveling wheels by rotating a handle to direct the vehicle. In this case, the left side operation switch and the right side operation switch may be operated by one operation lever. Therefore, the operating tools (9a) and (9b) are simply replaced by the human operating tools (9a) and (9b).
a), (9b), and a switch operating tool (19a)
, (19b) to automatic cutting means (19a), (19
b) It is called.

Incidentally, although reference numerals are written in the claims section for convenient comparison with the drawings, the present invention is not limited to the structure shown in the accompanying drawings.

[Brief explanation of drawings]

The drawings show an embodiment of the direction indicating device for a working vehicle according to the present invention, in which Fig. 1 is a partially cutaway rear view of the steering lever installation part, Fig. 2 is an electric circuit diagram, and Fig. 3 (A). Figure 4 is an explanatory view of the operating state of the detection mechanism, and Figure 4 is a side view of the entire transport vehicle. (6)...Detection mechanism, (9a), (9b)
...... Human operating tool, (13) ... Aircraft direction device, (18) ... Direction instruction control mechanism, (1
9a), (19b)... automatic cutting means, (
LW), (RW)...Direction light.

Claims (1)

[Claims] 1. A pair of left and right direction indicator lights (LW) and (RW) are provided with human operating tools (9a) and (9b), and the aircraft orientation device (13) is oriented toward the aircraft. A detection mechanism (6) is provided to detect the orientation of the aircraft, and based on the orientation of the aircraft detected by this detection mechanism (6), the direction indicator lights (LW) and (RW) are automatically set to the on state and off state corresponding to the orientation of the aircraft detected. A direction indicator control mechanism (18) is provided to operate the direction indicator light (LW), (
The direction indication control mechanism (
18), and the direction indicator lights (LW) and (RW) are controlled by the direction indicator control mechanism (18).
A human operating tool (
The human operating tools (9a), (9b) and the direction indicator control mechanism (18) are linked to the direction indicator lights (LW), (RW) in a state where priority is given to the turning operation by 9a), (9b). A direction indicator for a work vehicle. 2. Automatic cut-off means (19a) for restoring the human operating tools (9a) and (9b) to the cut-off position (OFF) so that they are in the cut-off position (OFF) when the aircraft is traveling straight;
19b).The direction indicating device for a working vehicle according to claim 1, further comprising: 19b).