JPH029607Y2 - - Google Patents

Description

[Detailed description of the invention] In order to prevent the seedling planting depth from changing due to the ups and downs of the tiller, the present invention uses one or substantially one wheel and a pitching angle detector on the machine body. This invention relates to a wheel position correction device for a rice transplanter that is equipped with a control mechanism that automatically raises and lowers the float so as to maintain a substantially constant pitching posture based on information from the rice transplanter.

When the above-mentioned rice transplanter turns, the machine pitches by slightly lifting the control handle extended to the rear in order to reduce mud pushing by the float, but conventionally, pitching of the machine is directly detected. In the type where the wheels are raised and lowered relative to the aircraft, the automatic wheel elevation control continues to lift the aircraft during turns, causing the aircraft to become too high and the left-right balance of the aircraft to become unstable. On the other hand, with the type that indirectly detects the pitching of the aircraft by detecting the weight of the ground contact point, the automatic wheel lift control continues to lower the aircraft during the turn, and the aircraft tilts forward too steeply. The front end of the aircraft was more likely to plunge into the mud, making turning maneuvers difficult.

In view of the above-mentioned conventional situation, the purpose of this invention is to focus on the movement of the aircraft during turning operations, and to make it easier to perform turning operations through rational improvements that effectively utilize the movements of the aircraft. be.

The characteristic configuration of the present invention is that, in the rice transplanter mentioned above, there is a body rolling angle detector and a check mechanism that prevents the controller from raising and lowering the wheel relative to the float when the detected value by the rolling angle detector is higher than a set value. This is because there is a .

In other words, when making a turn, the general procedure is to first pitch the aircraft by lifting the handle without rolling the aircraft, and then roll the aircraft towards the inside of the turn. By providing a check mechanism that prevents the automatic lifting and lowering of the wheels by the controller, the vehicle can be moved until the end of the turn when the left-right tilt toward the inside of the turn is canceled without the need for special operations.
It is possible to reliably maintain the machine in a moderate forward-sloping posture that makes it easy to turn, making turning operations extremely easy with good weight balance and low mud resistance.As a result, work efficiency is improved. It has now become possible to effectively improve this and suppress work fatigue.

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

As shown in FIG. 1, a fuselage frame is provided with one propulsion wheel 1 at the center of the left and right sides of the fuselage, and a pair of left and right floats 2 with the longitudinal center slightly behind the propulsion wheel 1. A driving unit 4 is mounted on the front end of the slanted seedling tray 5 which moves back and forth horizontally at a constant stroke, and from the lower end row of two left and right pine-shaped seedlings placed on the slanted seedling tray 5. The rear part of the fuselage frame 3 is configured to double as a transmission case for a seedling planting device 7 equipped with various devices such as two seedling planting claws 6 for sequentially taking out seedlings one by one and planting them on the mud surface. Directly connected to, and further provided with a pair of left and right rearwardly extending control handles 8,
In other words, it is a walk-behind rice transplanter that plants two rows of seedlings as the machine moves.

In addition, 9 in the figure is a fuel tank, and even when the handle 8 is released and the aircraft stops traveling in a tilted forward position when replenishing seedlings, etc., the fuel tank 9
In order to smoothly supply fuel to the carburetor 11 of the engine 10, the lower surface of the tank 9 is positioned so that the entire fuel tank 9 is located above the carburetor 11 even in the forward tilted position, as shown in FIG. is formed in an inclined state with respect to the horizontal attitude of the aircraft.

The propulsion wheel 1 is configured to be able to be driven up and down with respect to both floats 2 in order to properly maintain the pitching attitude of the machine during planting travel, and the lifting and lowering structure thereof will be described in detail below.

As shown in FIG. 2, a wheel transmission case 12 supporting a wheel 1 at its lower end is attached to a horizontal support shaft 13 fixed to the front end of the fuselage frame 3.
The arm 14 is pivotally connected to the support shaft 13 while being integrally connected to the wheel transmission case 12, and is attached to the front and rear center portion of the fuselage frame ₃ so as to be swingable back and forth. Relay swing arm 1
5 are interlocked and connected by a rod 17 provided with an elongated hole flexible pin connection part 16, and a spring 18 for preventing rocking rattling of the wheel transmission case 12 is placed between the arm 14 and the relay rocking arm 15. The arms 14 and 15 are interposed in a tensioned and biased state, and the wheel 1 is provided with a ground cushioning function by the flexible action of the elongated hole 16a and the biasing action of the spring 18. be.

On the other hand, a cylindrical member that connects and supports a hydraulic motor 19 for driving the wheels up and down to the front end side of the fuselage frame 3, and that is screwed into a threaded rod 21 that is connected to the drive shaft of the motor 19 via a gear reducer 20. 22 is pivotally connected to the relay swinging arm 15;
By operating the motor 19 in the forward and reverse directions, the threaded rod 21 and the cylindrical member 22 are expanded and contracted, and the wheel transmission case 12
The wheels 1 are configured to be driven to swing up and down, and to drive the wheels 1 up and down.

Regarding the operation structure, as shown in FIGS. 2 and 3, the rotary spool type control valve 23 for the hydraulic motor 19 is connected to its spool operation shaft 23a.
is attached to the main body of the motor 19 in a state in which it protrudes horizontally to the left and right of the aircraft, and the arm 2 is attached to the operating shaft 23a.
A weight 25 is attached to the lower swing end of the arm 24 to rotate the operating shaft 23a through the arm 24 when the aircraft is in the proper rolling attitude.
is connected to the control valve 23 in a state in which it is operated to a neutral state, and the connecting rod portion 25a is connected to the arm 24.
A pivot connecting portion 25b that allows the weight 25 to swing around the longitudinal axis _P2 is interposed therein. Then, a horizontal locking pin 24a is fixed to the upper swinging end of the arm 24, and the upper swinging end of the arm 24 is engaged with the wheel lift operation lever 26 attached to the control handle 8. The locking pin 24a is interlocked and connected by a wire 28 through a connecting member 27 with an elongated hole 27a, and the connecting member 27 is pulled by the wire 28 in the opposite direction to the pulling operation direction. A spring 29 is attached to apply pressure.

The above-described operation structure is configured to obtain the following three operation states (a), (b), and (c).

(a) By operating the lever 26 to the automatic control position A of its guide hole 30 and holding the lever 26 at that position A by the biasing force of the spring 29,
The connecting member 27 is held in position so that the locking pin 24a of the arm 24 in the neutral state is located at the front and back center of the elongated hole 27a, and the weight 25 is prevented from pitching due to pitching of the machine body due to unevenness of the tiller. A state in which automatic rotation of the operating shaft 23a due to the action of its own weight is permitted through the flexible action of the elongated hole 27a, and automatic elevation control of the wheels 1 is permitted in order to maintain an appropriate rolling posture of the aircraft during traveling work.

(b) By operating the lever 26 to the fixed position N of the guide hole 30 and engaging the lever 26 in the guide hole notch 30b at that position against the spring 29, the arm 24 in the neutral state is engaged. The connecting member 27 is held in position with the stop pin 24a in contact with the end of the elongated hole 27a, and the rotation operation of the operating shaft 23a toward the wheel raising operation side due to the weight of the weight 25 is locked with the elongated hole 27a. A state in which the automatic lifting of the wheel 1 is inhibited by the contact and locking action of the pin 24a, and the automatic lifting of the wheel 1 is inhibited when traveling on the road or when the aircraft is stopped.

(c) By operating the lever 26 against the spring 29 to the wheel lowering position U of the guide hole 30,
With the locking action of the locking pin 24a and the end of the elongated hole 27a, the operating shaft 23a is forcibly rotated to the wheel lowering operation side, and the wheel 1 is forcibly lowered in order to raise the aircraft when traveling on the road or when the aircraft is stopped. situation.

These are the three operation states.

In addition, weight 25 due to pitching of the aircraft
A guide member 31 having an upwardly open "C" shape in cross section when viewed in the longitudinal direction is provided to guide the longitudinal swing of the aircraft. orientation axis
Connecting rod part 2 of weight 25 that swings around P ₂
A notch 31a is formed which engages with the connecting rod portion 25a and guides the weight 25 toward the neutral state side of the control valve 23 as the rolling inclination angle of the fuselage increases.

In other words, when the aircraft is turning, the weight 25 swings around the longitudinal axis P ₂ due to the rolling operation inward of the aircraft's turn in conjunction with the lift operation of the handle 8 to avoid mud pushing by the float 2. The automatic lifting and lowering operation of the wheel by the weight 25 is automatically prevented by the guide action of the notch 31a, and the automatic lifting and lowering of the wheel 1 due to the lifting operation of the handle 8 is automatically checked, and the aircraft is maintained at an appropriate level. It is configured so that it can easily and smoothly turn while maintaining a forward-sloping posture.

Incidentally, to detect pitching of the aircraft body, instead of using the weight 25 that swings back and forth, the pitching of the aircraft body may be detected by sensing changes in the ground load of the float 2 that swings up and down depending on the grounding state. , various configuration changes are possible, and these devices for pitching detection are collectively referred to as the aircraft pitching angle detector 25.

In addition, the specific control structure for raising and lowering the wheel 1 relative to the float 2 so as to maintain a substantially constant pitching attitude of the aircraft based on the information from the pitching angle detector 25, as well as the wheel raising and lowering structure, are subject to various configuration changes. In particular, the control structure thereof is collectively referred to as the control mechanism 23.

Furthermore, in order to detect rolling of the aircraft, instead of using the rolling detection weight 25 described above, various types of tilt detectors such as a pendulum type or a liquid level tilt detection type may be provided separately, and these detectors can be used for detection. These devices are collectively called the aircraft rolling angle detector.

The specific structure for preventing the controller 23 from raising and lowering the wheel 1 relative to the float 2 when the detected value of the body rolling detector is higher than the setting is as described above. Instead of a mechanical restraint structure such as providing a notch 31a that prevents the weight 25 from swinging back and forth due to the rolling of the weight 25, it is possible to apply various restraint structures such as an electric type or a hydraulic type. The check structures are collectively referred to as a check mechanism 31a.

The invention comprises one or substantially one wheel;
It also applies to various types of rice transplanters equipped with floats.

[Brief explanation of the drawing]

The drawings illustrate an embodiment of the wheel position correction device for a rice transplanter according to the present invention, in which Fig. 1 is an overall side view, Fig. 2 is an enlarged side view showing a wheel elevating structure, and Fig. 3 is a wheel elevating control structure. The perspective view and FIG. 4 are enlarged side views showing the fuel tank. DESCRIPTION OF SYMBOLS 1...Wheel, 2...Float, 23...Control mechanism, 25...Pitching angle detector, 31a...Check mechanism.

Claims (1)

[Scope of utility model registration request] A control mechanism 23 is provided for automatically raising and lowering one or substantially one wheel 1 relative to the float 2 so as to maintain a substantially constant pitching attitude of the aircraft based on information from an aircraft pitching angle detector 25. The rice transplanter is provided with a body rolling angle detector and a check mechanism 31a that prevents the controller 23 from lifting or lowering the wheel 1 relative to the float 2 when the detected value by the rolling angle detector is higher than a setting. A rice transplanter wheel position correction device featuring: