JPH04110406U - Mounting structure of work equipment - Google Patents

Abstract

(57) [Summary] [Configuration] To removably attach the front loader device to the front of the tractor body, the control valves 26 and 27 of each cylinder for bucket tilting and boom lifting and lowering, and their operating levers 25 are set. Right mounting bracket A installed with
The loader device is attached to the fuselage via the left mounting bracket A and the left mounting bracket A, and the loader device is configured to be able to be attached to and removed from the fuselage either by itself or with the left and right mounting brackets A. [Effect] Drive operation unit (control valve) for attached work equipment
We provide a mounting structure for working equipment that can be used for multiple purposes and eliminates inconveniences such as mechanical waste and high costs.

Description

[Detailed explanation of the idea]

0001

[Industrial application field]

This invention can be detachably attached to work vehicles such as tractors and transport vehicles. The present invention relates to a mounting structure for a working device such as a front loader or a backhoe device.

0002

[Conventional technology]

This type of working device is mounted on a tractor shown in Japanese Utility Model Application Publication No. 1-74710. Like a front loader, a connecting support is attached to the mast members attached to the left and right sides of the aircraft. The front loader can be installed and removed by assembling and removing these mast members. It is detachable from the aircraft. And a control valve for bucket tilt with an operation lever. and a control valve for raising and lowering the boom are attached and fixed to the right mast member, and the front It was designed to be attached and detached together with the loader.

0003

[Problem that the idea aims to solve]

According to the above technology, the drive consisting of a control valve and its operating lever is activated by attaching and detaching the working device. The drive control section is also convenient because it can be attached and detached, but on the other hand, it is necessary to prepare a drive control section for each work device. This makes it difficult for users who change and use a wide variety of work equipment, and For homeowners, etc., duplication of the drive operation parts is mechanically wasteful and cost-effective. There was also an inconvenience that caused a burden on the client. The present invention aims to improve the above-mentioned disadvantages.

0004

[Means to solve the problem]

For the above purpose, the present invention provides a hydraulic cylinder to a self-propelled aircraft equipped with a hydraulic pump. When installing a working device as a drive means in a removable manner, a control for operating its hydraulic cylinder is required. A mounting bracket with a control valve is removably attached to the self-propelled aircraft. It is characterized in that the working device is removably attached to the top.

[0005]

[Effect] In other words, a control valve is always required for work equipment that uses a hydraulic cylinder as a driving means. From there, the work equipment can be attached to the machine via the mounting bracket with its control valve. This allows the mounting bracket to remain attached to the machine even when the implement is removed. This allows the control valve to be used for other work equipment. The mounting bracket itself is also removable from the aircraft, so if it is not needed The mounting bracket can also be removed to make the aircraft more nimble.

[0006]

[Effect of the idea]

Therefore, by using a structural design that allows the work equipment to be mounted via a mounting bracket, The drive operation unit can be used for the same purpose as the installation equipment, reducing mechanical waste and high costs. Therefore, it is possible to provide a mounting structure for a working device in which the above disadvantages are improved.

[0007]

【Example】

Embodiments of the present invention will be described below based on the drawings. Figure 4 shows an agricultural tractor. This agricultural tractor has approximately the entire length in the longitudinal direction of the machine. An engine 2 is mounted above the front of a pair of left and right fuselage frames 1, 1 extending over At the same time, a mission case 3 is installed at the rear of the aircraft, and the power from engine 2 is transferred to the mission. The structure is such that the power is supplied to the front and rear wheels 4 and 5 through the engine case 3 to drive the vehicle. A front loader device, which is an example of a working device, is attached to the section. Each of the fuselage frames 1, 1 has its rear side located lower than its front side, and Front wheels 4 equipped with a steering mechanism are formed by bending the intermediate connecting portions 7, 7 in a stepped manner. While maintaining the axle of By lowering it, it is configured to improve the handling stability of the aircraft.

[0008] Next, the connection structure of the front loader device 6 will be explained. Shown in Figures 1 and 2 As shown in FIG. A support member 9 made of bent material is horizontally connected, and this support member 9 is attached to each fuselage frame. It is made to protrude laterally from the frames 1, 1, and the rear part of the protruding parts 9a, 9a It is bent with the side facing upward. In other words, the support member 9 supports the fuselage frame 1, The plate material is bent along the lower surface of the intermediate connecting parts 7, 7 of 1, and is fixed by welding. At the same time, the inner edges of the upper rising parts of the protrusions 9a, 9a are connected to the fuselage frame 1, It is fixed by welding to the side of 1. The left and right protrusions 9a, 9a of this support member 9 Mounting brackets A and A for the front loader device 6 are attached and fixed to the front loader device 6.

[0009] To be more specific, the upwardly open U-shaped area formed in the protrusion 9a is downwardly opened. A reinforcing member 11 bent into an open U-shape is installed inside, and these are connected and fixed together. A box-shaped support frame structure is constructed. The connecting supports 10, 10 extend to the outer side of the fuselage, and have a flap on the upper surface of the outer end. Fixedly attach the insertion connectors 13, 13 of the masts 12, 12 of the rotoloader device 6. There is. The insertion connector 13 is a U-shaped frame 1 welded and fixed to the connector support 10. 3a is attached, and a wedge-shaped receiver 13b is attached to the inside, as well as a The lower end of the striker 12 is tapered to fit into the wedge-shaped receiver 13b.

0010 A connecting fixture 14 is fixed to the upper and lower intermediate positions of the left and right masts 12, and this The attachment 14 includes a pair of attachments that are supported and connected to the support portion 15 at the front end of the fuselage frame 1. The support arms 16, 16 are connected to each other. The front end of each support arm 16, 16 is They are connected by a connecting pipe 17, and this connecting pipe 17 is connected and supported by the support part 15. There is. As shown in FIG. Brackets 15a, 15a attached and fixed to the side, and brackets 15a, 15a It consists of seats 15b, 15b welded to the seats 15b, 15b, and the connection A pipe 17 is placed and connected with bolts. Also, a boom 18 of the front loader device 6 is pivotally supported at the upper end of the mast 12. A bracket plate 19 in the middle of the arm 18 and a pivot part 20 in the middle of the lower part of the mast 12 The lifting cylinder 21 of the boom 18 is connected to the bracket plate 19 and the bucket 22. Tilt cylinders 23 for tilting the buckets are connected to each other.

[0011] As shown in FIGS. 1 and 2, the right side connection support 10 has a mounting section made of a plate material. 24 is provided, and this mounting part 24 has an elevating system operated by a single operating lever 25. A control valve 26 for the cylinder 21 and a control valve 27 for the tilt cylinder 23 are installed. Ru. The supply and discharge hoses 28 of each cylinder 21 and 23 are connected to the hydraulic system on the aircraft side. A connecting hose 30 is connected to the control valves 26 and 27. In other words, the front loader device 6 is attached to the aircraft body via the left and right mounting brackets A, A. If the mast 12 is attached to another working device, attach the mast 12 to the mounting bracket. At the same time as attaching and detaching to A, attaching and detaching the supply and discharge hoses 28 of each cylinder 21 and 23. It performs operations.

0012 For reference, the hydraulic circuit of this tractor is shown in Figure 3, and 32 is the diagram provided at the rear of the machine. A lift cylinder for lifting and lowering the link mechanism (not shown), 33 is a rolling circuit section, 34 is a A control section, 35 is a front wheel speed increasing circuit section, and 36 is a hydraulic pump. 36 and the flow priority valve 37. 8 is a configuration in which the supply/discharge hose 30 on the pressure oil supply side is attached and detached.

[0013] In addition, in order to facilitate comparison with the drawings, symbols are written in the scope of claims for utility model registration. However, the present invention is not limited to the configuration shown in the attached drawings.

[Brief explanation of drawings]

[Figure 1] Overall side view showing the attachment/detachment structure of the work device

[Figure 2] Exploded perspective view of main parts showing the mounting structure of the mast and mounting bracket

[Figure 3] Hydraulic circuit diagram

[Figure 4] Side view of the tractor with the working equipment installed

[Explanation of symbols]

6 Working equipment 21 Hydraulic cylinder 26 Control valve 36 Hydraulic pump A Mounting block

Claims (1)

[Scope of utility model registration request] 1. In order to removably attach a working device (6) using a hydraulic cylinder (21) as a driving means to a self-propelled aircraft having a hydraulic pump (36),
1) A mounting bracket (A) equipped with a control valve (26) for operation is removably attached to the self-propelled aircraft, and the working device (6) is removably attached to this mounting bracket (A). Mounting structure of working equipment.