JPH08214673A - Cabin vibration-damping, supporting machine body structure for combine - Google Patents

Abstract

PURPOSE: To effectively damp vibration and support a cabin and to enable rise in rigidity of structure of a machine body behind the cabin. CONSTITUTION: A threshing part B and a cabin rear frame 4 of a rigid material to be connected to a chassis frame 3 at the lower part of a machine body are installed between a cabin A and a grain tank C. The upper rear part of the cabin A is connected through plural vibration damping rubber 5 to the upper part of the cabin rear frame 4. A rotary support 2 of the grain tank C is built on an engine room frame 6 at the front side of a rigid material laid on the chassis frame 3 at the front part of an engine room D. The tip of a longitudinal frame 7 of the grain tank fixed to the grain tank C and extended forward is detachably connected and fixed to the cabin rear frame 4.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a combine cabin vibration damping system which can limit the pitching and lateral wobbling of the cabin, can effectively support vibration damping, and can increase the rigidity of the body structure behind the cabin. Support structure.

[0002]

2. Description of the Related Art Conventionally, the lower side is behind a cabin supported by a rubber vibration isolator on the lower side, and the lateral direction of the threshing section is centered on the rotation fulcrum of the vertical axis. In a combine configured by deploying an openable Glen tank and arranging an engine room in the rear direction of the Glen tank, the cabin is only supported via a vibration isolating rubber below, and, Japanese Patent Laid-Open No. 5-25
As seen in Japanese Patent No. 2816, a machine body structure in which a threshing portion, a mounting frame for a driver's seat, and a frame side of an engine room are integrally connected to a frame body supported by the machine body frame is known.

[0003]

However, since the cabin is only supported by the vibration isolating rubber below,
When the aircraft suddenly turns or stops, the cabin shakes greatly, giving passengers a feeling of discomfort and danger, and hindering safe driving. Further, JP-A-5-252816 discloses In the airframe structure as shown in Fig. 1, since the driver's seat is integrally connected to the frame, there is a problem that the driver's seat cannot have a vibration isolation structure.

[0004]

SUMMARY OF THE INVENTION The present invention solves such a problem, can restrict the pitching and lateral wobbling of the cabin, can effectively support the vibration isolation, and can provide a fuselage structure behind the cabin. It is possible to increase the rigidity.Therefore, the lower side is behind the cabin that is supported by the lower vibration-proof rubber, and the lateral direction of the threshing part is the lateral outer side of the machine with the vertical fulcrum center In a combine that is configured by arranging a side-openable Glen tank and arranging an engine room in the rear direction of the Glen tank, the threshing unit and the chassis frame at the bottom of the fuselage are located between the cabin and the Glen tank. A rigid rear frame of the cabin connected to the upper rear part of the cabin and a plurality of anti-vibration rubbers on the upper part of the rear frame of the cabin. And a rigid front engine room frame that is erected on the chassis frame in the front part of the engine room and is provided with a rotation fulcrum of the Glen tank, and is fixed to the Glen tank and extends forward. The front end portions of the front and rear frames of the Glen tank are detachably connected and fixed to the rear frame of the cabin.

[0005]

Therefore, although the cabin is supported in a vibration-proof state by the vibration-proof rubber below, even if the aircraft suddenly turns or stops and shakes greatly, the cabin upper rear and the cabin behind it Pitching and lateral wobbling of the cabin are restricted by the multiple anti-vibration rubbers that are interposed between the upper part of the rear frame and the cabin, and the cabin is in a condition that is well-vibrated to prevent large swaying of passengers. ,
Also, with the Glen tank closed, the front part of the Glen tank connected to the engine room frame will be connected to the cabin rear frame that supports the upper rear part of the cabin. The rigidity of the airframe structure can be increased, and the structure can be robust and simple.

[0006]

EXAMPLE FIG. 1 is a perspective view schematically showing a part of a combine. A cabin A is provided on the right lateral side of the front part of the fuselage, which is behind the reaping section, and is behind the cabin A. A grain tank C is provided in the right lateral direction of the threshing section B, an engine room D is provided in the rear direction of the grain tank C, and the grain tank C is grained in the grain tank C from the threshing section B through the grain raising cylinder. Grains can be loaded, and the grain can be discharged to a vertical auger at the rear of the engine room D by a carry-out conveyor provided in the lower inside of the Glen tank C, and the grain can be discharged from the upper part of the vertical auger by a discharge auger. As in the conventional structure.

Further, U-shaped support metal fittings 8 are fixed downward at the four corners of the bottom surface of the cabin A,
A lower end portion 9a of an upstanding stay 9 is fixed to an upper surface portion of the chassis frame 3 below each supporting metal fitting 8, and a vibration-proof rubber is attached to a lateral supporting cylinder 9b provided above each stay 9. 1 inside each, and the anti-vibration rubber 1
Both sides of the support shaft 10 fitted into the center of the engine are mounted on the support fitting 8, while the front engine room frame 6 and the rear engine room frame 6a of the engine room D are connected by the connecting frame 11. At the same time, the one end portions 12, 12a of both engine room frames 6, 6a are fixed to the lateral side surface of the threshing portion B, and the other end side lower end portions 13, 13a are fixed to the upper surface of the chassis frame 3, respectively. Upper and lower support cylinders 14 and 14a are fixed to the upright portion on the outer side of the fuselage, and upper and lower support cylinders 15 and 15a are fixed to the rear right end of the Glen tank C to support the upper and lower supports. The cylinders 15, 14 and 15a, 14a are fitted with vertical axes that serve as rotation fulcrums 2, respectively, and the Glen tank C can be rotated around the fulcrums 2 and 2 to be side-opened laterally outward of the machine body. It is configured.

A post-cabin frame 4 is installed between the cabin A and the Glen tank C. The post-cabin frame 4 is a horizontal frame at the upper end of a vertical frame 4a which stands upright in a horizontal direction. One end side of 4b is connected and fixed to form an L-shape, the lower end 16 of the vertical frame 4a is fixed to the upper surface of the chassis frame 3, and a connecting plate provided on the other end side of the horizontal frame 4b. 17 is fixed to the inner surface of the threshing part B, and the upper rear part of the cabin A is connected to the upper part of the cabin rear frame 4 via a plurality of anti-vibration rubbers 5. C-shaped support fittings 19, 19 are fixed to both lateral side portions of the rear surface 18 so as to face rearward, and the upper surface portion of the horizontal frame 4b below the support fittings 19, 19 is fixed. Stood upright The lower end portion 20a of the tape 20 is fixed, respectively, the transverse direction of the support tube 2 provided on the top of both stays 20
0b is formed by mounting the anti-vibration rubber 5 on each side, and attaching both ends of the support shaft 21 fitted into the center of the anti-vibration rubber 5 to the support fittings 19 and 19, respectively.

On the outer surface of the Glen tank C on the outer side of the fuselage, there is fixedly mounted a front and rear frame 7 of the Glen tank extending horizontally from the portion of the support cylinder 15 forward from the front end of the Glen tank C. A screw hole 24 is provided at an intermediate portion of the vertical frame 4a so that a butterfly bolt 23 fitted into a hole 22 formed at the front end of the Glen tank front and rear frame 7 can be detachably inserted.

Incidentally, the means for detachably connecting and fixing the front end portions of the Glen tank front and rear frames 7 to the cabin rear frame 4 can be connected and fixed similarly to the wing bolt 23 of the embodiment. May be used.

Therefore, when performing maintenance and inspection on the inner side of the Glen tank C, as shown in FIG. 2, the butterfly bolts 23 are removed and the Glen tank C is rotated together with the front and rear frames 7 of the Glen tank. Although it can be opened sideways while rotating in the direction of arrow 2 toward the center of the center, the tip of the Glen tank front and rear frame 7 is attached to the cabin rear frame 4 via the wing bolts 23 at the time of combine work, as shown in FIG. The Glen tank C is connected and fixed, and the Glen tank C is closed and stored. In this state, the front portion of the Glen tank C connected to the rigid front engine room frame 6 supports the cabin rear frame 4 supporting the upper rear portion of the cabin A. Will be connected to the cabin rear frame 4 and the rear body structure can be increased in rigidity, It can be a simple fuselage structure in the prison.

The cabin A on which the driver rides is supported in a vibration-proof state by the four vibration-damping rubbers 1 below, but if the aircraft suddenly turns or stops and tries to shake greatly, the cabin A will be shaken. The pitching and the lateral wobbling of the cabin A are restricted by the both anti-vibration rubbers 5 and 5 interposed between the upper rear part of the cabin and the upper part of the cabin rear frame 4 behind the cabin A. The passengers will be able to drive safely, as they will be well-vibrated to prevent vibration.

[0013]

As described above, according to the present invention, the cabin A on which the driver rides is supported in a vibration-proof state by the vibration-proof rubber 1 below, but the body makes a sharp swing or stops, causing a large fluctuation. Even if it tries, the pitching and the lateral wobbling of the cabin A are restricted by the plurality of anti-vibration rubbers 5 interposed between the upper rear part of the cabin A and the upper part of the rear cabin frame 4 behind it. A is in a good vibration-proof state so that it does not shake greatly, and the passenger can drive safely. Further, when the Glen tank C is closed and stored, it is connected to the rigid front engine room frame 6. The front portion of the Glen tank C is connected to the cabin rear frame 4 supporting the upper rear portion of the cabin A via the Glen tank front and rear frames 7, and the cabin rear frame 4 will be behind the fuselage structure can be rigidity, it has an advantage that can suitably carried out can be robust and simple mechanical structure.

[Brief description of drawings]

FIG. 1 is a perspective view schematically showing a main part of an embodiment of the present invention.

FIG. 2 is a perspective view showing a main part where the Glen tank is side-opened.

FIG. 3 is a vertical sectional view showing a part of FIG.

FIG. 4 is a perspective view showing a part of FIG. 1 in an enlarged manner.

5 is a vertical cross-sectional view showing a part of FIG.

[Explanation of symbols]

 1 Anti-vibration rubber A Cabin B Threshing part 2 Rotation fulcrum C Glen tank D Engine room 3 Chassis frame 4 Cabin rear frame 5 Anti-vibration rubber 6 Engine room frame 7 Glen tank front and rear frames

─────────────────────────────────────────────────── ─── Continuation of the front page (51) Int.Cl. ⁶ Identification code Office reference number FI technical display location B62D 24/02 B62D 27/04 D

Claims (1)

[Claims] 1. The lower side is behind a cabin A supported via a rubber cushion 1 on the lower side, and in the lateral direction of the threshing section B, it is located laterally outward of the fuselage with a rotation fulcrum 2 on the vertical axis as the center. In a combine having a side-openable Glen tank C and an engine room D in the rear direction of the Glen tank C, the threshing section B and the body are provided between the cabin A and the Glen tank C. A rigid cabin rear frame 4 connected to the lower chassis frame 3 is erected, and an upper rear portion of the cabin A is connected to an upper portion of the cabin rear frame 4 via a plurality of anti-vibration rubbers 5. In the front part of the room D, the rotation front fulcrum 2 of the Glen tank C is provided on the rigid front engine room frame 6 which is erected on the chassis frame 3, and the Glen tank C is A cabin anti-vibration support body structure in which a front end portion of a front and rear frame 7 of a Glen tank which is fixed and extends forward is detachably connected to and fixed to the rear frame 4 of the cabin.