JPH10210848A - Machine body frame structure for work wagon - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a titled machine body frame structure useful for a combine or the like capable of securing strength, easily inserting a machine body center frame and improving the assemblability of a machine body frame by connecting the machine body center frame and plural side frames with each other. SOLUTION: A machine body right side frame 1 and a machine body left side frame 2 turned to a machine body front and back direction are provided and the plural side frames 3-7 turned to a machine body left and right direction are disposed and connected with prescribed intervals along the machine body front and back direction over the machine body right side frame 1 and the machine body left side frame 2. The machine body center frame 14 turned to the machine body front and back direction is passed through the plural side frames 3-7 and the machine body center frame 14 and the plural side frames 3-7 are connected to each other. Also, it is preferable to project the respective port edge parts 5b and 6b of an opening part in the same direction of a machine body front direction or a machine body rear direction.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a structure of a body frame of a working vehicle represented by a combine for agricultural work or the like.

[0002]

2. Description of the Related Art A body frame of a work vehicle is provided with a body right side frame and a body left side frame which are oriented in the longitudinal direction of the body, and a plurality of horizontal frames which are oriented in the body left and right direction.
In many cases, the body frame is formed in a ladder-like shape by connecting the body right side frame and the body left side frame at predetermined intervals along the body front-rear direction.

[0003]

When the body frame is configured as a ladder as described above, in order to increase the bending strength in the body front-rear direction, the body center frame facing the body front-rear direction is provided with a body right side frame and a vehicle right side frame. It is conceivable to provide between the left side frames of the aircraft. According to the present invention, in the work vehicle body frame structure configured as a ladder by the body right side frame, the body left side frame, and a plurality of side frames as described above, the body center frame as described above has sufficient strength. It is intended to be configured so that it can be prepared without waste.

[0004]

[Means for Solving the Problems]

[I] When the fuselage center frame is arranged between the fuselage right horizontal frame and the fuselage left horizontal frame, if the structure is such that the fuselage central frame is simply connected to the upper surface of the horizontal frame, the fuselage central frame protrudes above the fuselage frame. Therefore, when the engine and various working devices are mounted on the upper part of the body frame, the mounting may be difficult. Conversely, if the structure is such that the fuselage central frame is simply connected to the lower surface of the horizontal frame, the fuselage central frame protrudes below the fuselage frame, so that the minimum ground clearance as a work vehicle is reduced.

According to the first aspect of the present invention, the center frame of the fuselage is disposed so as to penetrate the plurality of horizontal frames, so that the center frame of the fuselage is located within the upper and lower ranges of the horizontal frame. The frame does not protrude above or below the horizontal frame. in this case,
Since the body center frame and the plurality of side frames are connected to each other instead of simply penetrating the body center frame through the plurality of side frames, strength near the body center frame and the side frames is ensured.

[II] According to the features of the second aspect, similar to the case of the first aspect, the "action" described in the above-mentioned [I] is provided, and in addition, the following "action" is provided. ing. According to the second aspect of the present invention, in the case where the fuselage central frame is made to penetrate through a plurality of horizontal frames, openings are formed in the plurality of horizontal frames so that the edge portions are bent and projected in a cylindrical shape, and the fuselage central frame is opened. Part. In this way, by bending the rim portion into a tubular shape at the opening, the strength near the opening of the horizontal frame is increased.

[III] According to the feature of claim 3, similarly to the case of claim 2, the "action" described in the above items [I] and [II] is provided. Has "action". When inserting the fuselage central frame into the opening where the lip is bent and projected into a tubular shape, it is easier to insert the fuselage central frame into the opening from the side opposite to the side where the lip protrudes, There is no such thing as the center frame of the body being hooked on the rim and being difficult to insert into the opening.

According to a third aspect of the present invention, when a plurality of horizontal frames are provided with openings whose mouth edges are bent and protruded in a cylindrical shape, each of the mouth edges of the openings is directed forward or rearward. It is projected in the direction. Thereby, when inserting the fuselage center frame across the openings of the plurality of horizontal frames, the fuselage center frame is inserted into the opening from the side opposite to the side from which the edge protrudes, so that the plurality of horizontal frames can be inserted. The center frame of the fuselage can be easily inserted without being caught over the opening of the frame.

[0009]

FIG. 1 shows an airframe of an agricultural combine, which is an example of a work vehicle, which is provided with an airframe right lateral frame 1 and an airframe left lateral frame 2 which are oriented in the longitudinal direction of the airframe. The first, second, third, fourth, and fifth horizontal frames 3, 4, 5, 6, and 7, which are directed in the directions, extend at predetermined intervals along the fuselage front-rear direction over the right body horizontal frame 1 and the left body horizontal frame 2. It is erected and connected.

The body right side frame 1 and the body left side frame 2 are formed in a U-shaped cross section, and the open sides face the left and right centers of the body so as to face each other. As shown in FIGS. 2 (a) and 2 (b), the first horizontal frame 3 is also formed in a U-shape in cross section, and the open side is set to face the rear of the body, and the front wall 3c is oblique in cross section. It is bent in a crank shape, and a rear part 3e of the upper wall part 3d is extended like an eave and bent obliquely downward. Both ends of the first horizontal frame 3 are butted and welded to the airframe right horizontal frame 1 and the airframe left horizontal frame 2.

As shown in FIGS. 1 and 2 (a) and (b),
The second to fifth horizontal frames 4 to 7 are formed in a U-shaped cross section,
The open sides of the second, fourth, and fifth horizontal frames 4, 6, and 7 are set to face the fuselage forward, and the open sides of the third horizontal frames 5 are set to face the fuselage backward. As shown in FIGS.
A body in which convex portions 8 are formed at both ends of the second to fifth horizontal frames 4 to 7 and rivet holes 12 are provided at lower portions of both ends, and both ends of the second to fifth horizontal frames 4 to 7 are connected. An elongated first welding hole 9, a second welding hole 10, and a rivet hole 11 are provided in the right lateral frame 1 and the body left lateral frame 2.

Thus, the second to fifth horizontal frames 4 to 7
Are inserted into the second welding holes 10 of the body right lateral frame 1 and the body left lateral frame 2, and the first and second welding holes 9, 10 are filled by welding to form rivet holes 11, 12.
The second to fifth horizontal frames 4 to 7 are erected and connected to the right lateral frame 1 and the left lateral frame 2 of the vehicle by attaching the rivets 13.

As shown in FIGS. 1 and 2 (a) and (b),
Openings 5a, 6a are formed in the left and right central portions of the body of the third and fourth horizontal frames 5, 6 by burring to bend the rims 5b, 6b into a cylindrical shape. 5b and 6b are set to the same forward direction. Round pipe-shaped fuselage center frame 14 facing the fuselage longitudinal direction
Are the openings 5a, 6a of the third and fourth horizontal frames 5, 6.
Are arranged so as to penetrate each other, and the side opposite to the edge portions 5b, 6b in the openings 5a, 6a of the third and fourth horizontal frames 5, 6 and the fuselage center frame 14 are mutually separated. Welded. Second and fifth horizontal frames 4,
7 does not have the above-described opening, and the fuselage center frame 14 is butted and welded to the second and fifth horizontal frames 4 and 7.

The combine body frame is configured as described above, and the entire body frame is reduced in weight while securing necessary strength. In this case, FIG.
, An engine (not shown) disposed on the front right side of the fuselage is installed on the right side of the first and second horizontal frames 3 and 4 (on the right side of the right lateral frame 1), and is disposed on the right side of the rear of the fuselage. The Glen tank (not shown) is located on the rear side of the right side frame 1 of the body, and the third, fourth, and fifth side frames 5, 6, and 7.
Is installed over the right side of the aircraft (the side of the right lateral frame 1). Threshing device (not shown) located on the rear left side of the fuselage
Are the rear side of the fuselage left lateral frame 2 and the third, fourth, fifth
Aircraft left side of horizontal frames 5, 6 and 7 (Aircraft left horizontal frame 2
Side).

As shown in FIG. 4, a pair of left and right support frames 15 in the form of a square pipe facing in the longitudinal direction of the body
The first support portion 16 and the second support portion 17 made of a sheet metal press are fixed to the support frame 15 and are connected to the lower surfaces of the horizontal frames 4 to 7. The combine includes a pair of right and left crawler traveling devices 18 as shown in FIG. 5, and the crawler traveling devices 18 are supported by the first and second support portions 16 and 17 of the support frame 15.

As shown in FIGS. 4 and 5, first and second
The support shaft 2 is attached to the boss portions 16a and 17a of the support portions 16 and 17.
2 is rotatably supported, an arm 22a fixed to the outer end of the support shaft 22 extends rearward of the fuselage, and an arm 22b fixed to the inner end of the support shaft 22 extends upwardly of the fuselage. I have. A link rod 23 is provided over the front and rear arms 22b, and a hydraulic cylinder 24 is connected to the arm 22b on the rear side of the fuselage. Crawler traveling device 1
8 is provided with a track frame 21 for supporting a plurality of rolling wheels 19 and a guide wheel 20, and ends of front and rear arms 22 a are pivotally connected to the track frame 21 to form driving wheels 25.
Are supported on the front side of the body of the first support portion 16, and a crawler 26 is wound around the driving wheel 25, the rolling wheel 19 and the guide wheel 20.

With the above structure, the track frame 21 can be moved up and down by driving the hydraulic cylinder 24 to expand and contract to drive the arm 22a up and down. Thus, by operating the left and right track frames 21 in the same direction, the height from the ground to the aircraft can be changed.
Can be changed in the opposite direction (by moving one track frame 21 up and down) to change the left-right angle of the aircraft with respect to the ground or to keep the aircraft horizontal on the inclined ground. .

[First Embodiment of the Invention] As shown in FIG. 6B, the first, second, and fifth horizontal frames 3, 4, and 7 are also provided with openings 3a, 4a, and 7a by burring. The forward edge 3b, 4b, 7b of the fuselage is provided to extend the fuselage center frame 14 to extend the first, second, fifth horizontal frames 3, 4, 7
May be inserted into the openings 3a, 4a, 7a. In this case, the sides opposite to the rims 3b to 7b and the fuselage center frame 14 are welded to the openings 3a to 7a of the first to fifth horizontal frames 3 to 7, respectively. Further, as shown in FIG. 6A, the third horizontal frame 5 is
As in the case of the 2, 4, 5 horizontal frames 3, 4, 6, 7, the open side may be set to the body forward.

Second Embodiment of the Invention As shown in FIG. 7, when the fuselage center frame 14 is extended to the first horizontal frame 3, the first horizontal frame 3 is attached to the first horizontal frame 3 as shown in FIGS. The airframe center frame 14 may be abutted and welded to the first horizontal frame 3 without providing the opening 3a as shown. In this case, since the engine (not shown) is installed on the right side of the first and second horizontal frames 3 and 4 (on the side of the right horizontal frame 1), the first and second horizontal frames 3 on the fuselage center frame 14 are arranged. , 4, the right side frame 1 side of the fuselage is recessed,
The configuration may be such that interference between the portion 14a and an engine (not shown) is avoided.

[Third Alternative Embodiment of the Invention] The connecting structure between the both ends of the second to fifth horizontal frames 4 to 7 and the body right side frame 1 and the body left side frame 2 is constructed as shown in FIG. May be. As shown in FIG. 8, the airframe right lateral frame 1 on which a heavy-weight Glen tank (not shown) is installed is configured to have a large vertical width (a large section modulus),
The left lateral frame 2 on which the relatively lightweight threshing device (not shown) is installed is configured to have a smaller vertical width than the right lateral frame 1. The first to second welding holes 9 and 10 and the rivet holes 11 as shown in FIGS. The end portions 27 of the frames 4 to 7 are bent to the open side, and the body left side frame 2 of the second to fifth side frames 4 to 7 is formed.
A slit 28 is provided on the side. Second to fifth horizontal frames 4 to
No rivet holes 12 are also provided in 7.

With the above structure, the ends 27 of the second to fifth horizontal frames 4 to 7 are inserted into the right lateral frame 1 and welded in the right lateral frame 1 as shown in FIG. In the fuselage left lateral frame 2, the end portions 27 of the second to fifth horizontal frames 4 to 7 are inserted into the fuselage left lateral frame 2, and the lower wall 2 a of the aircraft left lateral frame 2 is inserted into the slit 28 and welded. .

[Fourth Embodiment of the Invention] The right side frame 1 and the left side frame 2 and the second to fifth side frames 4 to 7 shown in FIGS. 1 to 8 shown in FIGS. The cross section may be formed to have a C-channel shape as shown in FIG. Also, the fuselage center frame 14 is not a round pipe,
It can be formed in the shape of a square pipe, or the first to fifth horizontal frames 3 to 7
The edge portions 3b to 7b may be set to face the rear of the aircraft.

[0023]

According to the first aspect of the present invention, in a work vehicle body frame structure formed of a ladder shape by a body right side frame, a body left side frame, and a plurality of side frames, while having sufficient strength. The center frame of the fuselage can be provided so that it does not protrude upward and downward from the fuselage frame, and it is difficult to mount the engine and various working devices on the upper part of the fuselage frame. Problems such as a decrease in ground clearance could be prevented beforehand.

According to the feature of claim 2, the "effect of the invention" of claim 1 is provided as in the case of claim 1. According to the second aspect of the present invention, by providing the opening portion of the horizontal frame through which the fuselage center frame penetrates and having the lip portion bent and projected in a cylindrical shape, the strength near the opening portion of the horizontal frame can be increased. In terms of security.

According to the feature of the third aspect, the "effect of the invention" of the first and second aspects is provided similarly to the case of the second aspect. According to the feature of the third aspect, by setting the rim of the opening to the same direction as the forward or rearward of the fuselage, the fuselage center frame can be easily inserted over the openings of the plurality of horizontal frames. As a result, the assemblability of the body frame could be improved.

[Brief description of the drawings]

FIG. 1 is an overall perspective view of an airframe.

FIG. 2 is a longitudinal sectional side view of the vicinity of an aircraft central frame.

FIG. 3 is a diagram showing a right lateral frame and a left lateral frame of the aircraft and a first frame.
Perspective view and longitudinal sectional front view showing a connection portion with the fifth to fifth horizontal frames.

FIG. 4 is an overall side view of the body frame.

FIG. 5 is an overall side view of the crawler traveling device.

FIG. 6 is a longitudinal sectional side view of the vicinity of an airframe center frame according to the first alternative embodiment of the present invention;

FIG. 7 is a plan view of the vicinity of a front portion of an airframe according to a second modification of the present invention;

FIG. 8 is a vertical sectional front view showing a connecting portion between a right lateral frame and a left lateral frame and first to fifth lateral frames according to a third different embodiment of the invention;

FIG. 9 is a sectional view of an airframe right lateral frame, an airframe left lateral frame, and first to fifth horizontal frames according to a fourth different embodiment of the present invention.

[Explanation of symbols]

 1 Aircraft right horizontal frame 2 Aircraft left horizontal frame 3,4,5,6,7 Horizontal frame 3a, 4a, 5a, 6a, 7a Opening 3b, 4b, 5b, 6b, 7b Edge 14 Aircraft center frame

Claims (3)

[Claims] An airframe includes a right lateral frame and a left lateral frame that are oriented in the longitudinal direction of the aircraft, and a plurality of lateral frames oriented in the lateral direction of the aircraft are arranged across the right lateral frame and the left lateral frame of the aircraft. At the same time, the aircraft center frame is oriented at a predetermined interval along the direction, and the fuselage central frame facing the fuselage longitudinal direction is penetrated across the plurality of horizontal frames, and the aircraft central frame and the plurality of horizontal frames are connected to each other. The body frame structure of the working vehicle. 2. A vehicle comprising a body right-side frame and a body left-side frame facing in the vehicle body front-rear direction, and a plurality of side frames facing in the body left-right direction, and At the same time, the plurality of horizontal frames are provided with an opening having an edge portion bent and projecting in a cylindrical shape, and the airframe central frame facing in the front-rear direction of the airframe is provided in the plurality of horizontal frames. The body frame structure of the working vehicle, wherein the body center frame and the opening are connected to each other so as to penetrate through each of the body frames. 3. Each of the rims of the opening is projected in the same direction, that is, forward or rearward.
The body frame structure of the described working vehicle.