JP5240838B2 - Cab support structure - Google Patents

Description

  The present invention relates to a cab support structure using an anti-vibration mount.

  The work machine shown in FIG. 4 is a hydraulic excavator 1, and in order to reduce the vibration generated during operation from being transmitted from the swing frame 2 to the cab 4 mounted together with the work device 3 on the swing frame 2, As shown in FIG. 5, a mount mounting portion 6 is provided on the support beam 5 on the revolving frame 2, and the cab 4 is elastically supported via a vibration-proof mount (not shown) installed on the mount mounting portion 6. A cab support structure is generally supported.

  The cab load during normal operation is supported by the anti-vibration mount, but it cannot be supported by the anti-vibration mount alone against the large load acting on the side of the cab 4 when the fuselage falls. If a large load is applied to the cab 4, There is a possibility that the cab 4 may be detached from the revolving frame 2 due to damage to the vibration-proof mount or the mount mounting portion 6.

  For this reason, work machines that work on sloping ground are required to have a Roll Over Protective Structure that protects the operator in the cab when the aircraft falls.

  As the occupant protection structure at the time of the fall, the fall control device that regulates the fall of the cab with respect to the swing frame is provided between the cab support portion of the swing frame and the base frame body of the cab, and the cushion clearance gap (See, for example, Patent Document 1).

In the overturning restricting device described in Patent Document 1, a mount mounting portion is provided at the center of a cross section of a support beam member fixed to a turning frame, and a lower portion of a cab is provided by a vibration-proof mount attached to the mount mounting portion. Is elastically supported, and a stopper bolt attached to the lower portion of the cab is provided through a clearance at the offset position of the cross section.
JP 2005-344394 A (page 13, FIG. 2 and FIG. 13)

  With the stopper bolts arranged at the offset position of the cross section of the support beam, when a large load is applied to the cab when the aircraft falls, the center of the cross section of the support beam is transferred from the cab to the support beam via the stopper bolt. Torsional load corresponding to the amount of offset from the surface acts, local stress is generated due to torsional deformation of the support beam material, the same part is damaged, and the anti-vibration mount and mount mounting part are damaged due to the lowering of the stopper bolt locking function There is a risk.

  The present invention has been made in view of the above points, and provides a cab support structure that can reliably prevent the vibration-proof mount and the mount mounting portion from being damaged when a large load is applied to the cab when the aircraft falls. Objective.

The invention described in claim 1 includes a fuselage frame on which a cab is mounted, a support beam member fixed to the fuselage frame, a mount attachment portion provided at a cross-sectional offset position of the support beam member, and a mount attachment portion. A cab support structure comprising: a vibration isolating mount that is elastically supported on the lower part of the cab, and a stopper that is disposed on the lower side of the center of the cross section of the support beam member via a clearance and attached to the lower part of the cab. The anti-vibration mounts are installed at four locations corresponding to the four corners of the cab, and the stoppers are installed at least in the vicinity of the anti-vibration mounts located outside the rear of the anti-vibration mounts arranged at the four locations. The mount mounting part is provided at the offset position of the cross section of the support beam with the stopper placed at the center of the cross section and deformed by the load transmitted from the stopper That is displaceable between the cab supporting structure according to the deformation of the support beam member.

請 Motomeko 2 invention described, the stopper in the cab supporting structure of claim 1 Symbol placement, so that the vibration damping mount is clearance 0 between the support beam member and the stopper by deformation region not irreversible The initial clearance adjustment is performed.

According to the first aspect of the present invention, when a large load is applied to the cab when the aircraft falls or the like, the load that cannot be supported by the vibration isolating mount alone is distributed and supported by both the stopper and the vibration isolating mount. This prevents damage to the anti-vibration mount and mount mounting part, prevents the cab from being detached due to breakage of the anti-vibration mount, and ensures sufficient rigidity for the stopper that supports the large load acting on the cab when the aircraft falls Since it is arranged at the center of the cross section of the support beam that can be supported, the torsional load that acts according to the offset amount from the center of the cross section of the support beam when the load acts on the support beam from the stopper can be reduced, and the support Prevents local parts caused by torsional deformation of the beam material from damaging the same part and deteriorating the stopper function, ensuring damage to the anti-vibration mount and mount mounting part. It can secure sufficient strength in both minimal reinforcement and thickness up can be prevented. In particular, if the support beam is deformed by the load transmitted from the stopper due to an excessive load such as a fall, the mount mounting part is displaced following the deformation of the support beam. It is possible to prevent the mounting portion from being damaged, and further, by preventing the vibration-proof mount and the mount mounting portion from being damaged, it is possible to disperse and support an excessive load such as during a fall by the vibration-proof mount and the stopper.

According to the invention described in 請 Motomeko 2, by anti-vibration mounts performs initial clearance adjustment as a stopper clearance in deformation areas not return to the original is in contact with the zero support beam members, vibration damping mount When an excessive load is applied, the load can be dispersed and supported by the stopper and the vibration-proof mount.

  Hereinafter, the present invention will be described in detail with reference to an embodiment shown in FIGS.

  As shown in FIGS. 1 and 2, a mounting bracket 10 for mounting the work device 3 (FIG. 4) is fixed to the revolving frame 2 as a body frame on which the cab 4 is mounted by welding or the like. At the same time, support beam members 11 for mounting the cab 4 are fixed by welding or the like, and the mount portions 12 are provided at four locations corresponding to the four corners of the cab 4 by the support beam members 11. A mounting hole 13 is opened in each 12.

  As shown in FIG. 2, the two rear mounting attachment portions 12 are provided in a cantilever structure at the offset position of the cross section of the support beam member 11 and can be displaced according to the deformation of the support beam member 11. On the other hand, a bolt insertion hole 14 for installing a stopper is provided in the central portion of the cross section of the support beam member 11 in the vicinity of the mount mounting portion 12 located outside the rear portion. A perforated reinforcing plate 15 is welded to the upper side of the bolt insertion hole 14.

  As shown in FIG. 1, vibration-proof mounts 16 that elastically support the lower portion of the cab 4 are attached to the mounting holes 13 of the mount mounting portions 12 at the four corners. As shown in FIG. 3, the anti-vibration mount 16 has a mount body 18 fixed to the upper surface of the support beam 11 by a mounting flange 17 and is elastically held by the mount body 18 so as to protrude from the mount body 18. 19 is inserted into the lower frame 4f of the cab 4 through the floor plate 21, and the lower frame 4f is fastened by a nut 22 that is screwed onto the screw shaft 19.

  As shown in FIG. 3, a stopper 23 attached to the lower frame 4 f of the cab 4 is disposed below the central portion of the cross section of the support beam member 11. The stopper 23 is attached to a spacer 24 welded to the lower frame 4 f of the cab 4 with screws 25. As a result, the stopper 23 that supports a large load is disposed at the center of the cross section of the support beam 11 that can ensure sufficient rigidity.

  When an excessive lateral load is applied when the machine falls, the load is distributed to each part of the machine frame according to the rigidity balance. In the cab support structure shown in FIG. 2, the load transmitted to the support beam member 11 on which the highly rigid rear mount is located is maximized. Therefore, the stopper 23 is installed in the vicinity of the outer rear mount.

  As shown in FIGS. 2 and 3, the mount mounting portion 12 provided together with the stopper 23 is provided in the cantilever structure portion 26 so as to be offset rearward from the support beam member 11. For this reason, when an excessive load is applied, such as when the aircraft falls, the support load by the stopper 23 is set to be larger than the support load by the anti-vibration mount 16 (the stopper load is larger than the mount load due to the rigidity balance). Become). As a result, even if an excessive load is applied, the load is supported by the stopper 23, and after being locked by the stopper 23, the mount mounting portion 12 is not deformed.

  As shown in FIG. 3, a stopper 23 attached to the lower portion of the cab 4 is disposed below the central portion of the cross section of the support beam member 11 via a clearance 27. This stopper 23 is adjusted in the initial stage so that the clearance 27 between the support beam 11 and the stopper 23 becomes 0 in the deformation region where the vibration isolating mount 16 does not return to the original position, and the support beam 11 comes into contact. By doing so, the optimal position is set.

  The anti-vibration mount 16 and the stopper 23 shown in FIG. 1 may be attached to the floor plate 21 integrated with the cab 4, but it is preferable to attach them directly to the lower frame 4 f of the cab 4.

  Next, the function and effect of this embodiment will be described.

  When a large load is applied to the cab 4 when the machine body falls or the like, the load is locked at the center of the cross section of the support beam member 11 in contact with the stopper 23. As a result, the cab 4 is locked by the stopper 23 to such an extent that the anti-vibration mount 16 is not broken even if it is plastically deformed, thereby preventing the cab 4 from being detached due to the anti-vibration mount 16 being broken.

  When the position of the stopper 23 is away from the center of the cross section of the support beam 11, a torsional load is applied to the support beam 11 according to the offset amount, but the stopper 23 is placed at the center of the cross section of the support beam 11. By arranging, the torsional load acting on the support beam member 11 through the stopper 23 can be reduced.

  By reducing the torsional load, local stress acting on the support beam member 11 and the support welded portion can be reduced. Since this local stress can be reduced, sufficient strength of the support beam member 11 can be ensured only by performing minimum reinforcement or increasing the plate thickness, and the cab 4 can be prevented from being detached due to the breakage of the support beam member 11.

  When a large load is applied, the mount mounting part 12 moves in accordance with the displacement / deformation of the support beam 11, so that excessive force acting on the anti-vibration mount 16 can be reduced, and the anti-vibration mount 16 breaks and the mount mounting part 12 Can also be prevented. That is, structurally, the mount mounting portion 12 is subordinate to the support beam member 11, and moves according to the displacement / deformation of the support beam member 11, so that the relief function works.

  Since breakage of the vibration isolating mount 16 and damage to the mount mounting portion 12 can be prevented, the load can be distributed and supported by both the stopper 23 and the vibration isolating mount 16. Further, it is structurally more advantageous to support the load in a distributed manner than to support the load only by the stopper 23. Similarly, since the anti-vibration mount 16 supports the load in a distributed manner, the load acting on the stopper 23 can be reduced, and the structure is advantageous for the strength design of the stopper 23.

  In this way, when a large load is applied to the cab 4 when the fuselage falls, a load that cannot be supported by the vibration isolating mount 16 alone is distributed and supported by both the stopper 23 and the vibration isolating mount 16, thereby preventing vibration. The stopper 16 that can prevent damage to the mount 16 and the mount mounting portion 12, can prevent the cab 4 from being detached due to breakage of the vibration-proof mount 16, and supports a large load acting on the cab 4 when the fuselage falls is sufficiently rigid. Is arranged at the center of the cross section of the support beam 11 so that when the load is applied to the support beam 11 from the stopper 23, the torsion acts according to the offset amount from the center of the cross section of the support beam 11. The load can be reduced and local stress caused by torsional deformation of the support beam 11 and the stopper function deterioration due to breakage of the same part can be prevented, and damage to the anti-vibration mount 16 and mount mounting part 12 is ensured. In addition, it is possible to ensure sufficient strength with minimal reinforcement and increased thickness.

  The anti-vibration mounts 16 installed at four locations corresponding to the four corners of the cab 4 are most susceptible to impact when the anti-vibration mounts 16 are located outside the rear when the aircraft falls, so the stopper 23 has four anti-vibration mounts. Providing the vibration mount 16 in the vicinity of the vibration isolation mount 16 located outside the rear part that can secure at least the rigidity to hold a large load at the time of the fall is effective for the occupant protection structure during the fall and the installation of the stopper 23 The number can also be minimized.

  When an excessive load is applied, such as when the machine falls, the clearance 27 of the stopper 23 becomes 0, and the support beam 11 is deformed by the load transmitted from the stopper 23. At this time, since the mount mounting portion 12 can be displaced following the deformation of the support beam member 11, damage to the anti-vibration mount 16 and the mount mounting portion 12 can be prevented. Breaks when exceeding. Further, by preventing the vibration isolating mount 16 and the mount mounting portion 12 from being damaged, it is possible to distribute and support an excessive load such as when the airframe falls over the vibration isolating mount 16 and the stopper 23.

  That is, since the mount mounting portion 12 is provided in a structure subordinate to the support beam material 11 on which the stopper 23 is installed, when the load is excessively loaded, the anti-vibration mount is changed according to the deformation of the support beam material 11. By moving 16, an excessive load acting on the vibration-proof mount 16 can be reduced, and breakage of the vibration-proof mount 16 and damage to the mount mounting portion 12 can be prevented.

  By adjusting the initial clearance so that the clearance 27 of the stopper 23 becomes 0 and comes into contact with the support beam 11 in the deformation region where the vibration isolating mount 16 does not return to its original shape, the anti-vibration mount 16 is prevented from being broken and excessively large. When a load is applied, the load can be distributed and supported by the vibration-proof mount 16 and the stopper 23.

  The present invention is applicable not only to a swing type hydraulic excavator but also to other work machines in which a cab is mounted on a non-turn type body frame via a vibration isolation mount.

It is a disassembled perspective view which shows one Embodiment of the cab support structure which concerns on this invention. It is a perspective view of the turning frame which concerns on a support structure same as the above. It is sectional drawing of a support structure same as the above. It is a side view of a hydraulic excavator. It is a perspective view of the revolving frame concerning the conventional cab support structure.

2 Revolving frame as the fuselage frame 4 Cab
11 Support beam
12 Mounting bracket
16 Anti-vibration mount
23 Stopper
27 Clearance

Claims (2)

The fuselage frame on which the cab is mounted,
Support beam material fixed to the fuselage frame,
Mount mounting portion provided at the offset position of the cross section of the support beam material,
An anti-vibration mount that is attached to the mount attachment and elastically supports the lower part of the cab;
In the cab support structure provided with a stopper disposed at the lower side of the cab and disposed below the central portion of the cross section of the support beam member via a clearance ,
Anti-vibration mounts are installed at four locations corresponding to the four corners of the cab,
The stopper is installed in the vicinity of the anti-vibration mount located at least outside the rear among the anti-vibration mounts arranged at four locations,
Mount mounting part is provided at the cross-section offset position of the support beam material with the stopper placed in the center of the cross section, and can be displaced according to the deformation of the support beam material deformed by the load transmitted from the stopper The cab support structure. The stopper is
Cab supporting structure according to claim 1 Symbol mounting clearance and performing initial clearance adjusted so as to be 0 between the support beam member and the stopper by deformation region where vibration damping mount does not return to the original.

Images