CN218713468U

CN218713468U - Mining excavator hood

Info

Publication number: CN218713468U
Application number: CN202222733025.5U
Authority: CN
Inventors: 朱宝山; 蒙小行; 白会群; 徐晓宇; 胡卫东; 宋诗峰; 刘虹
Original assignee: LOVOL Engineering Machinery Group Co Ltd
Current assignee: Lovol Heavy Industry Group Co ltd
Priority date: 2022-10-18
Filing date: 2022-10-18
Publication date: 2023-03-24
Anticipated expiration: 2032-10-18

Abstract

The utility model relates to an excavator covering technical field specifically is a mining excavator aircraft bonnet, including covering material and aircraft bonnet skeleton, the covering material is including the left side covering that covers and connect its left side limit and set up downwards. The left side covering is inboard to be equipped with the reinforcing plate of laminating on it, and the inboard middle part in its fore-and-aft direction of reinforcing plate is equipped with the first backup pad of perpendicular to left side covering, and left side covering includes the bodiness position of lower part. The weight of the left side skin is almost completely pressed on the lower part, only the lower part is thickened, and the reinforcing plate is arranged, so that the bearing capacity of the left side skin is effectively improved, and the weight of the whole left side skin cannot be excessively increased; the bearing capacity of aircraft bonnet has further been improved in setting up of first backup pad, and can effectively prevent that left side covering from warping, has ensured its stability in use and reliability. The setting of aircraft bonnet skeleton has improved the holistic bearing capacity of aircraft bonnet and stability in use, has ensured the reliability that the aircraft bonnet used.

Description

Mining excavator hood

Technical Field

The utility model relates to an excavator covering technical field specifically is a mining excavator aircraft bonnet.

Background

At present, the left side engine cover and the right side engine cover of the covering piece of the domestic excavator have poor bearing capacity and reliability, and the situations of deformation, welding and tearing and the like are easy to occur in the using process, and the main reasons for the situation are that the thickness of the engine cover skin material is small and the strength is poor; secondly, there is no support inside the left or right side hood.

Disclosure of Invention

The utility model aims at providing a mining excavator aircraft bonnet that bearing capacity is strong, stable in structure, stability in use are high to above problem.

In order to achieve the above object, the utility model discloses a mining excavator aircraft bonnet, including the skin material, the skin material includes the left side skin that the covering set up downwards and connect its left side limit. The left side covering inboard is equipped with the reinforcing plate of laminating on it, the inboard middle part at its fore-and-aft direction of reinforcing plate is equipped with the first backup pad of perpendicular to left side covering, left side covering includes the bodiness position of lower part. The weight of the left side skin is almost completely pressed on the lower part, only the lower part of the left side skin is thickened, and the reinforcing plate is arranged, so that the bearing capacity of the left side skin is effectively improved, and the weight of the whole left side skin cannot be excessively increased; the bearing capacity of aircraft bonnet has further been improved in setting up of first backup pad, and can effectively prevent that left side covering warp, has ensured its stability in use and reliability.

Preferably, the tip level in bodiness position is inwards extended the setting, and the tip is equipped with the support diaphragm that fits its upper surface under the bodiness position, first backup pad lower extreme is connected on supporting the diaphragm, has further strengthened the bearing capacity and the stability in use and the reliability of aircraft bonnet.

Preferably, the thickness of the thickened part on the left side skin is 2 times of the thickness of the rest part.

Preferably, the reinforcing plate is equipped with two that parallel around, the inboard of bodiness position is equipped with the second backup pad that is located between two reinforcing plates, the setting of second backup pad perpendicular to left side covering, second backup pad lower extreme is connected on supporting the diaphragm. The bearing capacity of the thickened part is enhanced by the second supporting plate, and the use stability and reliability of the hood are further enhanced.

Preferably, the covering material further comprises a front side covering, the upper side of the front side covering is connected with the front side of the top covering, and the left side of the front side covering is connected with the front side of the left side covering.

Preferably, still include the aircraft bonnet skeleton that is located the skin material, the aircraft bonnet skeleton includes: a first upper support cross bar, a second upper support cross bar, a third upper support cross bar and a fourth upper support cross bar which are respectively connected with the left side edge, the right side edge, the front side edge and the right side edge of the top skin; the upper end of the first support vertical rod is connected with the front end of the first upper support cross rod and the left end of the third upper support rod, and the upper end of the first support vertical rod is connected with the rear end of the first upper support cross rod and the second support vertical rod at the left end of the fourth upper support cross rod; the third supporting vertical rod is connected with the right side edge of the front side skin, and the upper end of the third supporting vertical rod is connected with the front end of the second upper supporting cross rod and the right end of the third upper supporting cross rod; the upper end is connected with the right end of the fourth upper supporting cross rod and a fourth supporting vertical rod at the rear end of the second upper supporting cross rod. The setting of aircraft bonnet skeleton has improved the holistic bearing capacity of aircraft bonnet and stability in use, has ensured the reliability that the aircraft bonnet used.

Preferably, the aircraft bonnet skeleton is still including the lower support horizontal pole of connecting left side skin lower limb, first support montant and second support montant lower extreme are connected respectively at both ends around the lower support horizontal pole. The structural stability of the hood framework is improved.

Preferably, the aircraft bonnet skeleton still includes the fifth support montant that is located between first support montant and the second support montant, first upper supporting horizontal pole and lower supporting horizontal pole are connected respectively at both ends about the fifth support montant. The structural stability of the hood framework at the left side skin part is further improved.

Preferably, the cross sections of the first upper supporting cross rod, the second upper supporting cross rod, the third upper supporting cross rod, the fourth upper supporting cross rod, the first supporting vertical rod, the second supporting vertical rod, the third supporting vertical rod, the fourth supporting vertical rod, the lower supporting cross rod and the fifth supporting vertical rod are all in a U-shaped structure. The integral stability of the hood framework is improved.

To sum up, the beneficial effects of the utility model reside in that: in the utility model, the weight of the left side skin is almost completely pressed on the lower part, only the lower part is thickened, and the reinforcing plate is arranged, so that the bearing capacity is effectively improved, and the weight of the whole left side skin cannot be excessively increased; the bearing capacity of aircraft bonnet has further been improved in setting up of first backup pad, and can effectively prevent that left side covering from warping, has ensured its stability in use and reliability. The setting of aircraft bonnet skeleton has improved the holistic bearing capacity of aircraft bonnet and stability in use, has ensured the reliability that the aircraft bonnet used.

Drawings

FIG. 1 is a schematic view of the structure of the coating material of the present invention;

FIG. 2 is an enlarged view of portion A of FIG. 1;

FIG. 3 is a schematic view of the hood framework of the present invention;

fig. 4 is a schematic structural diagram of the mining excavator hood of the present invention;

in the figure: 1. top covering, 2, left side covering, 2-1, bodiness position, 3, front side covering, 4, the reinforcing plate, 5, first backup pad, 6, the second backup pad, 7, first last supporting cross rod, 8, supporting cross rod on the second, 9, supporting cross rod on the third, 10, fourth last supporting cross rod, 11, first supporting montant, 12, second supporting montant, 13, third supporting montant, 14, fourth supporting montant, 15, fifth supporting montant, 16, lower supporting cross rod, 17, supporting transverse plate.

Detailed Description

The following detailed description of the embodiments of the present invention is provided with reference to the accompanying drawings and examples. The following examples are intended to illustrate the invention, but are not intended to limit the scope of the invention.

In the description of the present application, it is to be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, merely for convenience of description and simplicity of description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present application.

The terms "first", "second", "third", "fourth", "fifth" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implying any indication of the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless otherwise specified.

In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.

The following is a description of preferred embodiments of the present invention with reference to the accompanying drawings.

The utility model discloses a mining excavator aircraft bonnet, as shown in fig. 1-4, including covering material, covering material includes top covering 1 and connects the left side covering 2 of its left side limit downward setting. The inner side of the left side skin 2 is provided with a reinforcing plate 4 attached to the inner side of the left side skin, the middle part of the inner side of the reinforcing plate 4 in the front-back direction is provided with a first supporting plate 5 vertical to the left side skin 2, and the left side skin 2 comprises a thickening part 2-1 at the lower part. Furthermore, the thickness of the thickened part 2-1 on the left side skin 2 is 2 times of that of the rest parts. As shown in fig. 1 and 2, the lower end of the thickened portion 2-1 extends horizontally and inwardly, the lower end of the thickened portion 2-1 is provided with a supporting transverse plate 17 attached to the upper surface thereof, and the lower end of the first supporting plate 5 is connected to the supporting transverse plate 17.

As shown in fig. 1, the two reinforcing plates 4 are arranged in parallel front and back, a second supporting plate 6 is arranged between the two reinforcing plates 4 on the inner side of the thickened part 2-1, the second supporting plate 6 is arranged perpendicular to the left skin 2, and the lower end of the second supporting plate 6 is connected to a supporting transverse plate 17. The covering material further comprises a front side covering 3, the side edge of the front side covering 3 is connected with the front side edge of the top covering 1, and the left side edge of the front side covering 3 is connected with the front side edge of the left side covering 2.

As shown in fig. 3 and 4, the aircraft further comprises a hood framework located in the skin material, and the hood framework comprises: a first upper support cross bar 7, a second upper support cross bar 8, a third upper support cross bar 9 and a fourth upper support cross bar 10 which are respectively connected with the left side edge, the right side edge, the front side edge and the right side edge of the top skin 1; the upper end of the first vertical support rod 11 is connected with the front end of the first upper support cross rod 7 and the left end of the third upper support rod, and the upper end of the second vertical support rod 12 is connected with the rear end of the first upper support cross rod 7 and the left end of the fourth upper support cross rod 10; a third supporting vertical rod 13 connected with the right side edge of the front side skin 3, wherein the upper end of the third supporting vertical rod 13 is connected with the front end of the second upper supporting cross rod 8 and the right end of the third upper supporting cross rod 9; the upper end of the fourth supporting vertical rod 14 is connected with the right end of the fourth upper supporting cross rod 10 and the rear end of the second upper supporting cross rod 8; the lower supporting cross bar 16 is connected with the lower side edge of the left skin 2, and the front end and the rear end of the lower supporting cross bar 16 are respectively connected with the lower ends of the first supporting vertical bar 11 and the second supporting vertical bar 12; and a fifth support vertical rod 15 positioned between the first support vertical rod 11 and the second support vertical rod 12, wherein the upper end and the lower end of the fifth support vertical rod 15 are respectively connected with a first upper support cross rod 7 and a lower support cross rod 16.

For improving the stability of the hood framework, as shown in fig. 3, the cross sections of the first upper supporting cross rod 7, the second upper supporting cross rod 8, the third upper supporting cross rod 9, the fourth upper supporting cross rod 10, the first supporting vertical rod 11, the second supporting vertical rod 12, the third supporting vertical rod 13, the fourth supporting vertical rod 14, the lower supporting cross rod 16 and the fifth supporting vertical rod 15 are all U-shaped structures.

The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications and replacements can be made without departing from the technical principle of the present invention, and these modifications and replacements should also be regarded as the protection scope of the present invention.

Claims

1. The utility model provides a mining excavator aircraft bonnet, includes the covering material, the covering material includes top covering (1) and connects left side covering (2) that its left side limit set up downwards, a serial communication port, left side covering (2) inboard is equipped with reinforcing plate (4) on the laminating, reinforcing plate (4) inboard middle part at its fore-and-aft direction is equipped with first backup pad (5) of perpendicular to left side covering (2), left side covering (2) are including bodiness position (2-1) of lower part.

2. The mining excavator hood according to claim 1, characterized in that the lower end of the thickened part (2-1) extends horizontally and inwards, a supporting transverse plate (17) attached to the upper surface of the thickened part (2-1) is arranged at the lower end of the thickened part, and the lower end of the first supporting plate (5) is connected to the supporting transverse plate (17).

3. The mining excavator hood according to claim 1, characterized in that the thickness of the thickened portion (2-1) of the left side skin (2) is 2 times the thickness of the remaining portion.

4. The mining excavator hood according to claim 2, characterized in that the reinforcing plates (4) are arranged in two juxtaposed positions, a second supporting plate (6) is arranged between the two reinforcing plates (4) on the inner side of the thickened portion (2-1), the second supporting plate (6) is arranged perpendicular to the left side skin (2), and the lower end of the second supporting plate (6) is connected to the supporting transverse plate (17).

5. The mining excavator hood according to claim 1, characterized in that the skin material further comprises a front skin (3), the front skin (3) has an upper side connected to the front side of the top skin (1), and the front skin (3) has a left side connected to the front side of the left skin (2).

6. The mining excavator hood of claim 5, further comprising a hood framework located within the skin, the hood framework comprising:

a first upper supporting cross rod (7), a second upper supporting cross rod (8), a third upper supporting cross rod (9) and a fourth upper supporting cross rod (10) which are respectively connected with the left side edge, the right side edge, the front side edge and the right side edge of the top skin (1);

the upper end of the first supporting vertical rod (11) is connected with the front end of the first upper supporting cross rod (7) and the left end of the third upper supporting rod, and the upper end of the second supporting vertical rod (12) is connected with the rear end of the first upper supporting cross rod (7) and the left end of the fourth upper supporting cross rod (10);

a third supporting vertical rod (13) connected with the right side of the front side skin (3), wherein the upper end of the third supporting vertical rod (13) is connected with the front end of the second upper supporting cross rod (8) and the right end of the third upper supporting cross rod (9);

the upper end is connected with the right end of the fourth upper supporting cross rod (10) and a fourth supporting vertical rod (14) at the rear end of the second upper supporting cross rod (8).

7. The mining excavator hood according to claim 6, characterized in that the hood framework further comprises a lower support cross bar (16) connected with the lower side of the left side skin (2), and the front end and the rear end of the lower support cross bar (16) are respectively connected with the lower ends of the first support vertical bar (11) and the second support vertical bar (12).

8. The mining excavator hood according to claim 7, characterized in that the hood framework further comprises a fifth vertical support rod (15) between the first vertical support rod (11) and the second vertical support rod (12), and the upper end and the lower end of the fifth vertical support rod (15) are respectively connected with the first upper support cross rod (7) and the lower support cross rod (16).

9. The mining excavator cover according to claim 8, characterized in that the cross sections of the first upper support cross bar (7), the second upper support cross bar (8), the third upper support cross bar (9), the fourth upper support cross bar (10), the first support vertical bar (11), the second support vertical bar (12), the third support vertical bar (13), the fourth support vertical bar (14), the lower support cross bar (16) and the fifth support vertical bar (15) are all U-shaped structures.