Splicing type machine body and machine tool

Abstract

The utility model provides a splicing type machine body and a machine tool, the splicing type machine body comprises at least two sections of machine bodies and a splicing assembly, the machine bodies are provided with body sliding rails, and the at least two sections of machine bodies are sequentially arranged along the length direction of the body sliding rails; the fuselage has a splicing end face; the splicing assembly is used for connecting the two adjacent sections of machine bodies; the splicing assembly comprises a splicing sliding rail, the two ends of the splicing sliding rail are installed on the two adjacent machine bodies correspondingly, the splicing sliding rail is arranged between the body sliding rails on the two adjacent machine bodies, and the splicing sliding rail is used for connecting the body sliding rails on the two adjacent machine bodies. And the splicing sliding rails and the body sliding rails of the two adjacent sections of machine bodies jointly form a combined sliding rail capable of connecting the two sections of machine bodies. The two ends of the splicing sliding rail are installed on the two adjacent sections of the machine body respectively, meanwhile, the body sliding rails on the two adjacent sections of the machine body are connected, and therefore the coplanarity and connectivity of the sliding rail faces of the splicing machine body can be effectively guaranteed.

Description

Technical Field

[0001] The utility model belongs to the technical field of machine tools, and in particular relates to a spliced ​​machine body and a machine tool. Background Art

[0002] The machine body is the most basic part of CNC machine tools. Most of them are equipped with slide rails, etc. The workbench, processing robot and other processing equipment move on the machine body through the slide rails. The accuracy of the slide rails and rack mounting surfaces plays a decisive role in the accuracy and performance of the entire machine tool.

[0003] With the development of the industry, the processing parts are becoming more and more diversified. Among them, the processing demand for long profiles is also increasing. For example, it is necessary to process long profiles of more than ten meters or tens of meters. For this type of long profiles, specific large-scale processing machine tools are required. Although there is also a splicing process, that is, a method of splicing and combining multiple sections of the machine body to meet the processing needs of profiles of various lengths. However, the machine body of this type of spliced ​​long-stroke machine tool has high requirements for the accuracy of the machine body slide rail installation surface.

[0004] At present, although the existing technology provides a connection method of connecting two adjacent fuselage sections by using a connecting block so that the slide rails on the two adjacent fuselage sections are close to each other, thereby realizing the connection of the slide rails on each fuselage section, but in actual use, since the end surface of the slide rail of each fuselage section is flush with the splicing end surface of the fuselage, and the cross-section and weight of each fuselage section are large, although the tightness of the connection point can be ensured by only using a connecting block, it is still difficult to ensure the tightness of the connection at the spliced ​​fuselage slide rail. Utility Model Content

[0005] In order to overcome the shortcomings of the prior art, the utility model provides a spliced ​​fuselage and a machine tool to solve the problem in the prior art that the end surfaces of the slide rails of each section of the fuselage are flush with the splicing end surfaces of the fuselage, and the cross-section and weight of each section of the fuselage cannot ensure the tightness of the connection of the slide rail surfaces of the spliced ​​fuselage.

[0006] One embodiment of the utility model provides a spliced ​​fuselage, comprising:

[0007] At least two sections of the fuselage, the fuselage is equipped with a main body slide rail, and the at least two sections of the fuselage are arranged in sequence along the length direction of the main body slide rail; the fuselage has a splicing end face, and a preset distance is set between the terminal end face of the main body slide rail and the splicing end face;

[0008] A splicing assembly, used to connect two adjacent fuselage sections; wherein the splicing assembly includes a splicing slide rail, both ends of which are respectively mounted on two adjacent fuselage sections, and the splicing slide rail is arranged between the main body slide rails on the two adjacent fuselage sections, and the splicing slide rail is used to connect the main body slide rails on the two adjacent fuselage sections;

[0009] The splicing slide rail and the main body slide rails of two adjacent fuselage sections together form a combined slide rail capable of connecting the two fuselage sections.

[0010] In one embodiment, the cross-sectional outer contour shape of the spliced ​​slide rail is the same as the cross-sectional outer contour shape of the main body slide rail; wherein the outer surface of the spliced ​​slide rail in the combined slide rail and the corresponding outer surface of the main body slide rail in the combined slide rail are arranged in the same plane or are within a preset flatness range.

[0011] In one embodiment, a main body rack is further installed on the fuselage, and a preset distance is set between the end face of the terminal end of the main body rack and the splicing end face;

[0012] The splicing assembly also includes a splicing rack, the two ends of which are respectively mounted on two adjacent sections of the fuselage, and the splicing rack is arranged between the main body racks on the two adjacent sections of the fuselage, and the splicing rack is used to connect the main body racks on the two adjacent sections of the fuselage;

[0013] The spliced ​​rack and the main racks of the two adjacent fuselage sections together form a combined rack capable of connecting the two fuselage sections.

[0014] In one of the embodiments, the splicing end surface is provided with a groove;

[0015] Alternatively, a splicing end surface of one section of the fuselage is provided with a groove, and a splicing end surface of the fuselage adjacent to the one section of the fuselage is provided with a boss that matches the groove.

[0016] In one of the embodiments, the splicing assembly further includes a splicing unit, and the top surface and both side surfaces of two adjacent fuselage sections are provided with the splicing unit.

[0017] In one embodiment, the splicing unit includes:

[0018] A fixing seat, the fixing seat being installed on the splicing end of the fuselage;

[0019] A first fastener is used to connect the fixing seats on two adjacent fuselage sections;

[0020] a second fastener;

[0021] The first assembling piece has two ends connected to fixing seats on two adjacent fuselage sections respectively through the second fasteners.

[0022] In one embodiment, two ends of the first splicing piece are respectively a first connecting end and a second connecting end, and a width of the first connecting end is smaller than a width of the second connecting end.

[0023] In one embodiment, the first splicing piece is in a "T" shape.

[0024] In one embodiment, the fixing seat comprises:

[0025] A first mounting seat is provided with a first groove matched with the first connecting end, the first connecting end is installed in the first groove, and the first mounting seat is connected to the first connecting end;

[0026] A second mounting seat is provided with a second groove matched with the second connecting end, the second connecting end is installed in the second groove, and the second mounting seat is connected to the second connecting end;

[0027] Wherein, the first mounting seat and the second mounting seat are respectively mounted on the splicing ends of two adjacent fuselage sections.

[0028] One embodiment of the utility model further provides a machine tool, comprising a spliced ​​machine body as described in any one of the above items.

[0029] The spliced ​​machine body and machine tool provided in the above embodiments have the following beneficial effects:

[0030] By setting a preset distance between the end face of the main body slide rail and the splicing end face, and respectively installing the two ends of the splicing slide rail on two adjacent fuselage sections, and connecting the main body slide rails on the two adjacent fuselage sections, at this time, the splicing slide rail and the main body slide rails of the two adjacent fuselage sections together form a combined slide rail that can connect the two fuselage sections, thereby effectively ensuring the coplanarity and connection tightness of the splicing fuselage slide rail surface, thereby improving working stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0032] Figure 1 A schematic diagram of the structure of a spliced ​​fuselage provided in an embodiment of the utility model;

[0033] Figure 2 for Figure 1 A partial enlarged schematic diagram of the spliced ​​fuselage at A;

[0034] Figure 3 for Figure 1 A partial enlarged schematic diagram of a splicing portion of a spliced ​​fuselage;

[0035] Figure 4 for Figure 2 An enlarged schematic diagram of the B region of the spliced ​​fuselage;

[0036] Figure 5 It is a three-dimensional schematic diagram of the splitting of two sections of the spliced ​​fuselage;

[0037] Figure 6 for Figure 5 A partial enlarged schematic diagram of the C portion of the spliced ​​fuselage;

[0038] Figure 7 It is a schematic diagram of the right side view of the spliced ​​fuselage.

[0039] Figure numbers: 1, body, 11, main body slide rail, 12, splicing end face, 121, groove, 13, main body rack, 2, splicing assembly, 21, splicing slide rail, 22, splicing unit, 221, fixing seat, 221-1, first mounting seat, 221-2, second mounting seat, 222, first fastener, 223, second fastener, 224, first splicing piece, 23, splicing rack, 3, combined slide rail, 4, combined rack. DETAILED DESCRIPTION

[0040] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0041] It should be noted that if the embodiments of the present invention involve directional indications (such as up, down, left, right, front, back...), the directional indications are only used to explain the relative position relationship, movement status, etc. between the components in a certain specific posture. If the specific posture changes, the directional indications will also change accordingly.

[0042] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the utility model, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features limited to "first" and "second" may explicitly or implicitly include at least one of the features. In addition, if "and / or" or "and / or" appears in the full text, its meaning includes three parallel solutions. Taking "A and / or B" as an example, it includes solution A, solution B, or solutions that satisfy both A and B. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the utility model.

[0043] See also Figure 1-7 One embodiment of the utility model provides a spliced ​​fuselage 1, comprising:

[0044] At least two sections of the fuselage 1, on which a main body slide rail 11 is installed, and at least two sections of the fuselage 1 are arranged in sequence along the length direction of the main body slide rail 11; the fuselage 1 has a splicing end surface 12, and a preset distance is set between the end end surface of the main body slide rail 11 and the splicing end surface 12;

[0045] The splicing assembly 2 is used to connect two adjacent fuselage sections 1 so that the splicing end surfaces 12 of the two adjacent fuselage sections 1 are close to or close to each other; wherein the splicing assembly 2 includes a splicing rail 21, both ends of which are respectively installed on the two adjacent fuselage sections 1, and the splicing rail 21 is arranged between the main body rails 11 on the two adjacent fuselage sections 1, and the splicing rail 21 is used to connect the main body rails 11 on the two adjacent fuselage sections 1;

[0046] The splicing rail 21 and the main body rails 11 of two adjacent fuselage sections 1 together form a combined rail 3 that can connect the two fuselage sections 1 .

[0047] In this embodiment, a preset spacing is set between the end face of the main body slide rail 11 and the splicing end face 12, and the two ends of the splicing slide rail 21 are respectively installed on the two adjacent fuselage sections 1, and at the same time, the main body slide rails 11 on the two adjacent fuselage sections 1 are connected. At this time, the splicing slide rail 21 and the main body slide rails 11 of the two adjacent fuselage sections 1 jointly form a combined slide rail 3 that can connect the two fuselage sections 1, thereby effectively ensuring the coplanarity and connection tightness of the slide rail surface of the spliced ​​fuselage 1, thereby improving the working stability.

[0048] The total number of sections of the fuselage 1 is M, and the total number of the splicing components 2 is N, where M≥2 and N=M-1. Figure 1 As shown, when the total number of fuselage sections is 2, the total number of splicing components 2 is 1.

[0049] See also Figure 2 In one embodiment, the cross-sectional outer contour shape of the splicing rail 21 is the same as the cross-sectional outer contour shape of the main body rail 11, and the length of the splicing rail 21 is twice the preset spacing; wherein the outer surface of the splicing rail 21 in the combined slide rail 3 and the corresponding outer surface of the main body rail 11 in the combined slide rail 3 are arranged in the same plane.

[0050] In this embodiment, since the cross-sectional outer contour shape of the splicing slide rail 21 is consistent with the cross-sectional outer contour shape of the main body slide rail 11, that is, the shapes of the end faces that are attached to each other are consistent, it is ensured that the slider can slide smoothly on the splicing slide rail 21 and the main body slide rail 11 to ensure the stability of the processing. At the same time, the length of the splicing slide rail 21 is twice the preset spacing, that is, the two end faces of the splicing slide rail 21 can stably and accurately fit the end faces of the main body slide rail 11 on the two adjacent sections of the fuselage 1, so as to connect the main body slide rails 11 on the two adjacent sections of the fuselage 1, thereby effectively ensuring the coplanarity and connectivity of the slide rail surface of the spliced ​​fuselage 1 to improve the working stability.

[0051] As required, the splicing rail 21 is configured identically to a section of the main body rail 11 to ensure that it can be connected to the main body rail 11 , that is, the combined rail 3 is an extended main body rail 11 .

[0052] As required, the main body slide rail 11 and the splicing slide rail 21 are connected to the fuselage 1 through fasteners to facilitate the installation of the slide rails and to facilitate the coplanarity adjustment of the main body slide rail 11 and the splicing slide rail 21 .

[0053] See also Figure 2 In one embodiment, a main body rack 13 is further installed on the fuselage 1, and a preset distance is set between the end face of the main body rack 13 and the splicing end face 12;

[0054] The splicing assembly 2 further includes a splicing rack 23, the two ends of which are respectively mounted on two adjacent fuselage sections 1, and the splicing rack 23 is arranged between the main body racks 13 on the two adjacent fuselage sections 1, and the splicing rack 23 is used to connect the main body racks 13 on the two adjacent fuselage sections 1;

[0055] The splicing rack 23 and the main racks 13 of the two adjacent fuselage sections 1 together form a combined rack 4 that can connect the two fuselage sections 1 .

[0056] In this embodiment, a preset spacing is set between the terminal end face of the main body rack 13 and the splicing end face 12, and the two ends of the splicing rack 23 are respectively installed on the two adjacent fuselage sections 1, and at the same time, the main body racks 13 on the two adjacent fuselage sections 1 are connected. At this time, since the splicing rack 23 and the main body racks 13 of the two adjacent fuselage sections 1 jointly form a combined rack 4 that can connect the two fuselage sections 1, the coplanarity and connectivity of the rack surface of the spliced ​​fuselage 1 can be effectively guaranteed to improve the working stability, and the working performance with the processing mechanism can be further improved through the combined rack 4.

[0057] It can be understood that the outer contour shape of the spliced ​​rack 23 is the same as the outer contour shape of the main rack 13, that is, the tooth shape, tooth pitch, etc. are the same, or the same as one section of the main rack 13, to ensure that it can be connected to the main rack 13, and the straight teeth of the combined rack 4 formed after the connection are the same and equidistantly arranged, that is, the combined rack 4 is an extended main rack 13.

[0058] Since the cross-sectional outer contour shape of the splicing rack 23 is consistent with the cross-sectional outer contour shape of the main body rack 13, the splicing continuity of the splicing rack 23 and the main body rack 13 is ensured, and the stability of the processing is ensured. At the same time, the length of the splicing rack 23 is twice the preset spacing, that is, the two end faces of the splicing rack 23 can stably and accurately fit the end faces of the main body rack 13 on the two adjacent sections of the fuselage 1, so as to connect the main body racks 13 on the two adjacent sections of the fuselage 1, and the top surface of the splicing rack 23 in the combined rack 4 and the corresponding top surface of the main body rack 13 in the combined rack 4 are arranged in the same plane, thereby effectively ensuring the coplanarity and connectivity of the rack surface of the spliced ​​fuselage 1 to improve the working stability.

[0059] As required, the main body rack 13 and the spliced ​​rack 23 are connected to the fuselage 1 through fasteners to facilitate rack installation and coplanar adjustment of the main body rack 13 and the spliced ​​rack 23.

[0060] In one embodiment, see Figure 5-6 The splicing end surface 12 is provided with a groove 121; when two adjacent sections of the fuselage 1 are spliced, the groove 121 of the two adjacent sections of the fuselage 1 can reduce the contact area of ​​the two fuselages 1, reduce the repulsive force, and thus enhance the connectivity.

[0061] Alternatively, the splicing end face 12 of one section of the fuselage 1 is provided with a groove 121, and the splicing end face 12 of the fuselage 1 adjacent to the one section of the fuselage 1 is provided with a boss that matches the groove 121. When two adjacent sections of the fuselage 1 are spliced, the groove 121 and the boss of the two adjacent sections of the fuselage 1 cooperate to prevent the two fuselages 1 from moving around, thereby enhancing connectivity.

[0062] See also Figure 4 , 7 In one of the embodiments, the splicing assembly 2 further includes a splicing unit 22, and the top surface and both side surfaces of two adjacent fuselage sections 1 are provided with the splicing unit 22.

[0063] In this embodiment, by arranging the splicing units 22 on the top surface and the two side surfaces of two adjacent fuselage sections 1, the two adjacent fuselage sections 1 can be connected in multiple directions, thereby improving the overall connectivity and stability.

[0064] See also Figure 4 , 7 In one embodiment, the splicing unit 22 includes:

[0065] A fixing seat 221, wherein the fixing seat 221 is installed on the splicing end of the fuselage 1;

[0066] The first fastener 222 is used to connect the fixing seats 221 on two adjacent sections of the fuselage 1;

[0067] A second fastener 223;

[0068] The first assembling piece 224 has two ends connected to the fixing seats 221 on two adjacent sections of the fuselage 1 through the second fasteners 223 .

[0069] In this embodiment, by installing a fixing seat 221 on the splicing end of the fuselage 1, connecting the fixing seats 221 on two adjacent fuselage sections 1 through a first fastener 222, and connecting the first splicing piece 224 to the fixing seats 221 of the two adjacent fuselage sections 1 through a second fastener 223, a multiple-mode reinforcement connection of the two adjacent fuselage sections 1 is achieved, thereby improving the overall connectivity and stability.

[0070] It can be understood that the first fastener 222 and the second fastener 223 can be bolts.

[0071] See also Figure 4 In one embodiment, two ends of the first splicing piece 224 are respectively a first connecting end and a second connecting end, and the width of the first connecting end is smaller than the width of the second connecting end.

[0072] In this embodiment, since the width of the first connecting end is smaller than the width of the second connecting end, the connectivity between two adjacent sections of the fuselage 1 can be further enhanced.

[0073] See also Figure 4 In one embodiment, the first splicing piece 224 is in a "T" shape to improve the connection strength and stability.

[0074] See also Figure 4 , 7 In one embodiment, the fixing seat 221 includes:

[0075] The first mounting seat 221-1 is provided with a first groove matched with the first connecting end, the first connecting end is installed in the first groove, and the first mounting seat 221-1 is connected to the first connecting end;

[0076] The second mounting seat 221-2 is provided with a second groove matched with the second connecting end, the second connecting end is installed in the second groove, and the second mounting seat 221-2 is connected to the second connecting end;

[0077] The first mounting seat 221 - 1 and the second mounting seat 221 - 2 are respectively mounted on the joint ends of two adjacent sections of the fuselage 1 .

[0078] In this embodiment, by installing the first mounting seat 221-1 and the second mounting seat 221-2 on the splicing ends of the two adjacent sections of the fuselage 1 respectively, and by providing the first groove and the second groove corresponding to the first connecting end and the second connecting end of the first splicing piece 224 on the first mounting seat 221-1 and the second mounting seat 221-2, the connectivity between the first splicing piece 224 and the first mounting seat 221-1 and the second mounting seat 221-2 is improved, so as to realize the integrated setting of the first splicing piece 224 and the first mounting seat 221-1 and the second mounting seat 221-2, enhance the connection strength of the two adjacent sections of the fuselage 1, and ensure the working stability.

[0079] like Figure 5-6 , the dotted line is a schematic diagram of the connection path when the first fastener 222 connects the first mounting seat 221-1 and the second mounting seat 221-2.

[0080] One embodiment of the utility model further provides a machine tool, comprising a spliced ​​machine body 1 as described in any one of the above items.

[0081] The above description is only a preferred embodiment of the utility model, and does not limit the patent scope of the utility model. All equivalent structural changes made by using the contents of the utility model specification and drawings under the utility model concept, or directly / indirectly used in other related technical fields are included in the patent protection scope of the utility model.

Claims

1. A spliced ​​fuselage, characterized in that: include: At least two sections of the fuselage, the fuselage is equipped with a main body slide rail, and the at least two sections of the fuselage are arranged in sequence along the length direction of the main body slide rail; the fuselage has a splicing end face, and a preset distance is set between the terminal end face of the main body slide rail and the splicing end face; A splicing assembly, used to connect two adjacent fuselage sections; wherein the splicing assembly includes a splicing slide rail, both ends of which are respectively mounted on two adjacent fuselage sections, and the splicing slide rail is arranged between the main body slide rails on the two adjacent fuselage sections, and the splicing slide rail is used to connect the main body slide rails on the two adjacent fuselage sections; The splicing slide rail and the main slide rails of two adjacent fuselage sections together form a combined slide rail capable of connecting the two fuselage sections.

2. The spliced ​​fuselage according to claim 1, characterized in that: The cross-sectional outer contour shape of the spliced ​​slide rail is the same as the cross-sectional outer contour shape of the main body slide rail; wherein, the outer surface of the spliced ​​slide rail in the combined slide rail and the corresponding outer surface of the main body slide rail in the combined slide rail are arranged in the same plane.

3. The spliced ​​fuselage according to claim 1, characterized in that: A main body rack is also installed on the fuselage, and a preset distance is set between the end face of the terminal end of the main body rack and the splicing end face; The splicing assembly also includes a splicing rack, the two ends of which are respectively mounted on two adjacent sections of the fuselage, and the splicing rack is arranged between the main body racks on the two adjacent sections of the fuselage, and the splicing rack is used to connect the main body racks on the two adjacent sections of the fuselage; The spliced ​​rack and the main racks of the two adjacent fuselage sections together form a combined rack capable of connecting the two fuselage sections.

4. The spliced ​​fuselage according to claim 1, characterized in that: The splicing end surface is provided with a groove; Alternatively, a splicing end surface of one section of the fuselage is provided with a groove, and a splicing end surface of the fuselage adjacent to the one section of the fuselage is provided with a boss that matches the groove.

5. The spliced ​​fuselage according to any one of claims 1 to 4, characterized in that: The splicing assembly further comprises a splicing unit, and the top surface and both side surfaces of two adjacent fuselage sections are provided with the splicing unit.

6. The spliced ​​fuselage according to claim 5, characterized in that: The splicing unit comprises: A fixing seat, the fixing seat being installed on the splicing end of the fuselage; A first fastener is used to connect the fixing seats on two adjacent fuselage sections; a second fastener; The first assembling piece has two ends connected to fixing seats on two adjacent fuselage sections respectively through the second fasteners.

7. The spliced ​​fuselage according to claim 6, characterized in that: Two ends of the first splicing piece are respectively a first connecting end and a second connecting end, and a width of the first connecting end is smaller than a width of the second connecting end.

8. The spliced ​​fuselage according to claim 7, characterized in that: The first splicing piece is in a "T" shape.

9. The spliced ​​fuselage according to claim 7, characterized in that: The fixing seat comprises: A first mounting seat is provided with a first groove matched with the first connecting end, the first connecting end is installed in the first groove, and the first mounting seat is connected to the first connecting end; A second mounting seat is provided with a second groove matched with the second connecting end, the second connecting end is installed in the second groove, and the second mounting seat is connected to the second connecting end; Wherein, the first mounting seat and the second mounting seat are respectively mounted on the splicing ends of two adjacent fuselage sections.

10. A machine tool, characterized in that: It comprises a spliced ​​fuselage as described in any one of claims 1-9.

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