CN210083337U - Cockpit frame mosaic structure and vehicle - Google Patents

Cockpit frame mosaic structure and vehicle Download PDF

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Publication number
CN210083337U
CN210083337U CN201920716404.9U CN201920716404U CN210083337U CN 210083337 U CN210083337 U CN 210083337U CN 201920716404 U CN201920716404 U CN 201920716404U CN 210083337 U CN210083337 U CN 210083337U
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assembly
cockpit
post
top cover
floor
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白军伟
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Beijing Electric Vehicle Co Ltd
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Beijing Electric Vehicle Co Ltd
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Abstract

The utility model discloses a cockpit frame mosaic structure and vehicle, wherein cockpit frame mosaic structure includes: cockpit subassembly, preceding enclose assembly, back enclose assembly and top cap roof beam assembly before enclosing. The front wall assembly is arranged on the front side of the cockpit sub-assembly and is fixedly spliced with the cockpit sub-assembly; the rear wall assembly is arranged at the rear side of the cockpit sub-assembly and is fixedly spliced with the cockpit sub-assembly; the top cover beam assembly is arranged above the cockpit sub-assembly, the front wall assembly and the rear wall assembly, and the top cover beam assembly is spliced and fixed with the front wall assembly and the rear wall assembly respectively. Each part of the splicing structure of the cockpit frame is independently manufactured, and then the splicing structure is fixed together in a splicing and fixing mode, and because each part is independently manufactured, each part of the cockpit frame can be more conveniently disassembled for maintenance or replacement after being damaged.

Description

Cockpit frame mosaic structure and vehicle
Technical Field
The utility model relates to a vehicle technical field particularly, relates to a cockpit frame mosaic structure and vehicle.
Background
The cockpit skeleton of traditional vehicle all adopts the form of punching press to form an organic whole, because a stamping die only corresponds the cockpit skeleton of a motorcycle type, wants to make neotype cockpit skeleton, need research and development new stamping die, wastes time and energy, and because cockpit skeleton is integrated into one piece spare, consequently the maintenance of each part of cockpit skeleton is not convenient for, exists and improves the space.
SUMMERY OF THE UTILITY MODEL
The utility model discloses aim at solving one of the above-mentioned technical problem among the prior art to a certain extent at least. Therefore, the utility model provides a cockpit frame mosaic structure, each part of this cockpit frame mosaic structure is the independent manufacturing, later adopts the fixed mode of concatenation to fix together again, because be the independent manufacturing between each part, consequently, the maintenance or the change of dismantling after each part of cockpit frame damage of being more convenient for.
The utility model also provides a vehicle of having above-mentioned cockpit frame mosaic structure.
According to the utility model discloses a cockpit frame mosaic structure, include: a cockpit subassembly; the front wall assembly is arranged on the front side of the cockpit sub-assembly and is fixedly spliced with the cockpit sub-assembly; the rear wall assembly is arranged at the rear side of the cockpit sub-assembly and is fixedly spliced with the cockpit sub-assembly; the top cover beam assembly is arranged above the cockpit sub-assembly, the front wall assembly and the rear wall assembly, and the top cover beam assembly is spliced and fixed with the front wall assembly and the rear wall assembly respectively.
According to the utility model discloses a cockpit frame mosaic structure, each part of this cockpit frame mosaic structure is independent manufacturing, later adopts the fixed mode of concatenation to fix together again, because be independent manufacturing between each part, consequently, the maintenance or the change of dismantling after each part of cockpit frame damage of being more convenient for.
In addition, according to utility model embodiment's cockpit frame mosaic structure, can also have following additional technical characterstic:
according to some embodiments of the utility model, the cockpit subassembly includes: cockpit lower part skeleton assembly, front floor and back floor, front floor sets up the front side on back floor, front floor with the concatenation of back floor is fixed on cockpit lower part skeleton assembly.
According to some embodiments of the utility model, cockpit lower part skeleton assembly includes: left side wall, right side wall, floor intermediate beam, cockpit front beam, cockpit rear beam, floor intermediate beam the cockpit front beam and cockpit rear beam is connected left side wall with between the right side wall and respectively with left side wall with the concatenation is fixed on the right side wall, cockpit front beam sets up the front side of cockpit rear beam, floor intermediate beam sets up cockpit front beam with between the cockpit rear beam.
According to some embodiments of the utility model, the cockpit front beam with be connected with between the floor centre sill along longitudinal extension's cockpit front longitudinal beam and cockpit centre longitudinal beam.
According to some embodiments of the utility model, the cockpit front longitudinal is located the both sides of longeron in the middle of the cockpit, the cockpit front longitudinal with longeron in the middle of the cockpit respectively with the cockpit front beam and the floor middle beam concatenation is fixed.
According to some embodiments of the utility model, the left side wall includes: left side A post, left B post, left threshold roof beam assembly and left threshold mounting panel, left side A post sets up the front side of left side B post, left side threshold roof beam assembly is connected left side A post with between the left side B post and respectively with left side A post with left side B post concatenation is fixed, left side threshold mounting panel with left side threshold roof beam assembly concatenation is fixed.
According to some embodiments of the utility model, the right side wall includes: right side A post, right B post, right threshold roof beam assembly and right threshold mounting panel, right side A post sets up the front side of right side B post, right side threshold roof beam assembly is connected right side A post with between the right side B post and respectively with right side A post with right side B post concatenation is fixed, right side threshold mounting panel with right side threshold roof beam assembly concatenation is fixed.
According to some embodiments of the invention, the roof beam assembly comprises: the top cover left longitudinal beam assembly, the top cover right longitudinal beam assembly, the top cover front cross beam and the top cover rear cross beam are arranged on the front side of the top cover rear cross beam, the top cover front cross beam and the top cover rear cross beam are connected respectively between the top cover left longitudinal beam assembly and the top cover right longitudinal beam assembly, and the top cover left longitudinal beam assembly and the top cover right longitudinal beam assembly are connected fixedly with the top cover front cross beam and the top cover rear cross beam respectively.
According to some embodiments of the utility model, top cap left side longeron assembly and the front end of top cap right side longeron assembly is buckled downwards respectively in order to form windshield both sides stand frame.
According to the utility model discloses a vehicle of another aspect, including foretell cockpit frame mosaic structure.
Drawings
Fig. 1 is a schematic structural diagram of a splicing structure of a cockpit frame according to an embodiment of the present invention;
fig. 2 is a schematic structural view of a cockpit sub-assembly according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of a lower frame assembly of a cockpit according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a left side wall and a right side wall according to the embodiment of the present invention.
Reference numerals:
the splicing structure comprises a cockpit frame splicing structure 100, a cockpit sub-assembly 1, a front wall assembly 2, a rear wall assembly 3, a top cover beam assembly 4, a cockpit lower framework assembly 11, a front floor 12, a rear floor 13, a left front floor 121, a right front floor 122, a left side wall 111, a right side wall 112, a floor middle cross beam 113, a cockpit front cross beam 114, a cockpit rear cross beam 115, a cockpit front longitudinal beam 116, a cockpit middle longitudinal beam 117, a left a column 1111, a left B column 1112, a left threshold beam assembly 1113, a left threshold mounting plate 1114, a right a column 1121, a right B column 1122, a right threshold beam assembly 1123, a right threshold mounting plate 1124, a top cover left longitudinal beam assembly 41, a top cover right longitudinal beam assembly 42, a top cover front cross beam 43 and a top cover rear cross beam 44.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present invention, and should not be construed as limiting the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and to simplify the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating 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 invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically connected, electrically connected or can communicate with each other; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
In the present disclosure, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact between the first and second features, or may comprise contact between the first and second features not directly. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
A cockpit frame mosaic 100 according to an embodiment of the present invention is described below with reference to fig. 1-4.
According to the utility model discloses cockpit frame mosaic structure 100 can include: cockpit subassembly 1, preceding enclose assembly 2, enclose assembly 3 and roof beam assembly 4 after.
As shown in fig. 1, the cowl assembly 2 is disposed at a front side of the cockpit sub-assembly 1 and is fixed to the cockpit sub-assembly 1 by using a clinch nut, a clinch stud, a blind rivet, and the like. Wherein, the front wall assembly 2 is fixed with the front end of the cockpit subassembly 1. The rear wall assembly 3 is arranged on the rear side of the cockpit subassembly 1 and is spliced and fixed with the cockpit subassembly 1 through a press rivet nut, a press rivet stud, a pull rivet nut, a rivet and the like. Wherein, the rear wall assembly 3 is fixed with the rear end of the cockpit subassembly 1.
Further, top cap roof beam assembly 4 sets up in cockpit sub-assembly 1, preceding enclose assembly 2 and enclose assembly 3's top after and to top cap roof beam assembly 4 uses pressure rivet nut, pressure rivet double-screw bolt, rivet nut and rivet etc. to enclose assembly 2 and enclose assembly 3 concatenation after with respectively and fix. Wherein, the front end of the top cover beam assembly 4 is fixed with the front wall assembly 2, and the rear end of the top cover beam assembly 4 is fixed with the rear wall assembly 3.
In summary, the cockpit sub-assembly 1, the front wall assembly 2, the rear wall assembly 3 and the roof beam assembly 4 are all manufactured independently and then spliced and fixed together by using fasteners to form a stable whole.
Because each part is independently made, consequently, can make each part the commonality stronger, can have more modes of assembling to the each part of cooperation different models forms different cockpit structures. And the condition that a traditional vehicle needs to research and develop a new frame stamping die when producing a new vehicle is avoided, and the research and development cost can be effectively reduced.
And also facilitates the disassembly, maintenance and replacement of damaged components of the cockpit frame mosaic 100. I.e., after a component is damaged, it can be removed from the overall structure and repaired separately or replaced with a new component. Therefore, the maintenance is more convenient.
Moreover, by adopting the integral splicing and fixing mode, the reasonable arrangement of an instrument panel, an auxiliary instrument panel, a seat and a relevant controller in the cockpit can be met.
Wherein, enclose assembly 2 and enclose assembly 3 after before can adopt forms such as die-casting or casting to make to enclose assembly 2 and enclose the intensity of assembly 3 after before guaranteeing.
Wherein, cockpit sub-assembly 1, preceding enclose assembly 2, enclose assembly 3 after and top cap roof beam assembly 4 all can adopt the aluminium alloy processing to make and form. From this, can effectively reduce cockpit frame mosaic structure 100's whole weight, and then realize the purpose of whole car lightweight.
According to the utility model discloses cockpit frame mosaic structure 100, each part of this cockpit frame mosaic structure 100 is independent manufacturing, later adopts the fixed mode of concatenation to fix together again, because be independent manufacturing between each part, consequently, the maintenance of dismantling or the change after each part of cockpit frame damage of being more convenient for.
With reference to the embodiment shown in fig. 1-3, the cockpit subassembly 1 comprises: the cab lower framework assembly comprises a cab lower framework assembly 11, a front floor 12 and a rear floor 13, wherein the front floor 12 is arranged on the front side of the rear floor 13, and the front floor 12 and the rear floor 13 can be spliced and fixed on the cab lower framework assembly 11 in a welding mode.
As shown in fig. 3 and 4, the lower frame assembly 11 of the cockpit includes: the left side wall 111, the right side wall 112, the floor middle beam 113, the cockpit front beam 114, the cockpit rear beam 115, the floor middle beam 113, the cockpit front beam 114 and the cockpit rear beam 115 are connected between the left side wall 111 and the right side wall 112 and are respectively spliced and fixed with the left side wall 111 and the right side wall 112, the cockpit front beam 114 is arranged at the front side of the cockpit rear beam 115, and the floor middle beam 113 is arranged between the cockpit front beam 114 and the cockpit rear beam 115. The floor middle cross beam 113, the cockpit front cross beam 114 and the cockpit rear cross beam 115 are arranged in parallel to ensure the overall stability of the lower frame assembly 11 of the cockpit.
Preferably, the middle cross beam, the front cockpit cross beam 114 and the rear cockpit cross beam 115 are fixed to the left side wall 111 and the right side wall 112 by welding.
Referring to fig. 2 and 3, a front longitudinal cockpit beam 116 and a middle longitudinal cockpit beam 117 extending in the longitudinal direction are connected between the front cockpit beam 114 and the middle floor beam 113. Wherein, the front floor 12 includes: a left front floor 121 and a right front floor 122, and a cabin center sill 117 is provided between the left front floor 121 and the right front floor 122. The front and middle longitudinal beams 116, 117 may be fixed between the front and middle cross beams 114, 113 by welding or screwing. The overall strength of the lower framework assembly 11 of the cab can be effectively increased by arranging the front longitudinal beam 116 and the middle longitudinal beam 117 of the cab.
Further, the front cockpit longitudinal beam 116 is located on both sides of the middle cockpit longitudinal beam 117, and the front cockpit longitudinal beam 116 and the middle cockpit longitudinal beam 117 are respectively fixed to the front cockpit cross beam 114 and the middle floor cross beam 113 in a splicing manner. Thus, the front side member 116 can assist in cooperating with the middle side member 117 to form a stable reinforcing frame, and the strength of the lower frame assembly 11 can be further increased.
With reference to the embodiment shown in fig. 2-4, the left side gusset 111 includes: left A post 1111, left B post 1112, left threshold beam assembly 1113 and left threshold mounting panel 1114, left A post 1111 sets up the front side at left B post 1112, left threshold beam assembly 1113 connect between the lower extreme of left A post 1111 and the lower extreme of left B post 1112 and can adopt the spiro union mode to splice fixedly with left A post 1111 and left B post 1112 respectively, left threshold mounting panel 1114 can adopt welded mode and left threshold beam assembly 1113 to splice fixedly.
Further, the right skirt 112 includes: the left sill beam assembly comprises a left A column 1121, a right B column 1122, a left sill beam assembly 1123 and a left sill mounting plate 1124, wherein the left A column 1121 is arranged on the front side of the left B column 1122, the right sill beam assembly 1123 is connected between the lower end of the left A column 1121 and the lower end of the right B column 1122 and can be spliced and fixed with the left A column 1121 and the right B column 1122 in a threaded manner, and the right sill mounting plate 1124 can be spliced and fixed with the left sill beam assembly 1123 in a welded manner.
Connecting pieces such as press riveting nuts, press riveting studs and rivets can be added on the left and right columns A, the left and right columns B, the left and right threshold beam assemblies and the left and right threshold mounting plates according to the structure and mounting requirements, and are used for subsequently mounting related parts of the whole vehicle. For example, the floor center cross member 113, the rear cockpit cross member 115, the left rocker beam assembly 1113, and the right rocker beam assembly 1123 may be used to mount a power battery pack.
The left and right rear trailing arm attachment members are connected to the cabin rear cross member 115 and the left and right B-pillars by welding, and are used for attaching the rear suspension trailing arm.
As shown in fig. 1, the roof rail assembly 4 includes: the roof structure comprises a roof left longitudinal beam assembly 41, a roof right longitudinal beam assembly 42, a roof front cross beam 43 and a roof rear cross beam 44, wherein the roof front cross beam 43 is arranged on the front side of the roof rear cross beam 44, the roof front cross beam 43 and the roof rear cross beam 44 are respectively connected between the roof left longitudinal beam assembly 41 and the roof right longitudinal beam assembly 42, and the roof left longitudinal beam assembly 41 and the roof right longitudinal beam assembly 42 are respectively spliced and fixed with the roof front cross beam 43 and the roof rear cross beam 44 in a welding mode.
Further, the top cover left longitudinal beam assembly 41 and the top cover right longitudinal beam assembly 42 may be tubular structural members, front ends of the two are respectively bent downward to form front windshield two-side upright frames, and lower ends of the front windshield two-side upright frames are adapted to be respectively screwed or welded with upper ends of the left a pillar 1111 and the right a pillar 1121 to form an a pillar assembly and a B pillar assembly of the vehicle.
The beam structural members and the floor member may be manufactured by extrusion, die casting, or the like, so as to ensure the overall strength of the cockpit frame splicing structure 100.
To sum up, the embodiment of the utility model provides an it is fixed all to adopt the form of concatenation between each component to form a complete whole, so that increase the commonality, and be convenient for each parts damage the back can dismantle maintenance or change.
According to another aspect of the present invention, the vehicle includes the cockpit frame splicing structure 100 described in the above embodiments. Other configurations of the vehicle, such as transmissions, braking systems, steering systems, etc., are known in the art and well known to those skilled in the art, and therefore will not be described in detail herein.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples described in this specification can be combined and combined by those skilled in the art.
Although embodiments of the present invention have been shown and described, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art without departing from the scope of the present invention.

Claims (10)

1. A cockpit frame mosaic structure, comprising:
a cockpit subassembly;
the front wall assembly is arranged on the front side of the cockpit sub-assembly and is fixedly spliced with the cockpit sub-assembly;
the rear wall assembly is arranged at the rear side of the cockpit sub-assembly and is fixedly spliced with the cockpit sub-assembly;
the top cover beam assembly is arranged above the cockpit sub-assembly, the front wall assembly and the rear wall assembly, and the top cover beam assembly is spliced and fixed with the front wall assembly and the rear wall assembly respectively.
2. The cockpit frame mosaic structure of claim 1 wherein said cockpit subassembly comprises: cockpit lower part skeleton assembly, front floor and back floor, front floor sets up the front side on back floor, front floor with the concatenation of back floor is fixed on cockpit lower part skeleton assembly.
3. The cockpit frame mosaic structure of claim 2, wherein said cockpit lower frame assembly comprises: left side wall, right side wall, floor intermediate beam, cockpit front beam, cockpit rear beam, floor intermediate beam the cockpit front beam and cockpit rear beam is connected left side wall with between the right side wall and respectively with left side wall with the concatenation is fixed on the right side wall, cockpit front beam sets up the front side of cockpit rear beam, floor intermediate beam sets up cockpit front beam with between the cockpit rear beam.
4. The splicing structure of a cab frame according to claim 3, wherein a longitudinally extending front and middle longitudinal cab beams are connected between the front and middle floor beams.
5. The splicing structure of the cab frame according to claim 4, wherein the front longitudinal beams are located on two sides of the middle longitudinal beam, and the front longitudinal beams and the middle longitudinal beams are spliced and fixed with the front cross beam and the middle cross beam respectively.
6. The cockpit frame mosaic structure of claim 3 wherein said left side surround comprises: left side A post, left B post, left threshold roof beam assembly and left threshold mounting panel, left side A post sets up the front side of left side B post, left side threshold roof beam assembly is connected left side A post with between the left side B post and respectively with left side A post with left side B post concatenation is fixed, left side threshold mounting panel with left side threshold roof beam assembly concatenation is fixed.
7. The cockpit frame mosaic structure of claim 3 wherein said right side surround comprises: right side A post, right B post, right threshold roof beam assembly and right threshold mounting panel, right side A post sets up the front side of right side B post, right side threshold roof beam assembly is connected right side A post with between the right side B post and respectively with right side A post with right side B post concatenation is fixed, right side threshold mounting panel with right side threshold roof beam assembly concatenation is fixed.
8. The cab frame splicing structure of claim 1, wherein the roof beam assembly comprises: the top cover left longitudinal beam assembly, the top cover right longitudinal beam assembly, the top cover front cross beam and the top cover rear cross beam are arranged on the front side of the top cover rear cross beam, the top cover front cross beam and the top cover rear cross beam are connected respectively between the top cover left longitudinal beam assembly and the top cover right longitudinal beam assembly, and the top cover left longitudinal beam assembly and the top cover right longitudinal beam assembly are connected fixedly with the top cover front cross beam and the top cover rear cross beam respectively.
9. The splicing structure of the cab frame according to claim 8, wherein front ends of the roof left side member assembly and the roof right side member assembly are respectively bent downward to form a front windshield side pillar frame.
10. A vehicle comprising a cockpit frame mosaic structure according to any one of claims 1-9.
CN201920716404.9U 2019-05-17 2019-05-17 Cockpit frame mosaic structure and vehicle Active CN210083337U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201920716404.9U CN210083337U (en) 2019-05-17 2019-05-17 Cockpit frame mosaic structure and vehicle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201920716404.9U CN210083337U (en) 2019-05-17 2019-05-17 Cockpit frame mosaic structure and vehicle

Publications (1)

Publication Number Publication Date
CN210083337U true CN210083337U (en) 2020-02-18

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN201920716404.9U Active CN210083337U (en) 2019-05-17 2019-05-17 Cockpit frame mosaic structure and vehicle

Country Status (1)

Country Link
CN (1) CN210083337U (en)

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