Wire harness isolation plate and battery module

Abstract

The application discloses a wire harness isolation plate, comprising: an isolation plate body, a plurality of aircraft buckles are arranged on the isolation plate body; a plurality of clips, each clip is connected with at least one aircraft buckle; wherein the isolation plate body is further provided with a plurality of elastic sheets, and each clip corresponds to at least one elastic sheet, so that the elastic sheet and the engaged clip are in interference fit. The aircraft buckle and the elastic sheet are designed between the clip and the isolation plate body, the stability of the clip is improved, in the CCS assembly incoming material and assembly process, the problem of the pressure point falling caused by the shaking of the clip itself is reduced, and the problem of the pressure point falling caused by the shaking of the plastic support is reduced.

Description

Technical Field

[0001] This invention relates to the field of battery technology, and in particular to a wire harness separator and a battery module. Background Technology

[0002] In current power battery CCS modules, the methods for fixing the battery cells and the separator body are as follows:

[0003] 1. In most power battery modules, clips are used to fix the battery cells to the separator body. Under normal circumstances, each battery cell should have at least two clips to prevent it from falling off.

[0004] 2. Use hot-riveting posts to fix the bar to the isolation plate body. Generally, each bar should be designed with at least 2 hot-riveting posts to prevent the bar from falling off.

[0005] 3. The bar sheet is fixed to the isolation plate body using a combination of clips and hot riveting posts. To meet assembly requirements, an assembly space is usually designed. The bar sheet is fixed to the isolation plate body by clips or hot riveting posts.

[0006] Of the three methods mentioned above, the first method, the snap-fit ​​method, has the following problems: the area directly below the snap-fit ​​needs to be cleared, which increases the number of ejector pins used when opening the mold, thus increasing the mold cost. Furthermore, the snap-fit ​​is prone to breakage during assembly, increasing production costs. The second method, the hot-riveting method, adds a process, correspondingly increasing the cost of the entire voltage and temperature acquisition component. The third method, after fixing via a combined process, causes the battery cells to wobble, and the material receiving and assembly processes can easily lead to the pressure sampling points falling off. Additionally, after the CCS component and the battery cell are welded and assembled into a module, the separator body wobbles, posing a risk of pressure sampling points falling off during long-term operation, thus preventing normal pressure sampling and causing the battery system to malfunction. Summary of the Invention

[0007] To overcome at least one of the defects described in the prior art, the present invention provides a wire harness separator and a battery module. This solves the problem of pressure point detachment caused by plate movement during CCS module material handling and assembly, thereby improving production speed and reducing production costs.

[0008] The technical solution adopted by this invention to solve its problem is:

[0009] A wire harness isolation plate includes: an isolation plate body with a plurality of aircraft clips disposed on the isolation plate body; a plurality of latches, each latch being connected to at least one aircraft clip; wherein the isolation plate body is further provided with a plurality of spring clips, and each latch corresponds to at least one spring clip, so that the spring clips and the latches are in an interference fit.

[0010] By adopting the above solution, the spring sheet is used to support and lift the pad, which effectively reduces the shaking of the pad during the CCS component feeding and assembly process, thereby reducing the probability of the pad falling off the pressure point.

[0011] Furthermore, the aircraft buckle includes: a fixing seat having a supporting structure; a limiting ridge wrapped around the edge of the fixing seat; and a snap-fit ​​portion connected to the supporting structure, wherein the buckle snaps into the snap-fit ​​portion.

[0012] By adopting the above solution, the stability of the aircraft buckle itself is improved, thereby improving the stability of the connection with the plate.

[0013] Furthermore, the snap-fit ​​portion includes: a support portion connected to a support structure; a snap-fit ​​end connected to the support portion; and an attacking end connected to the support portion, wherein both the snap-fit ​​end and the attacking end are located at the end of the support portion away from the support structure, and the attacking end is farther from the support structure than the snap-fit ​​end.

[0014] By adopting the above solution, the snap-fit ​​capability of the snap-fit ​​part is improved, and its own connection convenience can be achieved. When inserted, it is connected through the attack end, and after sliding out, it is snapped back through the snap-fit ​​end.

[0015] Furthermore, the bar includes a fitting surface and a snap-fit ​​surface. When the bar is assembled, the offensive end passes through the bar. At this time, the fitting surface abuts against the spring clip, and the snap-fit ​​surface abuts against the snap-fit ​​end of the aircraft buckle.

[0016] By adopting the above solution, the contact effect between the pad and the isolation plate body is achieved.

[0017] Furthermore, both the bonding surface and the snap-fit ​​surface are provided with a stepped structure, and the height difference and slope of the stepped structure are the same for both.

[0018] By adopting the above solution, the buckle can be better connected to the aircraft buckle. By setting a stepped structure, sufficient snap-fit ​​space is reserved between the buckle and the isolation plate body without increasing the distance between them.

[0019] Furthermore, two stepped structures are provided on both the bonding surface and the snap-fit ​​surface, so that the bonding surface of the pad forms a groove and the snap-fit ​​surface of the pad forms a convex beam.

[0020] By adopting the above solution, and by setting the protruding beam and the groove, there is sufficient interlocking space between the bar plate and the isolation plate body. With the help of the spring sheet, the interference fit between the two can be achieved.

[0021] Furthermore, the pad has at least one through hole penetrating the mating surface and the snap-fit ​​surface, and the support portion of the airplane buckle penetrates the through hole so that the snap-fit ​​end of the airplane buckle snaps into the snap-fit ​​surface of the pad.

[0022] By adopting the above solution and setting perforations, it can be used to connect with aircraft clips, thus achieving the effect of connecting the bar sheet.

[0023] Furthermore, the isolation plate body is provided with multiple recessed mounting grooves for assembling the bar plate, and the mounting groove includes two clearance holes, with the aircraft buckle disposed between the two clearance holes.

[0024] By adopting the above scheme, the avoidance hole exposes a positive terminal and a negative terminal for connection with the barcode, and the concave mounting groove is used to indicate the installation position of the barcode. At the same time, the recessed part can correspond to the edge of the barcode to avoid misalignment during installation.

[0025] Furthermore, at least two spring tabs are distributed around each of the clearance holes, and the spring tabs are symmetrically arranged with respect to the clearance holes as the center, so as to support the bar tabs and keep the bar tabs horizontal with the isolation plate body at all times.

[0026] By adopting the above scheme, the bar sheet can be supported by at least two spring sheets, which improves the stability of the bar sheet itself. At the same time, the symmetrically distributed at least two spring sheets create a buffer gap between the bar sheet and the isolation plate body, thereby ensuring that the bar sheet always remains horizontal with the isolation plate body.

[0027] Furthermore, a bone position is provided at one corner of the placement groove, and an alignment part is provided corresponding to the bone position of the brace, and the bone position and the alignment part are assembled accordingly.

[0028] By adopting the above method and setting the bone position, the reverse installation of the brace can be effectively prevented, thus improving the installation accuracy rate.

[0029] Furthermore, it also includes an FPC acquisition component, which is disposed on the isolation plate body, and the pads are linearly distributed on both sides along the length direction of the FPC acquisition component, and the pads are electrically connected to the FPC acquisition component.

[0030] By adopting the above scheme, linearly distributed plates can improve space utilization, while the acquired signal is stable and the welding points are easy to set.

[0031] Furthermore, the edge of the FPC acquisition device is provided with multiple buffer structures, which are connected to the barcode to provide buffer space for the connection between the barcode and the FPC acquisition device.

[0032] By adopting the above solution and setting a buffer structure, the welding point between the FPC acquisition component and the sensor plate can have a buffer space, which can reduce the impact of the sensor plate shaking on the welding point during installation or transportation. Therefore, the welding point will not fall off and affect the acquisition of the FPC acquisition component.

[0033] Furthermore, the spring clip is integrally bent into shape with the isolation plate body.

[0034] By adopting the above solution, manufacturing processes are simplified while production costs are reduced.

[0035] Furthermore, the spring is bent twice in opposite directions, forming a Z-shape, to provide elasticity to the bar plate away from the isolation plate body.

[0036] By adopting the above scheme, the spring sheet is formed into a Z-shape through two reverse bends, which helps to achieve its own elasticity and reset effect.

[0037] Furthermore, the aircraft buckle is attached to the plate.

[0038] By adopting the above solution, there is no adhesive between the aircraft buckle and the plate, so assembly and maintenance are very simple, and the overall cost is greatly reduced.

[0039] A battery module includes a wiring harness separator.

[0040] By adopting the above solution, the stability of the battery module can be improved, the service life of the wire harness separator can be extended, and the replacement frequency of the wire harness separator in the battery module can be reduced.

[0041] In summary, the wire harness isolation plate provided by the present invention has the following technical effects:

[0042] 1. By designing aircraft-style fasteners and spring clips between the pad and the isolation plate body, a stable working environment can be provided for the pad, improving the stability of the pad. During the incoming material and assembly process of CCS components, the problem of pressure point detachment caused by the pad's own shaking is reduced.

[0043] 2. After the CCS components and battery cells are welded and assembled into modules, the interference fit between the aircraft clips and springs reduces the problem of pressure point detachment caused by the shaking of the plastic bracket. Attached Figure Description

[0044] Figure 1 This is a schematic diagram of the isolation plate body structure according to an embodiment of the present invention;

[0045] Figure 2 This is a schematic diagram of the isolation plate body structure on the welding side of the battery cell according to an embodiment of the present invention;

[0046] Figure 3 for Figure 1 Enlarged view of area A in the image;

[0047] Figure 4 for Figure 2 Enlarged view of area B in the image;

[0048] Figure 5 This is a schematic diagram of the three-dimensional structure of the isolation plate body;

[0049] Figure 6 for Figure 5 Enlarged view of area C;

[0050] Figure 7 This is a schematic diagram of the mounting plate structure on the isolation plate body of an embodiment of the present invention;

[0051] Figure 8 for Figure 7 A partial cross-sectional view at point DD;

[0052] Figure 9 for Figure 8 Enlarged view of area E in the middle.

[0053] The meanings of the reference numerals in the attached drawings are as follows: 1. Isolation plate body; 11. Spring piece; 12. Installation groove; 121. Bone position; 13. Clearance hole; 14. Aircraft buckle; 141. Snap-fit ​​part; 1411. Support part; 1412. Snap-fit ​​end; 1413. Attack end; 142. Fixing seat; 143. Limiting ridge; 2. Bar piece; 21. Alignment part; 22. Protruding beam; 221. Perforation; 23. Alignment hole; 24. Snap-fit ​​surface; 25. Fitting surface; 26. Groove; 27. Stepped structure; 3. FPC acquisition component; 31. Buffer structure; 311. Buffer part; 312. Buffer groove; 4. Nickel sheet; 5. Positive output composite bar; 6. Negative output composite bar; 7. Connector. Detailed Implementation

[0054] To better understand and implement this invention, the technical solutions in the embodiments of this invention will be clearly and completely described and discussed below with reference to the accompanying drawings. Obviously, what is described here is only a part of the examples of this invention, not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the protection scope of this invention.

[0055] To facilitate understanding of the embodiments of the present invention, further explanations and descriptions will be provided below with reference to the accompanying drawings and specific embodiments, and these embodiments do not constitute a limitation on the embodiments of the present invention.

[0056] In the description of this invention, it should be noted that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", and "outer" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0057] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention.

[0058] In related technologies, battery modules often use a snap-fit ​​and welding method to fix the battery pack 2. The snap-fit ​​is used to snap the battery pack 2 into the mounting groove 12 to prevent the battery pack 2 from falling off. Then, the battery cell of the battery module is welded or bolted to the battery pack 2 through the clearance hole 13 in the mounting groove 12. However, when the separator plate body 1 shakes and the battery pack 2 shakes, the pressure sampling point may fall off during material receiving, assembly, or long-term operation, thus preventing normal pressure sampling and causing the battery system to malfunction.

[0059] In view of this, refer to Figure 1-9 As shown, this embodiment 1 provides a wire harness isolation plate: including an isolation plate body 1 and multiple clips 2, wherein the isolation plate body 1 is provided with multiple aircraft clips 14; each clip 2 is connected to at least one aircraft clip 14; wherein the isolation plate body 1 is also provided with several spring clips 11, and each clip 2 corresponds to at least one spring clip 11, the clip 2 is kept horizontal with the isolation plate body 1 by the elastic force, so that there is an interference fit between the spring clip 11 and the engaged clip 2, the spring clip 11 supports and lifts the clip 2 and keeps the clip 2 horizontal with the isolation plate body 1, effectively reducing the shaking of the clip 2 during the incoming and assembly of CCS components. Generally speaking, the number of spring clips 11 is even, which can better provide stable support for the clip 2. When there is only one spring clip 11, the spring clip is spiral or U-shaped to ensure the stability of the clip 2, so that the clip 2 is kept horizontal with the isolation plate body 1.

[0060] The aircraft clip 14 and the electrode plate 2 are not attached, so there is no adhesive between them, making assembly and maintenance very simple and significantly reducing overall costs. The CCS assembly is located between the top and the top cover of the battery module. The CCS assembly specifically includes a separator body 1, an FPC collector 3, and multiple electrode plates 2. The separator body 1 has a negative output composite row 6 and a positive output composite row 5 at both ends, and a connector 7 is also provided at one end of the FPC collector 3. The following is a detailed description of the fixing structure between the electrode plate 2 and the separator body 1 of a CCS assembly:

[0061] See Figures 1-4 The separator body 1 is rectangular, with two rows of battery strips 2 arranged along its length. An FPC (Flexible Printed Circuit) acquisition unit 3 is located between the two rows of battery strips 2. The battery strips 2 are made of aluminum or copper. The side of the battery strip facing the FPC acquisition unit 3 is connected to the FPC acquisition unit 3 via a nickel sheet 4. The nickel sheet 4 is located on the side of the battery strip 2 away from the separator body 1. The separator body 1 has a mounting groove 12 on the side near the battery strip 2, with the groove's outline matching the strip's shape. The mounting groove 12 is recessed into the surface of the separator body 1. Each mounting groove 12 has two clearance holes 13, each exposing a positive terminal and a negative terminal for connection to the battery strip 2. An aircraft-shaped buckle 14 is located on the separator body 1 between the two clearance holes 13. The battery module's terminals are connected to the side of the battery strip 2 near the separator body 1 via the clearance holes 13. This connection includes, but is not limited to, welding and bolting. The CCS (Clean Cell Module) component enables the acquisition of cell parameters, ensuring the safety and stability of the square power battery module.

[0062] In other embodiments, the pressure plate 2 can be arranged in two or more rows, with each row of pressure plates 2 connected to the FPC acquisition component 3. Each pressure plate 2 is welded to the FPC acquisition component 3 through a nickel sheet 4 to form a pressure sampling point, which can achieve multi-point pressure sampling effect.

[0063] The aircraft 14 buckle includes a snap-fit ​​part 141, a fixing seat 142, and a limiting ridge 143. The fixing seat 142 has a support structure 1421, and the snap-fit ​​part 141 is connected to the support structure 1421. The limiting ridge 143 wraps around the edge of the fixing seat 142. In this embodiment 1, the fixing seat 142 is circular with a hollow center. The support structure 1421 is a connecting rod with a circular diameter that passes through the fixing seat 142. The snap-fit ​​part 141 is vertically connected to the support structure 1421. The limiting ridge 143 wraps around the circumference of the fixing seat 142 and extends towards the bar to form a circular rib, providing a good connection environment and support for the snap-fit ​​part 141. Through the snap-fit ​​of the snap-fit ​​part 141 and the bar 2, the stability of the connection between the isolation plate body 1 and the bar 2 is improved. In other embodiments, the shapes of the fixing seat 142 and the limiting ridge 143 can be other than circular.

[0064] For more details, see [link to relevant documentation]. Figure 3 , 4 As shown in Figures 6 and 9, the aircraft buckle 14 has two latching portions 141, which are symmetrically arranged. Each latching portion 141 includes a support portion 1411, a latching end 1412, and an attacking end 1413. The latching end 1412 is integrally connected to the support portion 1411, and the attacking end 1413 is integrally connected to the support portion 1411. Of course, in other embodiments, the latching end 1412 and the support portion 1411, and the attacking end 1413 and the support portion 1411, may not be integrally connected. In this embodiment, no specific limitations are made; both the snap-fit ​​end 1412 and the attack end 1413 are located at the end of the support portion 1411 away from the support structure 1421, and the attack end 1413 is farther from the support structure 1421 than the snap-fit ​​end 1412. The surface of the attack end 1413 is inclined and has an arc. The two attack ends 1413 form a cone shape, which can be used to complete the connection operation by inserting a hole-type structure. The snap-fit ​​portion 141 is kept horizontal with the isolation plate body 1 for snap-fit ​​fixation with the bar plate 2.

[0065] Reference Figure 1-8As shown, the clip 2 includes a mating surface 25 and a snap-fit ​​surface 24. When the clip 2 is assembled, the attack end 1413 passes through the clip 2. At this time, the mating surface 25 abuts against the spring clip 11, and the snap-fit ​​surface 24 abuts against the snap-fit ​​end 1412 of the aircraft clip 14. Both the mating surface 25 and the snap-fit ​​surface 24 are provided with stepped structures 27, and the height difference and slope of the stepped structures 27 are the same for both. In this embodiment 1, two stepped structures 27 are symmetrically arranged on the mating surface 25 and the snap-fit ​​surface 24, so that the mating surface 25 of the clip 2 forms a groove 26, and the snap-fit ​​surface 24 of the clip 2 forms a protruding beam 22. Furthermore, both the protruding beam 22 and the groove 26 are centrally located on the plate 2. A through hole 221 is also provided at the central position of the protruding beam 22 and the groove 26 on the plate 2. The airplane buckle 14 passes through the through hole 221 and engages with the plate 2, so that the engaging end 1412 of the airplane buckle 14 engages with the engaging surface 24 of the plate 2. One end of the through hole 221 is located in the groove 26 of the mating surface 25, and the other end is located on the protruding beam 22 of the engaging surface 24.

[0066] It should be noted that in other embodiments, the number of the protruding beam 22 and the groove 26 is not limited to one, but the overall arrangement of the bar plate 2 should be uniform or symmetrical to maintain a horizontal and interference fit with the isolation plate body. The number of perforations 221 on the corresponding protruding beam 22 and groove 26 is also not limited and can be more than one, as long as a stable connection between the bar plate 2 and the isolation plate body 1 is ensured.

[0067] In this embodiment, the two snap-fit ​​parts 141 of the aircraft buckle 14 are snap-fitted and fixed to both sides of the through hole 221. The shape of the buckle and the shape of the aircraft buckle 14 are not specifically limited. By setting the protruding beam 22, the tabs 2 at both ends of the protruding beam 22 can be closer to the spring pieces 11 on the isolation plate body 1, and a space is reserved between the tabs 2 and the isolation plate body 1 to provide space for the spring pieces 11 to reset and buffer.

[0068] Of course, in some embodiments, the fixing seat 142 and the limiting ridge 143 can be omitted, and the aircraft buckle can be directly fixed vertically to the isolation plate body 1. The aircraft buckle 14 is provided with only one columnar snap-fit ​​part 141, and the top of the snap-fit ​​part 141 is provided with a fork, which replaces the two snap-fit ​​parts 141 in Embodiment 1. It also has the effect of snap-fit ​​in opposite directions. The specific connection structure between the aircraft buckle 14 and the isolation plate body 1 is only the structure of this embodiment. In other embodiments, it can be changed to other installation structures, which are only used to fix the aircraft buckle 14 to the isolation plate body 1. In other embodiments, the overall shape of the aircraft buckle 14 can be other shapes, and the through hole 221 that snaps into the aircraft buckle 14 is also consistent with the shape of the aircraft buckle 14 to meet the snap-fit ​​conditions.

[0069] Specifically, the convex beam 22 is arch-shaped, and its cross-section can be arched or trapezoidal, or inverted U-shape, or a variation of the above two shapes, such as replacing the straight edge with a curved edge. In other embodiments, the convex beam 22 can also be replaced with a protrusion. Of course, the convex beam 22 and the protrusion can also be designed as grooves, pits, planes or other structures, only used to serve as a connection with the aircraft buckle 14.

[0070] In this embodiment 1, each of the clearance holes 13 has a spring piece 11 distributed on its upper and lower sides, which can support the bar plate 2 and improve the stability of the bar plate 2 itself. In other embodiments, the number of spring pieces 11 is not limited. There can be a single spring piece, which can stably support the bar plate and keep it horizontal with the isolation plate body 1. There can also be other numbers of spring pieces, whose function is only to provide elastic force to the bar plate 2 and keep the two sides of the protruding beam 22 of the bar plate 2 horizontal and in a relatively static state.

[0071] Specifically, the spring piece 11 is integrally bent and formed with the isolation plate body 1, saving manufacturing process and reducing production cost. In this embodiment 1, the spring piece 11 is Z-shaped to provide elastic force to the bar piece 2 away from the isolation plate body 1. By bending twice in opposite directions, the spring piece 11 forms a Z-shape, which is beneficial to achieving its own elastic force and reset effect. The spring piece 11 is hollowed out on three sides, and only one side is connected to the isolation plate body 1. The spring piece 11 located above the avoidance hole 13 is relatively isolated, while the spring piece 11 located below the avoidance hole 13 is designed in conjunction with the lower end of the avoidance hole 13 to save space in the mounting slot 12, which greatly saves space in the mounting slot 12. In other embodiments, the spring piece 11 can be in other shapes and is only used to provide elastic force to the bar piece 2. Of course, the spring piece 11 can also be replaced with other elastic structures, including but not limited to springs, spring pieces, etc.

[0072] Compared to existing battery packs, the area of ​​the battery pack 2 in this embodiment 1 is increased, exceeding the area of ​​the original two packs. This reduces the number of connection points between the battery pack 2 and the FPC acquisition unit 3. A buffer structure 31 can also be provided at the connection point between the FPC acquisition unit 3 and the battery pack 2. The buffer structure 31 includes a buffer groove 312 and a buffer section 311. The buffer section 311 is connected to the battery pack 2 via a nickel sheet 4. One side of the nickel sheet 4 is welded to the buffer section 311, and the other side is welded to the battery pack 2. The buffer section 311 is sheet-shaped, and the buffer groove 312 is located circumferentially around it. The buffer section 311 is integrally connected to the FPC acquisition unit 3, therefore sharing the same material and possessing a certain elastic deformation capability. By providing the buffer structure 31, a buffering effect is achieved, reducing the stress at the connection point between the battery pack 2 and the FPC acquisition unit 3. This reduces the probability of damage to the nickel sheet 4 or the battery pack itself between the battery pack 2 and the FPC acquisition unit 3, thus extending the service life of the square power battery module.

[0073] In this embodiment 1, a bone position 121 can be optionally set at one corner of the placement groove 12. Therefore, an alignment part 21 needs to be set at the position of the bar piece 2 corresponding to the bone position 121. The bone position 121 can be set on any side of the placement groove 12, or it can be set in the center of the placement groove 12. The bar piece 2 only needs to reserve an installation opening at the bone position 121 set in the placement groove 12 to serve as the alignment part 21. Through the above-mentioned foolproof design, it can play the role of installation indication, improve the installation accuracy of the bar piece 2 and the placement groove 12, and effectively prevent the bar piece 2 from being installed backwards or incorrectly, thereby improving the installation accuracy.

[0074] The electrode plate 2 also includes two symmetrical alignment holes 23, which are used for welding with the battery cell. During the connection process between the electrode plate 2 and the battery cell, the electrode post and the electrode plate 2 can be connected by welding.

[0075] This invention also relates to a battery module, including a wire harness separator. The wire harness separator can incorporate at least one of the technical solutions described above, which can improve the stability of the battery module, extend the service life of the wire harness separator, and thus reduce the replacement frequency of the wire harness separator in the battery module. In the battery module, according to the requirements of the battery module, the width and / or length of the separator body 1 can be extended to form a multi-row sensor structure 2, increasing the number of sampling points on the separator body 1, thereby reducing the number of separator bodies 1 used in the battery module.

[0076] The following is an introduction and explanation of the installation process and working principle of the CCS component in the battery module:

[0077] First, the CCS module is placed at the terminal end of the battery module, and multiple cells are connected in series through the electrode plate 2, with output through one electrode plate 2. During the connection between the electrode plate 2 and the cells, the terminal and electrode plate 2 are connected by welding. The pad 2 is first placed in the mounting groove 12. The correct placement of the pad 2 is ensured by the alignment part 21 of the mounting groove 12 and the alignment part 121 of the pad 2. Then, the buckle on the protruding beam 22 of the pad 2 is aligned with the snap-fit ​​part 141 of the aircraft buckle 14 and pressed down so that the two snap-fit ​​parts 141 of the aircraft buckle 14 are snapped and fixed with the two ends of the buckle. The pad 2 on both sides of the protruding beam 22 is in contact with the four spring pieces 11 to form an interference fit. At this time, the alignment hole 23 on the pad 2 is opposite to the corresponding positive and negative terminals. During the material supply and assembly of the CCS component, due to the interference fit between the pad 2 and the spring pieces 11, the problem of pressure point detachment caused by the shaking of the pad 2 itself and the problem of pressure point detachment caused by the shaking of the plastic bracket are reduced. Therefore, the problem of pressure point detachment in the CCS component is solved.

[0078] In summary, the fixing structure between the plate 2 and the isolation plate body 1 of the CCS component provided by the present invention has the following technical effects:

[0079] 1. By designing an aircraft buckle 14 and a spring clip 11 between the bar plate 2 and the isolation plate body 1, a stable working environment can be provided for the bar plate 2, improving the stability of the bar plate 2. During the incoming material and assembly process of CCS components, the problem of pressure point detachment caused by the shaking of the bar plate 2 itself is reduced.

[0080] 2. After the CCS components and battery cells are welded and assembled into modules, the interference fit between the aircraft buckle 14 and the spring piece 11 reduces the problem of pressure point detachment caused by the shaking of the plastic bracket;

[0081] 3. The aircraft buckle 14 and the plate 2 are connected by a zero-attachment technology, which improves production speed and reduces production costs;

[0082] 4. By setting the alignment part 21 on the bone position 121 and the bar plate 2, the problem of easy reverse installation and difficult assembly of the bar plate 2 and the isolation plate body 1 is effectively reduced.

[0083] The technical means disclosed in this invention are not limited to those disclosed in the above embodiments, but also include technical solutions composed of any combination of the above technical features. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of this invention, and these improvements and modifications are also considered within the scope of protection of this invention.

Claims

1. A wire harness isolation plate, characterized in that: include: The isolation plate body (1) is provided with a plurality of aircraft buckles (14); Multiple flaps (2), each flap (2) being connected to at least one aircraft buckle (14); The isolation plate body (1) is also provided with a number of spring pieces (11), and each bar piece (2) has at least one corresponding spring piece (11) so that the spring piece (11) and the engaged bar piece (2) are in an interference fit. The aircraft buckle (14) passes through the bar (2) and is snapped onto the surface of the bar (2) facing away from the isolation plate body (1). The spring clip (11) supports the bar (2) on the side of the bar (2) facing the isolation plate body (1). The isolation plate body (1) is provided with a plurality of recessed mounting grooves (12) for assembling the bar plate (2). The mounting groove (12) includes two clearance holes (13), and the aircraft buckle (14) is disposed between the two clearance holes (13). There is a reserved space between the bar plate (2) and the bottom wall of the mounting groove (12). At least two spring clips (11) are distributed around each of the aforementioned clearance holes (13); The spring clip (11) is integrally bent into shape with the isolation plate body (1); The spring piece (11) is hollowed out on three sides, and only one side is connected to the isolation plate body (1). Each of the clearance holes (13) has a spring piece (11) on its upper and lower sides. The spring piece (11) located on the upper side of the clearance hole (13) is isolated from the clearance hole (13), and the spring piece (11) located on the lower side of the clearance hole (13) is designed together with the lower end of the clearance hole (13).

2. The wire harness isolation plate according to claim 1, characterized in that: The aircraft buckle (14) includes: A fixing base (142) having a support structure (1421); A limiting edge (143) is provided, which is wrapped around the edge of the fixing base (142); The snap-fit ​​part (141) is connected to the support structure (1421), and the tab (2) snaps into the snap-fit ​​part (141).

3. A wire harness isolation plate according to claim 2, characterized in that: The snap-fit ​​portion (141) includes: A support portion (1411) is connected to a support structure (1421); A snap-fit ​​end (1412) is connected to a support portion (1411); An offensive end (1413) is connected to a support part (1411); The snap-fit ​​end (1412) and the attack end (1413) are both located at the end of the support part (1411) away from the support structure (1421), and the attack end (1413) is farther from the support structure (1421) than the snap-fit ​​end (1412).

4. A wire harness isolation plate according to claim 3, characterized in that: The plate (2) includes a fitting surface (25) and a snap-fit ​​surface (24). When the plate (2) is assembled, the attack end (1413) passes through the plate (2). At this time, the fitting surface (25) abuts against the spring clip (11), and the snap-fit ​​surface (24) abuts against the snap-fit ​​end (1412) of the aircraft buckle (14).

5. A wire harness isolation plate according to claim 4, characterized in that: Both the bonding surface (25) and the snap-fit ​​surface (24) are provided with a stepped structure (27), and the height difference and slope of the stepped structure (27) are the same for both.

6. A wire harness isolation plate according to claim 5, characterized in that: Two stepped structures (27) are provided on both the bonding surface (25) and the snap-fit ​​surface (24) so ​​that the bonding surface (25) of the pad (2) forms a groove (26) and the snap-fit ​​surface (24) of the pad (2) forms a protruding beam (22).

7. A wire harness isolation plate according to claim 4, characterized in that: The pad (2) has at least one through hole (221) through the fitting surface (25) and the snap-fit ​​surface (24), and the support part (1411) of the airplane buckle (14) passes through the through hole (221) so that the snap-fit ​​end (1412) of the airplane buckle (14) snaps into the snap-fit ​​surface (24) of the pad (2).

8. A wire harness isolation plate according to any one of claims 1-7, characterized in that: The spring clip (11) is symmetrically arranged around the clearance hole (13) to support the bar clip (2) so that the bar clip (2) always remains horizontal with the isolation plate body (1).

9. A wire harness isolation plate according to claim 8, characterized in that: A bone position (121) is provided at one corner of the placement groove (12), and the bar piece (2) is provided with a matching part (21) corresponding to the bone position (121). The bone position (121) and the matching part (21) are assembled accordingly.

10. A wire harness isolation plate according to any one of claims 1-7, characterized in that: It also includes an FPC acquisition component (3), which is disposed on the isolation plate body (1). The pads (2) are distributed at intervals on both sides along the length direction of the FPC acquisition component (3), and the pads (2) are electrically connected to the FPC acquisition component (3).

11. A wire harness isolation plate according to claim 10, characterized in that: The FPC acquisition unit (3) has multiple buffer structures (31) on its edge. The buffer structures (31) are connected to the bar plate (2) to provide buffer space for the connection between the bar plate (2) and the FPC acquisition unit (3).

12. A wire harness isolation plate according to any one of claims 1-7, characterized in that: The spring sheet (11) is bent twice in opposite directions, forming a Z-shape, to provide elasticity to the bar sheet away from the isolation plate body (1).

13. A wire harness isolation plate according to any one of claims 1-7, characterized in that: The aircraft buckle (14) and the bar sheet (2) are attached to each other.

14. A battery module, characterized in that: Includes the wire harness isolation plate as described in any one of claims 1-13.

Images