Electric tail durability test fixture

Abstract

The present disclosure relates to an electric tail durability test tool, belonging to the technical field of vehicle test tools. The electric tail durability test tool comprises a frame and at least two counterweight assemblies. The frame comprises a chassis and two supports connected to each other; the two supports are respectively located on both sides of the chassis in a first direction. The counterweight assemblies are respectively elastically connected to the two supports, and the chassis and the at least two counterweight assemblies are sequentially and spacedly arranged along the direction of gravity. The chassis is used to be connected to a fixed part of an electric tail. The at least two counterweight assemblies are used to gradually apply a downward pressure to a spoiler in the electric tail during rotation of the spoiler. The first direction is parallel to the length direction of the spoiler. The electric tail durability test tool can improve the accuracy of the service life data obtained by the durability test.

Description

Technical Field

[0001] This disclosure relates to the field of vehicle testing fixture technology, and in particular to an electric tail wing durability testing fixture. Background Technology

[0002] Compared to fixed rear wings, electric rear wings involve a more complex load environment during operation. The raising, lowering, and tilting of the electric rear wing are triggered by vehicle speed, resulting in cyclical excitation of aerodynamic loads and affecting its lifespan. Therefore, durability testing of electric rear wings is necessary to verify their service life.

[0003] The downforce experienced by the electric tail wing varies at different opening angles. Therefore, during durability testing, it is necessary to simulate the corresponding pressure changes to ensure the accuracy of the electric tail wing durability test.

[0004] In related technologies, the load applied to the electric tail fin is prone to being too small or too large. If the load is too small, it cannot adequately simulate the stress conditions under the maximum opening angle of the tail fin; if the load is too large, the electric tail fin will experience excessive stress when the opening angle is small, making the verification conditions too harsh. Both of these will lead to inaccurate lifespan data. Summary of the Invention

[0005] Therefore, this disclosure provides an electric tail fin durability testing fixture, which can improve the accuracy of service life data obtained from durability testing. The technical solution is as follows: In a first aspect, an electric tail fin durability testing fixture is provided, the electric tail fin durability testing fixture comprising: a frame and at least two counterweight components; The frame includes a base frame and two supports connected to each other; the two supports are respectively located on both sides of the base frame in a first direction; The counterweight assembly is elastically connected to the two supports respectively, and the base frame and the at least two counterweight assemblies are arranged sequentially at intervals along the direction of gravity. The base frame is used to connect with the fixed part of the electric tail wing; the at least two counterweight components are used to gradually apply downward pressure to the spoiler during the rotation of the spoiler in the electric tail wing; the first direction is parallel to the length direction of the spoiler.

[0006] In some possible implementations, for any one of the counterweight components, the counterweight component includes: a support plate, and at least one counterweight block located on the side of the support plate opposite to the base frame; the support plate is strip-shaped, and the length direction of the support plate is parallel to the first direction; The support plate of the counterweight assembly is connected to the two brackets respectively via an elastic component; for the elastic component connected to any one of the counterweight assemblies, the elastic component includes: two spring groups; the two spring groups are respectively connected to both sides of the support plate in the first direction, and are respectively connected to the two brackets.

[0007] In some possible implementations, for the spring assembly connected to the support plate on either side of the first direction, the spring assembly includes two tension springs distributed in the second direction; One end of each of the two tension springs is connected to the support plate near the two corners in the second direction, and the other end of each is connected to the bracket. The second direction is parallel to the width direction of the support plate.

[0008] In some possible implementations, the counterweight assembly closest to the base frame among the at least two counterweight assemblies is the first counterweight assembly, and the tension spring connected to the support plate in the first counterweight assembly is the first tension spring; the counterweight assembly adjacent to the first counterweight assembly among the at least two counterweight assemblies is the second counterweight assembly, and the tension spring connected to the support plate in the second counterweight assembly is the second tension spring. Specifically, for the two first tension springs and the two second tension springs connected to the same bracket, in the second direction, the positions where the two second tension springs are connected to the bracket are both located between the positions where the two first tension springs are connected to the bracket.

[0009] In some possible implementations, when the support plate in the first counterweight assembly is suspended, the two first tension springs in the same spring group have the same length, and the support plate in the first counterweight assembly is perpendicular to the direction of gravity.

[0010] In some possible implementations, when the support plate in the second counterweight assembly is suspended, the two second tension springs in the same spring group have different lengths, and the angle between the support plate in the second counterweight assembly and the reference horizontal plane is an acute angle, the reference horizontal plane being perpendicular to the direction of gravity.

[0011] In some possible implementations, the support plate in the second counterweight assembly is configured such that it comes into contact with the counterweight block in the first counterweight assembly after the spoiler is in a state of rotating from the minimum angle to the target angle. The counterweight is plate-shaped and parallel to the support plate; the target angle is the angle between the support plate in the second counterweight assembly and the reference horizontal plane when the support plate is suspended in the air, and the reference horizontal plane is perpendicular to the direction of gravity.

[0012] In some possible implementations, the electric tail wing durability testing fixture further includes at least one first contour block for detachable connection with the spoiler; Wherein, when the spoiler is at its minimum angle, the side of the at least one first contour block facing away from the spoiler is in contact with the support plate in the first counterweight assembly.

[0013] In some possible implementations, the frame further includes a contouring fixing seat located on the upper side of the base frame and detachably connected to the base frame; The contour fixing seat extends along the first direction and is used to fix it to the fixing part.

[0014] In some possible implementations, the frame further includes a base that is fixedly connected to the underframe; The contour-following fixing seat is detachably connected to the base; The base also has a plurality of second contour blocks, which are distributed at intervals around the contour fixing seat; The surfaces of the plurality of second contour blocks facing away from the base are respectively used to abut against the plurality of buffer pads located on the spoiler plate.

[0015] In the scheme disclosed herein, the spoiler of the electric tail wing and at least two counterweight components are arranged sequentially and at intervals along the direction of gravity. When the spoiler is at a small angle, a small amount of downforce can be applied to the spoiler by a small number of counterweight components, avoiding excessive stress on the spoiler. When the spoiler is at a large angle, a large amount of downforce can be applied to the spoiler by a large number of counterweight components, avoiding insufficient stress on the spoiler. Therefore, the stress situation of the spoiler at any angle within its stroke can be simulated more realistically, improving the accuracy of the service life data obtained from durability tests. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this disclosure, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the structure of an electric tail fin provided in an embodiment of this disclosure; Figure 2 This is a schematic diagram of the structure of an electric tail fin durability testing fixture provided in this embodiment of the present disclosure, in the case where an electric tail fin is installed. Figure 3 This is a front view schematic diagram of an electric tail fin durability testing fixture with an electric tail fin installed, provided in an embodiment of this disclosure. Figure 4 This is a schematic diagram of the structure of a counterweight component and an elastic component connected according to an embodiment of this disclosure; Figure 5 This is a side view of a durability testing fixture for an electric tail fin with an electric tail fin installed, provided in an embodiment of this disclosure. Figure 6 This is a side view of a frame structure provided in an embodiment of this disclosure; Figure 7 This is a side cross-sectional view of an embodiment of the present disclosure showing the connection between an electric tail wing, a contour-following mounting base, and a first contour-following block. Figure 8 This is a bottom view of a spoiler structure provided in an embodiment of this disclosure; Figure 9 This is a schematic diagram of the structure of a spoiler's buffer pad abutting against a second contour block, provided in an embodiment of this disclosure.

[0018] Explanation of reference numerals in the attached figures 1. Frame; 11. Base frame; 12. Support; 121. Second fixing pin; 13. Contouring fixing seat; 14. Base; 141. Second contouring block; 2. Counterweight assembly; 2a. First counterweight assembly; 2b. Second counterweight assembly; 21. Support plate; 211. Connector; 2111. First fixing pin; 22. Counterweight block; 3. Elastic assembly; 31. Spring assembly; 311. Tension spring; 311a. First tension spring; 311b. Second tension spring; 4. First contouring block; 41. First limiting part; 42. Second limiting part; 200. Electric tail wing; 201. Fixing part; 202. Spoiler; 2021. Buffer pad; 2022. Buffer pad; 203. Drive mechanism. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of this disclosure clearer, the embodiments of this disclosure will be described in further detail below with reference to the accompanying drawings.

[0020] Generally, reference Figure 1As shown, the electric rear wing 200 includes a mounting part 201, a spoiler 202, and a drive mechanism 203. The mounting part 201 can be a component fixedly mounted on the vehicle; for example, it can be a mounting bracket. The mounting bracket can be fixed to the trunk lid, rear body panel, or tailgate by bolts, welding, or other methods. The drive mechanism 203 can be a four-link lifting mechanism or a lead screw lifting mechanism, etc. The drive mechanism 203 can be mounted on the mounting part 201. Figure 8 As shown, the lower surface of the spoiler 202 may have a buffer pad 2021 and multiple drive connectors 2022. For example, in Figure 1 In this design, the lower surface of the spoiler 202 may have two drive connectors 2022. The drive connectors 2022 may be sheet metal structures, connected to the drive mechanism 203 via bolts, thus connecting the spoiler 202 to the drive mechanism 203. The drive mechanism 203 can drive the spoiler 202 to rise and fall and to rotate at different angles.

[0021] Firstly, this embodiment relates to an electric tail fin durability testing fixture, as shown in the reference. Figure 2 As shown, the electric tail fin durability testing fixture includes a frame 1 and at least two counterweight components 2. For example, the electric tail fin durability testing fixture may include two, three, four, or five counterweight components 2, etc. The frame 1 includes a base frame 11 and two supports 12 connected to each other. The two supports 12 are located on opposite sides of the base frame 11 in a first direction.

[0022] For example, in Figure 2 In this design, the base frame 11 can be rectangular. The two supports 12 can be portal frames. The two portal frames can face each other, and the two ends of the portal frames can be fixedly connected to the base frame 11 near its two corners in a second direction by welding, bolts, or other means. The first direction can be perpendicular to the direction of gravity.

[0023] Continue to refer to Figure 2 As shown, the counterweight assembly 2 is elastically connected to each of the two supports 12. Combined with... Figure 3 As shown, the base frame 11 and at least two counterweight components 2 are arranged sequentially at intervals along the direction of gravity.

[0024] The base frame 11 is used to connect to the mounting part 201 of the electric tail wing 200. At least two counterweight components 2 are used to gradually apply downward pressure to the spoiler 202 during rotation of the spoiler 202 in the electric tail wing 200. For example, when the mounting part 201 is connected to the base frame 11, the length direction of the spoiler 202 can be parallel to the first direction.

[0025] Since at least two counterweight components 2 are arranged sequentially and at intervals along the direction of gravity, when the rotation angle is small, the spoiler 202 will only be subjected to the downward pressure from a small number of counterweight components 2 that are relatively close to the spoiler 202; when the rotation angle is large, the spoiler 202 can also be subjected to the downward pressure from more counterweight components 2 that are farther apart. Therefore, during the reciprocating motion of the spoiler 202 from the minimum angle to the maximum angle, each counterweight component 2 can apply a variable load force to the spoiler 202, thus conducting a durability test on the electric tail wing 200.

[0026] For example, the electric tail wing 200 under test can have three positions: zero, first, and second. When the electric tail wing 200 is in zero position, the angle between the spoiler 202 and the horizontal plane can be 0°; when the electric tail wing 200 is in first position, the angle between the spoiler 202 and the horizontal plane can be 3° to 8°, for example, 3°, 4°, 5°, 6°, 7°, or 8°; when the electric tail wing 200 is in second position, the angle between the spoiler 202 and the horizontal plane can be 10° to 16°, for example, 10°, 11°, 12°, 13°, 14°, 15°, or 16°. For example, the angle between the spoiler 202 and the horizontal plane is 6° when the electric tail wing 200 is in first position and 13° when the electric tail wing 200 is in second position. 0° can be the minimum angle of spoiler 202, and 13° can be the maximum angle of spoiler 202.

[0027] The electric tail wing durability testing fixture may include two counterweight components 2. When the rotation angle of the spoiler 202 is 0°, no counterweight component 2 may be used to apply downforce to the spoiler 202; when the rotation angle of the spoiler 202 is between 0° and 6° (excluding 0°), one counterweight component 2 may be used to apply downforce to the spoiler 202; when the rotation angle of the spoiler 202 is between 6° and 13° (excluding 6°), both counterweight components 2 may be used to apply downforce to the spoiler 202.

[0028] For example, the electric tail wing 200 under test can have four positions: zero, first, second, and third. When the electric tail wing 200 is in zero position, the angle between the spoiler 202 and the horizontal plane can be 0°; when the electric tail wing 200 is in first position, the angle between the spoiler 202 and the horizontal plane can be 3° to 8°, for example, 3°, 4°, 5°, 6°, 7°, or 8°; when the electric tail wing 200 is in second position, the angle between the spoiler 202 and the horizontal plane can be 10° to 16°, for example, 10°, 11°, 12°, 13°, 14°, 15°, or 16°; and when the electric tail wing 200 is in third position, the angle between the spoiler 202 and the horizontal plane can be 18° to 26°, for example, 18°, 19°, 20°, 21°, 22°, 24°, or 26°. Taking the following scenarios as an example: when the electric tail wing 200 is in its first gear, the angle between the spoiler 202 and the horizontal plane is 6°; when the electric tail wing 200 is in its second gear, the angle is 13°; and when the electric tail wing 200 is in its third gear, the angle is 24°. 0° can be considered the minimum angle of the spoiler 202, and 24° can be considered the maximum angle of the spoiler 202.

[0029] The electric tail wing durability testing fixture may include three counterweight components 2. When the rotation angle of the spoiler 202 is 0°, no counterweight components 2 may apply downforce to the spoiler 202; when the rotation angle of the spoiler 202 is between 0° and 6° (excluding 0°), only one counterweight component 2 may apply downforce to the spoiler 202; when the rotation angle of the spoiler 202 is between 6° and 13° (excluding 6°), only two counterweight components 2 may apply downforce to the spoiler 202. When the rotation angle of the spoiler 202 is between 13° and 24° (excluding 13°), all three counterweight components 2 may apply downforce to the spoiler 202.

[0030] As described above, the spoiler 202 of the electric tail wing 200 and at least two counterweight components 2 are arranged sequentially upwards along the direction of gravity. When the spoiler 202 is at a small angle, a small downforce can be applied to the spoiler 202 by a small number of counterweight components 2, avoiding excessive force on the spoiler 202. When the spoiler 202 is at a large angle, a large downforce can be applied to the spoiler 202 by a large number of counterweight components 2, avoiding insufficient force on the spoiler 202. Therefore, the stress situation of the spoiler 202 at any angle within its stroke can be simulated more realistically, improving the accuracy of the service life data obtained from durability tests.

[0031] In some examples, reference Figure 4 As shown, for any one of the counterweight components 2, the counterweight component 2 includes: a support plate 21, and at least one counterweight block 22 located on the side of the support plate 21 away from the base frame 11. The support plate 21 is strip-shaped, and the length direction of the support plate 21 is parallel to the first direction. The support plate 21 can be made of aluminum profile, which is suitable for high and low temperature test conditions while ensuring a light weight.

[0032] For example, in Figure 4 In this embodiment, the counterweight assembly 2 may include two counterweight blocks 22. However, in other possible examples, the counterweight assembly 2 may include one, two, three, or four counterweight blocks 22, etc. In this embodiment, the number of counterweight blocks 22 in each counterweight assembly 2 is not limited, and the appropriate number of counterweight blocks 22 can be selected according to the downward pressure to be applied in the test. Where the counterweight assembly 2 includes multiple counterweight blocks 22, the multiple counterweight blocks 22 are spaced apart in the first direction.

[0033] Continue to refer to Figure 4 As shown, the support plate 21 of the counterweight assembly 2 is connected to the two supports 12 respectively via elastic components 3. For example, the counterweight assembly 2 and the elastic components 3 can correspond one-to-one, and the counterweight assembly 2 can be connected to the two supports 12 respectively via the corresponding elastic components 3. Wherein, Figure 2 In this example, the electric tail wing durability testing fixture may include two counterweight components 2 and two elastic components 3. However, in other possible examples, the electric tail wing durability testing fixture may also include three counterweight components 2 and three elastic components 3, four counterweight components 2 and four elastic components 3, or five counterweight components 2 and five elastic components 3, etc.

[0034] For any one of the counterweight components 2, the elastic component 3 includes two spring groups 31. The two spring groups 31 are respectively connected to both sides of the support plate 21 in the first direction, and are combined... Figure 2 As shown, the two spring assemblies 31 are respectively connected to the two brackets 12.

[0035] In this way, the downward pressure applied to the spoiler 202 can have a higher uniformity, thus more closely resembling the actual operating conditions, which is beneficial to improving the accuracy of the service life data obtained from the durability test.

[0036] In some examples, the counterweight 22 can be detachably connected to the support plate 21.

[0037] For example, the counterweight 22 can be detachably connected to the support plate 21 by means of bolts, snap-fits, etc. Figure 4As shown, the counterweight 22 can be in the shape of a circular plate. The center of the circular counterweight 22 can have a first mounting hole, and the support plate 21 can have a second mounting hole. A fastener can pass through the first and second mounting holes to achieve a detachable connection between the support plate 21 and the counterweight 22. Specifically, the fastener can be a bolt, pin, or screw, etc.

[0038] This allows for the replacement of the counterweight 22, and facilitates durability testing of different electric tail fins 200 under varying stress conditions during actual use, thereby improving the versatility of the electric tail fin durability testing fixture.

[0039] In some examples, reference Figure 4 and Figure 5 As shown, for the spring assembly 31 connected to either side of the support plate 21 in the first direction, the spring assembly 31 includes two tension springs 311 distributed in the second direction.

[0040] One end of each of the two tension springs 311 is connected to a support plate 21 near one of its two corners in a second direction, and the other end of each is connected to a bracket 12. The second direction is parallel to the width direction of the support plate 21. Thus, the spring assembly 3, used to connect the bracket 12 and the counterweight assembly 2, can simultaneously apply tension to all four corners of the support plate 21, preventing the support plate 21 from becoming unbalanced and ensuring a reliable connection to the counterweight assembly 2.

[0041] Furthermore, as the spoiler 202 flips upward, the tension spring 311 gradually shortens and gradually reduces the upward tension on the connected counterweight component 2. As a result, the downward pressure exerted by the counterweight component 2 on the spoiler 202 can gradually increase, thus more realistically simulating the stress situation of the spoiler 202 in actual use.

[0042] In some examples, such as Figure 4 As shown, the support plate 21 has connectors 211 at both ends in the first direction. The connectors 211 are strip-shaped and parallel to the second direction. The connectors 211 can be fixedly connected to the end face of the support plate 21 in the first direction by welding, bolts, or other methods. The side of the connector 211 facing away from the support plate 21 has two first fixing pins 2111. The two first fixing pins 2111 are located near two corners of the support plate 21 in the second direction. Both first fixing pins 2111 can be fixedly connected to the connectors 211 by welding, snap-fitting, or bolts.

[0043] Combination Figure 2 and Figure 4As shown, each of the two supports 12 has multiple second fixing pins 121 on its opposite side. The number of second fixing pins 121 on each support 12 can be twice the number of counterweight components 2 in the electric tail fin durability testing fixture. Among the multiple second fixing pins 121 on the same support 12, each pair can form a group. The two second fixing pins 121 in the same group can be symmetrically distributed in the second direction. Furthermore, in the second direction, the two second fixing pins 121 in each group can correspond to the two first fixing pins 2111 on a connector 211 on the same side. The second fixing pins 121 can be fixedly connected to the support 12 by welding, snap-fitting, or bolting.

[0044] Continue to refer to Figure 4 As shown, both ends of the tension spring 311 can have hooks. Each tension spring 311 can be hooked to a first fixing pin 2111 and a second fixing pin 121 respectively through two hooks, thereby realizing the connection between the support plate 21 and the bracket 12. Therefore, the tension spring 311 in the electric tail wing durability testing fixture can be replaced, which can further improve the versatility of the electric tail wing durability testing fixture.

[0045] In some examples, reference Figure 5 As shown, the counterweight assembly 2 closest to the base frame 11 among the at least two counterweight assemblies 2 is the first counterweight assembly 2a. The tension spring 311 connected to the support plate 21 in the first counterweight assembly 2a is the first tension spring 311a. The counterweight assembly 2 adjacent to the first counterweight assembly 2a among the at least two counterweight assemblies 2 is the second counterweight assembly 2b. The tension spring 311 connected to the support plate 21 in the second counterweight assembly 2b is the second tension spring 311b.

[0046] Specifically, for the two first tension springs 311a and the two second tension springs 311b connected to the same bracket 12, in the second direction, the positions where the two second tension springs 311b are connected to the bracket 12 are both located between the positions where the two first tension springs 311a are connected to the bracket 12.

[0047] For example, in Figure 2 and Figure 5 In this configuration, each of the two portal frames can have two sets of second fixing pins 121 on opposite sides. One set of second fixing pins 121 connected to the first tension spring 311a can be located on the two uprights of the portal frame. The other set of second fixing pins 121 connected to the second tension spring 311b can be located on the crossbeam of the portal frame.

[0048] This prevents interference between the first tension spring 311a and the second tension spring 311b, thus avoiding affecting the normal use of the electric tail fin durability testing fixture.

[0049] In some examples, reference Figure 5 As shown, when the support plate 21 in the first counterweight assembly 2a is suspended, the two first tension springs 311a in the same spring group 31 have the same length, and the support plate 21 in the first counterweight assembly 2a is perpendicular to the direction of gravity. This simplifies the selection of the first tension spring 311a, improves the accuracy of simulating the actual load when the spoiler 202 is at a small angle, and thus improves the accuracy of the service life data obtained from the durability test.

[0050] In some examples, when the support plate 21 in the second counterweight assembly 2b is suspended, the two second tension springs 311b in the same spring group 31 have different lengths. Furthermore, the angle between the support plate 21 in the second counterweight assembly 2b and the reference horizontal plane is acute, and the reference horizontal plane is perpendicular to the direction of gravity. For example, the angle between the support plate 21 in the second counterweight assembly 2b and the reference horizontal plane can be 3° to 8°, such as 3°, 4°, 5°, 6°, 7°, or 8°. Thus, when the spoiler 202 holds the first counterweight assembly 2a in contact with the support plate 21 of the second counterweight assembly 2b, the tilt angle of the support plate 21 of the second counterweight assembly 2b is relatively close to the tilt angle of the counterweight block 22 of the first counterweight assembly 2a, which helps to avoid single-point force and reduce the accuracy of the simulation of the actual load.

[0051] In some examples, the support plate 21 in the second counterweight assembly 2b is configured such that it comes into contact with the counterweight block 22 in the first counterweight assembly 2a after the spoiler 202 has been rotated from its minimum angle to the target angle. Furthermore, the target angle is less than the difference between the maximum angle and the minimum angle of the spoiler 202.

[0052] The counterweight 22 is plate-shaped and parallel to the support plate 21. For example, in Figure 4 In this example, the counterweight 22 can be in the shape of a circular plate, but in other possible examples, the counterweight 22 can also be in the shape of a rectangular plate, a square plate, or a rhomboid plate, etc.

[0053] The target angle is the angle between the support plate 21 in the second counterweight assembly 2b and the reference horizontal plane when the support plate 21 is in a suspended state, and the reference horizontal plane is perpendicular to the direction of gravity.

[0054] For example, when the support plate 21 in the second counterweight assembly 2b is in a suspended state, the angle between it and the reference horizontal plane can be: the angle that the spoiler 202 needs to rotate when the electric tail wing 200 under test switches from zero gear to first gear.

[0055] Taking the electric tail wing 200 in zero gear with the angle between the spoiler 202 and the horizontal plane at 0° as an example: When the electric tail wing 200 is in first gear, the target angle can be 6° when the angle between the spoiler 202 and the horizontal plane is 6°. When the electric tail wing 200 is in first gear, the target angle can be 5° when the angle between the spoiler 202 and the horizontal plane is 5°. When the electric tail wing 200 is in first gear, the target angle can be 4° when the angle between the spoiler 202 and the horizontal plane is 4°. The electric tail wing 200 under test can have at least three gears, including zero gear, first gear, and second gear.

[0056] Therefore, before the spoiler 202 rotates from its minimum angle to the target angle, it is subjected to the downward pressure applied by the first counterweight component 2a, but not by the downward pressure applied by the second counterweight component 2b, thus preventing excessive force on the spoiler 202. After the spoiler 202 rotates from its minimum angle to the target angle, as it continues to rotate to a larger angle, the second counterweight component 2b and the first counterweight component 2a can jointly apply downward pressure to the spoiler 202, preventing the spoiler 202 from experiencing insufficient force. This improves the accuracy of simulating the actual force on the spoiler 202.

[0057] In some examples, reference Figure 5 As shown, the electric tail wing durability testing fixture also includes at least one first contour block 4, which is used for detachable connection with the spoiler 202. For example, in Figure 2 In this design, the electric tail wing durability testing fixture may include two first contour blocks 4. However, in other possible examples, the electric tail wing durability testing fixture may include one, three, or four first contour blocks 4, etc. The first contour blocks 4 may be made of high-temperature resistant lightweight plastic or rubber, etc.

[0058] Specifically, when the spoiler 202 is at its minimum angle, at least one of the first contouring blocks 4, on the side facing away from the spoiler 202, is in contact with the support plate 21 in the first counterweight assembly 2a. Furthermore, the force between the first contouring block 4 and the support plate 21 in the first counterweight assembly 2a is zero. For example, in... Figure 5 In the case where the spoiler 202 is at its minimum angle, the side of the first contour block 4 away from the spoiler 202 can be a plane, and this plane can be perpendicular to the direction of gravity and fits perfectly with the support plate 21.

[0059] Thus, when the spoiler 202 is at its minimum angle, no first counterweight component 2a applies downward pressure to the spoiler 202. Moreover, as soon as the spoiler 202 begins to rotate, downward pressure can be gradually applied to the spoiler 202 through the first counterweight component 2a. This allows for a more realistic simulation of the force situation of the spoiler 202 at any angle within its stroke.

[0060] In some examples, reference Figure 5 As shown, the surface of the first contour block 4 facing away from the first counterweight assembly 2a is attached to the upper surface of the spoiler 202. For example, the shape of the surface of the first contour block 4 facing away from the first counterweight assembly 2a can be consistent with the shape of the upper surface of the first counterweight assembly 2a. This improves the uniformity of the force applied to the spoiler 202 and avoids abnormal deformation caused by localized stress on the spoiler 202.

[0061] In some examples, reference Figure 5 As shown, the first contour block 4 has a first limiting part 41 and a second limiting part 42 on the side opposite to the first counterweight assembly 2a. The first limiting part 41 and the second limiting part 42 are respectively attached to the first side and the second side of the spoiler 202, wherein the first side and the second side are opposite sides in the width direction of the spoiler 202. In this way, during the flipping movement of the spoiler 202, the first contour block 4 will not deviate from the spoiler 202, and will not detach from the spoiler 202.

[0062] In some examples, the electric tail wing durability testing fixture includes multiple first contour blocks 4, which correspond to multiple drive connectors 2022 of the spoiler 202. For example, the first contour blocks 4 and the drive connectors 2022 of the spoiler 202 can correspond one-to-one. Figure 1 In the middle, the spoiler 202 may have two drive connectors 2022. Combined Figure 2 As shown, the electric tail wing durability testing fixture may include two first contour blocks 4. However, in other possible embodiments, the spoiler 202 may have three drive connectors 2022, four drive connectors 2022, or five drive connectors 2022, etc. Accordingly, the electric tail wing durability testing fixture may include three first contour blocks 4, four first contour blocks 4, or five first contour blocks 4, etc.

[0063] refer to Figure 7 As shown, the first contour block 4 is used to at least partially overlap with the projection of the corresponding drive connector 2022 in the gravity direction. For example, the projection of the first contour block 4 in the gravity direction may cover the projection of the corresponding drive connector 2022 in the gravity direction, or the center position of the projection of the first contour block 4 in the gravity direction may coincide with the center position of the projection of the corresponding drive connector 2022 in the gravity direction.

[0064] Generally, in actual use, the spoiler 202 experiences relatively uniform force across its entire upper surface, and the resultant force can be transmitted to the drive mechanism 203 via the drive connector 2022. In this embodiment, the applied downward pressure is directly transmitted to the drive connector 2022 via the first contour block 4. This improves the accuracy of the force simulation on the spoiler 202 and helps prevent abnormal deformation of other parts of the spoiler 202 due to stress.

[0065] In some examples, reference Figure 6 As shown, the frame 1 also includes a contoured mounting base 13, which is located on the upper side of the base frame 11 and is detachably connected to the base frame 11. The contoured mounting base 13 extends along a first direction and is used for fixed connection with the fixing part 201. The contoured mounting base 13 may have multiple connecting structures, which can be connected to the fixing part 201 and provide support for it. The connecting structures are the same as the connecting structures of the fixing part 201 on the vehicle. Furthermore, when the fixing part 201 is mounted on the contoured mounting base 13, the relative positions between the multiple connecting structures and the fixing part 201 are the same as the relative positions between the multiple connecting structures and the fixing part 201 on the vehicle. For example, the connecting structure of the fixing part 201 on the vehicle can be a bolted connection, and the connecting structure between the contoured mounting base 13 and the fixing part 201 can also be a bolted connection.

[0066] This allows for the simulation of the actual constraints of the electric rear wing 200 on the entire vehicle, which helps reduce testing errors. Furthermore, it eliminates the need to mount components such as the trunk lid, rear body panel, or tailgate onto frame 1 as a whole, significantly reducing the space occupied by the electric rear wing durability testing fixture and facilitating testing.

[0067] In some examples, reference Figure 6 As shown, frame 1 also includes a base 14, which is fixedly connected to the base frame 11. For example, base 14 may include a connected base plate and multiple support blocks. The base plate can be fixedly connected to the base frame 11 by bolts, welding, or other means. Multiple support blocks can be fixedly connected to the upper surface of the base plate by bolts, welding, or other means.

[0068] The contour mounting bracket 13 is detachably connected to the base 14. For example, the contour mounting bracket 13 can be detachably connected to the end face of multiple support blocks away from the base 14 by means of bolts, snap-fit, etc. Thus, the contour mounting bracket 13 can be replaced, thereby enabling testing of electric tail wing 200 with different structural fixing parts 201.

[0069] Continue to refer to Figure 6As shown, the base 14 also has a plurality of second contour blocks 141, which are spaced apart around the contour fixing seat 13. For example, the second contour blocks 141 can be fixedly connected to the upper surface of the base plate by means of bolts, welding, etc. The surfaces of the plurality of second contour blocks 141 facing away from the base 14 are respectively used to abut against the plurality of buffer pads 2021 located on the spoiler 202.

[0070] For example, the number and position of the second contour blocks 141 of the base 14 correspond to the number and position of the buffer pads 2021 on the lower surface of the spoiler 202. Figure 9 As shown, when the spoiler 202 is at its minimum angle, the upper surface of the second contour block 141 can abut against the corresponding buffer pad 2021.

[0071] Therefore, the second contour block 141 can provide a buffer matching surface for the buffer pad 2021 of the spoiler 202, thus more accurately simulating the actual constraint of the electric rear wing 200 on the whole vehicle and further reducing test errors.

[0072] In this embodiment, the spoiler 202 of the electric tail wing 200 and at least two counterweight components 2 are arranged sequentially upwards along the direction of gravity. When the spoiler 202 is at a small angle, a small downforce can be applied to the spoiler 202 by a small number of counterweight components 2 and elastic components 3, avoiding excessive force on the spoiler 202. When the spoiler 202 is at a large angle, a large downforce can be applied to the spoiler 202 by a large number of counterweight components 2 and elastic components 3, avoiding insufficient force on the spoiler 202. Thus, the stress situation of the spoiler 202 at any angle within its stroke can be simulated more realistically, improving the accuracy of the service life data obtained from durability tests.

[0073] It should be noted that, in the description of this application, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0074] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, features defined as "first" or "second" may explicitly or implicitly include one or more features. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0075] In the description of this specification, the references to the terms "certain embodiments", "one embodiment", "some embodiments", "illustrative embodiment", "example", "specific example", or "some examples" refer to specific features, structures, materials, or characteristics described in connection with the embodiments or examples that are included in at least one embodiment or example of this application.

[0076] The above are merely embodiments of this application and are not intended to limit this application. Any modifications, equivalent substitutions, improvements, etc., made within the principles of this application should be included within the protection scope of this application.

Claims

1. A durability testing fixture for an electric tail fin, characterized in that, The electric tail wing durability test fixture includes: a frame (1) and at least two counterweight components (2); The frame (1) includes a base frame (11) and two supports (12) connected to each other; the two supports (12) are respectively located on both sides of the base frame (11) in a first direction; The counterweight assembly (2) is elastically connected to the two supports (12) respectively, and the base frame (11) and the at least two counterweight assemblies (2) are arranged at intervals along the direction of gravity; The base frame (11) is used to connect with the fixing part (201) of the electric tail wing (200); the at least two counterweight components (2) are used to gradually apply downward pressure to the spoiler (202) during the rotation of the spoiler (202) in the electric tail wing (200); the first direction is parallel to the length direction of the spoiler (202).

2. The electric tail fin durability testing fixture according to claim 1, characterized in that, For any one of the counterweight components (2), the counterweight component (2) includes: a support plate (21), and at least one counterweight block (22) located on the side of the support plate (21) away from the base frame (11); the support plate (21) is strip-shaped, and the length direction of the support plate (21) is parallel to the first direction; The support plate (21) of the counterweight assembly (2) is connected to the two brackets (12) respectively through the elastic component (3); for the elastic component (3) connected to any one of the counterweight assemblies (2), the elastic component (3) includes: two spring groups (31); the two spring groups (31) are respectively connected to the two sides of the support plate (21) in the first direction, and are respectively connected to the two brackets (12).

3. The electric tail fin durability testing fixture according to claim 2, characterized in that, For the spring assembly (31) connected to the support plate (21) on either side in the first direction, the spring assembly (31) includes two tension springs (311) distributed in the second direction. One end of each of the two tension springs (311) is connected to the support plate (21) at a position near the two corners in the second direction, and the other end of each is connected to the bracket (12); The second direction is parallel to the width direction of the support plate (21).

4. The electric tail fin durability testing fixture according to claim 3, characterized in that, The counterweight assembly (2) closest to the base frame (11) among the at least two counterweight assemblies (2) is the first counterweight assembly (2a), and the tension spring (311) connected to the support plate (21) in the first counterweight assembly (2a) is the first tension spring (311a); the counterweight assembly (2) adjacent to the first counterweight assembly (2a) among the at least two counterweight assemblies (2) is the second counterweight assembly (2b), and the tension spring (311) connected to the support plate (21) in the second counterweight assembly (2b) is the second tension spring (311b). Among them, for the two first tension springs (311a) and the two second tension springs (311b) connected to the same bracket (12), in the second direction, the positions where the two second tension springs (311b) are connected to the bracket (12) are all located between the positions where the two first tension springs (311a) are connected to the bracket (12).

5. The electric tail fin durability testing fixture according to claim 4, characterized in that, When the support plate (21) in the first counterweight assembly (2a) is in a suspended state, the two first tension springs (311a) in the same spring group (31) have the same length, and the support plate (21) in the first counterweight assembly (2a) is perpendicular to the direction of gravity.

6. The electric tail fin durability testing fixture according to claim 5, characterized in that, When the support plate (21) in the second counterweight assembly (2b) is in a suspended state, the lengths of the two second tension springs (311b) in the same spring group (31) are different, and the angle between the support plate (21) in the second counterweight assembly (2b) and the reference horizontal plane is an acute angle, and the reference horizontal plane is perpendicular to the direction of gravity.

7. The electric tail fin durability testing fixture according to claim 6, characterized in that, The support plate (21) in the second counterweight assembly (2b) is configured to contact the counterweight block (22) in the first counterweight assembly (2a) after the spoiler (202) is in the state of rotating from the minimum angle to the target angle. The counterweight (22) is plate-shaped and parallel to the support plate (21); the target angle is the angle between the support plate (21) in the second counterweight assembly (2b) and the reference horizontal plane when the support plate (21) is in a suspended state, and the reference horizontal plane is perpendicular to the direction of gravity.

8. The electric tail fin durability testing fixture according to claim 5, characterized in that, The electric tail wing durability test fixture also includes at least one first contour block (4), which is used to be detachably connected to the spoiler (202); When the spoiler (202) is at its minimum angle, the side of the first contour block (4) facing away from the spoiler (202) is in contact with the support plate (21) in the first counterweight assembly (2a).

9. The electric tail fin durability testing fixture according to any one of claims 1 to 8, characterized in that, The frame (1) also includes a contour fixing seat (13), which is located on the upper side of the base frame (11) and is detachably connected to the base frame (11); The contour fixing seat (13) extends along the first direction and is used to be fixedly connected to the fixing part (201).

10. The electric tail fin durability testing fixture according to claim 9, characterized in that, The frame (1) also includes a base (14), which is fixedly connected to the base frame (11); The contour fixing seat (13) is detachably connected to the base (14). The base (14) also has a plurality of second contour blocks (141), which are distributed at intervals around the contour fixing seat (13); Among them, the surfaces of the plurality of second contour blocks (141) facing away from the base (14) are respectively used to abut against the plurality of buffer pads (2021) located on the spoiler (202).

Images