Spoiler linkage mechanism, spoiler assembly and vehicle

Abstract

A spoiler linkage mechanism (100), comprising a base (1), a first hinge structure (2), a second hinge structure (3), and a bracket (4) for mounting a spoiler (200), wherein the first hinge structure (2) is disposed between the base (1) and the bracket (4); the second hinge structure (3) is disposed between the base (1) and the bracket (4); the first hinge structure (2) is hinged to the bracket (4) at a first hinge point (5), and the second hinge structure (3) is hinged to the bracket (4) at a second hinge point (6); and the first hinge point (5) and the second hinge point (6) are respectively located at two ends of the bracket (4) in a length direction thereof. Further provided is a spoiler assembly (300) and a vehicle (400). The spoiler linkage mechanism helps prevent the spoiler from detaching from the vehicle.

Description

Tail wing connecting rod mechanism, tail wing assembly and vehicle

[0001] Cross-reference to related applications

[0002] The present disclosure claims priority to the Chinese patent application No. 2024215075245, filed on June 27, 2024, and entitled "Tail wing connecting rod mechanism, tail wing assembly and vehicle", the entire content of which is incorporated herein by reference. TECHNICAL FIELD

[0003] The present disclosure relates to the technical field of vehicle tail wing, in particular, to a tail wing connecting rod mechanism, a tail wing assembly and a vehicle. BACKGROUND

[0004] The vehicle tail wing is connected with the vehicle through a connecting rod mechanism, which can control the lifting of the tail wing, so as to raise or lower the tail wing in different vehicle use scenarios.

[0005] During the driving of the vehicle, on the one hand, the tail wing itself has a certain weight and needs to be supported by the connecting rod mechanism, and on the other hand, the tail wing will also be shaken by the air flow. In the related art, the connecting rod mechanism has insufficient support for the tail wing and poor support stability, which can easily cause the tail wing to be affected in normal work due to shaking during use, increase the driving wind resistance, and even cause the tail wing to fall off the vehicle. SUMMARY

[0006] The purpose of the present disclosure is to provide a tail wing connecting rod mechanism, a tail wing assembly and a vehicle to at least partially solve the above technical problems.

[0007] In order to achieve the above purpose, as a first aspect of the present disclosure, the present disclosure provides a tail wing connecting rod mechanism, comprising a base, a first hinge structure, a second hinge structure and a support, the support being used for mounting a tail wing;

[0008] The first hinge structure is arranged between the base and the support, and the second hinge structure is arranged between the base and the support.

[0009] The first hinge structure and the support are hinged at a first hinge point, and the second hinge structure and the support are hinged at a second hinge point, and the first hinge point and the second hinge point are respectively located at two ends of the length direction of the support.

[0010] Optionally, the first hinge structure comprises at least an A connecting rod, and the second hinge structure comprises at least a B connecting rod, the A connecting rod and the support are hinged at the first hinge point, and the B connecting rod and the support are hinged at the second hinge point.

[0011] Optionally, the second hinge structure further comprises a C-link;

[0012] One end of the C-link is hinged to the B-link, and the other end of the C-link is hinged to the base.

[0013] Optionally, the B-link has opposite first and second ends;

[0014] One end of the C-link is hinged to the first end, and the other end of the C-link is hinged to the bracket.

[0015] Optionally, the second hinge structure further comprises a D-link;

[0016] One end of the D-link is hinged to the base, and the other end of the D-link is hinged to the B-link at a third hinge point;

[0017] The C-link is hinged to the B-link at a fourth hinge point, and the third hinge point is located between the second hinge point and the fourth hinge point.

[0018] Optionally, the B-link comprises a first link segment and a second link segment connected in series;

[0019] The first link segment is a part of the B-link located between the fourth hinge point and the third hinge point;

[0020] The second link segment is a part of the B-link located between the third hinge point and the second hinge point;

[0021] The first link segment and the second link segment are connected at an angle in a height direction of the tail link mechanism, and the height direction is a direction in which the base and the bracket are spaced apart.

[0022] Optionally, a plurality of hinge positions are pre-set on the B-link, and the D-link is selectively matched with the plurality of hinge positions.

[0023] Optionally, the tail link mechanism comprises a plurality of second link segments with different lengths and a plurality of brackets with different lengths;

[0024] The plurality of brackets are selectively used, the plurality of second link segments are selectively used, and each second link segment is used in cooperation with a corresponding bracket.

[0025] Optionally, the B-link is provided with a protruding portion protruding towards the D-link in a thickness direction of the base;

[0026] The protruding portion is located at a position where the first link segment and the second link segment are connected.

[0027] Optionally, the A-link is hinged to the base at a fifth hinge point;

[0028] The C connecting rod is hinged to the base at a sixth hinge point;

[0029] The D connecting rod is hinged to the base at a seventh hinge point;

[0030] The fifth, sixth and seventh hinge points are located at three vertices of a same triangle respectively.

[0031] Optionally, the first hinge structure further comprises an E connecting rod and an F connecting rod;

[0032] One end of the E connecting rod is hinged to the base, the other end of the E connecting rod is hinged to one end of the F connecting rod, and the other end of the F connecting rod is hinged to the A connecting rod;

[0033] The E connecting rod is adapted to be drivingly connected to the driving mechanism.

[0034] Optionally, the A connecting rod comprises a third rod segment and a fourth rod segment;

[0035] The third rod segment and the fourth rod segment are angularly connected in the height direction of the tail wing connecting rod mechanism;

[0036] One end of the third rod segment away from the fourth rod segment is hinged to the base, and one end of the fourth rod segment away from the third rod segment is hinged to the support.

[0037] Optionally, the F connecting rod is hinged to the connection position of the third rod segment and the fourth rod segment.

[0038] Optionally, the third rod segment and the fourth rod segment are connected at a Q point, the F connecting rod is adapted to be connected to the driving mechanism at a T point, one end of the third rod segment away from the fourth rod segment is a first end of the A connecting rod, one end of the fourth rod segment away from the third rod segment is a second end of the A connecting rod, and the Q point and the T point are located on two sides of the line connecting the first end and the second end.

[0039] As a second aspect provided by the present disclosure, the present disclosure provides a tail wing assembly, comprising a tail wing and the tail wing connecting rod mechanism described above, wherein the tail wing is mounted to the support.

[0040] As a third aspect provided by the present disclosure, the present disclosure provides a vehicle comprising the tail wing assembly described above.

[0041] By the technical solution, the first hinge joint and the second hinge joint are arranged at the two ends of the support in the length direction of the support, so that the first hinge structure and the second hinge structure can provide support at the two ends of the support in the length direction of the support, that is, at the two ends of the tail wing in the width direction of the tail wing. In this way, even if the width of the tail wing is large, the stability of supporting the tail wing can be ensured, so that the tail wing is prevented from being affected by shaking during use to affect the normal work of the tail wing, or even from falling off the vehicle.

[0042] Other features and advantages of the present disclosure will be described in detail in the following detailed description section. BRIEF DESCRIPTION OF DRAWINGS

[0043] The accompanying drawings are included to provide a further understanding of the present disclosure and constitute a part of the specification, which together with the detailed description, serve to explain the present disclosure. The drawings illustrate embodiments of the present disclosure and, together with the description, serve to explain the principles of the present disclosure. In the drawings:

[0044] Fig. 1 is a side view schematic diagram of a tail wing linkage mechanism according to an embodiment of the present disclosure.

[0045] Fig. 2 is a perspective view schematic diagram of a hinge structure of the tail wing linkage mechanism according to an embodiment of the present disclosure, wherein a transmission shaft of a driving mechanism is shown.

[0046] Fig. 3 is a perspective view schematic diagram of a B linkage of the tail wing linkage mechanism according to an embodiment of the present disclosure.

[0047] Fig. 4 is a perspective view schematic diagram of the tail wing linkage mechanism according to an embodiment of the present disclosure, wherein the tail wing linkage mechanism is in a lifting state.

[0048] Fig. 5 is a side view schematic diagram of the first hinge structure, the second hinge structure and the support of the tail wing linkage mechanism according to an embodiment of the present disclosure in an assembled state.

[0049] Fig. 6 is a simplified schematic diagram of the tail wing linkage mechanism according to an embodiment of the present disclosure.

[0050] Fig. 7 is a perspective view schematic diagram of the support of the tail wing linkage mechanism according to an embodiment of the present disclosure.

[0051] Fig. 8 is a structural block diagram of a vehicle according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0052] The detailed description of the specific embodiments of the present disclosure will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only used to illustrate and explain the present disclosure, and are not used to limit the present disclosure.

[0053] In the present disclosure, the orientation words such as "upper, lower" are generally defined with the drawing surface direction of the corresponding drawing as the reference, unless otherwise stated. "Inner, outer" refers to the inner and outer of the contour of the corresponding component. In addition, the terms "first", "second" and the like are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0054] As one aspect of the present disclosure, as shown in FIGS. 1-7, the present disclosure provides a tail wing linkage mechanism 100, comprising a base 1, a first hinged structure 2, a second hinged structure 3 and a bracket 4 for mounting a tail wing 200. The first hinged structure 2 is arranged between the base 1 and the bracket 4, and the second hinged structure 3 is arranged between the base 1 and the bracket 4. Among them, the first hinged structure 2 and the bracket 4 are hinged at a first hinge point 5, and the second hinged structure 3 and the bracket 4 are hinged at a second hinge point 6. The first hinge point 5 and the second hinge point 6 are respectively located at both ends of the length direction of the bracket 4.

[0055] The length direction of the bracket 4 is the same as the width direction of the tail wing 200. Since the bracket 4 of the tail wing linkage mechanism 100 extends along the width direction of the tail wing 200, by the above technical solution, the first hinge point 5 and the second hinge point 6 are respectively arranged at both ends of the length direction of the bracket 4, so that the first hinged structure 2 and the second hinged structure 3 can provide support at both ends of the length direction of the bracket 4, that is, at both ends of the width direction of the tail wing 200. In this way, even if the width of the tail wing 200 is large, it is also beneficial to ensure the stability of the support of the tail wing 200, thereby avoiding the situation that the tail wing 200 shakes during use and affects the normal work of the tail wing 200, or even the tail wing 200 falls off the vehicle.

[0056] It can be understood that here, the first hinge point 5 and the second hinge point 6 respectively located at both ends of the length direction of the bracket 4 can refer to that the first hinge point 5 and the second hinge point 6 are respectively located at both ends of the length direction of the bracket 4, that is, the end faces including both ends of the length direction of the bracket 4, and also including the parts close to the end faces. In other words, the distance between the first hinge point 5 and the end face of one end of the length direction of the bracket 4 is less than the distance between the first hinge point 5 and the center line in the length direction of the bracket 4, and the distance between the second hinge point 6 and the end face of the other end of the length direction of the bracket 4 is less than the distance between the second hinge point 6 and the center line in the length direction of the bracket 4.

[0057] Optionally, as shown in FIG. 1, the first hinged structure 2 comprises at least an A-link 21, the second hinged structure 3 comprises at least a B-link 31, the A-link 21 is hinged to the support 4 at a first hinged point 5, and the B-link 31 is hinged to the support 4 at a second hinged point 6. The A-link 21 and the B-link 31 can provide support at both ends of the length direction of the support 4, i.e. at both ends of the width direction of the tail wing 200. The use of the A-link 21 and the B-link 31 can provide stable support for the tail wing, simplify the structure of the tail wing linkage mechanism 100, and reduce the manufacturing cost.

[0058] Optionally, as shown in FIG. 1, the second hinged structure 3 further comprises a C-link 32, one end of the C-link 32 is hinged to the B-link 31, and the other end of the C-link 32 is hinged to the base 1. The tail wing linkage mechanism 100 can comprise a lifting state and a stowed state. In the lifting state, the tail wing linkage mechanism 100 can lift the tail wing 200. The connection of the B-link 31 and the base 1 through the C-link 32 can reduce the length of the C-link 32 and the B-link 31 in the case of lifting the same height. Meanwhile, the B-link 31 and the C-link 32 can be bent at the hinged points, thereby reducing the size of the tail wing linkage mechanism 100 in the height direction and the length direction of the support 4 in the stowed state, and further reducing the occupied space of the tail wing linkage mechanism 100.

[0059] The present disclosure does not limit the hinged manner between the B-link 31 and the C-link 32. In an embodiment of the present disclosure, the B-link 31 has opposite first and second ends 311 and 312, one end of the C-link 32 is hinged to the first end 311 of the B-link 31, and the second end 312 of the B-link 31 is hinged to the support 4. The connection of the two ends of the B-link 31 to the support 4 and the C-link 32 respectively can increase the height of the tail wing 200 in the lifting state of the tail wing linkage mechanism 100, and also increase the range of movement of the B-link 31.

[0060] In order to improve the supporting effect of the tail wing linkage mechanism 100, the second hinge structure 3 further comprises a D linkage 33, one end of the D linkage 33 is hingedly connected to the base 1, and the other end of the D linkage 33 is hingedly connected to the third hinge point 7 with the B linkage 31. The C linkage 32 is hingedly connected to the fourth hinge point 8 with the B linkage 31, and the third hinge point 7 is located between the second hinge point 6 and the fourth hinge point 8. When the tail wing linkage mechanism 100 is in the lifting state, the A linkage 21 and the B linkage 31 are respectively hingedly connected to the two ends of the support 4 along the length direction, the B linkage 31 extends obliquely upward along the length direction of the support 4 and is connected to the support 4, and the D linkage 33 is hingedly connected to the third hinge point 7 with the B linkage 31, and the third hinge point 7 is located between the second hinge point 6 and the fourth hinge point 8, so that when the B linkage 31 supports one end of the support 4, the D linkage 33 can also support the B linkage 31, making up for the problem of insufficient supporting force caused by the longer length of the B linkage 31, avoiding the shaking of the tail wing linkage mechanism 100, and further improving the reliability of supporting the tail wing 200.

[0061] Optionally, as shown in FIGS. 2, 3 and 6, the B linkage 31 comprises a first linkage segment 313 and a second linkage segment 314 connected in angle, the first linkage segment 313 is a part of the B linkage 31 between the fourth hinge point 8 and the third hinge point 7, and the second linkage segment 314 is a part of the B linkage 31 between the third hinge point 7 and the second hinge point 6. The first linkage segment 313 and the second linkage segment 314 are connected in angle in the height direction of the tail wing linkage mechanism 100, and the height direction is the direction in which the base 1 and the support 4 are arranged in space. When the tail wing linkage mechanism 100 is in the stowed state, the B linkage 31 can be accommodated in the accommodation space between the support 4 and the base 1, the B linkage 31 is divided into the first linkage segment 313 and the second linkage segment 314, and the first linkage segment 313 and the second linkage segment 314 are connected in angle in the height direction of the tail wing linkage mechanism 100, that is, the B linkage 31 is not a straight rod in the height direction of the tail wing linkage mechanism 100, but at least comprises the first linkage segment 313 and the second linkage segment 314 connected in angle. In this way, the first linkage segment 313 can be as close as possible to the support 4, so as to fully utilize the space between the support 4 and the base 1, and at the same time, the overall structure of the tail wing linkage mechanism 100 is more compact, which is conducive to reducing the space occupied by the tail wing linkage mechanism 100.

[0062] In order to adapt to different specifications of the tail wing 200, optionally, a plurality of hinge positions are pre-set on the B connecting rod 31, and the D connecting rod 33 is selectively matched with the plurality of hinge positions. Since the widths of different tail wings 200 are different, the positions of the centers of gravity of the tail wings 200 are also different. The plurality of hinge positions provided on the B connecting rod 31 can adjust the hinge positions between the D connecting rod 33 and the B connecting rod 31 for different center of gravity positions of tail wings 200 of different widths, so that the hinge positions of the D connecting rod 33 and the B connecting rod 31 are always close to the center of gravity of the tail wing 200, thereby being able to provide stable support for tail wings 200 of different specifications.

[0063] In another embodiment provided in the present disclosure, the tail wing connecting rod mechanism 100 can include a plurality of second rod segments 314 with different lengths and a plurality of supports 4 with different lengths. The plurality of supports 4 are selectively used, the plurality of second rod segments 314 are selectively used, and each second rod segment 314 is used in cooperation with a corresponding support 4. For tail wings 200 with different widths, by replacing the support 4 that is adapted to the width of the tail wing 200, more comprehensive support can be provided for the tail wing 200 to avoid the problem of insufficient support caused by the support 4 being too short. Moreover, adjusting the length of the second rod segment 314 according to the length of the support 4 can also make the center of gravity of the tail wing 200 closer to the support center of the support 4, thereby improving the support force and support effect of the tail wing connecting rod mechanism 100 on the tail wing 200.

[0064] In order to further increase the integrity of the tail wing connecting rod mechanism 100, optionally, as shown in FIGS. 2 and 3, the B connecting rod 31 is provided with a protruding portion 315 protruding toward the D connecting rod 33 in the thickness direction of the base 1, and the protruding portion 315 is located at the position where the first rod segment 313 and the second rod segment 314 are connected. One end of the D connecting rod 33 is hinged to the B connecting rod 31, and the other end of the D connecting rod 33 is hinged to the base 1. In order to ensure the support effect of the D connecting rod 33, the hinge point of the D connecting rod 33 to the base 1 is located at the middle of the support 4 in the width direction. The setting of the protruding portion 315 makes the B connecting rod 31 close to the D connecting rod 33 located in the middle, so as to be directly connected to the D connecting rod 33 through the protruding portion 315, thereby reducing the setting of the connection structure, making the connection of the D connecting rod 33 and the B connecting rod 31 more integrated, the force transmission path more direct, and the shaking caused by too many connection points reduced.

[0065] Moreover, reducing the connection structure can also reduce the occupation of the connection structure to the accommodation space, further reducing the space occupied by the tail wing connecting rod mechanism 100.

[0066] In order to improve the stability of the tail wing linkage mechanism 100, as shown in FIG. 2 and FIG. 4, the A linkage 21 is hingedly connected to the base 1 at a fifth hinge point 9, the C linkage 32 is hingedly connected to the base 1 at a sixth hinge point 10, and the D linkage 33 is hingedly connected to the base 1 at a seventh hinge point 11. The fifth hinge point 9, the sixth hinge point 10, and the seventh hinge point 11 are respectively located at the three vertices of the same triangle. The support 4 is directly or indirectly connected to the base 1 through the A linkage 21, the B linkage 31, the C linkage 32, and the D linkage 33. The fifth hinge point 9, the sixth hinge point 10, and the seventh hinge point 11 are respectively arranged at the three vertices of the same triangle, so that the three linkages can support each other, thereby preventing the three linkages from easily changing the support state when a force is applied thereto in the lifted state of the tail wing linkage mechanism 100, and maintaining the support of the tail wing 200.

[0067] As shown in FIG. 4 and FIG. 5, the first hinge structure 2 further includes an E linkage 22 and an F linkage 23. One end of the E linkage 22 is hingedly connected to the base 1, the other end of the E linkage 22 is hingedly connected to one end of the F linkage 23, and the other end of the F linkage 23 is hingedly connected to the A linkage 21. The E linkage 22 is adapted to be drivingly connected to the driving mechanism 13, and the E linkage 22 can be configured as a crank of the first hinge structure 2. The tail wing linkage mechanism 100 can be switched between the lifted state and the stowed state under the driving of the driving mechanism 13. The E linkage 22 is connected to the transmission shaft 12 of the driving mechanism 13 and is configured as a crank, so that the E linkage 22 can drive the F linkage 23 to perform a planar compound motion of swinging and moving when the E linkage 22 rotates, thereby driving the A linkage 21 to rise or fall, so as to lift or stow the support 4.

[0068] As shown in FIG. 5 and FIG. 6, the A linkage 21 can include a third linkage segment 211 and a fourth linkage segment 212. The third linkage segment 211 and the fourth linkage segment 212 are connected at an angle in the height direction of the tail wing linkage mechanism 100. One end of the third linkage segment 211 away from the fourth linkage segment 212 is hingedly connected to the base 1, and one end of the fourth linkage segment 212 away from the third linkage segment 211 is hingedly connected to the support 4. That is, the A linkage 21 is not a straight rod in the height direction of the tail wing linkage mechanism 100, but at least includes the third linkage segment 211 and the fourth linkage segment 212 connected at an angle. The third linkage segment 211 and the fourth linkage segment 212 of the A linkage 21 are arranged to be connected at an angle, so that the A linkage 21 is configured as a bent rod. When the tail wing linkage mechanism 100 is in the lifted state or the stowed state, the A linkage 21 occupies a smaller space in the height direction of the tail wing linkage mechanism 100 (which can be the same as the height direction of the vehicle), which is conducive to reducing the space occupied by the tail wing linkage mechanism 100.

[0069] As shown in FIG. 5, optionally, one end of the third rod segment 211 away from the fourth rod segment 212 is the first end 213 of the A-link 21, i.e. the first end 213 of the A-link 21 is hinged to the base 1, and the other end of the fourth rod segment 212 away from the third rod segment 211 is the second end 214 of the A-link 21, i.e. the second end 214 of the A-link 21 is hinged to the bracket 4. The third rod segment 211 and the fourth rod segment 212 are connected at the Q point, and the F-link 23 and the driving mechanism 13 are connected at the T point (as shown in FIG. 5). The Q point and the T point are located on both sides of the line connecting the first end 213 and the second end 214, in other words, by locating the Q point and the T point on both sides of the line connecting the first end 213 and the second end 214, the A-link 21 can be bent towards the direction of the F-link 23 and the driving mechanism 13, and the projection of the F-link 23 and the A-link 21 on the base 1 extends along the length direction of the base 1 (e.g. the left-right direction of the drawing plane in FIG. 5), i.e. the bending opening of the A-link 21 faces the F-link 23, so that the F-link 23 can be at least partially accommodated in the bending opening of the A-link 21. In this way, it is beneficial to reduce the size of the overall structure of the A-link 21 and the F-link 23 in the length direction of the base 1, and to reduce the space occupation.

[0070] It can be understood that the T point can be located on the F-link 23 itself, or on an intermediate piece connected between the F-link 23 and the driving mechanism 13, e.g. on the E-link 22 connected between the transmission shaft 12 and the F-link 23.

[0071] Optionally, as shown in FIG. 5 and FIG. 6, the F-link 23 is hinged at the connection position of the third rod segment 211 and the fourth rod segment 212. During the process of converting the tail wing linkage mechanism 100 from the stowed state to the raised state, since the F-link 23 is hinged at the connection position of the third rod segment 211 and the fourth rod segment 212, the F-link 23 can drive the third rod segment 211 and the fourth rod segment 212 to rotate around the base 1 and the bracket 4 respectively under the drive of the driving mechanism 13, thereby driving the bracket 4 to rise, and the A-link 21 is rotated to the supporting position. At the same time, by reasonable design, in the embodiment shown in FIG. 6, the E-link 22 and the F-link 23 are collinear, and a self-locking structure can be formed. At this time, under the abutting action of the F-link 23, the A-link 21 does not move along the length direction and the height direction of the tail wing linkage mechanism 100, thereby forming a larger self-locking structure with the E-link 22 and the F-link 23, and ensuring the stability of the tail wing linkage mechanism 100.

[0072] The present disclosure does not make specific limitation on the length of each connecting rod. In an embodiment provided by the present disclosure, as shown in FIG. 6, the ratio between the lengths of the E connecting rod 22, the F connecting rod 23, the third rod segment 211, the fourth rod segment 212, the first rod segment 313, the D connecting rod 33 and the C connecting rod 32 can be any appropriate ratio. The lengths of each connecting rod can be scaled proportionally under the condition of meeting the ratio range to meet the needs of the supporting effect of tail wings 200 of different specifications, so that smaller connecting rod lengths are used to meet the supporting effect of tail wings 200, reduce the requirement for the driving force of the driving mechanism 13, and make the entire tail wing connecting rod mechanism 100 smaller in size and lighter in weight under the premise of meeting the supporting needs of tail wings 200.

[0073] Optionally, as shown in FIG. 7, the bracket 4 further comprises a first plate 42 and a second plate 43 connected to each other, a connecting portion 44 extending along the height direction of the tail wing connecting rod mechanism 100 is formed between the first plate 42 and the second plate 43, a first protrusion 45 is formed on the first plate 42 along the height direction of the tail wing connecting rod mechanism 100, and one end of the B connecting rod 21 is hinged to the connecting portion 44, and the first protrusion 45 is used to be hinged to the A connecting rod 23.

[0074] As a second aspect provided by the present disclosure, as shown in FIG. 8, the present disclosure provides a tail wing assembly 300 comprising the tail wing 200 and the tail wing connecting rod mechanism 100 described above, and the tail wing 200 is mounted on the bracket 4.

[0075] As a third aspect provided by the present disclosure, as shown in FIG. 8, the present disclosure provides a vehicle 400 comprising the tail wing assembly 300 described above.

[0076] The preferred embodiments of the present disclosure are described in detail above with reference to the drawings, but the present disclosure is not limited to the specific details in the above-described embodiments. Within the technical concept range of the present disclosure, various simple modifications can be made to the technical solutions of the present disclosure, and these simple modifications all belong to the protection range of the present disclosure.

[0077] In addition, it should be noted that each specific technical feature described in the above specific embodiments can be combined in any appropriate manner without contradiction. In order to avoid unnecessary repetition, the present disclosure does not further describe various possible combinations.

[0078] In addition, any combination between various different embodiments of the present disclosure can also be made as long as it does not deviate from the idea of the present disclosure, and it should also be considered as disclosed by the present disclosure.

Claims

1. A tail fin linkage mechanism (100), characterized in that, It includes a base (1), a first hinge structure (2), a second hinge structure (3) and a bracket (4), wherein the bracket (4) is used to install a tail fin (200); The first hinge structure (2) is disposed between the base (1) and the bracket (4); The second hinge structure (3) is disposed between the base (1) and the bracket (4); The first hinge structure (2) is hinged to the bracket (4) at the first hinge point (5), and the second hinge structure (3) is hinged to the bracket (4) at the second hinge point (6). The first hinge point (5) and the second hinge point (6) are located at the two ends of the length direction of the bracket (4).

2. The tail fin linkage mechanism (100) according to claim 1, characterized in that, The first hinge structure (2) includes at least a link A (21), and the second hinge structure (3) includes at least a link B (31). The link A (21) is hinged to the bracket (4) at the first hinge point (5), and the link B (31) is hinged to the bracket (4) at the second hinge point (6).

3. The tail fin linkage mechanism (100) according to claim 2, characterized in that, The second hinge structure (3) also includes a C-link (32); One end of the C-link (32) is hinged to the B-link (31), and the other end of the C-link (32) is hinged to the base (1).

4. The tail fin linkage mechanism (100) according to claim 3, characterized in that, The B-link (31) has a first end (311) and a second end (312) opposite to each other; One end of the C-link (32) is hinged to the first end (311), and the second end (312) is hinged to the bracket (4).

5. The tail fin linkage mechanism (100) according to claim 3 or 4, characterized in that, The second hinge structure (3) also includes a D-link (33); One end of the D-link (33) is hinged to the base (1), and the other end of the D-link (33) is hinged to the B-link (31) at the third hinge point (7). The C link (32) and the B link (31) are hinged at the fourth hinge point (8), and the third hinge point (7) is located between the second hinge point (6) and the fourth hinge point (8).

6. The tail fin linkage mechanism (100) according to claim 5, characterized in that, The B-link (31) includes a first link segment (313) and a second link segment (314) connected together; The first segment (313) is the part of the B link (31) located between the fourth hinge point (8) and the third hinge point (7); The second link segment (314) is the portion of the B link (31) located between the third hinge point (7) and the second hinge point (6); The first rod segment (313) and the second rod segment (314) are connected at an angle in the height direction of the tail wing linkage mechanism (100), and the height direction is the direction in which the base (1) and the bracket (4) are arranged at intervals.

7. The tail fin linkage mechanism (100) according to claim 5 or 6, characterized in that, The B link (31) has multiple hinge positions, and the D link (33) is selected to cooperate with one of the multiple hinge positions.

8. The tail fin linkage mechanism (100) according to claim 6, characterized in that, The tail fin linkage mechanism (100) includes multiple second rod segments (314) of different lengths and multiple brackets (4) of different lengths; Multiple supports (4) are used in one way, multiple second segments (314) are used in one way, and each second segment (314) is used in conjunction with the corresponding support (4).

9. The tail fin linkage mechanism (100) according to claim 6 or 8, characterized in that, The B link (31) is provided with a protrusion (315) that protrudes toward the D link (33) along the thickness direction of the base (1); The protrusion (315) is located at the position where the first rod segment (313) and the second rod segment (314) are connected.

10. The tail fin linkage mechanism (100) according to any one of claims 5-9, characterized in that, The A connecting rod (21) is hinged to the base (1) at the fifth hinge point (9); The C-link (32) is hinged to the base (1) at the sixth hinge point (10); The D-link (33) is hinged to the base (1) at the seventh hinge point (11); The fifth hinge point (9), the sixth hinge point (10), and the seventh hinge point (11) are located at the three vertices of the same triangle.

11. The tail fin linkage mechanism (100) according to any one of claims 2-10, characterized in that, The first hinge structure (2) further includes link E (22) and link F (23); One end of the E-link (22) is hinged to the base (1), the other end of the E-link (22) is hinged to one end of the F-link (23), and the other end of the F-link (23) is hinged to the A-link (21); The E-link (22) is adapted to be connected to the drive mechanism (13) for transmission.

12. The tail fin linkage mechanism (100) according to claim 11, characterized in that, The A link (21) includes a third segment (211) and a fourth segment (212); The third link segment (211) and the fourth link segment (212) are connected at an angle in the height direction of the tail fin linkage mechanism (100); The third rod segment (211) is hinged to the base (1) at the end away from the fourth rod segment (212), and the fourth rod segment (212) is hinged to the bracket (4) at the end away from the third rod segment (211).

13. The tail fin linkage mechanism (100) according to claim 12, characterized in that, The F-link (23) is hinged at the connection position between the third link segment (211) and the fourth link segment (212).

14. The tail fin linkage mechanism (100) according to claim 12 or 13, characterized in that, The third link segment (211) and the fourth link segment (212) are connected at point Q. The F link (23) is adapted to be connected to the drive mechanism at point T. The end of the third link segment (211) away from the fourth link segment (212) is the first end (211) of the A link (21). The end of the fourth link segment (212) away from the third link segment (211) is the second end (212) of the A link (21). The Q point and the T point are located on both sides of the line connecting the first end (211) and the second end (212).

15. A tail fin assembly (300), characterized in that, It includes a tail fin (200) and a tail fin linkage mechanism (100) according to any one of claims 1-14, wherein the tail fin is mounted on the bracket (4).

16. A vehicle (400), characterized in that, Includes the tail wing assembly (300) according to claim 15.

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