Connecting rod mechanism for wingspan plate of vehicle-mounted parking apron

Abstract

The utility model discloses a connecting rod mechanism for wingspan plates of a vehicle-mounted parking apron, which relates to the technical field of parking aprons, and is characterized by comprising a chassis, a first driving oil cylinder, a second driving oil cylinder and a third driving oil cylinder which are fixedly connected to a main wingspan plate and an auxiliary wingspan plate respectively, a first connecting mechanism is arranged between the first driving oil cylinder and the second driving oil cylinder, and a second connecting mechanism is arranged between the second driving oil cylinder and the third driving oil cylinder. The second driving oil cylinder, the third driving oil cylinder, the first connecting mechanism and the second connecting mechanism are combined with the main wingspan plate and the auxiliary wingspan plate, so that gaps among the main wingspan plate, the auxiliary wingspan plate and the supporting structure are reduced, and the stability of the surface of the parking apron is improved; and through cooperation of the multiple rotating shafts, the connecting plates and the connecting rods, the driving oil cylinders can drive the wing unfolding plates of the parking apron to be unfolded and folded only by doing back-and-forth linear motion, and the deployment efficiency of the vehicle-mounted parking apron is greatly improved.

Description

Technical Field

[0001] This utility model relates to the field of helipad technology, and more specifically, it relates to a linkage mechanism for a vehicle-mounted helipad wingplate. Background Technology

[0002] Currently, existing vehicle-mounted helipads are modified from semi-trailer tractors. Their main structure includes: tractor unit, chassis, wing-shaped platform, supporting boom, outriggers, electronic control system, and power system. The operating procedure is as follows: first, extend the boom; then, slowly lower the supporting boom and outriggers. Once the outriggers touch the ground, flatten the wing-shaped platform. Next, unfold the folded wing-shaped platform until it presses against the boom. Finally, analyze the stress on each outrigger using pressure sensors and adjust it so that the stress on each outrigger is approximately the same.

[0003] In the above scheme, the wing panel and the rotor arm are two independent structures. The rotor arm needs to be rotated out in two separate steps before the wing panel can be lowered. The deployment process is complex, time-consuming, and inefficient. It is difficult to handle urgent tasks such as emergency rescue and public safety. In addition, the wing panel and the supporting rotor arm are not connected. After multiple landing operations, the surface of the wing panel will inevitably deform, which will cause the wing panel and the rotor arm to not make complete contact, affecting the stability of the wing panel and creating a safety hazard for the landing of the vertical take-off and landing aircraft.

[0004] Therefore, a new solution is needed to address this problem. Utility Model Content

[0005] The purpose of this utility model embodiment is to provide a linkage mechanism for a vehicle-mounted helipad wing panel in order to solve the above-mentioned problems.

[0006] The above-mentioned technical objective of this utility model embodiment is achieved through the following technical solution: a linkage mechanism for a vehicle-mounted helipad wingplate, comprising a chassis, wherein a main wingplate, a support plate, and a secondary wingplate are sequentially arranged from the inside to the outside of the chassis, the chassis, the main wingplate, the support plate, and the secondary wingplate are sequentially hinged, and a first driving cylinder, a second driving cylinder, and a third driving cylinder are respectively fixedly connected to the chassis, the main wingplate, and the secondary wingplate, wherein a first connecting mechanism for driving the second driving cylinder is provided at one end of the first driving cylinder, and a second connecting mechanism for driving the third driving cylinder is provided at the end of the second driving cylinder away from the first driving cylinder, wherein a support cylinder is rotatably connected inside the secondary wingplate, and a third connecting mechanism for driving the support cylinder to rotate is provided between the second connecting mechanism and the support cylinder.

[0007] The present invention is further configured such that: a first rotating shaft is rotatably connected between the chassis and the main wing plate; a second rotating shaft and a third rotating shaft are rotatably connected between the support plate, the main wing plate, and the aileron plate, respectively; and a fourth rotating shaft is rotatably connected between the aileron plate and the support cylinder.

[0008] The present invention is further configured such that: a first mounting seat is provided in the chassis to rotate with the first driving cylinder; the first connecting mechanism includes a first connecting plate and a first connecting rod; the first connecting plate rotates with a first rotating shaft; the output end of the first driving cylinder is hinged to the end of the first connecting plate away from the first rotating shaft; the first driving cylinder and the first connecting rod are staggered; and the first connecting rod is hinged to the second driving cylinder.

[0009] The present invention is further configured such that: a second mounting seat is provided inside the aileron flap to rotate with the third drive cylinder; the second connecting mechanism includes a second connecting plate fixedly connected to the support plate; the output end of the second drive cylinder is hinged to the end of the second connecting plate away from the second rotating shaft; and the output end of the third drive cylinder is hinged to the end of the second connecting plate away from the third rotating shaft.

[0010] The present invention is further configured such that: the third connecting mechanism includes a second connecting rod disposed on the same side as the third driving cylinder, one end of the second connecting rod is hinged to the second connecting plate and located above the output end of the third driving cylinder, and the end of the second connecting rod away from the second connecting plate is hinged to the supporting cylinder.

[0011] The present invention is further configured to include a PLC controller, wherein the PLC controller is electrically connected to the first drive cylinder, the second drive cylinder, the third drive cylinder, and the support cylinder.

[0012] In summary, this utility model has the following beneficial effects:

[0013] By combining the second and third drive cylinders, as well as the first, second, and third connecting mechanisms, with the main wing panel and aileron panel, the gap between the main wing panel, aileron panel, and the supporting structure is reduced, thereby improving the stability of the apron surface.

[0014] Through the coordination of multiple rotating shafts, connecting plates, and connecting rods, the drive cylinders only need to perform back-and-forth linear motion to open and fold the helipad wingspan. During use, the chassis, main wingspan, support plate, and aileron wingspan are connected via the first, second, and third connecting mechanisms. The PLC controller drives the retraction of the first, second, and third drive cylinders, thereby rotating and opening the main wingspan, support plate, aileron wingspan, and support cylinders. This ensures the main wingspan, support plate, and aileron wingspan are aligned on the same plane, with the support cylinders perpendicular to the aileron wingspan, providing support for the helipad wingspan. After use, simply controlling the extension of the first, second, and third drive cylinders folds the main wingspan, support plate, aileron wingspan, and support cylinders, greatly improving the deployment efficiency of the vehicle-mounted helipad and making its use more efficient. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the linkage mechanism for a vehicle-mounted helipad wing panel according to the present invention. Figure 1 ;

[0016] Figure 2 This is a schematic diagram of the linkage mechanism for a vehicle-mounted helipad wing panel according to the present invention. Figure 2 ;

[0017] Figure 3 This is a schematic diagram of the linkage mechanism for a vehicle-mounted helipad wing panel according to the present invention. Figure 3 ;

[0018] Figure 4 This is a schematic diagram of the linkage mechanism for a vehicle-mounted helipad wing panel according to the present invention. Figure 4 .

[0019] Reference numerals: 1. Chassis; 2. Main wing flap; 3. Support plate; 4. Aileron flap; 5. First drive cylinder; 6. Second drive cylinder; 7. Third drive cylinder; 8. Support cylinder; 9. First pivot; 10. Second pivot; 11. Third pivot; 12. Fourth pivot; 13. First mounting base; 14. First connecting rod; 15. Second mounting base; 16. Second connecting plate; 17. Second connecting rod; 18. First connecting plate. Detailed Implementation

[0020] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0021] In one possible embodiment, please refer to Figure 1 As shown, a linkage mechanism for a vehicle-mounted helipad wingplate includes a chassis 1. The chassis 1 has a main wingplate 2, a support plate 3, and an aileron wingplate 4 arranged sequentially from the inside to the outside. The chassis 1, the main wingplate 2, the support plate 3, and the aileron wingplate 4 are hinged sequentially. A first pivot 9 is rotatably connected between the chassis 1 and the main wingplate 2. A second pivot 10 and a third pivot 11 are rotatably connected between the support plate 3 and the main wingplate and the aileron wingplate, respectively. By setting multiple pivots, the rotational coordination between the chassis 1, the main wingplate 2, the support plate 3, and the aileron wingplate 4 is realized.

[0022] For further details, please refer to Figure 1 and Figure 2 As shown, a first drive cylinder 5 is fixedly connected to the chassis 1. One end of the first drive cylinder 5 is provided with a first connecting mechanism for driving the second drive cylinder 6 to move. A first mounting seat 13 is provided inside the chassis 1 to rotate with the first drive cylinder 5. The first connecting mechanism includes a first connecting plate 18 and a first connecting rod 14. The first connecting plate 18 is rotatably connected with the first rotating shaft 9. The output end of the first drive cylinder 5 is hinged to the end of the first connecting plate 18 away from the first rotating shaft 9. The first drive cylinder 5 and the first connecting rod are staggered. Thus, in use, by retracting the output end of the first drive cylinder 5, the first connecting rod 14 can be driven to rotate around the first rotating shaft 9, thereby driving the main wing flap 2 to rotate with the chassis 1, so that the main wing flap 2 can be rotated open or folded.

[0023] For further details, please refer to Figure 2 and Figure 3 As shown, a second drive cylinder 6 is fixedly connected to the main wing plate. The first connecting rod 14 is hinged to the second drive cylinder 6. The end of the second drive cylinder 6 away from the first drive cylinder 5 is provided with a second connecting mechanism for driving the third drive cylinder 7 to move. The second connecting mechanism includes a second connecting plate 16 fixedly connected to the support plate 3. The output end of the second drive cylinder is hinged to the end of the second connecting plate 16 away from the second rotating shaft 10. By retracting the output end of the second drive cylinder 6, the second connecting plate 16 can be driven to rotate around the second rotating shaft 10, thereby driving the support plate 3 to rotate and cooperate with the main wing plate 2, so that the support plate 3 can be rotated open or folded.

[0024] For further details, please refer to Figure 3 and Figure 4 As shown, a third drive cylinder 7 is fixedly connected to the aileron plate. A second mounting seat 15 is provided inside the aileron plate 4 to rotate with the third drive cylinder 7. The output end of the third drive cylinder is hinged to the end of the second connecting plate 16 away from the third rotating shaft 11. By retracting the output end of the third drive cylinder 7, the aileron plate 4 can be driven to rotate around the third rotating shaft 11, thereby driving the aileron plate 4 to rotate with the support plate 3, so that the aileron plate 4 can be rotated open or folded.

[0025] For further details, please refer to Figure 3 and Figure 4 As shown, a support cylinder 8 is rotatably connected inside the aileron 4, and a fourth rotating shaft 12 is rotatably connected between the aileron 4 and the support cylinder 8. A third connecting mechanism for driving the support cylinder 8 to rotate is provided between the second connecting mechanism and the support cylinder 8. The third connecting mechanism includes a second connecting rod 17 arranged on the same side as the third driving cylinder 7. One end of the second connecting rod 17 is hinged to the second connecting plate 16 and located above the output end of the third driving cylinder 7. The end of the second connecting rod 17 away from the second connecting plate 16 is hinged to the support cylinder 8. Therefore, the contraction of the output end of the third driving cylinder 7 can also drive the rotation of the second connecting rod 17, thereby driving the rotation of the support cylinder 8. When the aileron 4 and the support plate 3 are on the same plane, the support cylinder 8 is perpendicular to the aileron 4 and is set perpendicular to the ground, thus providing support for the aileron 4.

[0026] For details, please refer to Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, by combining the second drive cylinder 6, the third drive cylinder 7, and the first, second, and third connecting mechanisms with the main wing panel 2 and the aileron panel 4, the gap between the main wing panel 2, the aileron panel 4, and the supporting structure is reduced, thereby improving the stability of the apron surface. Through the cooperation between multiple rotating shafts, connecting plates, and connecting rods, the drive cylinders only need to make back-and-forth linear movements to drive the opening and folding of the apron wing panels.

[0027] For further details, please refer to Figure 1 , Figure 2 , Figure 3 and Figure 4As shown, it also includes a PLC controller, which is electrically connected to the first drive cylinder 5, the second drive cylinder 6, the third drive cylinder 7, and the support cylinder 8. The PLC controller drives the synchronous retraction of the first drive cylinder, the second drive cylinder 6, and the third drive cylinder 7, thereby driving the rotation and opening of the main wing panel 2, the support plate 3, the aileron wing panel 4, and the support cylinder 8. This ensures that the main wing panel 2, the support plate 3, and the aileron wing panel 4 are on the same straight plane, and the support cylinder 8 is perpendicular to the aileron wing panel 4, providing support for the apron wing panel. After use, simply controlling the extension of the first drive cylinder, the second drive cylinder 6, and the third drive cylinder 7 can fold the main wing panel 2, the support plate 3, the aileron wing panel 4, and the support cylinder 8, thereby greatly improving the deployment efficiency of the vehicle-mounted helipad and making its use more efficient.

[0028] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the invention to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of this utility model, thereby enabling those skilled in the art to better understand and utilize it.

Claims

1. A linkage mechanism for a vehicle-mounted helipad wing panel, comprising a chassis (1), characterized in that: The chassis (1) is provided with a main wingplate (2), a support plate (3) and an aileron (4) from the inside to the outside. The chassis (1), main wingplate (2), support plate (3) and aileron (4) are hinged in sequence. A first drive cylinder (5), a second drive cylinder (6) and a third drive cylinder (7) are fixedly connected to the chassis (1), main wingplate (2) and aileron (4) respectively. A first connecting mechanism for driving the second drive cylinder (6) is provided at one end of the first drive cylinder (5). A second connecting mechanism for driving the third drive cylinder (7) is provided at the end of the second drive cylinder (6) away from the first drive cylinder (5). A support cylinder (8) is rotatably connected inside the aileron (4). A third connecting mechanism for driving the support cylinder (8) to rotate is provided between the second connecting mechanism and the support cylinder (8).

2. The linkage mechanism for a vehicle-mounted helipad wing panel according to claim 1, characterized in that: The chassis (1) is rotatably connected to the main wing panel (2) by a first rotating shaft (9), the support plate (3) is rotatably connected to the main wing panel and the aileron by a second rotating shaft (10) and a third rotating shaft (11) respectively, and the aileron panel (4) is rotatably connected to the support cylinder (8) by a fourth rotating shaft (12).

3. The linkage mechanism for a vehicle-mounted helipad wing panel according to claim 2, characterized in that: The chassis (1) is provided with a first mounting base (13) that rotates with the first drive cylinder (5). The first connecting mechanism includes a first connecting plate (18) and a first connecting rod (14). The first connecting plate (18) rotates with the first rotating shaft (9). The output end of the first drive cylinder (5) is hinged to the end of the first connecting plate (18) away from the first rotating shaft (9). The first drive cylinder (5) and the first connecting rod are staggered. The first connecting rod (14) is hinged with the second drive cylinder (6).

4. The linkage mechanism for a vehicle-mounted helipad wing panel according to claim 2, characterized in that: The aileron (4) is provided with a second mounting base (15) that rotates with the third drive cylinder (7). The second connecting mechanism includes a second connecting plate (16) that is fixedly connected to the support plate (3). The output end of the second drive cylinder (6) is hinged to the end of the second connecting plate (16) away from the second rotating shaft (10). The output end of the third drive cylinder (7) is hinged to the end of the second connecting plate (16) away from the third rotating shaft (11).

5. A linkage mechanism for a vehicle-mounted helipad wing panel according to claim 2, characterized in that: The third connecting mechanism includes a second connecting rod (17) disposed on the same side as the third driving cylinder (7). One end of the second connecting rod (17) is hinged to the second connecting plate (16) and located above the output end of the third driving cylinder (7). The end of the second connecting rod (17) away from the second connecting plate (16) is hinged to the support cylinder (8).

6. The linkage mechanism for a vehicle-mounted helipad wing panel according to claim 1, characterized in that: It also includes a PLC controller, which is electrically connected to the first drive cylinder (5), the second drive cylinder (6), the third drive cylinder (7) and the support cylinder (8).

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