Aircraft parking apron device

Abstract

The invention discloses an aircraft parking apron device, and relates to the technical field of aircraft parking aprons. An aircraft parking apron device comprises a shell with an opening, a transfer platform used for receiving an unmanned aerial vehicle is movably arranged in the shell, the shell is provided with a driving mechanism connected to the transfer platform, and the transfer platform is provided with an elastic supporting mechanism; the elastic supporting mechanism comprises a telescopic assembly installed on the transfer platform, an installation base connected to the telescopic assembly, an installation piece connected to the installation base in a sliding mode, a buffer spring connected to the installation piece and the installation base, and a supporting piece rotationally connected to the installation piece. Instantaneous impact force generated during landing of the unmanned aerial vehicle can be effectively buffered.

Description

Technical Field

[0001] This application relates to the technical field of aircraft parking aprons, and in particular to an aircraft parking apron device. Background Technology

[0002] With the rapid iteration of drone technology, its large-scale application in scenarios such as urban last-mile logistics delivery, field emergency rescue, and power and transportation line inspection is becoming increasingly widespread. To overcome the bottleneck of the limited endurance of drones themselves and achieve immediate take-off and on-demand operation, vehicle-mounted drone helipads, with their core advantage of being flexibly deployed using various vehicles such as SUVs, light trucks, and emergency command vehicles, and dynamically moving with the work area, have become a key research and development direction in the field of drone supporting equipment. Their performance directly affects the efficiency of drone operations and equipment safety.

[0003] Currently, most existing vehicle-mounted helipads use rigid metal brackets for their support structures, lacking the necessary elastic buffering capacity. During drone landing, the drone's weight and landing speed generate instantaneous impact on the helipad, which the rigid support structure cannot effectively absorb and buffer. This results in the impact being directly transmitted to the drone's fuselage, various parts of the helipad structure, and the vehicle's mounting points. On the one hand, this can cause problems such as drone landing gear deformation, affecting the drone's service life and operational stability. On the other hand, long-term repeated impacts can cause fatigue cracks in some structures of the helipad, reducing the safety of drone and vehicle use. Summary of the Invention

[0004] In order to effectively buffer the instantaneous impact force generated when a drone lands, this application provides an aircraft landing pad device.

[0005] The aircraft landing pad device provided in this application adopts the following technical solution: An aircraft landing pad device includes a housing with an opening, a transfer platform for receiving a drone is movably disposed within the housing, a drive mechanism connected to the transfer platform is mounted on the housing, and an elastic support mechanism is mounted on the transfer platform. The elastic support mechanism includes a telescopic component installed on the transfer platform, a mounting base connected to the telescopic component, a mounting member slidably connected to the mounting base, buffer springs respectively connected to the mounting member and the mounting base, and a support member rotatably connected to the mounting member.

[0006] By adopting the above technical solution, the drive mechanism can move the transfer platform at least partially outside the shell through the opening to receive the UAV. When the UAV lands on the transfer platform, the instantaneous impact force on the support component is transmitted to the mounting component. The mounting component slides along the mounting seat and compresses the buffer spring. The buffer spring absorbs part of the impact force through elastic deformation, preventing the impact force from being directly transmitted to the UAV fuselage, landing pad structure, and vehicle mounting point. This effectively protects the UAV landing gear, landing pad, and related vehicle structures, extends service life, and improves operational safety. This application can effectively buffer the instantaneous impact force generated when the UAV lands.

[0007] Preferably, the telescopic assembly includes a rotating shaft rotatably connected to the transfer platform, a driving component connected to the rotating shaft, a mounting block threadedly connected to the rotating shaft, and a telescopic frame connected to the mounting block. The mounting base is connected to the telescopic frame, and the rotation of the rotating shaft can drive the telescopic frame to extend or retract through the mounting block.

[0008] By adopting the above technical solution, when the drive component drives the rotating shaft to rotate, the mounting block threaded to the rotating shaft will move along the axial direction of the rotating shaft, thereby causing the telescopic frame to unfold or retract. After the drive mechanism moves the transfer platform part out of the housing, the drive component can cause the telescopic frame to extend or retract, so that the support component contacts the vehicle to ensure that the subsequent landing of the UAV can be buffered.

[0009] Preferably, there are two mounting blocks, namely a first mounting block and a second mounting block; the telescopic frame includes a first linkage plate and a second linkage plate, which are arranged crosswise and hinged at the intersection position. One end of the first linkage plate is hinged to the first mounting block, and the other end is hinged to a third linkage plate. One end of the second linkage plate is hinged to the second mounting block, and the other end is hinged to a fourth linkage plate. The third linkage plate and the fourth linkage plate are both hinged to the mounting base.

[0010] By adopting the above technical solution, the first and second linkage plates, together with the third and fourth linkage plates, can ensure structural stability. They can distribute the force, improve the load-bearing capacity and structural strength of the telescopic frame, and prevent the telescopic frame from deforming due to the impact of the drone or its own weight.

[0011] Preferably, the transfer platform includes a plate connected to the drive mechanism and a column slidably connected to the plate. The transfer platform also includes a bearing shell, the bearing shell including a connecting groove, the column being inserted into the connecting groove and being separable from the connecting groove. A locking component for locking the column is installed on the bearing shell.

[0012] By adopting the above technical solution, after the locking component is released from the column, the transfer platform, along with the drone, can be moved to another location.

[0013] Preferably, the locking assembly includes a fixing block connected to the bearing shell, a locking strip slidably connected to the fixing block, a locking groove on the column, and a screwing component threadedly connected to the locking strip.

[0014] By adopting the above technical solution, after the sliding locking bar is embedded into the locking groove of the column, tightening the screwing part will allow the locking bar to slide into the locking groove and thus fix the locking bar, achieving a stable lock between the column and the bearing shell. The locking structure is simple, reliable, and easy to operate; to unlock, simply loosen the screwing part and slide the locking bar.

[0015] Preferably, the plate has a guide groove, the column has a guide part, and the guide part is slidably connected to the guide groove; a compression spring is also provided in the guide groove, and the two ends of the compression spring are respectively connected to the guide groove and the guide part.

[0016] By adopting the above technical solution, the column slides along the guide groove of the plate through the guide part. The guide groove provides precise guidance for the movement of the column and avoids the column from deviating. The compression spring generates elastic resistance to the guide part. When the impact force generated by the drone landing is transmitted to the column, the compression spring can further absorb part of the impact force, forming a secondary buffer. At the same time, the compression spring is also used to ensure the reset and reliable position of the bearing shell.

[0017] Preferably, the carrier shell includes a receiving groove at the top, and the top of the carrier shell is attached to the inner wall of the shell.

[0018] By adopting the above technical solution, the containment tank can contain drones, and the above design can prevent dirt from entering the containment tank as much as possible.

[0019] Preferably, the housing is rotatably connected to an opening and closing plate, the opening and closing plate being rotatably open and close the opening, and the opening and closing plate and the housing are connected together by a torsion spring.

[0020] By adopting the above technical solution, the transfer platform can move and press against the opening and closing plate to drive the opening and closing plate to rotate and open the opening, thereby partially moving out of the shell. When the transfer platform is retracted into the shell, the torsion spring drives the opening and closing plate to automatically close the opening, which can protect the internal structure of the shell from dust, water, and impact.

[0021] Preferably, the housing is provided with a first magnetic attraction element, and the opening and closing plate is equipped with a second magnetic attraction element.

[0022] By adopting the above technical solution, the mutual attraction between the first magnetic component and the second magnetic component can enhance the sealing performance of the opening and closing plate, preventing rainwater, dust and other impurities from entering the housing through the opening gaps.

[0023] In summary, the present invention has at least one of the following beneficial technical effects: 1. The drive mechanism can move the transfer platform at least partially outside the shell through the opening to receive the UAV. When the UAV lands on the transfer platform, the instantaneous impact force on the support component is transmitted to the mounting component. The mounting component slides along the mounting base and compresses the buffer spring. The buffer spring absorbs part of the impact force through elastic deformation, preventing the impact force from being directly transmitted to the UAV fuselage, landing pad structure, and vehicle mounting point. This effectively protects the UAV landing gear, landing pad, and vehicle-related structures, extends service life, and improves operational safety. This application can effectively buffer the instantaneous impact force generated when the UAV lands. 2. After the locking component is released from the column, the transfer platform, along with the drone, can be moved to another location; 3. The column slides along the guide groove of the plate through the guide part. The guide groove provides precise guidance for the movement of the column and avoids the column from deviating. The compression spring generates elastic resistance to the guide part. When the impact force generated by the drone landing is transmitted to the column, the compression spring can further absorb part of the impact force, forming a secondary buffer. At the same time, the compression spring is also used to ensure the reset and reliable position of the bearing shell. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the overall structure of an aircraft landing pad device according to an embodiment of this application; Figure 2 This is a front sectional view of an aircraft parking apron device; Figure 3 This is a structural diagram used to illustrate the transfer platform; Figure 4 It is a top sectional view used to represent a column; Figure 5 yes Figure 4 Enlarged view of section A; Figure 6 This is a schematic diagram illustrating the structure of a compression spring; Figure 7 This is a structural diagram used to illustrate the telescopic component; Figure 8 yes Figure 2 Enlarged view of section B.

[0025] The following are labels in the attached diagram: 1. Shell; 2. Transfer platform; 21. Plate; 211. Guide groove; 22. Column; 221. Locking groove; 222. Guide part; 23. Bearing shell; 231. Connecting groove; 232. Receiving groove; 24. Locking assembly; 241. Fixing block; 242. Locking strip; 243. Twisting part; 3. Drive mechanism; 4. Elastic support mechanism; 41. Telescopic assembly; 411. Rotating shaft; 412. Driving part; 413. First mounting block; 414. Second mounting block; 415. Telescopic frame; 4151. First linkage plate; 4152. Second linkage plate; 4153. Third linkage plate; 4154. Fourth linkage plate; 42. Mounting base; 43. Mounting part; 44. Buffer spring; 45. Support part; 5. Compression spring; 6. Opening and closing plate; 61. First magnetic suction part; 7. Limiting post; 71. Limiting hole. Detailed Implementation

[0026] The present invention will be further described in detail below with reference to the accompanying drawings.

[0027] In the description of this invention, it should be understood that the orientation descriptions, such as up, down, front, back, left, right, etc., are based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0028] This application discloses an aircraft landing pad device. It is used to effectively buffer the instantaneous impact force generated when a drone lands.

[0029] Reference Figure 1 and Figure 2 An aircraft landing pad device includes a housing 1 with an opening at the left end. A suction cup can be installed at the bottom of the housing 1 for subsequent mounting on a vehicle via the suction cup. A transfer platform 2 for receiving a drone is movably disposed inside the housing 1. A drive mechanism 3 connected to the transfer platform 2 is installed on the housing 1. The drive mechanism 3 can drive the transfer platform 2 to move left and right. At least part of the transfer platform 2 can move to the left out of the housing 1. In this embodiment, the drive mechanism 3 is preferably a belt transmission mechanism. Of course, in other embodiments, it can also be a sprocket and chain transmission mechanism or a gear and rack transmission mechanism, etc. The transfer platform 2 is equipped with an elastic support mechanism 4.

[0030] When the drive mechanism 3 moves the transfer platform 2 through the opening to at least partially move it outside the shell 1 to prepare to receive the drone, when the drone lands on the transfer platform 2, the elastic support mechanism 4 will absorb part of the instantaneous impact force to achieve the purpose of buffering the drone's landing.

[0031] Reference Figure 2 and Figure 3The transfer platform 2 includes a plate 21 connected to the drive mechanism 3 and two columns 22 slidably connected to the plate 21, with the columns 22 arranged laterally. The transfer platform 2 also includes a bearing shell 23, which includes two laterally arranged connecting slots 231. The columns 22 are inserted into the connecting slots 231 and can be separated from the connecting slots 231. The bearing shell 23 is equipped with a plurality of locking components 24 for locking the columns 22. Two elastic support mechanisms 4 are provided, with one elastic support mechanism 4 installed on one column 22.

[0032] Reference Figure 3 The supporting shell 23 includes a receiving groove 232 at the top, combined with Figure 2 The top of the support shell 23 is attached to the inner wall of the top of the shell 1. The receiving slot 232 can accommodate the drone, and the above design can prevent dirt from entering the receiving slot 232 as much as possible. It should be noted that the relevant mechanisms for receiving the drone, such as the suction device for fixing the drone landing gear, the charging device for charging the drone, the alignment mechanism for aligning the drone's position, and the relevant sensors for detecting the drone's position, are all installed in the receiving slot 232. The specific structures mentioned above are all prior art and will not be described in detail here.

[0033] Reference Figure 4 and Figure 5 The locking component 24 includes a fixing block 241 connected to the bearing shell 23, a locking strip 242 slidably connected to the fixing block 241, a locking groove 221 on the column 22, and a screwing member 243 threadedly connected to the locking strip 242.

[0034] By rotating the screwing component 243, the locking bar 242 can be moved laterally to engage with or disengage from the locking groove 221, thereby locking or unlocking the column 22.

[0035] After unlocking the column 22, the carrier shell 23, along with the drone, can be moved to other locations for better deployment in urban last-mile logistics delivery, field emergency rescue, and power and transportation line inspection.

[0036] Reference Figure 6 and Figure 7 The elastic support mechanism 4 includes a telescopic component 41 mounted on the column 22, a mounting base 42 connected to the telescopic component 41, a mounting member 43 slidably connected to the mounting base 42, a buffer spring 44 respectively connected to the mounting member 43 and the mounting base 42, and a support member 45 rotatably connected to the mounting member 43, such as a support wheel.

[0037] Reference Figure 7The telescopic assembly 41 includes a rotating shaft 411 rotatably connected to the column 22, a driving component 412 connected to the rotating shaft 411, two mounting blocks threadedly connected to the rotating shaft 411, and a telescopic frame 415 connected to the two mounting blocks. The rotating shaft 411 is arranged laterally, the driving component 412 is, for example, a motor, and the mounting base 42 is connected to the telescopic frame 415. The rotation of the rotating shaft 411 can drive the telescopic frame 415 to extend or retract through the mounting blocks. For support and balance, two mounting blocks, two telescopic frames 415, two mounting bases 42, two mounting components 43, two buffer springs 44, and two support components 45 are provided.

[0038] When the drone lands in the receiving slot 232, the instantaneous impact force on the support member 45 is transmitted to the mounting member 43. The mounting member 43 slides along the mounting base 42 and compresses the buffer spring 44. The buffer spring 44 absorbs part of the impact force through elastic deformation, preventing the impact force from being directly transmitted to the drone fuselage, landing pad structure and vehicle mounting point, effectively protecting the drone landing gear and landing pad and vehicle-related structures.

[0039] Reference Figure 7 The two mounting blocks are a first mounting block 413 and a second mounting block 414. The telescopic frame 415 includes a first linkage plate 4151 and a second linkage plate 4152. The first linkage plate 4151 and the second linkage plate 4152 are arranged crosswise and hinged together at the intersection. The upper end of the first linkage plate 4151 is hinged to the first mounting block 413, and the lower end of the first linkage plate 4151 is hinged to a third linkage plate 4153. The upper end of the second linkage plate 4152 is hinged to the second mounting block 414, and the lower end of the second linkage plate 4152 is hinged to a fourth linkage plate 4154. The bottom ends of the third linkage plate 4153 and the fourth linkage plate 4154 are both hinged to the mounting base 42. The multiple sets of cross-hinged first linkage plates 4151 and second linkage plates 4152, together with the third linkage plates 4153 and fourth linkage plates 4154, can ensure structural stability, improve the load-bearing capacity and structural strength of the telescopic frame 415, and prevent the telescopic frame 415 from deforming due to the impact of the drone or its own weight.

[0040] When the drive component 412 drives the rotating shaft 411 to rotate, the first mounting block 413 and the second mounting block 414, which are threadedly connected to the rotating shaft 411, will move towards or away from each other along the axis of the rotating shaft 411, thereby causing the telescopic frame 415 to unfold or retract, thus achieving contact between the support member 45 and the housing 1 or the vehicle body. When the drive mechanism 3 moves part of the transfer platform 2 outside the housing 1, the drive component 412 can cause the telescopic frame 415 to extend or retract, thereby allowing the support member 45 to contact the vehicle to ensure that the subsequent landing of the UAV can be buffered.

[0041] Reference Figure 2In order to ensure that the bearing shell 23 is stable after moving back into the shell 1, the shell 1 is equipped with a limiting post 7. The left end of the post 22 has a limiting hole 71, and the limiting post 7 can be inserted into the limiting hole 71 to limit the position of the post 22.

[0042] Reference Figure 6 In order to better cushion the landing of the drone and ensure the reliable position of the support shell 23, a vertically arranged guide groove 211 is opened on the plate 21, and a guide part 222 is provided on the column 22. The guide part 222 is slidably connected to the guide groove 211. A pressure spring 5 is also provided in the guide groove 211. The two ends of the pressure spring 5 are respectively connected to the guide groove 211 and the guide part 222, and the pressure spring 5 is located below the guide part 222.

[0043] Reference Figure 8 and combined Figure 2 To minimize the entry of dirt and dust into the housing 1, a rotatable opening and closing plate 6 is connected to the housing 1. The opening and closing plate 6 can rotate to open and close the opening. A torsion spring is connected to the opening and closing plate 6 and the housing 1. After the opening and closing plate 6 is rotated to open the opening, the torsion spring ensures that the opening and closing plate 6 returns to its original position. To ensure the reliability of the opening and closing plate 6 in closing the opening, the housing 1 is provided with a first magnetic attractor 61, and the opening and closing plate 6 is equipped with a second magnetic attractor. The first magnetic attractor 61 is located below the opening. The first magnetic attractor 61 and the second magnetic attractor are, for example, magnetic strips.

[0044] The closure of the openings by the opening and closing plate 6 and the contact between the upper end of the bearing shell 23 and the inner wall of the shell 1 are both used to ensure that dirt cannot easily come into contact with the UAV's take-off and landing structures.

[0045] In this application, in order to further prevent the UAV from damaging other structures and the structure of the vehicle body mounting points when it lands repeatedly in the receiving slot 232, the bearing shell 23, column 22, mounting base 42, shell 1, telescopic frame 415 and other structures are all made of aluminum alloy. It can have high structural strength while ensuring that the overall weight of this application and the mass of the related cushioning structures are small. The aluminum alloy bearing shell 23 and related structures can be moved easily.

[0046] The implementation principle of an aircraft landing pad device in this application embodiment is as follows: The drive mechanism 3 drives the carrier shell 23 to move and press against the opening and closing plate 6. After being pressed, the opening and closing plate 6 rotates to open the opening. The carrier shell 23 moves at least partially outside the shell 1. The drive drive component 412 drives the rotating shaft 411 to rotate. The first mounting block 413 and the second mounting block 414 move apart, thereby driving the telescopic frame 415 to unfold. The support component 45 contacts the vehicle body. At this time, if the UAV lands in the receiving slot 232, the buffer elasticity and the pressure spring 5 are compressed, thereby absorbing part of the instantaneous impact force and thus achieving the purpose of buffering the UAV landing.

[0047] The embodiments described herein are preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Therefore, all equivalent changes made in accordance with the structure, shape, and principle of the present invention should be covered within the scope of protection of the present invention.

Claims

1. An aircraft parking apron device, characterized in that: It includes a housing (1) with an opening, a transfer platform (2) for receiving a drone is movably disposed inside the housing (1), a drive mechanism (3) connected to the transfer platform (2) is installed in the housing (1), and an elastic support mechanism (4) is installed in the transfer platform (2); The elastic support mechanism (4) includes a telescopic component (41) installed on the transfer platform (2), a mounting base (42) connected to the telescopic component (41), a mounting member (43) slidably connected to the mounting base (42), a buffer spring (44) respectively connected to the mounting member (43) and the mounting base (42), and a support member (45) rotatably connected to the mounting member (43).

2. The aircraft parking apron device according to claim 1, characterized in that: The telescopic assembly (41) includes a rotating shaft (411) rotatably connected to the transfer platform (2), a drive component (412) connected to the rotating shaft (411), a mounting block threaded to the rotating shaft (411), and a telescopic frame (415) connected to the mounting block. The mounting base (42) is connected to the telescopic frame (415). The rotation of the rotating shaft (411) can drive the telescopic frame (415) to extend and retract through the mounting block.

3. The aircraft parking apron device according to claim 2, characterized in that: The mounting block is provided in two parts, namely a first mounting block (413) and a second mounting block (414); the telescopic frame (415) includes a first linkage plate (4151) and a second linkage plate (4152), the first linkage plate (4151) and the second linkage plate (4152) are arranged crosswise and hinged at the intersection position, one end of the first linkage plate (4151) is hinged to the first mounting block (413), and the other end is hinged to a third linkage plate (4153), one end of the second linkage plate (4152) is hinged to the second mounting block (414), and the other end is hinged to a fourth linkage plate (4154), the third linkage plate (4153) and the fourth linkage plate (4154) are hinged together to the mounting base (42).

4. The aircraft parking apron device according to claim 1, characterized in that: The transfer platform (2) includes a plate (21) connected to the drive mechanism (3) and a column (22) slidably connected to the plate (21). The transfer platform (2) also includes a bearing shell (23). The bearing shell (23) includes a connecting groove (231). The column (22) is inserted into the connecting groove (231) and can be separated from the connecting groove (231). A locking component (24) for locking the column (22) is installed on the bearing shell (23).

5. The aircraft parking apron device according to claim 4, characterized in that: The locking assembly (24) includes a fixing block (241) connected to the bearing shell (23), the fixing block (241) is slidably connected to a locking strip (242), the column (22) has a locking groove (221), and the locking strip (242) is threadedly connected to a rotating part (243).

6. The aircraft parking apron device according to claim 4, characterized in that: The plate (21) has a guide groove (211), and the column (22) has a guide part (222), which is slidably connected to the guide groove (211). A pressure spring (5) is also provided in the guide groove (211), and the two ends of the pressure spring (5) are respectively connected to the guide groove (211) and the guide part (222).

7. The aircraft parking apron device according to claim 4, characterized in that: The support shell (23) includes a receiving groove (232) at the top, and the top of the support shell (23) is attached to the inner wall of the shell (1).

8. The aircraft parking apron device according to claim 1, characterized in that: The housing (1) is rotatably connected to an opening and closing plate (6), which can rotate to open and close the opening. The opening and closing plate (6) and the housing (1) are connected together to a torsion spring.

9. An aircraft parking apron device according to claim 8, characterized in that: The housing (1) is provided with a first magnetic suction member (61), and the opening and closing plate (6) is equipped with a second magnetic suction member.

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