Impact-resistant buffer support structure for hydrogen energy unmanned aerial vehicle chassis

Abstract

The application relates to the technical field of unmanned planes, and particularly relates to an impact-resistant buffer support structure for a hydrogen energy unmanned plane chassis, which comprises a support frame, a connecting seat and an adjusting mechanism; an installation rod and a support seat are arranged on the support frame, and the installation rod is connected with the support frame; the connecting seat is connected with the installation rod, and a limiting frame, a damper and a compression spring are arranged on the connecting seat; the limiting frame is connected with the connecting seat, the damper is connected with the limiting frame, a damping rod of the damper is connected with the support seat, the compression spring is sleeved on the damper, and the two ends of the compression spring are respectively connected with the limiting frame and the damping rod; damping medium is filled in the damper, and the adjusting mechanism is used for adjusting the flow resistance of the damping medium to adjust the damping force of the damper. The application realizes the function of adjusting the damping force according to the impact during landing, and solves the technical problem that the chassis is damaged due to the fact that the damping force of the buffer structure of the traditional unmanned plane is fixed and the unmanned plane is difficult to cope with different intensity impacts.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to an impact-resistant buffer support structure for a hydrogen-powered UAV chassis. Background Technology

[0002] Existing drone landing chassis designs are relatively simple, generally using springs as buffer components to offset the impact force generated during drone landing. However, springs are prone to resonance after deformation, which can compromise the stability of the drone during landing. In special conditions such as complex terrain or emergency landings, resonance can exacerbate fuselage swaying, potentially causing damage to onboard equipment or loss of relevant data. In addition, the connection between existing drone landing chassis and the drone body often relies on multiple fixing bolts, which not only makes the installation and disassembly process cumbersome, time-consuming, and labor-intensive, but may also cause the bolts to loosen due to continuous vibration during flight, affecting the connection's firmness and creating safety hazards. Therefore, we propose a new drone landing chassis structure.

[0003] To address this, Chinese Patent No. CN223721193U discloses a landing chassis structure for a surveying drone. This structure involves installing the drone body into a slot in a mounting base, then rotating a gear drive rod to drive two meshing gear driven screws on either side. This causes the threaded sleeves mounted on the two gear driven screws to move in tandem with the rotation of the screws, resulting in synchronous movement of mounting plates mounted on the threaded sleeves. The latches on the mounting plates penetrate the drone body and extend into the interior of the mounting base, securing the drone body to the mounting base and connecting it to the landing chassis. Disassembly of the drone body is achieved by reversing the gear drive rod, allowing for quick and convenient installation of the drone onto the landing chassis, saving time and effort.

[0004] However, while existing equipment has solved the problem of inconvenient installation and disassembly of drones and landing chassis, it lacks shock absorption performance. This comparative document only focuses on the ease of connection between the drone and the chassis and does not set up an effective shock absorption and buffer structure. When the drone lands, it will be subjected to impacts of varying intensities. Especially during emergency landings, the instantaneous peak acceleration is high. The lack of a shock absorption structure will cause the impact to be directly transmitted to the drone body, which can easily cause chassis deformation and equipment damage. Summary of the Invention

[0005] To address the aforementioned issues, an impact-resistant buffer support structure for hydrogen-powered drone chassis is provided. This structure, through a support frame, connecting seat, and adjustment mechanism, solves the technical problem that traditional drones, due to their fixed damping force in the buffer structure, struggle to withstand impacts of varying intensities, leading to chassis damage.

[0006] To address the problems of existing technologies, this invention provides an impact-resistant buffer support structure for a hydrogen-powered drone chassis, comprising a support frame, a connecting seat, and an adjustment mechanism. The support frame has a mounting rod and a support seat, the mounting rod being connected to the support frame. The connecting seat is connected to the mounting rod, and has a limiting frame, a damper, and a compression spring. The limiting frame is connected to the connecting seat, the damper is connected to the limiting frame, and the damping rod of the damper is connected to the support seat. The compression spring is sleeved on the damper, and its two ends are respectively connected to the limiting frame and the damping rod. The damper is filled with a damping medium, and the adjustment mechanism is used to adjust the flow resistance of the damping medium to adjust the damping force of the damper.

[0007] Preferably, the adjusting mechanism includes a piston, a damping channel, and a limiting component; the damper includes a cylinder, the piston is connected to a damping rod and disposed within the cylinder, the piston is sealed to the inner wall of the cylinder to seal and divide the inner cavity of the cylinder into a first cavity and a second cavity; a damping channel is provided on the piston, and the first cavity and the second cavity are connected through the damping channel; during the operation of the damper, the damping medium flows between the first cavity and the second cavity through the damping channel; the limiting component is used to limit the flow rate of the damping medium at the damping channel.

[0008] Preferably, the damping channel includes a first pipe and a second pipe, the second pipe having a larger diameter than the first pipe, and the limiting component is used to close the second pipe.

[0009] Preferably, the limiting component includes a first adjusting plate, a cover, and a first elastic element; the first adjusting plate is tightly fitted with the inner wall of the cylinder of the damper, the cover is disposed on the first adjusting plate, and the two ends of the first elastic element are respectively connected to the first adjusting plate and the piston. When the damping rod is compressed by pressure, the first adjusting plate is compressed and moves closer to the piston. When the cover abuts against the second pipe, the second pipe is closed.

[0010] Preferably, the damping channel includes a third pipe disposed on the piston; the cylinder of the damper is provided with an adjustment component for adjusting the flow area of ​​the third pipe.

[0011] Preferably, the adjustment assembly includes a second adjustment plate, an adjustment frame, and a second elastic element; the second adjustment plate is tightly fitted with the inner wall of the damper's cylinder; the adjustment frame is disposed on the second adjustment plate, and the adjustment frame is provided with a blocking block for blocking the third pipe, the blocking block is frustoconical and its cross-sectional area gradually changes along the axial direction, and the cross-sectional area of ​​the blocking block near the third pipe is smaller; the two ends of the second elastic element are respectively connected to the second adjustment plate and the piston.

[0012] Preferably, the damper cylinder is provided with an abutment plate and a flexible buffer, and the abutment plate is located at the end of the cylinder away from the damping rod, and the two ends of the flexible buffer are respectively connected to the abutment plate and the inner wall of the cylinder.

[0013] Preferably, the flexible buffer is an airbag that can elastically deform under pressure.

[0014] Preferably, the support base is connected to an elastic extension rod extending in a direction away from the support frame.

[0015] Preferably, a roller is rotatably mounted on the elastic extension rod.

[0016] The advantages of this invention compared to the prior art are: 1. This invention, through a support frame, connecting seat, and adjustment mechanism, achieves the function of adjusting the damping force according to the impact experienced during landing. It achieves the effect of adjusting the damping force based on landing speed, load, and ground hardness, thereby protecting the drone and solving the technical problem of traditional drones where the fixed damping force of the buffer structure makes it difficult to cope with impacts of varying intensities, leading to chassis damage. Based on the different impact intensities that the drone may encounter during flight, the adjustment mechanism adjusts the flow resistance of the damping medium, thereby adjusting the damping force of the damper, allowing the buffer support to adapt to different impact scenarios and ensuring stable buffering effect. The various structures work together to achieve effective impact buffering and flexible adjustment of the damping force, ensuring the safety and stability of the hydrogen-powered drone chassis and extending the equipment's service life.

[0017] 2. This invention achieves the function of adjusting the damping force of the damper through a piston, a damping channel, and a limiting component. By adjusting the flow rate of the damping channel, the resistance encountered by the damping medium during flow is adjusted, thereby changing the resistance provided by the damper. When the chassis is impacted, the damping rod drives the piston to move within the cylinder. The damping medium flows between the two chambers through the damping channel. The limiting component controls the flow rate of the medium by changing the flow area of ​​the damping channel, thereby changing the resistance generated during the flow of the medium and achieving adjustment of the damping force of the damper.

[0018] 3. This invention achieves automatic graded adjustment of damping force, realizing the effect of automatically adjusting the damping force according to the impact force received by the support. When the chassis is subjected to a strong impact, the damping rod contracts under pressure, driving the piston to move towards the first adjusting plate. At this time, the piston moves at a relatively fast speed, which increases the pressure on the first adjusting plate, causing the first adjusting plate to be compressed and close to the piston. The first elastic element is then compressed and deformed until the cap abuts against the second pipe, sealing the second pipe. At this time, the damping medium can only flow through the first pipe with a smaller diameter, increasing the flow resistance and correspondingly increasing the damping force. This can effectively absorb the energy brought by the strong impact and reduce the damage to the chassis. Attached Figure Description

[0019] Figure 1 This is a three-dimensional schematic diagram of an impact-resistant buffer bracket structure for a hydrogen-powered drone chassis, installed on a drone according to the present invention.

[0020] Figure 2 This is a three-dimensional schematic diagram of an impact-resistant buffer support structure for a hydrogen-powered drone chassis according to the present invention.

[0021] Figure 3 This is a three-dimensional schematic diagram of the connecting seat and support seat of an impact-resistant buffer bracket structure for a hydrogen-powered drone chassis according to the present invention.

[0022] Figure 4 This is a three-dimensional cross-sectional view of the damper and adjustment mechanism in the reset state of the first embodiment of the shock-resistant buffer support structure for the chassis of a hydrogen-powered unmanned aerial vehicle according to the present invention.

[0023] Figure 5 This is a three-dimensional cross-sectional view of the damper and adjustment mechanism in a retracted state, according to a first embodiment of an impact-resistant buffer support structure for a hydrogen-powered drone chassis of the present invention.

[0024] Figure 6 This is a three-dimensional schematic diagram of the damper and piston of the first embodiment of an impact-resistant buffer support structure for a hydrogen-powered drone chassis according to the present invention.

[0025] Figure 7 This is a three-dimensional exploded view of the damper and piston of the first embodiment of an impact-resistant buffer support structure for a hydrogen-powered drone chassis according to the present invention.

[0026] Figure 8 This is a three-dimensional schematic diagram of the damper and adjustment mechanism of a second embodiment of an impact-resistant buffer support structure for a hydrogen-powered drone chassis according to the present invention.

[0027] Figure 9 This is a three-dimensional exploded view of the damper and piston in a second embodiment of an impact-resistant buffer support structure for a hydrogen-powered drone chassis according to the present invention.

[0028] Figure 10 This is an exploded perspective view of the damper and adjustment mechanism of the first embodiment of the impact-resistant buffer support structure for the chassis of a hydrogen-powered drone according to the present invention.

[0029] The following are the labels in the diagram: 1. Support frame; 11. Mounting rod; 12. Support base; 121. Elastic extension rod; 122. Roller; 2. Connecting seat; 21. Limiting frame; 22. Damper; 221. Damping rod; 222. Abutment piece; 223. Flexible buffer; 23. Compression spring; 3. Adjusting mechanism; 31. Piston; 32. Damping channel; 321. First pipe; 322. Second pipe; 323. Third pipe; 33. Limiting component; 331. First adjusting piece; 332. Cover; 333. First elastic element; 34. Adjusting component; 341. Second adjusting piece; 342. Adjusting frame; 3421. Block; 343. Second elastic element. Detailed Implementation

[0030] To further understand the features, technical means, and specific objectives and functions achieved by the present invention, the present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments.

[0031] Reference Figures 1 to 4 An impact-resistant buffer support structure for a hydrogen-powered unmanned aerial vehicle (UAV) chassis includes a support frame 1, a connecting seat 2, and an adjustment mechanism 3. The support frame 1 is equipped with an mounting rod 11 and a support seat 12, with the mounting rod 11 connected to the support frame 1. The connecting seat 2 is connected to the mounting rod 11, and is equipped with a limiting frame 21, a damper 22, and a compression spring 23. The limiting frame 21 is connected to the connecting seat 2, the damper 22 is connected to the limiting frame 21, and the damping rod 221 of the damper 22 is connected to the support seat 12. The compression spring 23 is sleeved on the damper 22, and both ends of the compression spring 23 are connected to the limiting frame 21 and the damping rod 221, respectively. The damper 22 is filled with a damping medium, and the adjustment mechanism 3 is used to adjust the flow resistance of the damping medium to adjust the damping force of the damper 22.

[0032] This invention, through a support frame 1, a connecting seat 2, and an adjustment mechanism 3, achieves the function of adjusting the damping force according to the impact received during landing. It achieves the effect of adjusting the damping force based on landing speed, load, and ground hardness, thereby protecting the drone and solving the technical problem of traditional drones where the fixed damping force of the buffer structure makes it difficult to cope with impacts of varying intensities, leading to chassis damage. During operation, when the hydrogen-powered drone is impacted, the impact force is transmitted to the support seat 12. The support seat 12 drives the damping rod 221 of the damper 22 to move, and the compression spring 23 is compressed accordingly. Simultaneously, the damping medium inside the damper 22 is compressed, generating a damping force. This force, combined with the elastic force of the compression spring 23, buffers and absorbs the impact force, reducing the impact on the drone's chassis. As the compression spring 23 is compressed, its elastic force also increases, further increasing drag. Depending on the different impact intensities the drone may encounter during flight, the adjustment mechanism 3 adjusts the flow resistance of the damping medium, thereby adjusting the damping force of the damper 22, allowing the buffer support to adapt to different impact scenarios and ensuring stable buffering performance. The various structures work together to achieve effective impact buffering and flexible adjustment of damping force, ensuring the safety and stability of the hydrogen-powered drone chassis and extending the service life of the equipment.

[0033] Reference Figure 4 and Figure 5 The adjusting mechanism 3 includes a piston 31, a damping channel 32, and a limiting component 33; the damper 22 includes a cylinder, the piston 31 is connected to the damping rod 221 and disposed in the cylinder, the piston 31 is sealed to the inner wall of the cylinder to seal and divide the inner cavity of the cylinder into a first cavity and a second cavity; the piston 31 has a damping channel 32, and the first cavity and the second cavity are connected through the damping channel 32; during the operation of the damper 22, the damping medium flows between the first cavity and the second cavity through the damping channel 32; the limiting component 33 is used to limit the flow rate of the damping medium at the damping channel 32.

[0034] This invention achieves the function of adjusting the damping force of the damper 22 through the piston 31, damping channel 32, and limiting component 33. By adjusting the flow rate of the damping channel 32, the resistance encountered by the damping medium during flow is adjusted, thereby changing the resistance provided by the damper 22. When the chassis is impacted, the damping rod 221 drives the piston 31 to move within the cylinder. The damping medium flows between the two chambers through the damping channel 32. The limiting component 33 controls the flow rate of the medium by changing the flow area of ​​the damping channel 32, thereby changing the resistance generated during the flow of the medium and adjusting the damping force of the damper 22. Together with the compression spring 23, it absorbs and dissipates the impact energy, making the buffering process more stable. At the same time, the damping magnitude can be adjusted according to the usage scenario, improving the adaptability of the buffer bracket under different usage conditions and protecting the chassis structure of the hydrogen-powered UAV from impact damage.

[0035] Reference Figures 4 to 6 The damping channel 32 includes a first pipe 321 and a second pipe 322, the diameter of the second pipe 322 being larger than that of the first pipe 321, and the limiting component 33 being used to close the second pipe 322.

[0036] As a first embodiment of the present invention, the damping force is adjusted by regulating the flow path of the damping medium through the first pipe 321 and the second pipe 322. During operation, when the damper 22 is subjected to force, the damping medium can flow between the first cavity and the second cavity through the first pipe 321 and the second pipe 322. The second pipe 322, with its larger diameter, can reduce the flow resistance of the damping medium, resulting in a smaller overall damping force. When the limiting component 33 closes the second pipe 322, the damping medium can only flow through the first pipe 321, with its smaller diameter. The increased flow resistance causes the damping force output by the damper 22 to increase accordingly. When the UAV chassis is subjected to impacts of different magnitudes, the second pipe 322 can be opened or closed by the limiting component 33 to change the flow cross section of the damping medium, thereby achieving graded adjustment of the damping force. Combined with the compression spring 23, this forms a buffering effect that adapts to different working conditions, allowing the buffer bracket to function stably in both minor vibration and strong impact scenarios.

[0037] Reference Figures 5 to 7 The limiting component 33 includes a first adjusting plate 331, a cover 332, and a first elastic element 333. The first adjusting plate 331 is tightly fitted with the inner wall of the cylinder of the damper 22. The cover 332 is disposed on the first adjusting plate 331. The two ends of the first elastic element 333 are respectively connected to the first adjusting plate 331 and the piston 31. When the damping rod 221 is compressed and contracts, the first adjusting plate 331 is compressed and moves closer to the piston 31. When the cover 332 abuts against the second pipe 322, the second pipe 322 is closed.

[0038] This invention achieves automatic graded adjustment of damping force, realizing the effect of automatically adjusting the damping force according to the impact force received by the support seat 12. The first elastic element 333 is preferably a rubber block. When the damper 22 is working, the damping rod 221 is compressed and contracts, driving the piston 31 to move. The piston 31 squeezes the damping medium in the cylinder through the first adjusting plate 331, creating a pressure difference between the first cavity and the second cavity. When the damping medium flows through the damping channel 32, it generates hydraulic pressure / fluid resistance on the first adjusting plate 331. This pressure acts on the first adjusting plate 331 and overcomes the supporting force of the first elastic element 333, pushing the first adjusting plate 331 to overcome the elastic resistance and move closer to the piston 31. During operation, when the chassis of the hydrogen-powered drone is subjected to a slight impact, the damping rod 221 experiences relatively low pressure, the first elastic element 333 maintains its initial state, causing the first adjusting plate 331 to maintain a certain distance from the piston 31, and the cover 332 does not contact the second pipe 322. At this time, the damping medium can flow through the first pipe 321 and the second pipe 322 simultaneously between the first cavity and the second cavity. The flow resistance is low, the damping force is moderate, and a gentle buffering effect is achieved for slight impacts. When the chassis is subjected to a strong impact, the damping rod 221 contracts under pressure, causing the piston 31 to move towards the first adjusting plate 331. At this time, the piston 31 moves at a relatively fast speed, which increases the pressure on the first adjusting plate 331, causing it to move closer to the piston 31. The first elastic element 333 is then compressed and deformed until the cap 332 comes into contact with the second pipe 322, sealing the second pipe 322. At this point, the damping medium can only flow through the smaller diameter first pipe 321, increasing the flow resistance and correspondingly increasing the damping force. This effectively absorbs the energy from the strong impact and reduces damage to the chassis. After the impact, the first elastic element 333 returns to its original state, causing the first adjusting plate 331 and the cap 332 to move away from the piston 31. The second pipe 322 becomes unobstructed again, and the damping force returns to a moderate state, ready for the next impact buffering.

[0039] Reference Figure 8 and Figure 9 The damping channel 32 includes a third pipe 323 disposed on the piston 31; the cylinder of the damper 22 is provided with an adjustment component 34 for adjusting the flow area of ​​the third pipe 323.

[0040] As a second embodiment of the present invention, the function of continuously adjusting the flow area of ​​the damping medium is realized through the third pipe 323 and the adjusting component 34, achieving the effect of adjusting the damping force as needed. During operation, when the damping rod 221 is driven by force to move the piston 31 in the cylinder, the damping medium flows through the third pipe 323 between the first and second chambers. The adjusting component 34 controls the flow rate of the damping medium by changing the effective flow cross section of the third pipe 323, thereby changing the resistance generated by the flow of the medium to adjust the damping force. When the flow area is large, the flow of the damping medium is smooth and the overall damping force is small. When the flow area is small, the flow of the medium is obstructed and the overall damping force increases accordingly. When the UAV is subjected to impacts of different intensities, the flow state of the third pipe 323 can be flexibly adjusted by the adjusting component 34 to make the buffer support output a suitable damping force, which works together with the compression spring 23 to absorb the impact energy and improve the adaptability of the overall buffer structure.

[0041] Reference Figure 8 and Figure 9 The adjustment assembly 34 includes a second adjustment plate 341, an adjustment frame 342, and a second elastic element 343. The second adjustment plate 341 is tightly fitted with the inner wall of the cylinder of the damper 22. The adjustment frame 342 is disposed on the second adjustment plate 341, and the adjustment frame 342 is provided with a blocking block 3421 for blocking the third pipe 323. The blocking block 3421 is frustoconical and its cross-sectional area gradually changes along the axial direction. The cross-sectional area of ​​the blocking block 3421 near the third pipe 323 is smaller. The two ends of the second elastic element 343 are respectively connected to the second adjustment plate 341 and the piston 31.

[0042] This invention achieves continuously adjustable flow area of ​​the damping channel 32, resulting in smooth changes in damping force. It solves the technical problem of traditional adjustment methods having rigid adjustment ranges and failing to precisely match different impact intensities. During operation, when the damping rod 221 is impacted, causing the piston 31 to move, the distance between the piston 31 and the second adjusting plate 341 changes. The second elastic element 343 deforms accordingly, and the plug 3421 extends into or exits the third pipe 323. Utilizing the gradually changing cross-sectional area of ​​the frustum-shaped plug 3421, the actual flow area of ​​the third pipe 323 is continuously altered. The more the plug 3421 extends into the third pipe 323, the smaller the flow area and the greater the resistance to the damping medium flow. Conversely, the more the plug 3421 exits, the larger the flow area and the smaller the resistance to the damping medium flow. This achieves continuous and precise adjustment of the damping force, automatically adapting to the corresponding damping effect when the UAV experiences impacts of different magnitudes. Together with the compression spring 23, it absorbs impact energy, ensuring stable and reliable buffer protection for the chassis under various operating conditions.

[0043] Reference Figure 5 and Figure 10The damper 22 has an abutment piece 222 and a flexible buffer 223 inside the cylinder. The abutment piece 222 is located at the end of the cylinder away from the damping rod 221. The two ends of the flexible buffer 223 are respectively connected to the abutment piece 222 and the inner wall of the cylinder.

[0044] This invention achieves flexible limiting and buffering functions at the end of the damping rod 221's stroke, avoiding rigid impact at the end of the buffer stroke and solving the technical problem of component damage caused by rigid impact when the damping rod 221 moves to its limit position. During operation, when the damping rod 221 is subjected to a large impact, causing the piston 31 to move towards the bottom of the cylinder to near its limit position, the piston 31 will contact the abutment plate 222. The abutment plate 222 will transfer the remaining impact force to the flexible buffer 223. The flexible buffer 223 will deform to absorb the impact energy in the final stage, preventing the piston 31 from directly colliding with the bottom of the cylinder. This protects the internal structure of the damper 22, preventing components from deforming or being damaged due to severe impact. At the same time, it makes the entire buffering process smoother and more continuous. Combined with the compression spring 23 and the damping adjustment structure, it further improves the stability and service life of the buffer bracket, providing more comprehensive impact protection for the hydrogen-powered UAV chassis.

[0045] Reference Figure 10 The flexible buffer 223 is an airbag that can elastically deform under pressure.

[0046] This invention enables the damper 22 to deform and absorb impact when its end is compressed, and it can automatically recover after the pressure is removed. During operation, when the damping rod 221 is subjected to a large impact, causing the piston 31 to move towards the bottom of the cylinder and approach its limit position, the piston 31 will contact the abutment plate 222 and compress the air bladder. The air bladder will undergo elastic deformation under pressure, absorbing and dissipating the remaining impact energy transmitted by the piston 31, avoiding direct rigid contact between the piston 31 and the bottom of the cylinder, and reducing the damage to the internal structure of the damper 22 caused by impact vibration. After the impact ends, the air bladder will recover its original shape by its own elasticity, driving the abutment plate 222 to reset, preparing for the next buffering operation.

[0047] Reference Figures 1 to 3 The support base 12 is connected to an elastic extension rod 121 that extends in a direction away from the support frame 1.

[0048] This invention achieves a composite axial and lateral buffer support function, resulting in stronger overall impact resistance and more stable lateral force. The elastic extension rod 121 is arc-shaped. During operation, the elastic extension rod 121 undergoes elastic bending and deformation when the support frame 1 is subjected to lateral impact, absorbing and offsetting the lateral impact force. Together with the damper 22 and compression spring 23, it forms a multi-directional buffer system, which can not only cope with vertical impacts but also significantly improve the lateral impact resistance of the chassis, reducing damage to the chassis structure when the UAV tilts or falls sideways. This ensures that the buffer support maintains stable support even in complex take-off and landing environments, better protecting the chassis of the hydrogen-powered UAV.

[0049] Reference Figures 1 to 3 A roller 122 is rotatably mounted on the elastic extension rod 121.

[0050] This invention achieves the functions of extended support and sliding guidance of the buffer bracket, solving the technical problem of high frictional resistance and easy damage caused by the elastic extension rod 121 directly contacting the ground. During operation, the roller 122 can rotate freely on the elastic extension rod 121. When the UAV chassis is impacted, causing the elastic extension rod 121 to deform, the roller 122 forms a rolling engagement with the contacting parts, converting sliding friction into rolling friction, effectively reducing frictional resistance and minimizing component wear. When the impact ends and the elastic extension rod 121 drives the support structure to reset, the roller 122 ensures a smooth reset process. Simultaneously, in conjunction with the damper 22 and the compression spring 23, the roller 122 works with the elastic extension rod 121 to achieve buffering and support, further improving the overall operational stability and service life of the buffer bracket, providing more stable and reliable impact protection for the hydrogen-powered UAV chassis.

[0051] The above embodiments only illustrate one or more implementations of the present invention, and their descriptions are relatively specific and detailed, but they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the protection scope of the present invention. Therefore, the protection scope of the present invention should be determined by the appended claims.

Claims

1. An impact-resistant buffer support structure for a hydrogen-powered unmanned aerial vehicle chassis, characterized in that, It includes a support frame (1), a connecting seat (2), and an adjustment mechanism (3); The support frame (1) is provided with a mounting rod (11) and a support base (12), and the mounting rod (11) is connected to the support frame (1); The connecting seat (2) is connected to the mounting rod (11), and the connecting seat (2) is provided with a limiting frame (21), a damper (22) and a compression spring (23). The limiting frame (21) is connected to the connecting seat (2), the damper (22) is connected to the limiting frame (21), and the damping rod (221) of the damper (22) is connected to the support seat (12). The compression spring (23) is sleeved on the damper (22), and the two ends of the compression spring (23) are respectively connected to the limiting frame (21) and the damping rod (221). The damper (22) is filled with a damping medium, and the adjustment mechanism (3) is used to adjust the flow resistance of the damping medium to adjust the damping force of the damper (22).

2. The impact-resistant buffer support structure for a hydrogen-powered drone chassis according to claim 1, characterized in that, The adjustment mechanism (3) includes a piston (31), a damping channel (32), and a limiting component (33). The damper (22) includes a cylinder body, and the piston (31) is connected to the damping rod (221) and disposed in the cylinder body. The piston (31) is sealed to the inner wall of the cylinder body to seal and divide the inner cavity of the cylinder body into a first cavity and a second cavity. A damping channel (32) is provided on the piston (31), and the first cavity and the second cavity are connected through the damping channel (32). During the operation of the damper (22), the damping medium flows between the first cavity and the second cavity through the damping channel (32). The limiting component (33) is used to limit the flow rate of the damping medium at the damping channel (32).

3. The impact-resistant buffer support structure for a hydrogen-powered unmanned aerial vehicle chassis according to claim 2, characterized in that, The damping channel (32) includes a first pipe (321) and a second pipe (322), the diameter of the second pipe (322) being larger than that of the first pipe (321), and the limiting component (33) being used to close the second pipe (322).

4. The impact-resistant buffer support structure for a hydrogen-powered drone chassis according to claim 3, characterized in that, The limiting component (33) includes a first adjusting piece (331), a cover (332), and a first elastic member (333). The first adjusting plate (331) is tightly fitted with the inner wall of the cylinder of the damper (22). The cover (332) is set on the first adjusting plate (331). The two ends of the first elastic element (333) are respectively connected to the first adjusting plate (331) and the piston (31). When the damping rod (221) is compressed by pressure, the first adjusting plate (331) is pressed and moves closer to the piston (31). When the cover (332) abuts against the second pipe (322), the second pipe (322) is closed.

5. The impact-resistant buffer support structure for a hydrogen-powered unmanned aerial vehicle chassis according to claim 2, characterized in that, The damping channel (32) includes a third conduit (323) disposed on the piston (31); The damper (22) has an adjustment component (34) in its cylinder for adjusting the flow area of ​​the third pipe (323).

6. The impact-resistant buffer support structure for a hydrogen-powered drone chassis according to claim 5, characterized in that, The adjustment assembly (34) includes a second adjustment plate (341), an adjustment frame (342), and a second elastic element (343). The second adjusting plate (341) fits tightly against the inner wall of the cylinder of the damper (22); The adjusting frame (342) is set on the second adjusting plate (341), and the adjusting frame (342) is provided with a blocking block (3421) for blocking the third pipe (323). The blocking block (3421) is frustoconical and its cross-sectional area gradually changes along the axial direction. The cross-sectional area of ​​the blocking block (3421) near the third pipe (323) is smaller. The two ends of the second elastic element (343) are connected to the second adjusting plate (341) and the piston (31) respectively.

7. The impact-resistant buffer support structure for a hydrogen-powered unmanned aerial vehicle chassis according to claim 1, characterized in that, The damper (22) has an abutment plate (222) and a flexible buffer (223) inside its cylinder. The abutment plate (222) is located at one end of the cylinder away from the damping rod (221), and the two ends of the flexible buffer (223) are connected to the abutment plate (222) and the inner wall of the cylinder, respectively.

8. The impact-resistant buffer support structure for a hydrogen-powered unmanned aerial vehicle chassis according to claim 7, characterized in that, The flexible buffer (223) is an airbag that can elastically deform under pressure.

9. The impact-resistant buffer support structure for a hydrogen-powered unmanned aerial vehicle chassis according to claim 1, characterized in that, The support base (12) is connected to an elastic extension rod (121) that extends in a direction away from the support frame (1).

10. The impact-resistant buffer support structure for a hydrogen-powered unmanned aerial vehicle chassis according to claim 9, characterized in that, A roller (122) is rotatably mounted on the elastic extension rod (121).

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