Buffer mechanism for landing of unmanned aerial vehicle

Abstract

The invention discloses a buffer mechanism for landing of an unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles. Comprising a fixed support, a buffer adjusting mechanism and a landing rod, and the fixed support comprises a mounting cross rod and an adjusting plate connected with the mounting cross rod; the buffer adjusting mechanism comprises a mounting frame, two connecting plates, two limiting blocks, two driving motors, two supporting main rods, two fixing lantern rings, two fixing frames and two first rotating arms. Through the detachable connection design of the mounting cross rod and the adjusting plate in the fixed support and in cooperation with the adjusting hole structure in the adjusting plate, the problems that a traditional buffer mechanism is poor in adaptability and difficult to meet the mounting requirements of unmanned aerial vehicles of different models are solved, and the design can flexibly adjust the mounting position of the buffer adjusting mechanism; and meanwhile, disassembly is convenient and fast, later maintenance and component replacement are facilitated, and the universality and practicability of the mechanism are remarkably improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicles, and in particular to a buffer mechanism for landing of unmanned aerial vehicles. BACKGROUND

[0002] In the current rapid development of unmanned aerial vehicle technology, unmanned aerial vehicles have been widely used in aerial photography, logistics transportation, agricultural plant protection, power inspection and other fields due to their flexibility, maneuverability and wide range of operation, and have become an important tool for efficient operation in various industries. As a core component of unmanned aerial vehicles, the landing buffer mechanism directly bears the key role of absorbing the impact force of landing and protecting the safety of the fuselage and internal precision components. Its performance directly affects the service life and operation reliability of the unmanned aerial vehicle. The core working logic is to convert the instantaneous impact force of the unmanned aerial vehicle landing into releasable energy through the elastic deformation of the mechanical structure and the dispersion of force, thereby reducing the direct effect of the impact force on the fuselage and achieving smooth landing.

[0003] At present, although there are various landing buffer mechanisms for unmanned aerial vehicles on the market, there are still significant technical shortcomings. Some products use fixed structure design, and the installation position and support angle cannot be flexibly adjusted, making it difficult to adapt to unmanned aerial vehicles of different models and different loads. The buffer mechanism and the center of gravity of the unmanned aerial vehicle are easily misaligned, resulting in uneven force during landing and causing the fuselage to tilt and roll over. Some buffer devices rely only on a single spring or rubber pad for shock absorption, lack multi-stage collaborative buffer design, and have single buffer effect, making it difficult to cope with complex landing impact forces under different flight heights and different ground environments, and unable to fully absorb energy. SUMMARY

[0004] The present application aims to provide a landing buffer mechanism for unmanned aerial vehicles, which solves the technical problems raised in the background art.

[0005] To achieve the above-mentioned purpose, the present application provides the following technical solution: a landing buffer mechanism for unmanned aerial vehicles, comprising a fixed support, a buffer adjustment mechanism and a landing rod, the fixed support comprising an installation crossbar and an adjustment plate connected to the installation crossbar; The buffer adjustment mechanism comprises an installation frame, two connecting plates, two limiting blocks, two drive motors, two support main rods, two fixed collars, two fixed frames, two first rotating arms, two second rotating arms, two support secondary rods, two limiting rings, two fixed blocks, two fixed rods, two rotating shafts, two connecting rods, two pad plates and two buffer springs.

[0006] Preferably, the two connecting plates are symmetrically arranged on the two sides of the outer wall of the buffer adjusting mechanism, the two limiting blocks are symmetrically arranged on the outer wall of the connecting plate, the two drive motors are respectively fixedly installed on the inner wall of the corresponding limiting block, one end of the two support main rods is respectively connected with the two fixed frames through the corresponding fixed sleeve ring, the two ends of the two fixed frames are respectively rotationally connected with the corresponding side first rotating arm, each first rotating arm is respectively rotationally connected with the corresponding second rotating arm, and the output shafts of the two drive motors are respectively fixedly connected with the inner wall of the corresponding second rotating arm.

[0007] Preferably, the mounting cross bar of the fixed support is detachably fixedly connected with the adjusting plate, the adjusting plate is provided with an adjusting hole for adjusting the mounting position, the mounting cross bar is fixed through the bolt penetrating the adjusting hole, the position of the adjusting plate and the mounting cross bar is adjusted and fixed, and the top outer wall of the mounting frame is fixedly connected with the end, away from the mounting cross bar, of the adjusting plate.

[0008] Preferably, the top ends of the two support auxiliary rods are respectively fixedly connected with the corresponding limiting rings, the two fixed blocks are respectively fixedly installed on the middle outer wall of the corresponding support auxiliary rod, the two fixed rods are respectively transversely penetrated through the reserved holes of the corresponding fixed blocks and fixedly connected with the fixed blocks, the outer wall of each fixed rod is rotationally sleeved with a rotating shaft through a bearing, one end of each connecting rod is fixedly connected with the outer wall of the corresponding rotating shaft, the other end is fixedly connected with the top center position of the two pads, the two pads are circular structures, the diameters of the two pads are greater than the outer diameters of the corresponding buffer springs, the two pads are used for bearing the acting force of the buffer springs, the outer wall of each mounting frame is fixedly provided with a connecting plate, and the outer wall of each connecting plate is fixedly provided with a limiting block.

[0009] Preferably, the two buffer springs are respectively fixedly arranged between the corresponding pads and the limiting blocks, and the two buffer springs are symmetrically arranged, so that the buffer stress balance is ensured.

[0010] Preferably, the end, away from the corresponding support main rod, of each support auxiliary rod is fixedly connected with the corresponding landing rod, and the support auxiliary rod and the landing rod are coaxially arranged; the two landing rods are completely identical in structure size and symmetrically distributed below the buffer adjusting mechanism.

[0011] Preferably, the landing rod comprises rubber pads arranged at the two ends of the landing rod, and the surface of the rubber pad is provided with an anti-skid structure, which is used for absorbing the landing impact force and enhancing the landing stability.

[0012] Compared with the related art, the buffer mechanism for the unmanned aerial vehicle landing has the following beneficial effects: 1. The unmanned aerial vehicle landing buffer mechanism is characterized in that the detachable connection design of the horizontal rod and the adjusting plate in the fixed support is matched with the adjusting hole structure on the adjusting plate, the poor adaptability and the difficulty in matching the installation requirements of different models of unmanned aerial vehicles of the traditional buffer mechanism are solved, the installation position of the buffer adjusting mechanism can be flexibly adjusted, the buffer mechanism and the gravity center of the unmanned aerial vehicle are accurately aligned, the mechanism is convenient to disassemble, convenient to maintain and replace parts, and the universality and practicality of the mechanism are significantly improved.

[0013] 2. The unmanned aerial vehicle landing buffer mechanism is characterized in that the linkage structure of the driving motor, the first rotating arm, the second rotating arm and the support main rod in the buffer adjusting mechanism is combined with the multi-stage buffer system composed of the support auxiliary rod, the buffer spring and the pad, the single buffer effect and the difficulty in adapting to different landing conditions of the traditional buffer mechanism are solved. The driving motor can adjust the angle of the support main rod in advance, and the stress distribution is optimized; the symmetric arrangement and elastic buffer effect of the buffer spring are matched with the preliminary shock absorption and anti-skid function of the rubber pads at both ends of the landing rod, the multi-stage and balanced buffer effect is realized, the landing impact force is effectively absorbed, the unmanned aerial vehicle is prevented from rolling and sliding, the limiting effect of the limiting ring protects the stability of the mechanism structure, the damage of the impact force to the unmanned aerial vehicle body and internal elements is greatly reduced, and the safety and service life of the unmanned aerial vehicle landing are improved. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 It is a schematic diagram of the overall structure of the present application; Figure 2 It is another angle overall structure schematic diagram of the present application; Figure 3 It is a structure schematic diagram of the buffer adjusting mechanism of the present application; Figure 4 It is an exploded view of part of the buffer adjusting mechanism of the present application; Figure 5 It is a structure schematic diagram of the present application Figure 4 The enlarged view of structure A in the present application; Figure 6 It is an exploded view of part of the support main rod of the present application; Figure 7 It is a structure schematic diagram of the present application Figure 6 The enlarged view of structure B in the present application; Figure 8 It is a structure schematic diagram of the present application Figure 6 The enlarged view of structure C in the present application.

[0015] In the figure: 1, fixed support; 101, installation crossbar; 102, adjusting plate; 2, buffer adjusting mechanism; 201, installation frame; 202, connecting plate; 203, limiting block; 204, driving motor; 205, supporting main rod; 206, fixed sleeve ring; 207, fixed frame; 208, first rotating arm; 209, second rotating arm; 210, supporting secondary rod; 211, limiting ring; 212, fixed block; 213, fixed rod; 214, rotating shaft; 215, connecting rod; 216, pad plate; 217, buffer spring; 3, landing rod; 301, rubber pad. DETAILED DESCRIPTION

[0016] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by a person of ordinary skill in the art without creative work fall within the scope of protection of the present application.

[0017] Embodiment one: Please refer to Figures 1-8 The present application provides a technical solution: a buffer mechanism for unmanned aerial vehicle landing, comprising a fixed support 1, a buffer adjusting mechanism 2 and a landing rod 3, the fixed support 1 comprising an installation crossbar 101 and an adjusting plate 102 connected with the installation crossbar 101; The buffer adjusting mechanism 2 comprises an installation frame 201, two connecting plates 202, two limiting blocks 203, two driving motors 204, two supporting main rods 205, two fixed sleeve rings 206, two fixed frames 207, two first rotating arms 208, two second rotating arms 209, two supporting secondary rods 210, two limiting rings 211, two fixed blocks 212, two fixed rods 213, two rotating shafts 214, two connecting rods 215, two pad plates 216 and two buffer springs 217; The two connecting plates 202 are symmetrically arranged on the outer walls of the buffer adjusting mechanism 2, the two limiting blocks 203 are symmetrically arranged on the outer walls of the connecting plates 202, the two driving motors 204 are fixedly installed on the inner walls of the corresponding limiting blocks 203, one end of the two supporting main rods 205 is connected with the two fixed frames 207 one by one through the corresponding fixed sleeve rings 206, the two ends of the two fixed frames 207 are rotatably connected with the corresponding first rotating arms 208, each first rotating arm 208 is rotatably connected with the corresponding second rotating arm 209, and the output shafts of the two driving motors 204 are fixedly connected with the inner walls of the corresponding second rotating arms 209; The mounting cross bar 101 of the fixed support 1 is detachably fixedly connected with the adjusting plate 102, the adjusting plate 102 is provided with adjusting holes for adjusting the mounting position, the adjusting plate 102 is fixedly connected with the mounting cross bar 101 through the adjusting holes and bolts, and the position of the adjusting plate 102 and the mounting cross bar 101 is adjusted and fixed; the end, away from the mounting cross bar 101, of the adjusting plate 102 is fixedly connected with the top outer wall of the mounting frame 201; The end, away from the corresponding support main rod 205, of each support auxiliary rod 210 is fixedly connected with the corresponding landing rod 3, and the support auxiliary rod 210 and the landing rod 3 are coaxially arranged; the two landing rods 3 are completely identical in structure and symmetrically arranged below the buffer adjusting mechanism 2; The landing rod 3 is provided with rubber pads 301 at both ends thereof, the rubber pads 301 are provided with anti-skid structures on surfaces thereof, and are used for absorbing landing impact force and enhancing landing stability; In the embodiment, the fixed support 1 is stably connected with the unmanned aerial vehicle body through the mounting cross bar 101, the adjusting holes in the adjusting plate 102 are designed to be flexibly adaptable to the mounting requirements of unmanned aerial vehicles of different models, the mounting position of the buffer adjusting mechanism 2 can be accurately adjusted through bolt locking, the buffer mechanism can be ensured to be adapted to the center of gravity of the unmanned aerial vehicle, and a basis guarantee is provided for subsequent buffer effect; the driving motor 204 serves as a power adjusting component, the output shaft of the driving motor 204 drives the second rotating arm 209 to rotate, and then the first rotating arm 208 and the fixed frame 207 are linked to flexibly adjust the angle and stress posture of the support main rod 205, so that the buffer adjusting mechanism 2 can adjust the support angle in advance according to the actual working conditions such as the load of the unmanned aerial vehicle and the flight height, so as to optimize the buffer stress distribution, improve the pertinence and effectiveness of the buffer, and the rubber pads 301 at both ends of the landing rod 3 are made of high-elastic wear-resistant rubber material, and the surface anti-skid lines increase the friction force with the ground, so that part of the impact force can be absorbed in the landing moment, and the problems of rolling and sliding of the unmanned aerial vehicle caused by smooth ground or uneven impact force when landing can be effectively avoided, and the landing stability is significantly enhanced.

[0018] The top ends of the two support auxiliary rods 210 are fixedly connected with the corresponding limiting rings 211, the two fixed blocks 212 are fixedly installed on the middle outer walls of the corresponding support auxiliary rods 210, the two fixed rods 213 are transversely penetrated through the reserved holes of the corresponding fixed blocks 212 and fixedly connected with the fixed blocks 212, and the outer walls of each fixed rod 213 are rotatably sleeved with the rotating shafts 214 through bearings; one end of each of the two connecting rods 215 is fixedly connected with the outer wall of the corresponding rotating shaft 214, and the other end is fixedly connected with the top center position of the two pad plates 216, the two pad plates 216 are circular structures, and the diameters of the two pad plates 216 are greater than the outer diameters of the corresponding buffer springs 217, so as to bear the acting force of the buffer springs 217; one side outer wall of each mounting frame 201 is fixedly provided with a connecting plate 202, and the outer wall of each connecting plate 202 is fixedly provided with a limiting block 203; Two buffer springs 217 are respectively fixedly arranged between the corresponding base plates 216 and the limiting blocks 203, and the two buffer springs 217 are symmetrically arranged to ensure balanced buffering force; In the embodiment, the support secondary rod 210 is connected with the base plate 216 and the buffer spring 217 through the linkage structure composed of the fixing block 212, the fixing rod 213 and the rotating shaft 214, and when the unmanned aerial vehicle lands and generates an impact force, the support secondary rod 210 transmits the force to the fixing block 212, and through the rotating characteristics of the rotating shaft 214 and the conduction of the connecting rod 215, the impact force is uniformly dispersed to the base plate 216, and then is elastically buffered by the buffer spring 217. The base plate 216 is designed in a circular shape with a large diameter, can fully cover the end face of the buffer spring 217, avoids the deviation and distortion of the buffer spring 217 when the buffer spring 217 is stressed, ensures the vertical transmission of the buffering force, improves the buffering efficiency, and the two buffer springs 217 are symmetrically distributed on both sides of the buffering adjusting mechanism 2, which can ensure the balanced stress on the left and right sides of the unmanned aerial vehicle when the unmanned aerial vehicle lands, prevents the tilting of the machine body caused by the excessive stress on one side, and at the same time, the buffer spring 217 is selected from a high-strength compression spring, the elastic deformation range of which can adapt to different impact force scenes, quickly absorbs and releases the impact force through the elastic reset action, reduces the damage of the impact force to the machine body and internal elements of the unmanned aerial vehicle, the limiting ring 211 at the top end of the support secondary rod 210 can limit the movement stroke of the support secondary rod 210, avoids the excessive displacement of the support secondary rod 210 caused by the excessive impact force, and guarantees the stability of the overall structure of the buffering mechanism. The mounting frame 201 is fixedly connected with the limiting block 203 through the connecting plate 202, the limiting block 203 provides a stable installation carrier for the driving motor 204 and a fixed support point for the buffer spring 217, so that the components of the buffering mechanism form a whole in cooperative stress, and the reliability of the buffering effect is further improved.

[0019] Working principle: Before takeoff, the relative position of the buffer adjustment mechanism 2 with the mounting crossbar 101 can be adjusted through the adjustment holes of the adjustment plate 102 in the fixed support 1, according to the aircraft model, load, and expected flight scenario. Then, bolts are used to lock the position, ensuring precise alignment between the buffer adjustment mechanism 2 and the drone's center of gravity, laying the foundation for stable buffering. Simultaneously, by controlling the start of two drive motors 204, their output shafts drive the corresponding second rotating arm 209 to rotate. The second rotating arm 209, in conjunction with the first rotating arm 208, rotates around the fixed frame 207. This, in turn, adjusts the tilt angle of the main support rod 205 through the fixed collar 206, aligning the lower support sub-rod 210 with... The landing pole 3 is in a preset posture adapted to the landing conditions, completing the pre-adjustment of the buffer mechanism. When the drone is about to land, the rubber pads 301 at both ends of the landing pole 3 first contact the ground. The elastic deformation of the rubber pads 301 will initially absorb part of the landing impact force, while the anti-slip structure on its surface increases the friction with the ground, preventing the drone from sliding or shifting sideways and ensuring initial landing stability. The impact force will be transmitted through the landing pole 3 to the coaxially connected support rod 210. The support rod 210 transmits the force to the fixing block 212 on the outer wall in the middle. The fixing block 212 drives the fixing rod 213 to be stressed synchronously. At this time, the outer wall of the fixing rod 213 passes through... The bearing-mounted shaft 214 rotates adaptively, smoothly transmitting the impact force to the pad 216 via the connecting rod 215. Since the diameter of the pad 216 is larger than the outer diameter of the buffer spring 217, the impact force is evenly distributed to the buffer spring 217, causing it to elastically compress between the pad 216 and the limiting block 203, converting the impact force into elastic potential energy for secondary buffering and shock absorption. The two buffer springs 217 are symmetrically arranged to ensure force balance on both sides of the drone, preventing tilting. During this process, the limiting ring 211 at the top of the supporting rod 210 limits the maximum displacement of the supporting rod 210, preventing excessive impact force. The impact force causes excessive movement of the support rod 210, protecting the stability of the connection between the components of the buffer mechanism. The mounting frame 201 forms a stable support with the limiting block 203 through the connecting plate 202, providing a reliable force carrier for the drive motor 204 and the buffer spring 217, ensuring the coordinated action of the components. As the impact force gradually weakens, the buffer spring 217 releases its elastic potential energy, pushing the pad 216, connecting rod 215 and rotating shaft 214 to reset. The support rod 210 and the landing rod 3 return to their initial posture, completing the entire landing buffer process. This effectively reduces the damage to the drone's fuselage and internal components caused by the impact force, improving the safety and service life of the drone landing.

[0020] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, the phrase "comprising an element defined as..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes the element.

[0021] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A landing buffer mechanism for unmanned aerial vehicles (UAVs), comprising a fixed support (1), a buffer adjustment mechanism (2), and a landing pole (3), characterized in that: The fixed support (1) includes a mounting crossbar (101) and an adjusting plate (102) connected to the mounting crossbar (101); The buffer adjustment mechanism (2) includes a mounting frame (201), two connecting plates (202), two limiting blocks (203), two drive motors (204), two main support rods (205), two fixing collars (206), two fixing frames (207), two first rotating arms (208), two second rotating arms (209), two auxiliary support rods (210), two limiting rings (211), two fixing blocks (212), two fixing rods (213), two rotating shafts (214), two connecting rods (215), two pads (216), and two buffer springs (217).

2. The landing buffer mechanism for a drone according to claim 1, characterized in that: Two connecting plates (202) are symmetrically arranged on both sides of the outer wall of the buffer adjustment mechanism (2), two limiting blocks (203) are symmetrically arranged on both sides of the outer wall of the connecting plate (202), two drive motors (204) are respectively fixedly installed on the inner wall of the corresponding limiting block (203), one end of the two support rods (205) is respectively connected to the two fixed frames (207) through the corresponding fixed collars (206), the two ends of the two fixed frames (207) are respectively rotatably connected to the corresponding side first rotating arm (208), each first rotating arm (208) is respectively rotatably connected to the corresponding second rotating arm (209), and the output shafts of the two drive motors (204) are respectively fixedly connected to the inner wall of the corresponding second rotating arm (209).

3. The landing buffer mechanism for a drone according to claim 1, characterized in that: The mounting crossbar (101) of the fixed support (1) is detachably fixedly connected to the adjusting plate (102). The adjusting plate (102) is provided with an adjusting hole for adjusting the installation position. The adjusting plate (102) is fixed to the mounting crossbar (101) by bolts passing through the adjusting hole, thereby realizing the position adjustment and fixing of the adjusting plate (102) and the mounting crossbar (101). The end of the adjusting plate (102) away from the mounting crossbar (101) is fixedly connected to the top outer wall of the mounting frame (201).

4. The landing buffer mechanism for a drone according to claim 1, characterized in that: The top ends of the two supporting rods (210) are fixedly connected to the corresponding limiting rings (211), the two fixing blocks (212) are fixedly installed on the middle outer wall of the corresponding supporting rods (210), the two fixing rods (213) pass through the reserved holes of the corresponding fixing blocks (212) laterally and are fixedly connected to the fixing blocks (212), and the outer wall of each fixing rod (213) is fitted with a rotating shaft (214) through a bearing; one end of the two connecting rods (215) is fixedly connected to the outer wall of the corresponding rotating shaft (214), and the other end is fixedly connected to the top center of the two pads (216). The two pads (216) are both circular structures, and their diameters are larger than the outer diameter of the corresponding buffer springs (217) to bear the force of the buffer springs (217). A connecting plate (202) is fixedly installed on one side outer wall of each mounting frame (201), and a limiting block (203) is fixedly installed on the outer wall of each connecting plate (202).

5. A landing buffer mechanism for a drone according to claim 1, characterized in that: The two buffer springs (217) are respectively fixed between the corresponding pad (216) and the limiting block (203). The two buffer springs (217) are symmetrically arranged to ensure that the buffer force is balanced.

6. A buffer mechanism for drone landing according to claim 1, characterized in that: Each of the supporting sub-rods (210) has its end away from the corresponding supporting main rod (205) fixedly connected to the corresponding ground rod (3), and the supporting sub-rods (210) and the ground rod (3) are coaxially arranged; the two ground rods (3) have completely identical structural dimensions and are symmetrically distributed below the buffer adjustment mechanism (2).

7. A landing buffer mechanism for a drone according to claim 1, characterized in that: The landing pole (3) includes rubber pads (301) at both ends. The surface of the rubber pads (301) is provided with an anti-slip structure to absorb the impact force of landing and enhance landing stability.

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