A type of drone with stable landing

Abstract

This utility model relates to the field of unmanned aerial vehicle (UAV) technology and discloses a UAV with stable landing, including a UAV body, two sets of support frames, and two support rods. The UAV body includes a fuselage, multiple arms, and multiple propeller modules. Two sets of arc-shaped arms are provided at the bottom of the fuselage, and each set of arc-shaped arms is connected to an irregularly shaped base by a fixing component. This UAV with stable landing achieves different landing methods for different landing environments by setting spikes and suction cups on the irregularly shaped base. When landing on soil, the spikes can penetrate the soil with the impact force of landing, greatly increasing the friction with the ground and preventing the UAV from sliding, ensuring a stable landing. When landing on the surface of the UAV landing site, the suction cups can expel internal air under the impact force and adhere to the surface, providing a stable fixing force for the UAV and avoiding problems such as tipping over due to rebound or sliding during landing.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a UAV with stable landing. Background Technology

[0002] A drone typically consists of a flight platform, power unit, avionics system, mission payload equipment, ground remote control launch station, and integrated support system. The flight platform is the main body of the drone, used to carry various equipment and perform flight missions; the power unit provides the drone with the power required for flight; the avionics system is responsible for the drone's navigation, communication, and control; the mission payload equipment is configured according to the specific mission requirements of the drone, such as cameras and sensors; the ground remote control launch station is used to remotely control the drone's flight and mission execution; and the integrated support system provides services such as drone maintenance, upkeep, and troubleshooting.

[0003] An existing patent (publication number: CN214451803U) discloses a teaching drone with stable landing, including a fuselage and several support legs. The bottom of the fuselage is fixedly connected to the support legs, each support leg having a retractable cavity, a retractable rod, and a secondary support leg at its bottom end. The retractable cavity has a retractable rod opening and a support leg opening. One end of the retractable rod passes through the retractable rod opening and is inserted into the retractable cavity. A limiting block is provided at the end of the retractable rod within the retractable cavity, and the cross-sectional area of ​​the limiting block is larger than the area of ​​the retractable rod opening. One end of the secondary support leg has a gear, which is rotatably mounted around an axis at the support leg opening. The retractable rod also has a toothed groove that meshes tightly with the gear. This design improves the stability of the drone during landing, reduces the possibility of tipping over, and protects the drone's service life.

[0004] During the landing process of the aforementioned drone, the retractable boom makes initial contact with the ground. Through the meshing of gears and teeth, the support rod rotates and contacts the ground. Therefore, for the drone to land stably, the retractable boom needs to slide stably. However, during the drone's landing, after the retractable boom contacts the ground and the support rod rotates and contacts the ground, the retractable boom can no longer slide. This causes the impact force of the hard contact between the retractable boom and the support rod and the ground to be transmitted to the drone. The impact force transmitted to the drone will cause severe vibration of the drone's fuselage, affecting the drone's normal landing. Utility Model Content

[0005] To address the shortcomings of existing technologies, this invention provides a drone with stable landing capabilities, which solves the problems mentioned in the background section.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a drone with stable landing, comprising a drone body, two sets of support frames and two support rods. The drone body includes a fuselage, multiple arms and multiple propeller modules. Two sets of arc-shaped arms are provided at the bottom of the fuselage. Each set of arc-shaped arms is connected to an irregularly shaped base through a fixing component. Each irregularly shaped base is inclined. Multiple spikes with a conical structure are fixedly connected to the bottom surface of each irregularly shaped base. Multiple suction cups are fixedly connected to the other side of each irregularly shaped base. A U-shaped mounting bracket is fixedly connected to the bottom of the central area of ​​the fuselage. Two buffer cylinders are fixedly connected to the bottom of the mounting bracket. Each buffer cylinder has an air inlet at its bottom. A baffle is hinged to the inner wall of each air inlet. An exhaust port is opened in the central area of ​​the upper surface of each buffer cylinder. The inner diameter of each exhaust port is smaller than the inner diameter of the corresponding air inlet. A set of pistons is slidably connected inside each buffer cylinder. A return spring is fixedly connected between each set of pistons. One end of each piston is connected to the corresponding support rod through an auxiliary component.

[0007] Furthermore, each set of support frames is fixedly connected to the bottom of the machine body, and the two support rods are rotatably connected to the corresponding set of support frames.

[0008] With the above solution, the support rod can rotate relative to the support frame. During the landing or takeoff of the drone, the support rod can adjust its angle according to the pressure changes, laying the foundation for subsequent cushioning.

[0009] Furthermore, both ends of the two support rods are formed with annular blocks, and each annular block is fixedly connected to a torsion spring on its side, and the other end of each torsion spring is fixedly connected to the corresponding support frame.

[0010] With the above solution, the torsion spring allows the support rod to rotate under the deformation force of the torsion spring after being subjected to external force, and then tend to return to its original position. During the landing of the drone, the rotation of the support rod causes the torsion spring to deform, and the elasticity of the torsion spring can help buffer the landing impact force. Furthermore, when the drone completes landing or needs to take off, it helps the support rod return to its initial position.

[0011] Furthermore, the fixing component includes a rotating rod fixedly connected to the irregularly shaped base. The rotating rod is coaxially arranged with the irregularly shaped base. A fixing ring is fixedly connected to one end of the rotating rod. Two symmetrically arranged positioning holes are opened on the circumferential surface of the fixing ring. The side of the arc-shaped arm corresponding to the position of the fixing ring has a convex structure, and a screw is threadedly connected to the convex structure of the arc-shaped arm. One end of the screw is located in the positioning hole.

[0012] The above solution, through the cooperation of the rotating rod, the fixing ring and the screw, achieves a detachable fixed connection between the irregular base and the arc arm, which facilitates the installation, disassembly and maintenance of the irregular base. When the spike rod or suction cup is damaged, the irregular base can be easily replaced, while also maintaining the stability of the irregular base.

[0013] Furthermore, the auxiliary component includes a connecting plate hinged to one side of the piston away from the buffer cylinder, a cam fixedly connected to the circumferential surface of the support rod, and the other end of the connecting plate hinged to the protruding part of the cam.

[0014] With the above scheme, during the drone landing process, the arc arm is subjected to force and drives the support rod to rotate, which in turn drives the cam to rotate. The convex part of the cam pulls the piston to slide inside the buffer cylinder through the connecting plate, thereby realizing the linkage between the rotation of the support rod and the sliding of the piston. The landing impact force on the support rod is transmitted to the piston inside the buffer cylinder, and the buffer cylinder is used to absorb and disperse the impact force, thereby improving the stability of the drone during landing.

[0015] Furthermore, dampers are provided on opposite sides of the two buffer cylinders, and the two ends of the two dampers are respectively hinged to the two corresponding arc-shaped arms.

[0016] The above scheme further enhances the buffering effect of the drone during landing. During the landing process, the arc arm will swing due to the impact force. The damper can dissipate the energy of the arc arm swing through its own damping characteristics.

[0017] Furthermore, the multiple support arms are fixedly connected to multiple right-angle points of the fuselage, multiple propeller modules are fixedly installed at the ends of the multiple support arms, and support rods are fixedly connected to the bottom ends of the multiple support arms.

[0018] The above solution enhances the structural stability by fixing the support arm to the fuselage at a right angle. The propeller module installed at the end of the support arm provides the power required for the drone to fly. The support rod can contact the ground when the drone body is tilted, preventing the propeller from being damaged by contact with the ground.

[0019] Furthermore, in the initial stationary state before the drone lands, the multiple torsion springs and the two return springs are all in a pre-stretched state; during the drone's landing process, the torsion springs and return springs are further stretched as the support rod rotates, absorbing the landing impact force and generating a return tendency.

[0020] Through the above scheme, the torsion spring and the return spring work together to drive the arc arm and the piston to return to their original positions through their deformation force. When the UAV lands and touches the ground, the support rod is deflected by the impact of the ground and the torsion spring deforms and stores energy. At the same time, the support rod further stretches the return spring through the auxiliary component. Relying on the pre-tightening force of the torsion spring and the return spring, combined with the air buffer structure of the buffer cylinder, the landing impact is offset and the reset speed of the components is slowed down. After the buffering is completed, the pre-stretched torsion spring and the return spring drive each component to automatically reset, so as to achieve a smooth and buffered landing of the UAV.

[0021] Compared with the prior art, the technical solution of this utility model has the following beneficial effects: This stable-landing drone utilizes spikes and suction cups mounted on an irregularly shaped base to achieve different landing methods for various environments. When landing on soil, the spikes can penetrate the soil with the impact force, significantly increasing friction with the ground and preventing the drone from slipping, ensuring a stable landing. When landing on the surface of a drone airfield, the suction cups can expel internal air under the impact force and adhere to the surface, providing stable fixation for the drone and avoiding problems such as tipping over due to rebound or slippage during landing. This greatly enhances the drone's adaptability to various complex landing environments and significantly improves landing stability. Secondly, during the drone's descent, the piston slides within the buffer cylinder under the traction of the auxiliary components, creating a negative pressure environment within the buffer cylinder. Because the exhaust port diameter is smaller than the intake port, outside air quickly enters the buffer cylinder through the intake port and stretches the return spring. During this process, the impact force of the landing can be continuously absorbed. At the same time, after the impact force is buffered, the return spring drives the piston to return to its original position and compresses the air to be discharged through the exhaust port. Due to the smaller diameter of the exhaust port, the return time of the arc arm is extended, avoiding instability caused by too rapid return. In addition, the dampers set on both sides of the buffer cylinder constitute a secondary buffer, which can consume the swing energy of the arc arm and further reduce vibration. The multi-stage buffer structure works together to effectively reduce the impact of the landing impact on the drone and ensure a smooth landing. Attached Figure Description

[0022] Figure 1 This is a bottom view of the overall structure of this application; Figure 2 For this application Figure 1 Enlarged schematic diagram of the structure at point A; Figure 3 This is a cross-sectional view of the overall structure of this application; Figure 4 For this application Figure 3 Enlarged schematic diagram of the structure at point B; Figure 5 This is a schematic diagram of the overall structure of this application; Figure 6 This is a bottom view of the irregularly shaped base structure of this application; Figure 7 This is a top view of the irregularly shaped base structure of this application.

[0023] In the picture: 1. Drone body; 101. Fuselage; 102. Support arm; 103. Propeller module; 2. Support frame; 3. Support rod; 4. Arc arm; 5. Fixing components; 501. Rotating rod; 502. Retaining ring; 503. Positioning hole; 504. Screw; 6. Irregularly shaped base; 7. Spike rod; 8. Suction cup; 9. Fixing bracket; 10. Buffer cylinder; 11. Air inlet; 12. Baffle plate; 13. Exhaust port; 14. Piston; 15. Return spring; 16. Auxiliary components; 1601, connecting plate; 1602, cam; 17. Ring block; 18. Torsion spring; 19. Damper; 20. Support rod. Detailed Implementation

[0024] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0025] Please see Figures 1-7This embodiment describes a drone with stable landing, comprising a drone body 1, two sets of support frames 2, and two support rods 3. The drone body 1 includes a fuselage 101, multiple arms 102, and multiple propeller modules 103. Two sets of arc-shaped arms 4 are located at the bottom of the fuselage 101. Each set of arc-shaped arms 4 is connected to a shaped base 6 via a fixing component 5. Each shaped base 6 is inclined, and multiple conical spikes 7 are fixedly connected to the bottom surface of each shaped base 6. Multiple suction cups 8 are fixedly connected to the other side of each shaped base 6. The spikes 7 and suction cups 8 allow for different landing methods to be selected according to the user's landing requirements for the drone body 1. The spikes 7 can help the drone land... When the drone is on the ground, the impact force of the drone body 1 when it lands penetrates into the soil, increasing the friction between the drone body 1 and the ground. When the user lands the drone on an external drone airport, the suction cup 8 is affected by the impact force of the drone body 1 when it comes into contact with the surface of the drone airport. The suction cup 8 expels the air inside it, allowing it to adhere to the surface of the drone airport. The diverse landing methods enhance the drone's adaptability to different landing environments and improve landing stability. The inclined setting of the irregularly shaped base 6 allows the spike rod 7 or suction cup 8 to make contact with the landing area first when the drone body 1 lands, thereby assisting the drone body 1 to land stably.

[0026] A U-shaped mounting bracket 9 is fixedly connected to the bottom of the central area of ​​the fuselage 101. Two buffer cylinders 10 are fixedly connected to the bottom of the mounting bracket 9. Each buffer cylinder 10 has an air inlet 11 at its bottom. A baffle 12 is hinged to the inner wall of each air inlet 11. An exhaust port 13 is opened in the central area of ​​the upper surface of each buffer cylinder 10. The inner diameter of each exhaust port 13 is smaller than the inner diameter of the corresponding air inlet 11. A set of pistons 14 is slidably connected inside each buffer cylinder 10. A return spring 15 is fixedly connected between each set of pistons 14. One end of each piston 14 is connected to the corresponding support rod 3 through an auxiliary component 16. The pistons 14 and the buffer cylinders 10 work together so that when the UAV body 1 lands, the pistons 14 are pulled by the auxiliary component 16 and move within the buffer cylinders 10. The internal sliding creates a negative pressure environment inside the buffer cylinder 10. Due to the small diameter of the exhaust port 13, air takes a long time to enter the buffer cylinder 10. Under the influence of the negative pressure inside the buffer cylinder 10, the baffle can rotate inward towards the inside of the buffer cylinder 10, opening the air inlet 11 and allowing outside air to enter the buffer cylinder 10. During this process, the impact force of the drone body 1 during landing can be absorbed. After the impact force on the drone body 1 is buffered, the deformation force of the return spring 15 drives the piston 14 to return to its original position and compresses the air inside the buffer cylinder 10, causing the air inside the buffer cylinder 10 to be discharged through the exhaust port 13. During this process, the return time of the arc arm 4 is extended, allowing the arc arm 4 to return slowly and preventing the deformation force of the return spring 15 from causing instability to the drone body 1.

[0027] Each set of support frames 2 is fixedly connected to the bottom end of the fuselage 101. Two support rods 3 are rotatably connected to the corresponding set of support frames 2. The support rods 3 can rotate relative to the support frames 2. During the landing or takeoff of the UAV, the support rods 3 can adjust their angle according to the pressure changes, laying the foundation for subsequent buffering. Both ends of the two support rods 3 have annular blocks 17. Each annular block 17 has a torsion spring 18 fixedly connected to its side. The other end of each torsion spring 18 is fixedly connected to the corresponding support frame 2. The setting of the torsion spring 18 allows the support rod 3 to generate a return tendency under the deformation force of the torsion spring 18 after it rotates under the action of external force. During the landing of the UAV, the rotation of the support rod 3 causes the torsion spring 18 to deform. The elasticity of the torsion spring 18 can help buffer the landing impact force and help the support rod 3 return to its initial position when the UAV completes the landing or needs to take off. Multiple torsion springs 18 and two return springs 15 are in a stretched state. The cooperation of the torsion springs 18 and the return springs 15 can drive the arc arm 4 and the piston 14 to return to their original positions through their deformation force.

[0028] The fixing component 5 includes a rotating rod 501 fixedly connected to the irregular base 6. The rotating rod 501 is coaxially arranged with the irregular base 6. One end of the rotating rod 501 is fixedly connected to a fixing ring 502. The circumferential surface of the fixing ring 502 has two symmetrically arranged positioning holes 503. The side of the arc-shaped arm 4 corresponding to the position of the fixing ring 502 has a protruding structure, and a screw 504 is threadedly connected to the protruding structure of the arc-shaped arm 4. One end of the screw 504 is located in the positioning hole 503. Through the cooperation of the rotating rod 501, the fixing ring 502 and the screw 504, a detachable fixed connection between the irregular base 6 and the arc-shaped arm 4 is realized, which facilitates the installation, disassembly and maintenance of the irregular base 6. When the spike rod 7 or the suction cup 8 is damaged, the irregular base 6 can be easily replaced, and the stability of the irregular base 6 can also be maintained.

[0029] The auxiliary component 16 includes a piston 14 with a connecting plate 1601 hinged to one side away from the buffer cylinder 10. A cam 1602 is fixedly connected to the circumferential surface of the support rod 3. The other end of the connecting plate 1601 is hinged to the protrusion of the cam 1602. During the landing of the UAV, the arc arm 4 is subjected to force and drives the support rod 3 to rotate, which in turn drives the cam 1602 to rotate. The protrusion of the cam 1602 pulls the piston 14 to slide inside the buffer cylinder 10 through the connecting plate 1601, thereby realizing the linkage between the rotation of the support rod 3 and the sliding of the piston 14. The landing impact force received by the support rod 3 is transmitted to the piston 14 inside the buffer cylinder 10, and the buffering effect of the buffer cylinder 10 is used to absorb and disperse the impact force, thereby improving the stability of the UAV during landing.

[0030] Each of the two buffer cylinders 10 is equipped with a damper 19 on one side facing away from each other. The two ends of the two dampers 19 are respectively hinged to the two corresponding arc arms 4. The damper 19 further enhances the buffering effect when the UAV lands. During the UAV landing process, the arc arms 4 will swing due to the impact force. The damper 19 can dissipate the swing energy of the arc arms 4 through its own damping characteristics.

[0031] Multiple support arms 102 are fixedly connected to multiple right angles of the fuselage 101, and multiple propeller modules 103 are fixedly installed at the ends of the multiple support arms 102. Support rods 20 are fixedly connected to the bottom of the multiple support arms 102. The fixed connection between the support arms 102 and the fuselage 101 at the right angles enhances the stability of the structure. The propeller modules 103 installed at the ends of the support arms 102 can provide the power required for the drone to fly. The support rods 3 can contact the ground when the drone body 1 is tilted, preventing the propellers from being damaged by contact with the ground.

[0032] It should be noted that the propeller module 103 includes blades, a brushless motor, and an electronic speed controller. Powered by the internal power supply of the drone body, the brushless motor drives the blades to rotate, enabling the drone to hover in the air.

[0033] The working principle of the above embodiment is as follows: Before the user controls the drone body 1 to land using the control device, the user can switch the landing mode for different terrains by manually rotating the rotating rod 501. When the user needs to land on the soil, the user will rotate the rotating rod 501 to make the rotating rod 501 drive the irregular base 6 to rotate, so that the multiple spikes 7 face the bottom surface. Then the user fixes the rotating rod 501 to the arc arm 4 with the screw 504.

[0034] When the drone lands, the tilted design of the irregularly shaped base 6 allows multiple spikes 7 to penetrate the soil, increasing the friction between the drone body 1 and the ground. The force from the two irregularly shaped bases 6 is then transmitted to the corresponding arc-shaped arms 4, causing the arc-shaped arms 4 to rotate the corresponding support rods 3. During rotation, the two support rods 3 respectively drive the corresponding cams 1602 to rotate, and the protruding parts of the cams 1602, through the connecting plate 1601, drive the hinged piston 14 to slide within the corresponding buffer cylinder 10, stretching the return spring 15 and creating a negative pressure within the buffer cylinder 10. Once a negative pressure is created within the buffer cylinder 10, the baffle 12 installed inside the buffer cylinder 10 opens inwards, allowing outside air to quickly enter the buffer cylinder 10. Inside, when multiple arc-shaped arms 4 rotate simultaneously, the bottom end of the arc-shaped arm 4 moves away from the drone body 1 and converts the impact force into a pulling force on the damper 19. The damper 19 then uses the deformation force of the return spring 15 to buffer the impact force, thereby achieving buffering when the drone body 1 lands. After the impact force on the drone is buffered, the deformation force of the return spring 15 can pull the connected piston 14 to slide in the corresponding buffer cylinder 10 and squeeze the air inside the buffer cylinder 10. Since the baffle 12 closes the air inlet 11, the air can only be discharged through the exhaust port 13. Since the inner diameter of the exhaust port 13 is small, the air discharge speed is slow. Therefore, the reset time of the arc-shaped arm 4 is extended, avoiding the instability caused by too fast reset, and achieving a stable landing of the drone body 1.

[0035] When it is necessary to land the drone body 1 on the drone airport, the rotating rod 501 is rotated so that the suction cup 8 faces downward. When the drone lands, the suction cup 8 contacts the drone airport, and the impact force of the drone body 1 when landing causes the air inside the suction cup 8 to be discharged to form a negative pressure, so that the suction cup 8 is attached to the drone airport. With the cooperation of the buffer cylinder 10, piston 14 and damper 19, the drone body 1 is landed stably.

[0036] It should be noted that, in this document, relational terms such as "first" and "second" are used only 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, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0037] Although embodiments of this application 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 this application, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A landing-stable unmanned aerial vehicle (UAV), comprising a UAV body (1), two sets of support frames (2) and two support rods (3), characterized in that: The drone body (1) includes a fuselage (101), multiple arms (102) and multiple propeller modules (103). Two sets of arc-shaped arms (4) are provided at the bottom of the fuselage (101). Each set of arc-shaped arms (4) is connected to a shaped base (6) through a fixing component (5). Each shaped base (6) is inclined. Multiple spikes (7) with a conical structure are fixedly connected to the bottom surface of each shaped base (6). Multiple suction cups (8) are fixedly connected to the other side of each shaped base (6). A U-shaped mounting bracket (9) is fixedly connected to the bottom of the central area of ​​the fuselage (101). Two buffer cylinders (10) are fixedly connected to the bottom of the mounting bracket (9). An air inlet (11) is opened at the bottom of each of the two buffer cylinders (10). A baffle (12) is hinged to the inner wall of each of the two air inlets (11). An exhaust hole (13) is opened in the central area of ​​the upper surface of each of the two buffer cylinders (10). The inner diameter of each exhaust hole (13) is smaller than the inner diameter of the corresponding air inlet (11). A set of pistons (14) is slidably connected inside each of the two buffer cylinders (10). A return spring (15) is fixedly connected between each set of pistons (14). One end of each piston (14) is connected to the corresponding support rod (3) through an auxiliary component (16).

2. The landing-stable unmanned aerial vehicle according to claim 1, characterized in that: Each set of support frames (2) is fixedly connected to the bottom end of the body (101), and the two support rods (3) are rotatably connected to the corresponding set of support frames (2).

3. The landing-stable unmanned aerial vehicle according to claim 2, characterized in that: Both ends of the two support rods (3) are formed with annular blocks (17), and each annular block (17) is fixedly connected to a torsion spring (18) on its side. The other end of each torsion spring (18) is fixedly connected to the corresponding support frame (2).

4. The landing-stable unmanned aerial vehicle according to claim 1, characterized in that: The fixing component (5) includes a rotating rod (501) fixedly connected to the irregular base (6). The rotating rod (501) is coaxially arranged with the irregular base (6). One end of the rotating rod (501) is fixedly connected to a fixing ring (502). The circumferential surface of the fixing ring (502) has two symmetrically arranged positioning holes (503). The side of the arc-shaped arm (4) corresponding to the position of the fixing ring (502) has a convex structure, and a screw (504) is threadedly connected to the convex structure of the arc-shaped arm (4). One end of the screw (504) is located in the positioning hole (503).

5. A landing-stable unmanned aerial vehicle according to claim 1, characterized in that: The auxiliary component (16) includes a connecting plate (1601) hinged to one side of the piston (14) away from the buffer cylinder (10), a cam (1602) fixedly connected to the circumferential surface of the support rod (3), and the other end of the connecting plate (1601) hinged to the protrusion of the cam (1602).

6. A landing-stable unmanned aerial vehicle according to claim 1, characterized in that: Each of the two buffer cylinders (10) is provided with a damper (19) on the opposite side, and the two ends of the two dampers (19) are respectively hinged to the two corresponding arc arms (4).

7. A landing-stable unmanned aerial vehicle according to claim 1, characterized in that: Multiple support arms (102) are fixedly connected to multiple right angles of the fuselage (101), multiple propeller modules (103) are fixedly installed at the ends of multiple support arms (102), and support rods (20) are fixedly connected to the bottom ends of multiple support arms (102).

8. A landing-stable unmanned aerial vehicle according to claim 3, characterized in that: In the initial stationary state before the drone lands, the multiple torsion springs (18) and the two return springs (15) are all in a pre-stretched state; during the drone's landing process, the torsion springs (18) and the return springs (15) are further stretched as the support rod (3) rotates, absorbing the landing impact force and generating a return tendency.

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