Unmanned aerial vehicle landing damping protection structure

Abstract

The invention discloses an unmanned aerial vehicle landing damping protection structure, and belongs to the technical field of unmanned aerial vehicle landing damping. The unmanned aerial vehicle landing damping protection structure comprises a mounting frame, moving wheels are arranged at the bottom of the mounting frame, the mounting frame comprises a first mounting strip, two second mounting strips are connected to the first mounting strip, a cavity is formed in the first mounting strip, a rubber pad is arranged in the cavity, and the end of the second mounting strip extends into the cavity to be connected with the rubber pad; mounting shafts are connected to the lower ends of the second mounting strips, first buffer assemblies are arranged between the moving wheels and the mounting shafts, and second buffer assemblies are arranged between the two ends of the mounting shafts and the first mounting strips; through the arrangement of the first buffer assembly, the second buffer assembly and the rubber pad, a multi-stage damping structure is formed, so that the vibration force borne by the unmanned aerial vehicle during landing is sequentially and repeatedly relieved, the unmanned aerial vehicle body is not subjected to large vibration force in the descending process, and the safety of the unmanned aerial vehicle and carried equipment thereof is guaranteed.

Description

Technical Field

[0001] The present invention relates to the technical field of UAV landing shock absorption, and more specifically, to a UAV landing shock absorption protection structure. Background Art

[0002] With its flexibility and high efficiency, unmanned aerial vehicles (UAVs) have been widely used in many fields such as aerial photography and mapping, material delivery, environmental monitoring, and emergency rescue. With the continuous development of UAV technology, its application scenarios are becoming increasingly complex, and the requirements for the safe and reliable landing of UAVs are also getting higher and higher. During actual use, the landing process of UAVs is often accompanied by relatively large impact forces. Especially under non-ideal landing conditions, such as on uneven ground, slopes, or in strong wind environments, these impact forces may damage key components of the UAV body, sensors, power systems, etc., seriously affecting the service life and flight safety of the UAV. Currently, elastic materials for shock absorption usually use elastic elements such as rubber and springs, which absorb the impact force during landing through their own elastic deformation. However, such shock absorption structures have certain limitations. Rubber materials are prone to aging and reduced elasticity after long-term use, resulting in a decline in shock absorption effect; spring shock absorption has poor adaptability to impact forces of different intensities and is difficult to provide stable shock absorption performance under various complex landing conditions. In addition, with the development of UAVs towards high payload, long endurance, and high precision, the requirements for the shock absorption protection structure have expanded from simply buffering impacts to being able to maintain the stable attitude of the UAV during shock absorption. In view of this, we propose a UAV landing shock absorption protection structure. Summary of the Invention

[0003] The purpose of the present invention is to provide a UAV landing shock absorption protection structure to solve the problems raised in the above background art.

[0004] To achieve the above purpose, the present invention provides the following technical solutions: A UAV landing shock absorption protection structure includes a mounting frame. A moving wheel is provided at the bottom of the mounting frame. The mounting frame includes a first mounting strip, and two second mounting strips are connected to the first mounting strip. The second mounting strips are perpendicular to the first mounting strip. A cavity is formed inside the first mounting strip, and a rubber pad is provided inside the cavity. The end of the second mounting strip extends into the cavity and is connected to the rubber pad; A mounting shaft is connected to the lower end of the second mounting strip. A first buffer assembly is provided between the moving wheel and the mounting shaft, and a second buffer assembly is provided between both ends of the mounting shaft and the first mounting strip.

[0005] Preferably, the first buffer assembly includes a support frame. The upper end of the support frame is rotatably connected to the mounting shaft. The lower end of the support frame is rotatably connected to a connecting seat. A telescopic member is provided inside the support frame, and the output shaft of the telescopic member is rotatably connected to the connecting seat.

[0006] Preferably, a first connecting shaft and a second connecting shaft are provided at the lower end of the connecting seat. An elastic member is provided between the first connecting shaft and the second connecting shaft, and the second connecting shaft is connected to the fixed shaft of the moving wheel.

[0007] Preferably, the elastic member includes two relatively arranged elastic sheets. A housing is provided below the connecting seat, and the two elastic sheets are installed in the housing. The ends of the first connecting shaft and the second connecting shaft both extend into the housing and are in contact with the two elastic sheets respectively.

[0008] Preferably, the telescopic member is a gas spring telescopic rod.

[0009] Preferably, the second buffer assembly includes an installation cylinder. The installation cylinder is arranged in the first installation strip. A movable shaft is slidably connected in the installation cylinder. The end of the movable shaft extends out of the installation cylinder and is connected to the installation shaft. A spring is sleeved on the inner end of the movable shaft located in the installation cylinder; A sealing assembly is provided in the installation cylinder. One side of the sealing assembly in the installation cylinder is set as a hydraulic oil cavity, and the spring is located in the hydraulic oil cavity.

[0010] Preferably, a piston is sleeved on the part of the movable shaft located in the hydraulic oil cavity, and there is a gap between the piston and the inner wall of the hydraulic oil cavity.

[0011] Preferably, the sealing assembly includes a plurality of sealing rings and sealing gaskets. There are positioning grooves in the installation cylinder. A positioning cylinder and a positioning ring are arranged in the positioning grooves. The sealing gasket is arranged between the outer wall of the positioning cylinder and the inner wall of the installation cylinder; The sealing rings are arranged between the inner wall of the positioning cylinder and the outer wall of the movable shaft and between the inner wall of the positioning ring and the outer wall of the movable shaft.

[0012] Compared with the prior art, the beneficial effects of the present invention are as follows: (1) Through the first buffer assembly, the second buffer assembly and the rubber pad arranged inside the first installation strip, and the second installation strip extends into the cavity and is connected to the rubber pad, a multi-stage shock absorption structure is formed. When the drone lands, the shock force received is gradually reduced by the first buffer assembly, the second buffer assembly and the rubber pad for multiple times, so that the drone fuselage will not be subjected to a large shock force during the descent process, ensuring the safety of the drone and its carried equipment, and providing more stable support for the reliable landing of the drone under complex working conditions.

[0013] (2) By adjusting the angle between the support frame and the connecting seat, the angle between the support frame and the connecting seat can be adjusted by using the elongation and shortening of the telescopic member. When the drone lands and contacts the ground, the telescopic member contracts to make the drone fuselage continue to move downward a certain distance relative to the moving wheel, so that the fuselage obtains a longer buffer distance under the same shock absorption force, effectively extending the impact time, and thus the drone will not be subjected to a large inertial force during the descent. Description of the Drawings

[0014] Figure 1 Schematic diagram of the overall structure of the present invention installed on a drone; Figure 2 Schematic diagram of the overall structure of the present invention; Figure 3 Schematic diagram of the first buffer assembly of the present invention; Figure 4 Schematic diagram of the second buffer assembly of the present invention.

[0015] Description of the reference numerals in the figure: 1, mounting frame; 101, first mounting strip; 102, second mounting strip; 2, moving wheel; 3, mounting shaft; 4, first buffer assembly; 401, support frame; 402, connecting seat; 403, telescopic member; 404, first connecting shaft; 405, second connecting shaft; 406, elastic sheet; 407, housing; 5, second buffer assembly; 501, mounting cylinder; 502, movable shaft; 503, spring; 504, hydraulic oil chamber; 505, piston; 506, sealing ring; 507, sealing ring; 508, positioning cylinder; 509, positioning ring; 6, drone. Detailed implementation manners

[0016] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments.

[0017] Embodiment: Please refer to Figures 1-4 , a shock-absorbing and protecting structure for a drone landing, including a mounting frame 1, a moving wheel 2 is arranged at the bottom of the mounting frame 1, the mounting frame 1 includes a first mounting strip 101, two second mounting strips 102 are connected to the first mounting strip 101, the second mounting strip 102 is perpendicular to the first mounting strip 101, a cavity is opened inside the first mounting strip 101, a rubber pad is arranged in the cavity, the end of the second mounting strip 102 extends into the cavity and is connected to the rubber pad, the second mounting strip 102 can slide relative to the first mounting strip 101. When the moving wheel 2 contacts the ground, an upward force is generated, causing the second mounting strip 102 to squeeze the rubber pad, and using the rubber pad to slow down the force received by the first mounting strip 101, thereby achieving the shock-absorbing effect on the drone; this shock-absorbing and protecting structure is installed at the bottom of the drone.

[0018] At the lower end of the second mounting strip 102, there is a mounting shaft 3 connected. Between the moving wheel 2 and the mounting shaft 3, there is a first buffer assembly 4. When the moving wheel 2 contacts the ground and generates vibrations, the first buffer assembly 4 reduces the vibration force received by the mounting shaft 3. Between the two ends of the mounting shaft 3 and the first mounting strip 101, there is a second buffer assembly 5. Through the arrangement of the second buffer assembly 5, the vibrations generated by the second mounting strip 102 are further reduced. When the moving wheel 2 lands on an uneven bottom surface, through the cooperation of the second buffer assembly 5 and the rubber pad, the vibrations received by the drone are mitigated.

[0019] In this application, the first buffer assembly 4 includes a support frame 401. The support frame 401 is a bent structure. The upper end of the support frame 401 is rotatably connected to the mounting shaft 3. The lower end of the support frame 401 is rotatably connected to a connecting seat 402. The support frame 401 and the connecting seat 402 form a certain angle. Inside the support frame 401, there is a telescopic member 403; the output shaft of the telescopic member 403 is rotatably connected to the connecting seat 402. By using the elongation and shortening of the telescopic member 403, the angle between the support frame 401 and the connecting seat 402 can be adjusted. When the drone lands and contacts the ground, through the contraction of the telescopic member 403, the drone body continues to move downward relative to the moving wheel 2 by a certain distance, enabling the body to obtain a longer buffer distance under the same damping force, effectively extending the impact time, so that the drone will not be affected by a large inertial force of descent.

[0020] In a possible embodiment, the telescopic member 403 is a gas spring telescopic rod. Through the controllable damping effect, the remaining kinetic energy is converted into hydraulic heat energy.

[0021] In this application, at the lower end of the connecting seat 402, there are a first connecting shaft 404 and a second connecting shaft 405. Between the first connecting shaft 404 and the second connecting shaft 405, there is an elastic member. The second connecting shaft 405 is connected to the fixed shaft of the moving wheel 2. When the moving wheel 2 contacts the ground, the second connecting shaft 405 will apply force to the elastic member. After a part of the vibration force is released by the elastic member, the vibration force reaching the first connecting shaft 404 will be weakened.

[0022] In this application, the elastic member includes two relatively arranged elastic sheets 406. Below the connecting seat 402, there is a housing 407. The two elastic sheets 406 are installed inside the housing 407. The ends of the first connecting shaft 404 and the second connecting shaft 405 both extend into the housing 407 and are respectively in contact with the two elastic sheets 406. By the second connecting shaft 405 contacting the elastic sheet 406, the vibration force is thus mitigated.

[0023] In a possible embodiment, the telescopic member 403 adopts a speed-sensing damping valve design, and its damping coefficient (C) has a non-linear relationship with the piston rod movement speed (v): C = C0 + k・v² (C0 is the basic damping coefficient, and k is the adjustment coefficient). When the drone lands at a high speed (such as the vertical descent speed > 2 m / s), the damping force increases rapidly to inhibit excessive sinking of the fuselage; when landing at a low speed (such as < 0.5 m / s), the damping force decreases to ensure sensitive response of the shock absorption system. A micro pressure sensor is integrated inside the telescopic member 403 to monitor the hydraulic chamber pressure (P) in real time. When P exceeds the set threshold (such as 3 MPa), the intelligent control valve will open the bypass channel to allow some hydraulic oil to flow through the throttle hole for diversion, achieving overload protection while maintaining a stable buffering force.

[0024] In this application, the second buffer assembly 5 includes a mounting cylinder 501. The mounting cylinder 501 is disposed inside the first mounting strip 101. A movable shaft 502 is slidably connected inside the mounting cylinder 501. The end of the movable shaft 502 extends out of the mounting cylinder 501 and is connected to the mounting shaft 3, and the end of the movable shaft 502 extends out of the first mounting strip 101. A spring 503 is sleeved on the inner end of the movable shaft 502 located inside the mounting cylinder 501. During the descent of the drone, when the shock force generated by the contact between the drone and the ground is transmitted to the mounting shaft 3, the force received by the mounting shaft 3 acts on the movable shaft 502 and the spring 503 to further release and slow down the shock force.

[0025] A sealing assembly is provided inside the mounting cylinder 501. The side of the mounting cylinder 501 located on one side of the sealing assembly is a hydraulic oil chamber 504. The spring 503 is located inside the hydraulic oil chamber 504. Through the action of the hydraulic oil in the hydraulic oil chamber 504, the force when the spring 503 releases its elastic force is slowed down.

[0026] In this application, a piston 505 is sleeved on the part of the movable shaft 502 located in the hydraulic oil chamber 504. There is a gap between the piston 505 and the inner wall of the hydraulic oil chamber 504. When the piston moves with the movable shaft 502, the hydraulic oil reciprocates through the gap between the piston 505 and the inner wall of the hydraulic oil chamber 504, and a significant damping effect will be generated during this process. When the hydraulic oil flows in a narrow gap, it will be subject to viscous resistance, the internal friction between oil molecules, and the friction between the oil and the piston and the oil chamber wall surface, so that the kinetic energy of the drone during landing is converted into heat energy during the flow of the hydraulic oil, thereby dissipating a large amount of impact energy.

[0027] Compared to traditional elastic shock-absorbing structures, this shock-absorbing method based on hydraulic oil damping can automatically adjust the damping force according to the magnitude of the impact force when the drone lands. When the impact force is large, the flow rate of the hydraulic oil increases, and the damping force increases accordingly, which can quickly suppress the movement speed of the movable shaft 502 and effectively cushion high-intensity impacts. When the impact force is small, the flow rate of the hydraulic oil slows down and the damping force decreases, preventing the shock-absorbing structure from over-cushioning and affecting the drone's landing stability. In addition, the back-and-forth flow of hydraulic oil can keep the movable shaft 502 stable during movement, preventing the drone from tilting or flipping at the moment of landing due to local uneven force, further ensuring the safety of the drone and its onboard equipment, and providing more stable technical support for the drone's reliable landing in complex working conditions.

[0028] In this application, the sealing assembly includes multiple sealing rings 506 and sealing rings 507. There is a positioning groove in the mounting tube 501, and a positioning tube 508 and a positioning ring 509 are arranged in the positioning groove. The arrangement of the positioning tube 508 and the positioning ring 509 limits the position of the movable shaft 502 so that it always moves in the vertical direction. The sealing ring 507 is arranged between the outer wall of the positioning tube 508 and the inner wall of the mounting tube 501; the sealing installation between the positioning tube 508 and the mounting tube 501 is achieved by the sealing ring 507.

[0029] The sealing ring 506 is arranged between the inner wall of the positioning cylinder 508 and the outer wall of the movable shaft 502 and between the inner wall of the positioning ring 509 and the outer wall of the movable shaft 502. The positioning cylinder 508 and the movable shaft 502 are sealed and connected by the arrangement of the sealing ring.

[0030] In the first stage of the present application, at the moment when the moving wheel 2 touches the ground, the elastic part (shrapnel 406) absorbs the initial impact energy through elastic deformation; in the second stage, the telescopic part 403 converts the remaining kinetic energy into hydraulic heat energy through controllable damping; in the third stage, through the cooperation of the second buffer component 5 and the rubber pad, the viscoelasticity of the rubber is utilized to further dissipate the vibration energy, and the action of the spring 503 and the hydraulic oil in the second buffer component 5 enables the hydraulic oil to convert the kinetic energy of the drone during landing into heat energy during the flow process, thereby dissipating a large amount of impact energy.

[0031] In a possible embodiment, the first buffer assembly 4 adopts a ball joint connection design, allowing an angular deflection of ±15°. When the single-sided moving wheel 2 encounters a bump, the fuselage can be kept level through angular adjustment to avoid torque concentration.

[0032] The foregoing has shown and described the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. The above embodiments and the descriptions in the specification are only preferred examples of the present invention and are not used to limit the present invention. Without departing from the spirit and scope of the present invention, the present invention will have various changes and improvements, and all these changes and improvements fall within the scope of the present invention claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. A shock-absorbing and protective structure for an unmanned aerial vehicle landing, comprising a mounting frame (1), and a moving wheel (2) is arranged at the bottom of the mounting frame (1), characterized in that: The mounting bracket (1) includes a first mounting strip (101), two second mounting strips (102) are connected to the first mounting strip (101), the second mounting strip (102) is perpendicular to the first mounting strip (101), a cavity is formed inside the first mounting strip (101), a rubber pad is arranged in the cavity, and the end of the second mounting strip (102) extends into the cavity and is connected to the rubber pad; A mounting shaft (3) is connected to the lower end of the second mounting strip (102), a first buffer assembly (4) is arranged between the moving wheel (2) and the mounting shaft (3), and a second buffer assembly (5) is arranged between both ends of the mounting shaft (3) and the first mounting strip (101).

2. The shock absorption and protection structure for the landing of an unmanned aerial vehicle according to claim 1, characterized in that: The first buffer assembly (4) includes a support frame (401), the upper end of the support frame (401) is rotatably connected to the mounting shaft (3), the lower end of the support frame (401) is rotatably connected to a connection seat (402), a telescopic member (403) is arranged inside the support frame (401), and the output shaft of the telescopic member (403) is rotatably connected to the connection seat (402).

3. The shock absorption and protection structure for the landing of an unmanned aerial vehicle according to claim 2, wherein: A first connection shaft (404) and a second connection shaft (405) are arranged at the lower end of the connection seat (402), an elastic member is arranged between the first connection shaft (404) and the second connection shaft (405), and the second connection shaft (405) is connected to the fixed shaft of the moving wheel (2).

4. The shock absorption and protection structure for a drone landing according to claim 3, characterized in that: The elastic member includes two relatively arranged elastic pieces (406), a housing (407) is arranged below the connection seat (402), the two elastic pieces (406) are installed in the housing (407), and the ends of the first connection shaft (404) and the second connection shaft (405) both extend into the housing (407) and are respectively in contact with the two elastic pieces (406).

5. The shock absorption and protection structure for the landing of an unmanned aerial vehicle according to claim 1, characterized in that: The telescopic member (403) is a gas spring telescopic rod.

6. The shock absorption and protection structure for the landing of an unmanned aerial vehicle according to claim 1, characterized in that: The second buffer assembly (5) includes a mounting cylinder (501), the mounting cylinder (501) is arranged inside the first mounting strip (101), a movable shaft (502) is slidably connected inside the mounting cylinder (501), the end of the movable shaft (502) extends out of the mounting cylinder (501) and is connected to the mounting shaft (3), and a spring (503) is sleeved on the inner end of the movable shaft (502) located inside the mounting cylinder (501); A sealing assembly is arranged inside the mounting cylinder (501), one side of the mounting cylinder (501) inside the sealing assembly is a hydraulic oil chamber (504), and the spring (503) is located in the hydraulic oil chamber (504).

7. The shock absorption and protection structure for an unmanned aerial vehicle landing according to claim 6, characterized in that: A piston (505) is sleeved on the part of the movable shaft (502) located in the hydraulic oil chamber (504), and there is a gap between the piston (505) and the inner wall of the hydraulic oil chamber (504).

8. The shock absorption and protection structure for an unmanned aerial vehicle landing according to claim 6, characterized in that: The sealing assembly includes a plurality of sealing rings (506) and sealing gaskets (507), a positioning groove is formed inside the mounting cylinder (501), a positioning cylinder (508) and a positioning ring (509) are arranged in the positioning groove, and the sealing gasket (507) is arranged between the outer wall of the positioning cylinder (508) and the inner wall of the mounting cylinder (501); The sealing ring (506) is arranged between the inner wall of the positioning cylinder (508) and the outer wall of the movable shaft (502), and between the inner wall of the positioning ring (509) and the outer wall of the movable shaft (502).

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