Complex terrain self-adaptive unmanned aerial vehicle undercarriage buffering and damping structure

Abstract

The utility model discloses a complex terrain self-adaptive unmanned aerial vehicle undercarriage buffering and damping structure, which belongs to the technical field of unmanned aerial vehicles, and is characterized by comprising an unmanned aerial vehicle body, and the bottom of the unmanned aerial vehicle body is movably connected with a split type elastic mounting mechanism; an elastic buffer mechanism is movably connected to the inner side of the split type elastic mounting mechanism, and an undercarriage body is movably connected to the bottom of the split type elastic mounting mechanism, so that the unmanned aerial vehicle undercarriage can be mounted more flexibly, and damage to an unmanned aerial vehicle can be reduced; the second mounting plate of the undercarriage is clamped on the first mounting plate of the unmanned aerial vehicle, the servo motor is started, the clamping plate clamps the second mounting plate, the undercarriage model suitable for the landing environment can be flexibly changed, an elastic contact structure is arranged at the connecting position, and the impact force generated when the undercarriage is grounded cannot be directly transmitted to the unmanned aerial vehicle; the problems that an undercarriage cannot be flexibly replaced in traditional integrated connection and the unmanned aerial vehicle is damaged due to rigid connection are solved.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a UAV landing gear buffer and shock absorption structure that is adaptive to complex terrain. Background Technology

[0002] The landing gear of a drone is a device used to support the weight of the drone and bear the corresponding load when the drone is parked on the ground or taking off. Different landing gears are installed on the bottom of the drone depending on the landing location, such as motor tracked landing gear, motor roller landing gear, landing support or airbag landing gear.

[0003] In existing technologies, traditional landing gear is often integrated with the UAV through bolting or welding. On the one hand, this makes it impossible to flexibly adjust the model of the landing gear located at the bottom of the UAV according to the flight operation. On the other hand, the integrated rigid connection means that when the landing gear contacts the ground, the large impact force generated will directly act on the landing gear and be transmitted to the UAV, causing damage to the UAV. Furthermore, there is no cushioning during the landing process, resulting in the UAV being subjected to large impact forces and easily damaged.

[0004] To address this, a shock-absorbing and damping structure for UAV landing gear that adapts to complex terrain is proposed. Utility Model Content

[0005] The purpose of this invention is to provide a drone landing gear buffer and shock absorption structure that is adaptive to complex terrain, which can solve the problems of impact damage caused by the rigid connection between the drone and the landing gear, as well as the problem of large impact force caused by the lack of buffering for landing gear landing.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a complex terrain adaptive unmanned aerial vehicle (UAV) landing gear buffer and shock absorption structure, including a UAV body, a split elastic mounting mechanism movably connected to the bottom of the UAV body, an elastic buffer mechanism movably connected to the inner side of the split elastic mounting mechanism, and a landing gear body movably connected to the bottom of the split elastic mounting mechanism.

[0007] The split-type flexible mounting mechanism includes a first mounting block fixedly connected to the bottom of the UAV body, a second mounting block fixedly connected to the top of the landing gear body, a first mounting plate at the bottom of the first mounting block, a second mounting plate at the top of the second mounting block, and flexible snap-fit ​​components movably connected to the outer sides of both the first and second mounting plates. The first and second mounting blocks are movably connected to the inner side of the flexible snap-fit ​​components. The flexible buffer mechanism is movably connected to the bottom of the first mounting plate and to the top of the second mounting plate.

[0008] Preferably, the elastic buffer mechanism includes a fixed support fixedly connected to the top of the second mounting plate, a movable support slidably connected to the inner side of the fixed support, and the movable support fixedly connected to the bottom of the first mounting plate.

[0009] Preferably, a first array of telescopic support columns is fixedly connected to the top of the inner side of the movable support, a buffer plate is fixedly connected to the bottom of the first array of telescopic support columns, a second array of telescopic support columns is fixedly connected to the bottom of the buffer plate, and a first compression spring is fixedly connected to the inner side of both the first array of telescopic support columns and the second array of telescopic support columns.

[0010] Preferably, a first telescopic pressure rod is rotatably connected to both sides of the buffer plate, the first telescopic pressure rod is rotatably connected to the top of the inner side of the movable support, a second telescopic pressure rod is rotatably connected to both sides of the buffer plate, the second telescopic pressure rod is rotatably connected to the bottom of the inner side of the fixed support, and a second compression spring is fixedly connected to the outer sides of both the first telescopic pressure rod and the second telescopic pressure rod.

[0011] Preferably, the elastic snap-fit ​​assembly includes a support plate fixedly connected to the rear side of the second mounting plate, a servo motor fixedly connected to the front side of the support plate, a rotating block fixedly connected to the output end of the servo motor, the rotating block being disposed on the rear side of the support plate, pull rods being connected to both sides of the rotating block, and a linkage rod being rotatably connected to the outer side of the pull rod, the linkage rod being slidably connected to both sides of the rear side of the support plate.

[0012] Preferably, a telescopic rod is fixedly connected to the front side of the linkage rod, a second fixing plate is fixedly connected to the bottom of the telescopic rod, the second fixing plate is slidably connected to both sides of the bottom of the second mounting plate, a first fixing plate is fixedly connected to the top of the telescopic rod, the first fixing plate is slidably connected to both sides of the top of the first mounting plate, telescopic columns are fixedly connected to the outer sides of both the first and second fixing plates, a third compression spring is fixedly connected to the inner side of the telescopic column, and a contact plate is fixedly connected to the corresponding side of the telescopic column.

[0013] Preferably, both sides of the first mounting plate and the second mounting plate are provided with snap-fit ​​grooves, and the contact plate snaps into the inside of the snap-fit ​​grooves.

[0014] Preferably, positioning slots are provided on the top of the first mounting plate and the bottom of the second mounting plate.

[0015] Compared with the prior art, the beneficial effects of this utility model are:

[0016] 1. This application, by setting a split flexible installation mechanism, allows for more flexible installation of UAV landing gear and reduces damage to the UAV. Previously, the landing gear and UAV were connected as one unit, making it impossible to replace different models of landing gear. Now, with the transition structure, which consists of a first mounting plate, movable support, etc., during installation, the second mounting plate of the landing gear is snapped onto the first mounting plate of the UAV. By activating the servo motor, the clamping plate is held in place, allowing for flexible replacement of landing gear models suitable for the landing environment. Moreover, the connection has a flexible contact structure. After the contact plate is inserted into the slot, the compression spring will contract and buffer, so the impact force of the landing gear touching the ground will not be directly transmitted to the UAV. This solves the problems of traditional integrated connections that cannot flexibly replace landing gear and rigid connections that cause damage to the UAV.

[0017] 2. This application incorporates an elastic buffer mechanism to cushion the drone's landing process, reducing impact damage. Previously, the landing gear lacked cushioning, making drones susceptible to damage from impacts. Now, by setting up a movable structure with a fixed support and a movable support, during landing, the drone's inertia presses down on the first mounting plate. The movable support slides inward towards the fixed support, displacing the buffer plate inside the fixed support. This presses against the top and bottom telescopic struts and the first compression spring inside, accumulating elastic potential energy—this is vertical cushioning. Simultaneously, the first and second telescopic struts on both sides of the buffer plate, along with the second compression spring on their outer sides, contract. Because they are at the same rotation point, they form an oblique shear buffer. After accumulating potential energy, the first and second compression springs push back, reducing and neutralizing the impact force. This converts the descent impact force into multi-directional mechanical work and elastic potential energy, solving the problem of drones being easily damaged due to the lack of cushioning. Attached Figure Description

[0018] Figure 1 This is an overall structural diagram of the complex terrain adaptive UAV landing gear buffer and shock absorption structure of this utility model;

[0019] Figure 2 This is a disassembled overall structural diagram of the UAV landing gear buffer and shock absorption structure that adapts to complex terrain according to this utility model.

[0020] Figure 3 This is an overall structural diagram of the split-type elastic mounting mechanism of this utility model;

[0021] Figure 4 This is an overall structural diagram of the elastic snap-fit ​​assembly of this utility model;

[0022] Figure 5 This is an overall structural diagram of the elastic buffer mechanism of this utility model.

[0023] In the diagram, 1. UAV body; 2. Split-type elastic mounting mechanism; 21. First mounting block; 22. Second mounting block; 23. First mounting plate; 24. Second mounting plate; 25. Elastic snap-fit ​​assembly; 25a. Support plate; 25b. Servo motor; 25c. Rotating block; 25d. Pull rod; 25e. Linkage rod; 25f. Telescopic rod cylinder; 25g. Second fixed clamping plate; 25h. First fixed clamping plate; 25i. Telescopic column; 25j. Third compression spring; 25k. Contact clamping plate; 3. Elastic buffer mechanism; 31. Fixed support; 32. Movable support; 33. First array telescopic support column; 34. Buffer plate; 35. Second array telescopic support column; 36. First compression spring; 37. First telescopic pressure rod; 38. Second telescopic pressure rod; 39. Second compression spring; 4. Landing gear body; 5. Snap-fit ​​groove; 6. Positioning slot. Detailed Implementation

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

[0025] Please see Figure 1-5 The present invention provides the following technical solution:

[0026] A complex terrain adaptive unmanned aerial vehicle (UAV) landing gear buffer and shock absorption structure includes a UAV body 1, a split elastic mounting mechanism 2 movably connected to the bottom of the UAV body 1, an elastic buffer mechanism 3 movably connected to the inner side of the split elastic mounting mechanism 2, and a landing gear body 4 movably connected to the bottom of the split elastic mounting mechanism 2.

[0027] The split-type flexible mounting mechanism 2 includes a first mounting block 21 fixedly connected to the bottom of the UAV body 1, a second mounting block 22 fixedly connected to the top of the landing gear body 4, a first mounting plate 23 provided at the bottom of the first mounting block 21, a second mounting plate 24 provided at the top of the second mounting block 22, and flexible snap-fit ​​components 25 movably connected to the outer sides of both the first mounting plate 23 and the second mounting plate 24. The first mounting block 21 and the second mounting block 22 are movably connected to the inner side of the flexible snap-fit ​​components 25. An elastic buffer mechanism 3 is movably connected to the bottom of the first mounting plate 23 and to the top of the second mounting plate 24.

[0028] In this embodiment: When the drone lands via the landing gear body 4, due to descent inertia, the drone will press down on the first mounting plate 23. Because the fixed support 31 and the movable support 32 connecting the first mounting plate 23 and the second mounting plate 24 are movable structures, and the telescopic cylinder 25f is a telescopic structure, the movable support 32 at the bottom of the first mounting plate 23 will slide inward toward the fixed support 31. When sliding, the first mounting plate 23 presses down, causing the movable support 32 to slide inward toward the fixed support 31, reducing the distance between the movable support 32 and the interior of the fixed support 31. This causes the buffer plate 34 inside the fixed support 31 to shift. When the buffer plate 34 shifts, its top and bottom will respectively press against the movable support. The first array telescopic support column 33 and the second array telescopic support column 35, which are connected inside the fixed support 31 and the 32, will also have their first compression springs 36 compressed, thereby accumulating elastic potential energy and playing a vertical array buffering role. At the same time, when the buffer plate 34 moves downward, the first telescopic pressure rod 37, which is rotatably connected to the inner wall of the movable support 32 on both sides, and the second telescopic pressure rod 38, which is rotatably connected to the inner wall of the fixed support 31, will retract. The second compression springs 39 on the outer sides of the first telescopic pressure rod 37 and the second telescopic pressure rod 38 will also retract. Because the first telescopic pressure rod 37 and the second telescopic pressure rod 38 are at the same rotation point on both sides of the buffer plate 34, a shear-like oblique buffer will be formed.

[0029] Finally, after the first compression spring 36 and the second compression spring 39 have accumulated elastic potential energy, they will push back to reduce and neutralize the impact force, preventing too much impact force from being transmitted to the UAV body 1, and converting the impact force during descent into mechanical work in multiple directions and various elastic potential energies.

[0030] Specifically, such as Figure 1 , Figure 2 , Figure 5 As shown, the elastic buffer mechanism 3 includes a fixed support 31 fixedly connected to the top of the second mounting plate 24, and a movable support 32 slidably connected to the inner side of the fixed support 31. The movable support 32 is fixedly connected to the bottom of the first mounting plate 23.

[0031] Specifically, such as Figure 1 , Figure 2 , Figure 5 As shown, a first array telescopic support column 33 is fixedly connected to the top of the inner side of the movable support 32, a buffer plate 34 is fixedly connected to the bottom of the first array telescopic support column 33, a second array telescopic support column 35 is fixedly connected to the bottom of the buffer plate 34, and a first compression spring 36 is fixedly connected to the inner side of both the first array telescopic support column 33 and the second array telescopic support column 35.

[0032] Specifically, such as Figure 1 , Figure 2 , Figure 5As shown, a first telescopic pressure rod 37 is rotatably connected to both sides of the buffer plate 34. The first telescopic pressure rod 37 is rotatably connected to the top of the inner side of the movable support 32. A second telescopic pressure rod 38 is rotatably connected to both sides of the buffer plate 34. The second telescopic pressure rod 38 is rotatably connected to the bottom of the inner side of the fixed support 31. A second compression spring 39 is fixedly connected to the outer sides of both the first telescopic pressure rod 37 and the second telescopic pressure rod 38.

[0033] In this embodiment: When the UAV body 1 lands via the landing gear body 4, different types of landing gear bodies 4, such as motor-tracked landing gear, motor-roller landing gear, landing brackets, or airbag landing gear, are typically installed on the UAV body 1 depending on the landing location. However, these landing gear bodies 4 were usually connected to the UAV body 1 in an integrated manner by bolting or welding. This not only prevented the flexible replacement of the landing gear body 4 model at the bottom of the UAV body 1 according to the flight operation, but also caused the large impact force generated when the landing gear body 4 contacts the ground to act directly on the landing gear body 4 and be transmitted to the UAV body 1, causing damage to the UAV body 1. Now, the integrated structure is no longer used. Instead, a system consisting of a first mounting plate 23, a movable support 32, a fixed support 31, and a second mounting plate 24 is used. The transition structure is formed by installing the UAV body 1 and the landing gear body 4 respectively. The specific operation is as follows: Before the flight operation, the corresponding landing gear body 4 is selected according to the landing environment. The positioning slot 6 at the bottom of the second mounting plate 24 is snapped into the protruding position at the top of the second mounting block 22 at the top of the landing gear body 4. Then, the UAV body 1 is taken out, and the protruding position at the bottom of the first mounting block 21 at the bottom of the UAV body 1 is snapped into the positioning slot 6 at the top of the first mounting plate 23 to complete the initial positioning. Then, the UAV body 1 and the landing gear body 4 are elastically snapped together by the elastic snap-fit ​​component 25 to form a non-rigid connection elastic snap-fit ​​state. In this way, when the landing gear body 4 lands directly, the impact force on the landing gear body 4 can be elastically buffered at the connection with the UAV body 1, avoiding fatigue damage or even breakage caused by rigid connection.

[0034] Specifically, such as Figure 3 , Figure 4 As shown, the elastic snap-fit ​​assembly 25 includes a support plate 25a fixedly connected to the rear side of the second mounting plate 24. A servo motor 25b is fixedly connected to the front side of the support plate 25a. A rotating block 25c is fixedly connected to the output end of the servo motor 25b. The rotating block 25c is located on the rear side of the support plate 25a. Pull rods 25d are connected to both sides of the rotating block 25c. A linkage rod 25e is rotatably connected to the outer side of the pull rod 25d. The linkage rod 25e is slidably connected to both sides of the rear side of the support plate 25a.

[0035] Specifically, such as Figure 3 , Figure 4As shown, a telescopic rod cylinder 25f is fixedly connected to the front side of the linkage rod 25e. A second fixed clamping plate 25g is fixedly connected to the bottom of the telescopic rod cylinder 25f. The second fixed clamping plate 25g is slidably connected to both sides of the bottom of the second mounting plate 24. A first fixed clamping plate 25h is fixedly connected to the top of the telescopic rod cylinder 25f. The first fixed clamping plate 25h is slidably connected to both sides of the top of the first mounting plate 23. Telescopic columns 25i are fixedly connected to the inner sides of both the first fixed clamping plate 25h and the second fixed clamping plate 25g. A third compression spring 25j is fixedly connected to the inner side of the telescopic column 25i. A contact plate 25k is fixedly connected to the corresponding side of the telescopic column 25i.

[0036] In this embodiment: by activating the servo motor 25b on the front side of the support plate 25a, the rotating block 25c at the motor output end rotates accordingly. When the rotating block 25c rotates, the pull rods 25d connected to both sides rotate as well. The linkage rods 25e connected to the other end of the pull rods 25d are pulled, causing the linkage rods 25e on both sides to slide inwards along the rear side of the support plate 25a simultaneously. The front side of the linkage rods 25e is fixedly connected to the telescopic cylinders 25f. These telescopic cylinders 25f respectively support the first fixed clamping plate 25h of the clamping structure at the top of the first mounting plate 23 and the second fixed clamping plate 25g of the clamping structure at the bottom of the second mounting plate 24. When the linkage rods 25e slide inwards simultaneously, they will pull the telescopic cylinders 25f on both sides to move inwards at the same time, thereby driving the first fixed clamping plate 25h at the top and the second fixed clamping plate 25g at the bottom of the telescopic cylinders 25f to slide inwards towards the inner side of the first mounting plate 23 and the inner side of the second mounting plate 24 respectively, so that they slide from both sides towards the first mounting block 21 and the second mounting block 24. 2. On the inner sides of the first fixed clamping plate 25h and the second fixed clamping plate 25g, there are elastic contact structures. The structure consists of a telescopic column 25i and the third compression spring 25j on its inner side as elastic elements, and a contact plate 25k on the outer side of the telescopic column 25i. When the first fixed clamping plate 25h and the second fixed clamping plate 25g on both sides slide inward at the same time, the contact plates 25k on both sides of the first mounting block 21 and the second mounting block 22 will move closer to the sides of the two mounting blocks at the same time and insert into the snap-fit ​​grooves 5 on both sides. After snap-fitting, under the continued linkage of the first fixed clamping plate 25h and the second fixed clamping plate 25g, the telescopic column 25i between the contact plate 25k and the first fixed clamping plate 25h and the second fixed clamping plate 25g will retract accordingly, pressing the third compression spring 25j on the inner side of the telescopic column 25i. In this way, the UAV body 1 and the landing gear body 4 achieve elastic snap-fitting installation and form a non-rigid connection elastic snap-fitting state.

[0037] Specifically, such as Figure 2 As shown, both sides of the first mounting plate 23 and the second mounting plate 24 are provided with snap-fit ​​grooves 5, and the contact plate 25k is snapped into the inside of the snap-fit ​​grooves 5.

[0038] Specifically, such as Figure 2 As shown, positioning slots 6 are provided on the top of the first mounting plate 23 and the bottom of the second mounting plate 24.

[0039] In this embodiment: the snap-fit ​​slot 5 facilitates the insertion of the contact plate 25k, further increasing installation stability, and the positioning slot 6 allows for initial positioning of the UAV body 1 and landing gear body 4 before fixing.

[0040] Working principle: When the UAV body 1 lands via the landing gear body 4, different landing gear bodies 4 are installed on the UAV body 1 depending on the landing location, such as motor-driven tracked landing gear, motor-driven roller landing gear, landing arms, or airbag landing gear. However, these landing gear bodies 4 are often integrated with the UAV body 1 through bolting or welding. On the one hand, this makes it impossible to flexibly adjust the model of the landing gear body 4 located at the bottom of the UAV body 1 according to the flight operation. On the other hand, the integrated rigid connection means that when the landing gear body 4 contacts the ground, the large impact force generated will directly act on the landing gear body 4 and be transmitted to the UAV body 1, causing damage to the UAV body 1. Therefore, the integrated structure is no longer used. The UAV body 1 and landing gear body 4 are installed separately through a transition structure consisting of a first mounting plate 23, a movable support 32, a fixed support 31, and a second mounting plate 24. Before flight operations, the corresponding landing gear body 4 is selected according to the landing environment. The positioning slot 6 at the bottom of the second mounting plate 24 is engaged with the protruding position at the top of the second mounting block 22 on the top of the landing gear body 4. Then, the UAV body 1 is taken out, and the protruding position at the bottom of the first mounting block 21 at the bottom of the UAV body 1 is engaged with the positioning slot 6 at the top of the first mounting plate 23 to form a primary positioning. Then, the servo motor 25b located in front of the support plate 25a is started, causing the rotating block 25c located at the output end of the servo motor 25b to rotate. When the device moves, the pull rods 25d, which are rotatably connected on both sides, will rotate accordingly. During the rotation, the pull rods 25d will pull the linkage rods 25e, which are rotatably connected at their other ends, to move inwards simultaneously along the rear side of the support plate 25a. Telescopic cylinders 25f are fixedly connected to the front side of the linkage rods 25e, supporting the first fixed clamping plate 25h of the top clamping structure of the first mounting plate 23 and the second fixed clamping plate 25g of the bottom clamping structure of the second mounting plate 24. When the linkage rods 25e move inwards simultaneously, they will pull the telescopic cylinders 25f inwards simultaneously, and the first fixed clamping plate 25h at the top and the second fixed clamping plate 25g at the bottom of the telescopic cylinders 25f will move inwards simultaneously along the first mounting plate 23. The first mounting plate 25h and the second mounting plate 24 slide on the inner side of the first mounting plate 25h and the second mounting plate 24, thereby moving closer to the first mounting block 21 and the second mounting block 22 from both sides. During the approach process, the inner sides of the first fixing plate 25h and the second fixing plate 25g are provided with elastic elements composed of telescopic columns 25i and their inner third compression springs 25j, and contact plates 25k on the outer side of the telescopic columns 25i. When the first fixing plates 25h and the second fixing plates 25g on both sides move inward at the same time, the contact plates 25k on both sides of the first mounting block 21 and the second mounting block 22 will move closer to both sides of the first mounting block 21 and the second mounting block 22 at the same time, and insert into the inner side of the snap-fit ​​grooves 5 on both sides of the first mounting block 21 and the second mounting block 22. After snap-fit,Under the continued linkage of the first fixed clamping plate 25h and the second fixed clamping plate 25g, the telescopic column 25i between the contact plate 25k and the first fixed clamping plate 25h and the second fixed clamping plate 25g will retract and press the third compression spring 25j on the inner side of the telescopic column 25i, thereby realizing the elastic snap-fit ​​installation of the UAV body 1 and the landing gear body 4, and forming a non-rigid connection elastic snap-fit ​​state. Thus, when the landing gear body 4 lands directly, the impact force on the landing gear body 4 can be elastically buffered at the connection between the landing gear body 4 and the UAV body 1, avoiding rigid connection. The problem of fatigue damage caused by the connection, leading to fracture, and the fixed support 31 and movable support 32 connecting the first mounting plate 23 and the second mounting plate 24 are movable structures, and the telescopic cylinder 25f is a telescopic structure. To accommodate the above movable structure, when the landing gear body 4 lands, due to the descent inertia, the UAV body 1 will press down on the first mounting plate 23, causing the movable support 32 at the bottom of the first mounting plate 23 to slide inward toward the fixed support 31. During the sliding process, the following transmission path is formed, that is, the first mounting plate 23 presses down, driving the movable support 32 toward the fixed support 31. 1. Internal sliding reduces the distance between the movable support 32 and the fixed support 31, causing the buffer plate 34 inside the fixed support 31 to shift. This causes the top and bottom of the buffer plate 34 to press against the first array telescopic support column 33 and the second array telescopic support column 35 connected to the movable support 32 and the fixed support 31, respectively, and the first compression spring 36 inside them, accumulating elastic potential energy. For vertical array buffering, during the downward displacement of the buffer plate 34, the first telescopic pressure rod 37 rotatably connected to the inner wall of the movable support 32 on both sides and the first telescopic pressure rod 37 connected to the fixed support 31 on both sides... The second telescopic pressure rod 38, rotatably connected to the inner wall, and the second pressure spring 39 on its outer side retract respectively. The first telescopic pressure rod 37 and the second telescopic pressure rod 38 are located at the same rotation point on both sides of the buffer plate 34, thus forming a shear-like oblique shear buffer. In summary, after the first pressure spring 36 and the second pressure spring 39 accumulate elastic potential energy, the impact force is reduced and neutralized during the pushback, preventing a large impact force from being transmitted to the UAV body 1. The descent impact force is converted into multi-directional mechanical work and various elastic potential energies, thereby achieving buffering for the landing of the UAV body 1, which adapts to complex terrain.

[0041] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A complex terrain-adaptive unmanned aerial vehicle (UAV) landing gear shock absorption structure, comprising the UAV body (1), characterized in that: The bottom of the UAV body (1) is movably connected to a split elastic mounting mechanism (2), the inner side of the split elastic mounting mechanism (2) is movably connected to an elastic buffer mechanism (3), and the bottom of the split elastic mounting mechanism (2) is movably connected to a landing gear body (4). The split-type elastic mounting mechanism (2) includes a first mounting block (21) fixedly connected to the bottom of the UAV body (1), a second mounting block (22) fixedly connected to the top of the landing gear body (4), a first mounting plate (23) provided at the bottom of the first mounting block (21), a second mounting plate (24) provided at the top of the second mounting block (22), an elastic snap-fit ​​assembly (25) movably connected to the outer sides of the first mounting plate (23) and the second mounting plate (24), the first mounting block (21) and the second mounting block (22) movably connected to the inner side of the elastic snap-fit ​​assembly (25), the elastic buffer mechanism (3) movably connected to the bottom of the first mounting plate (23), and the elastic buffer mechanism (3) movably connected to the top of the second mounting plate (24).

2. The adaptive unmanned aerial vehicle landing gear shock absorption structure for complex terrain as described in claim 1, characterized in that: The elastic buffer mechanism (3) includes a fixed support (31) fixedly connected to the top of the second mounting plate (24), and a movable support (32) slidably connected to the inner side of the fixed support (31). The movable support (32) is fixedly connected to the bottom of the first mounting plate (23).

3. The complex terrain adaptive UAV landing gear shock absorption structure according to claim 2, characterized in that: The top of the inner side of the movable support (32) is fixedly connected to a first array telescopic support column (33), the bottom of the first array telescopic support column (33) is fixedly connected to a buffer plate (34), the bottom of the buffer plate (34) is fixedly connected to a second array telescopic support column (35), and the inner sides of the first array telescopic support column (33) and the second array telescopic support column (35) are both fixedly connected to a first compression spring (36).

4. The complex terrain adaptive UAV landing gear shock absorption structure according to claim 3, characterized in that: Both sides of the buffer plate (34) are rotatably connected to a first telescopic pressure rod (37), which is rotatably connected to the top of the inner side of the movable support (32). Both sides of the buffer plate (34) are rotatably connected to a second telescopic pressure rod (38), which is rotatably connected to the bottom of the inner side of the fixed support (31). Both the outer sides of the first telescopic pressure rod (37) and the second telescopic pressure rod (38) are fixedly connected to a second compression spring (39).

5. The complex terrain adaptive UAV landing gear shock absorption structure according to claim 1, characterized in that: The elastic snap-fit ​​assembly (25) includes a support plate (25a) fixedly connected to the rear side of the second mounting plate (24). A servo motor (25b) is fixedly connected to the front side of the support plate (25a). A rotating block (25c) is fixedly connected to the output end of the servo motor (25b). The rotating block (25c) is located on the rear side of the support plate (25a). Pull rods (25d) are connected to both sides of the rotating block (25c). A linkage rod (25e) is rotatably connected to the outer side of the pull rod (25d). The linkage rod (25e) is slidably connected to both sides of the rear side of the support plate (25a).

6. The complex terrain adaptive UAV landing gear shock absorption structure according to claim 5, characterized in that: The front side of the linkage rod (25e) is fixedly connected to a telescopic rod cylinder (25f), the bottom of the telescopic rod cylinder (25f) is fixedly connected to a second fixed clamping plate (25g), the second fixed clamping plate (25g) is slidably connected to both sides of the bottom of the second mounting plate (24), the top of the telescopic rod cylinder (25f) is fixedly connected to a first fixed clamping plate (25h), the first fixed clamping plate (25h) is slidably connected to both sides of the top of the first mounting plate (23), the outer sides of the first fixed clamping plate (25h) and the second fixed clamping plate (25g) are both fixedly connected to telescopic columns (25i), the inner side of the telescopic column (25i) is fixedly connected to a third compression spring (25j), and the corresponding side of the telescopic column (25i) is fixedly connected to a contact plate (25k).

7. The adaptive unmanned aerial vehicle landing gear shock absorption structure for complex terrain as described in claim 6, characterized in that: Both sides of the first mounting plate (23) and the second mounting plate (24) are provided with snap-fit ​​grooves (5), and the contact plate (25k) is snapped into the inside of the snap-fit ​​groove (5).

8. The adaptive unmanned aerial vehicle landing gear shock absorption structure for complex terrain as described in claim 1, characterized in that: Positioning slots (6) are provided on the top of the first mounting plate (23) and the bottom of the second mounting plate (24).

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