Unmanned aerial vehicle gap elimination and shock absorption structure and unmanned aerial vehicle

Abstract

The application discloses a UAV (unmanned aerial vehicle) gap-eliminating and shock-reducing structure and relates to the technical field of UAVs. The UAV gap-eliminating and shock-reducing structure comprises an upper shell, a lower shell, a cavity formed by the connection of the upper shell and the lower shell, a first clamping strip extending upward from the inner wall of the bottom end of the lower shell, a plurality of first reinforcing ribs arranged between the first clamping strip and the frame of the lower shell, a fixed cavity with an open upper end formed between the first clamping strip, the adjacent two first reinforcing ribs and the frame of the lower shell, a plurality of clamping keys arranged in the upper shell, the clamping keys being arranged along the frame of the upper shell, and a clamping gap formed between the adjacent clamping keys. When the upper shell and the lower shell are matched, the clamping keys are clamped in the fixed cavity, and the first reinforcing ribs are clamped in the clamping gap. The clamping strip and the reinforcing ribs are arranged to form the fixed cavity, and the clamping keys are matched, and the clamping gap and the reinforcing ribs are engaged, so that the torsional misalignment problem between the upper and lower shells during the matching of the UAV is solved, and the stress distribution in the UAV is more balanced.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle gap-eliminating and shock-reducing structure and unmanned aerial vehicle. BACKGROUND

[0002] In recent years, with the rise of unmanned aerial vehicles and the rapid development of related model aircraft and unmanned aerial vehicle technologies, unmanned aerial vehicles are increasingly applied in more and more occasions. In this process, more and more people have begun to touch unmanned aerial vehicles, and unmanned aerial vehicles have thus entered the civilian entertainment field, i.e. consumer-level unmanned aerial vehicles, from the professional and scientific research fields.

[0003] The housing of an unmanned aerial vehicle is generally a sealed mechanism, and the unmanned aerial vehicle circuit board for controlling the flight of the unmanned aerial vehicle is generally sealed and fixed inside the frame of the unmanned aerial vehicle. In order to facilitate production, existing consumer-level unmanned aerial vehicles generally adopt a plastic mold opening mode to quickly form the unmanned aerial vehicle shell. Since the upper and lower shells of the unmanned aerial vehicle are directly fixed by screws, the opening between the upper and lower shells of the unmanned aerial vehicle is large, which causes problems such as poor waterproof performance of the unmanned aerial vehicle, easy short circuit of the internal circuit, and poor torsional rigidity of the unmanned aerial vehicle. Moreover, the force receiving parts of the shell structure are plastic products, and the plastic has the characteristics of high toughness and poor rigidity, which is contrary to the high rigidity pursued by the design of the unmanned aerial vehicle shell structure. The insufficient rigidity of the unmanned aerial vehicle shell causes the overall resonance frequency of the unmanned aerial vehicle body to decrease, which causes resonance problems to occur under the rotation of the propeller and makes the flight control sensor unable to enter a fixed solution, resulting in loss of control of the unmanned aerial vehicle and even coupling phenomenon, which seriously affects the performance and safety of the entire machine.

[0004] In existing technologies, the upper and lower shells are connected by a buckle to solve the problems of large opening and poor torsional rigidity. The principle of the buckle connection is that after the buckle 11 on the upper shell body frame is buckled with the buckle groove 12 on the lower shell body frame to form an integrated whole, the upper and lower shells are connected by the buckle. Figure 1 When the upper and lower shells are twisted and misaligned, the misalignment between the upper and lower shell bodies is forcibly limited by the buckle due to the constraint between the buckle 11 and the buckle groove 12, so that the misalignment cannot continue. However, this structure has poor load resistance. Since the contact surface of the buckle is too small and the structural strength of the buckle part is weak, when the torsional force of the shell exceeds a certain degree, the buckle of the upper and lower shells will not be able to bear this load, causing the buckle to come off or the structure to be irreparably damaged.

[0005] Some existing consumer-level unmanned aerial vehicles solve the above problems by arranging a large number of complex reinforcing ribs inside the shell, which causes difficulties in reducing the weight of the aircraft, complex design, high cost, and poor effect. Some solve the problem by changing the high-strength plastic material, but this causes the structure of the aircraft to be heavy, the rigidity to be limited, and the mold cost to be increased. Some solve the problem by ultrasonic welding to weld the shell into an integrated whole to improve the torsional resistance of the aircraft, but this causes subsequent aircraft maintenance to be extremely difficult.

[0006] Therefore, how to solve the problem of torsional misalignment between the upper and lower shells of the unmanned aerial vehicle, improve the torsional resistance, make the internal stress of the unmanned aerial vehicle more balanced, reduce the deformation misalignment of the shell under stress, avoid the low-frequency resonance problem caused by the rotation of the propeller, increase the resonance interval to the rotation speed interval of the propeller, simplify the design of the structure, reduce the cost, and facilitate the production and maintenance in the later stage, are the key points of the unmanned aerial vehicle product to attract consumers. SUMMARY

[0007] The purpose of the present application is to solve the above-mentioned problems existing in the existing packaging box, and to provide an unmanned aerial vehicle gap elimination and shock reduction structure and an unmanned aerial vehicle with simple structure, strong torsional resistance, balanced internal stress, prevention of torsional deformation of the arm, and improved natural resonance frequency of the unmanned aerial vehicle body.

[0008] In order to solve the above technical problems, the present application is realized by the following technical scheme:

[0009] An unmanned aerial vehicle gap elimination and shock reduction structure, comprising an upper shell and a lower shell, the upper shell and the lower shell being connected to form a hollow cavity, the side of the upper shell forming an upper shell frame, and the side of the lower shell forming a lower shell frame.

[0010] A first clamping strip is upwardly extended from the inner wall of the bottom end of the lower shell, the first clamping strip is arranged along the lower shell frame, and a plurality of first reinforcing ribs are arranged between the first clamping strip and the lower shell frame.

[0011] A plurality of clamping keys are arranged in the upper shell, the clamping keys are arranged in sequence along the upper shell frame, and a clamping gap is formed between adjacent clamping keys; when the upper shell and the lower shell are matched, the clamping keys are clamped in the fixed cavity, and the first reinforcing ribs are clamped in the clamping gap.

[0012] Preferably, a connecting plate is arranged between adjacent clamping keys, a slot is arranged on the connecting plate, and the first reinforcing rib is clamped in the slot.

[0013] Preferably, the clamping key is a clamping frame, the clamping frame comprises a second clamping strip and positioning ribs arranged at both ends of the second clamping strip, and the positioning ribs are arranged towards the upper shell frame.

[0014] Preferably, the clamping frame extends beyond the edge of the upper shell frame, and the second clamping strip, the positioning ribs and the upper shell frame are an integral structure.

[0015] Preferably, the edge of the lower shell frame extends upward with a protrusion, the protrusion extends along the edge of the lower shell frame; the edge of the upper shell frame is provided with a downward opening, the opening extends along the edge of the upper shell frame; when the upper shell and the lower shell are matched, the protrusion is matched with the opening.

[0016] Preferably, the edge of the lower shell frame extends upward with a protrusion on one side of the inner wall, and the edge of the upper shell frame is provided with a downward opening on one side of the inner wall.

[0017] Preferably, the protrusion is in the shape of a trapezoid, a semicircle or a rectangle, and the opening is matched with the protrusion.

[0018] Preferably, the first reinforcing rib is in interference fit with the notch.

[0019] Preferably, the first reinforcing rib is arranged vertically to the lower shell frame, the first clamping strip is arranged parallel to the lower shell frame, and the positioning rib is arranged vertically to the upper shell frame.

[0020] Preferably, the length of the positioning rib is equal to the distance between the first clamping strip and the lower shell frame.

[0021] Preferably, a second reinforcing rib is further arranged between the lower shell frame and the first clamping strip, and the second reinforcing rib is arranged obliquely relative to the first reinforcing rib.

[0022] A UAV, comprising a fuselage, a plurality of arms, the plurality of arms being fixedly connected to the fuselage, the plurality of arms being arranged radially outward from the fuselage, and the UAV gap-eliminating and shock-reducing structure as described above being arranged in the arms.

[0023] Compared with the prior art, the UAV gap-eliminating and shock-reducing structure has the advantages that: the structure is simplified, the clamping strip, the reinforcing rib and the fixed cavity are arranged, and the clamping key is matched, the clamping gap and the reinforcing rib are engaged, the upper shell and the lower shell are tightly matched, the torsional misalignment between the upper shell and the lower shell is solved without increasing the weight of the shell, the torsional resistance of the structure is strong, the stress distribution in the UAV is more balanced, the deformation and misalignment of the shell under stress are reduced, the UAV is provided with the UAV gap-eliminating and shock-reducing structure, the low-frequency resonance problem of the UAV caused by the rotation of the propeller is avoided without changing the original material, the resonance interval is increased to above the rotation speed interval of the propeller, the torsional deformation of the arm is prevented, the cost is low, the structure is easy to disassemble, the waterproof performance is good, the production and maintenance in the later period are facilitated, and the use experience of consumers is improved. BRIEF DESCRIPTION OF DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description only show some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings shown without any creative effort.

[0025] Figure 1 is a structural diagram of a prior art unmanned aerial vehicle gap elimination and shock reduction structure in an embodiment of the present application;

[0026] Figure 2 is a structural diagram of a unmanned aerial vehicle gap elimination and shock reduction structure in an embodiment of the present application;

[0027] Figure 3 is another perspective view of a unmanned aerial vehicle gap elimination and shock reduction structure in an embodiment of the present application;

[0028] Figure 4 is a structural diagram of an upper shell of a unmanned aerial vehicle gap elimination and shock reduction structure in an embodiment of the present application;

[0029] Figure 5 is a structural diagram of a lower shell of a unmanned aerial vehicle gap elimination and shock reduction structure in an embodiment of the present application;

[0030] Figure 6 is a structural diagram of an assembly of the upper shell and the lower shell of a unmanned aerial vehicle gap elimination and shock reduction structure in an embodiment of the present application;

[0031] Figure 7 is another perspective view of an assembly of the upper shell and the lower shell of a unmanned aerial vehicle gap elimination and shock reduction structure in an embodiment of the present application;

[0032] Figure 8 is a structural diagram of an upper shell of a unmanned aerial vehicle in an embodiment of the present application,

[0033] Figure 9 is Figure 8 a partial enlarged view of part A in FIG. 7;

[0034] Figure 10 is a structural diagram of a lower shell of a unmanned aerial vehicle in an embodiment of the present application,

[0035] Figure 11 is Figure 10 a partial enlarged view of part B in FIG. 8;

[0036] Figure 12 is a structural diagram of a unmanned aerial vehicle in an embodiment of the present application;

[0037] Figure 13 is a left view of a unmanned aerial vehicle in an embodiment of the present application;

[0038] Figure 14 is Figure 13 is a sectional view in A-A direction in the middle of the figure;

[0039] Figure 15 is Figure 14 is a partial enlarged view of part C in the middle of the figure;

[0040] In the figure: 10 is the upper shell frame, 11 is the buckle, 12 is the positioning rib, 13 is the opening, 14 is the card gap, 15 is the connecting plate, 17 is the second clamping strip, 20 is the lower shell frame, 21 is the buckle groove, 22 is the first reinforcing rib, 23 is the protrusion, 24 is the first clamping strip, 25 is the second reinforcing rib, 26 is the third reinforcing rib, and 30 is the robot arm. DETAILED DESCRIPTION

[0041] In order to make the above-mentioned purposes, features and advantages of the present application more obvious and easy to understand, the present application will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0042] In the description of the present application, it should be understood that the terms "intermediate", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. The terms "first", "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features limited by "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "a plurality of" is two or more, unless otherwise explicitly specified and limited.

[0043] In addition, unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection", "fixing" and the like should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0044] In the present application, unless specifically and expressly defined otherwise, "on" or "under" of a first feature to a second feature can include that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, "on", "above" and "over" of a first feature to a second feature includes that the first feature is directly above and obliquely above the second feature, or only indicates that the first feature is higher than the second feature in horizontal height. "Under", "below" and "under" of a first feature to a second feature includes that the first feature is directly below and obliquely below the second feature, or only indicates that the first feature is lower than the second feature in horizontal height.

[0045] Embodiment 1:

[0046] Reference Figures 1-5 A UAV anti-gap shock-absorbing structure includes an upper shell and a lower shell, the upper shell and the lower shell are connected to form a hollow cavity, the side of the upper shell forms an upper shell frame 10, and the side of the lower shell forms a lower shell frame 20; the inner wall of the bottom end of the lower shell extends upward to have a first clamping strip 24, the first clamping strip 24 is arranged along the lower shell frame 20, a plurality of first reinforcing ribs 22 are arranged between the first clamping strip 24 and the lower shell frame 20, a fixing cavity with an open upper end 13 is formed between the first clamping strip 24, the adjacent two first reinforcing ribs 22 and the lower shell frame 20; a plurality of clamping keys are arranged in the upper shell, the plurality of clamping keys are arranged in sequence along the upper shell frame 10, and a clamping gap 14 is formed between adjacent clamping keys; when the upper shell and the lower shell are matched, the clamping keys are clamped in the fixing cavity, and the first reinforcing ribs 22 are clamped in the clamping gap 14.

[0047] Specifically, the anti-gap shock-absorbing structure of the unmanned aerial vehicle comprises an upper shell and a lower shell. In the embodiment, the upper shell refers to the upper half of the unmanned aerial vehicle when it is placed vertically, and the lower shell refers to the lower half of the unmanned aerial vehicle when it is placed vertically. The upper shell and the lower shell are connected to form a relatively closed hollow cavity. The flight control system and the processor of the unmanned aerial vehicle are installed in the cavity. The cooperation of the upper shell and the lower shell can protect the functional components from the invasion of rain, dust and other impurities. The inner wall of the bottom end of the lower shell extends upward to have a first clamping strip 24. The first clamping strip 24 is higher than the lower shell frame 20. In a specific embodiment, the first clamping strip 24 is arranged parallel to the lower shell frame 20. The first clamping strip 24 surrounds the lower shell frame 20 for one turn. A first reinforcing rib 22 is arranged between the first clamping strip 24 and the lower shell frame 20. In the embodiment, the first reinforcing rib 22 is arranged perpendicular to the first clamping strip 24. In another embodiment, the first reinforcing rib 22 can be arranged obliquely. The first clamping strip 24 and the adjacent two first reinforcing ribs 22 and the lower shell frame 20 are fixed in the fixing cavity of the upper end opening 13. A clamping key is arranged in the upper shell. In a specific embodiment, a plurality of fixing cavities are arranged in sequence along the lower shell frame 20, and a plurality of clamping keys are arranged in sequence along the upper shell frame 10. When the upper shell and the lower shell are matched, the clamping key is matched with the inside of the fixing cavity. In the embodiment, the clamping key extends out of the upper shell frame 10, so that the clamping key is higher than the lower shell frame 20, to ensure that the clamping key is matched in the fixing cavity. In a specific embodiment, the adjacent clamping keys form a clamping gap 14. The width of the first reinforcing rib 22 is slightly greater than the width of the clamping gap 14. When the upper and lower shells are tightly matched, the first reinforcing rib 22 is tightly matched with the clamping gap 14. The first reinforcing rib 22 is tightly clamped in the clamping gap 14, realizing the tight matching between the upper and lower shells, and avoiding the original torsional misalignment problem between the upper and lower shells of the unmanned aerial vehicle.

[0048] Specifically, a connecting plate 15 is arranged between the adjacent clamping keys. The connecting plate 15 is provided with a slot. The first reinforcing rib 22 is clamped in the slot. In a specific embodiment, the connecting plate 15 is connected with the adjacent clamping keys as an integral structure. The connecting plate 15 is connected with the upper shell as an integral structure. The slot is connected with the clamping gap 14 as an integral structure. The first reinforcing rib 22 is tightly matched with the slot.

[0049] Specifically, in order to reduce the cost and enhance the clamping cooperation between the clamping key and the fixing cavity, in the embodiment, the surface stress is adopted, that is, the clamping key is a clamping frame, the clamping frame includes the second clamping strip 12 and the positioning rib 12 arranged at both ends of the second clamping strip 12, the positioning rib 12 is arranged towards the upper shell frame 10, the positioning rib 12 is integrated with the upper shell and the second clamping strip 12, the length of the positioning rib 12 is equal to the distance between the first clamping strip 24 and the lower shell frame 20, the positioning rib 12 is arranged perpendicularly to the upper shell frame 10, when the clamping key cooperates with the fixing cavity, the second clamping strip 12 is attached to the clamping frame, the positioning rib 12 is attached to the inner wall of the first reinforcing rib 22 in the fixing cavity, at the same time, the clearance between the notch and the first reinforcing rib 22 is in interference fit, the stress area is large, the first reinforcing rib 22 cooperates with the notch, the transverse torsion of the positioning rib 12 is transmitted to the first reinforcing rib 22 and the longitudinal first clamping strip 24 and the second clamping strip 12, thereby playing a role in preventing deformation, the clearance elimination and shock absorption structure increases the natural resonance frequency of the upper and lower shells of the unmanned aerial vehicle after cooperation, avoids the torsional deformation of the unmanned aerial vehicle arm 30 in a certain low-frequency speed range under the condition of the rotation of the propeller, prevents the initiation of the body resonance, causes the unmanned aerial vehicle flight control to be unable to enter the fixed solution, and finally causes the unmanned aerial vehicle to lose control. The structure makes the natural resonance frequency of the unmanned aerial vehicle shell above the highest speed frequency range of the propeller; ensures that the propeller of the arm 30 will not produce torsional deformation effect on the shell in the low-frequency speed range during rotation, thereby unable to initiate the body resonance, and ensures the normal solution of the flight control sensor.

[0050] Specifically, the edge of the lower shell frame 20 extends upwards on one side of the inner wall and has a protrusion 23, the protrusion 23 extends along the lower shell edge for one turn; the edge of the upper shell frame 10 is provided with a downward opening 13 on one side of the inner wall, the opening 13 extends along the upper shell edge for one turn; when the upper shell and the lower shell are matched, the protrusion 23 is matched with the opening 13. In a specific embodiment, in order to ensure the sealing between the upper shell and the lower shell, prevent impurities such as dust or water droplets from entering between the upper shell frame 10 and the lower shell frame 20, the edge of the lower shell frame 20 extends upwards on one side of the inner wall and has a protrusion 23, the protrusion 23 can be a protrusion with a rectangular cross section or a protrusion with a trapezoidal cross section; the edge of the upper shell frame 10 is provided with a downward opening 13 on one side of the inner wall, the cross-sectional shape of the opening 13 is rectangular or trapezoidal, the protrusion 23 and the opening 13 are sealed and connected when the upper shell and the lower shell are assembled, the upper end surface of the protrusion 23 abuts against the bottom surface of the opening 13, achieving the positioning effect and the sealing effect before assembly.

[0051] Specifically, the second reinforcing rib 25 is arranged obliquely relative to the first reinforcing rib 22, and the second reinforcing rib 25, the first reinforcing rib 22 and the first clamping strip 24 form a triangular frame, so that the first reinforcing rib 22 and the first clamping strip 24 are more stable. When the upper shell and the lower shell are assembled, the positioning rib 12 abuts against the second reinforcing rib 25.

[0052] The UAV gap-eliminating and shock-reducing structure simplifies the design of the structure, and through the arrangement of the clamping strip, the reinforcing rib and the formation of the fixing cavity, and the cooperation with the clamping key, and the engagement between the clamping gap 14 and the reinforcing rib, the upper shell and the lower shell are tightly matched, the problem of torsional misalignment between the upper shell and the lower shell of the UAV is solved without increasing the weight of the shell, the torsional resistance is high, the stress distribution inside the UAV is more balanced, and the deformation and misalignment of the shell under stress are reduced.

[0053] Embodiment 2

[0054] A UAV includes a fuselage, a plurality of arms 30, the fuselage is formed by assembling an upper shell and a lower shell, the upper shell and the lower shell are further connected by screws, the plurality of arms 30 are fixedly connected to the fuselage, a plurality of third reinforcing ribs 26 are arranged in the arms 30, the third reinforcing ribs 26 extend upward along the bottom end of the lower shell, the third reinforcing ribs 26 are used to stabilize the structure of the lower shell, and specifically, the upper shell also has the third reinforcing ribs 26; the plurality of arms 30 are arranged in a radial manner outward from the fuselage, and the UAV gap-eliminating and shock-reducing structure in Embodiment 1 is arranged in the arms 30. Specifically, the UAV gap-eliminating and shock-reducing structure in Embodiment 1 is arranged in the arms 30, so that when the propeller of the arm 30 rotates, the torsional deformation effect on the upper shell and the lower shell in the low-frequency rotation speed range is prevented, the resonance of the UAV shell is prevented, and the normal calculation of the flight control sensor is ensured.

[0055] Through the UAV with the UAV gap-eliminating and shock-reducing structure, without changing the original material, the problem of low-frequency resonance caused by the rotation of the propeller of the UAV is avoided, the resonance range is increased to above the rotation speed range of the propeller, the torsional deformation of the arm 30 is prevented, the cost is low, the UAV is easy to disassemble, has good waterproof performance, is easy to maintain in the later period, and the use experience of consumers is improved.

[0056] The above merely illustrates the specific embodiments of the present application, but the protection scope of the present application is not limited thereto, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A gap-eliminating shock-absorbing structure for a drone, characterized by, The upper shell and the lower shell are connected to form a hollow cavity, and the side of the upper shell forms an upper shell frame, and the side of the lower shell forms a lower shell frame. The bottom end inner wall of the lower shell extends upwardly with a first clamping strip, the first clamping strip is arranged along the lower shell frame, and a plurality of first reinforcing ribs are arranged between the first clamping strip and the lower shell frame. A plurality of clamping keys are arranged in the upper shell, the clamping keys are arranged along the upper shell frame, and a clamping gap is formed between adjacent clamping keys. The clamping keys are clamped in the fixing cavities, and the first reinforcing ribs are clamped in the clamping gaps. A connecting plate is arranged between adjacent clamping keys, and the clamping keys are fixed through the connecting plate. The side of the connecting plate facing the first reinforcing ribs is provided with a notch, and the first reinforcing ribs are in interference fit with the notch. The clamping key is a clamping frame, the clamping frame includes a second clamping strip and positioning ribs arranged at both ends of the second clamping strip.

2. The drone anti-backlash vibration reduction structure of claim 1, wherein, The clamping frame extends beyond the edge of the upper shell frame, and the second clamping strip, the positioning ribs and the upper shell frame are an integral structure.

3. The drone anti-backlash vibration reduction structure of claim 2, wherein, The edge of the lower shell frame extends upwardly with a protrusion, the protrusion extends along the edge of the lower shell frame, the upper shell frame is provided with a downward opening, the opening extends along the edge of the upper shell frame, and the protrusion and the opening are matched when the upper shell and the lower shell are matched.

4. The gap elimination and shock reduction structure of the unmanned aerial vehicle according to claim 3, wherein, The first reinforcing rib is arranged perpendicularly to the lower shell frame, and the first clamping strip is arranged parallel to the lower shell frame.

5. A drone, characterized in that, The length of the positioning rib is equal to the distance between the first clamping strip and the lower shell frame. A second reinforcing rib is arranged between the lower shell frame and the first clamping strip, and the second reinforcing rib is arranged obliquely relative to the first reinforcing rib. The unmanned aerial vehicle gap elimination and shock absorption structure includes a body and a plurality of arms, the arms are fixedly connected to the body, the arms are arranged radially outwardly from the body, and the unmanned aerial vehicle gap elimination and shock absorption structure is as claimed in any one of claims 1-4.

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