Take-off and landing protection equipment for unmanned aerial vehicle

Abstract

The utility model relates to the technical field of takeoff and landing protection equipment, and discloses takeoff and landing protection equipment for an unmanned aerial vehicle, which comprises an unmanned aerial vehicle body, and a display connection signal screen is fixedly mounted on the outer wall of the unmanned aerial vehicle body. The foldable light and thin mounting plate is rapidly folded and unfolded through the rotating hinge and the small hydraulic push rod, in the flight state, the mounting plate is folded and tightly attached to the fuselage, air resistance is effectively reduced, the flight efficiency is improved, before landing, the hydraulic push rod rapidly pushes the mounting plate to be unfolded to the horizontal position, and the supporting area is enlarged; the unmanned aerial vehicle is in direct contact with the ground in cooperation with an anti-skid balancing weight, the friction force between the unmanned aerial vehicle and the ground is increased, the unmanned aerial vehicle is effectively prevented from sliding or rollover after landing, meanwhile, an inflation pump is arranged in an inflation box to inflate a buffering air bag, a flexible protection layer surrounding the unmanned aerial vehicle is formed, falling impact is effectively relieved, and the unmanned aerial vehicle is protected from falling. And the effect of improving the protection safety is achieved.

Description

Technical Field

[0001] This utility model relates to the technical field of landing protection equipment, specifically a landing protection device for unmanned aerial vehicles (UAVs). Background Technology

[0002] Unmanned aerial vehicles (UAVs), also known as drones, are unmanned aircraft controlled by radio remote control equipment and onboard program control devices, or fully autonomously operated by an onboard computer. They combine cutting-edge achievements from multiple fields, including aviation, communication, automation control, and sensor technology, and possess advantages such as flexibility, low cost, and low risk. With the rapid development of UAV technology, their applications in military reconnaissance, emergency rescue, logistics delivery, agricultural plant protection, and geographic surveying are becoming increasingly widespread. However, UAVs face numerous challenges during takeoff and landing, especially during landing, directly impacting operational safety and mission efficiency.

[0003] Traditional drone landing gear designs are often quite simple, typically employing fixed or simple retractable outrigger structures with limited cushioning performance. While this design may be barely usable on flat, hard ground, it falls short in the face of complex and varied real-world landing environments. In complex terrains such as mountains, hills, beaches, and construction sites, traditional landing gear struggles to ensure a stable landing, easily leading to tilting, tipping, or even crashes. Uneven ground causes uneven stress on the landing gear, resulting in excessive localized pressure and damage to the landing gear or fuselage structure. Furthermore, traditional landing gear uses a single cushioning method, usually relying on simple springs or rubber shock absorbers, which is insufficient to effectively absorb the impact energy during landing. Especially during high-speed landings or falls from a certain height, the impact energy is enormous, and a single cushioning method cannot provide adequate protection, easily damaging the drone's internal precision instruments and affecting its lifespan. Therefore, a landing protection device specifically designed for drones is needed. Utility Model Content

[0004] The purpose of this invention is to provide a landing protection device for unmanned aerial vehicles (UAVs), which solves the technical problem of impact damage during landing in complex terrain and achieves the goal of improving landing safety.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a take-off and landing protection device for unmanned aerial vehicles (UAVs), comprising a UAV body, a display and connection signal screen fixedly installed on the outer wall of the UAV body, a mounting frame fixedly installed on the bottom of the UAV body by fixing bolts, and the mounting frame having a dispersed arch shape, a U-shaped protective frame fixedly installed on the top of the inner wall of the mounting frame, and a camera disposed inside the U-shaped protective frame; a protective buffer assembly, the protective buffer assembly being disposed at the bottom and outer side of the mounting frame; the protective buffer assembly comprising: a buffer part, the buffer part being disposed at the bottom of the mounting frame; and a folding buffer part, the folding buffer part being disposed at the bottom and outer side of the mounting frame, and the folding buffer part being disposed on the outer side of the buffer part.

[0006] Preferably, the buffer portion includes: a bottom buffer connecting column, which is fixedly installed at the bottom of the mounting frame, and there are two sets of them arranged symmetrically; a connecting crossbar frame, which is fixedly connected between the mounting frames, and there are two sets of them arranged symmetrically; an arc-shaped buffer honeycomb plate is fixedly installed at the bottom of the bottom buffer connecting column, and a buffer pad is fixedly installed at the bottom of the arc-shaped buffer honeycomb plate.

[0007] Preferably, the bottom of the connecting crossbar frame is fixedly installed with a mounting plate, and there are two sets in total, arranged symmetrically. The bottom of the mounting plate is fixedly installed with a buffer damper, and there are two sets in total, located at the corners respectively. The bottom of the buffer damper is fixedly installed with a buffer plate, and there are two sets in total, located on the inner side of the bottom buffer connecting column respectively.

[0008] Preferably, the folding buffer part includes: a fixed long plate, which is fixedly installed on the outer wall of the arc-shaped buffer honeycomb plate by mounting nails, and there are two sets of the fixed long plate; an air box, which is fixedly installed on the top of the drone body; a rotating hinge is fixedly installed on the outer wall of the fixed long plate, and a folding thin mounting plate is fixedly installed on the outer wall of the other end of the rotating hinge, and fixing pins are fixedly installed at equal intervals on the top of the folding thin mounting plate.

[0009] Preferably, a small hydraulic rod seat is provided below the fixed long plate, and the small hydraulic rod seat is fixedly installed on the outer wall of the arc-shaped buffer honeycomb plate. A small hydraulic push rod is fixedly installed on the top of the small hydraulic rod seat, and the top of the small hydraulic push rod is fixedly connected to the bottom of the folding thin mounting plate.

[0010] Preferably, the bottom of the foldable thin mounting plate is fixedly mounted with mounting columns, and two columns are grouped together. The bottom of the mounting column is fixedly mounted with an anti-slip counterweight, and the top of the anti-slip counterweight is fixedly mounted with a buffer spring, which is sleeved on the outer wall of the mounting column.

[0011] Preferably, a cushioning airbag is fixedly installed at the bottom of the foldable thin mounting plate, an air pump is provided inside the air box, and an air pump is connected to an air inflating pipe. The air inflating pipe passes through the outer wall of the air box, the top of the foldable thin mounting plate, and extends into the interior of the cushioning airbag. A sealing ring is fitted on the outer wall of the air inflating pipe, and the sealing ring is located at the top of the foldable thin mounting plate.

[0012] This utility model provides a takeoff and landing protection device for unmanned aerial vehicles (UAVs). It has the following beneficial effects:

[0013] (1) This utility model has a four-level buffer structure consisting of an arc-shaped buffer honeycomb plate, a buffer base pad, a buffer damper, and a buffer airbag. The first layer of honeycomb plate absorbs most of the initial impact energy through crushing deformation. The buffer base pad further converts the impact force into deformation energy for secondary buffering. Then, the buffer damper suppresses the rebound of the fuselage through hydraulic damping effect, achieving three energy attenuation. Finally, the buffer airbag inflates at the moment of contact with the ground, forming the last flexible protective barrier, reducing the residual impact energy to the minimum, effectively preventing damage to the UAV body and precision payload due to violent impact, and achieving the effect of improving the safety of buffer protection.

[0014] (2) This utility model is equipped with a foldable and thin mounting plate that can be quickly folded and unfolded by rotating hinge and small hydraulic push rod. In flight, the mounting plate is folded and close to the fuselage, which effectively reduces air resistance and improves flight efficiency. Before landing, the hydraulic push rod quickly pushes the mounting plate to unfold to a horizontal position, expanding the support area and preparing for landing. This makes it easier to adapt to the take-off and landing requirements in narrow spaces. In conjunction with the anti-slip counterweight, it directly contacts the ground, increasing the friction with the ground and effectively preventing the drone from sliding or overturning after landing. At the same time, the air pump built into the air box inflates the buffer airbag, forming a flexible protective layer around the drone, which effectively mitigates the impact of falling and improves the safety of protection. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0016] Figure 2 This is a side view of the structure of a take-off and landing protection device for unmanned aerial vehicles according to this utility model;

[0017] Figure 3 This is a top view of the protective part of a take-off and landing protection device for unmanned aerial vehicles according to this utility model;

[0018] Figure 4 This is a top view of the inflation section of a landing protection device for unmanned aerial vehicles (UAVs) according to this utility model.

[0019] In the diagram: 1. UAV body, 2. Display and connection signal screen, 3. Mounting bracket, 31. U-shaped protective frame, 32. Camera, 4. Protective buffer assembly, 41. Buffer part, 411. Frame base buffer connecting column, 412. Arc-shaped buffer honeycomb plate, 413. Buffer base pad, 414. Connecting crossbar frame, 415. Mounting light plate, 416. Buffer damper, 417. Buffer plate, 42. Folding buffer part, 421. Fixed long plate, 422. Rotating hinge, 423. Folding thin mounting plate, 424. Fixing pin, 425. Small hydraulic rod seat, 426. Small hydraulic push rod, 427. Mounting column, 428. Anti-slip counterweight, 429. Buffer spring, 4210. Buffer airbag, 4211. Inflation box, 4212. Inflation connecting pipe, 4213. Sealing ring. Detailed Implementation

[0020] 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.

[0021] Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention. Example

[0022] In light of the existing problem of landing impact damage in complex terrain, the preferred embodiment of the landing protection device for unmanned aerial vehicles provided by this utility model is as follows: Figure 1-4 As shown: A takeoff and landing protection device for unmanned aerial vehicles (UAVs) includes a UAV body 1, a display and connection signal screen 2 fixedly installed on the outer wall of the UAV body 1, a mounting frame 3 fixedly installed on the bottom of the UAV body 1 by fixing bolts, and the mounting frame 3 is in the shape of a distributed arch. A U-shaped protective frame 31 is fixedly installed on the top of the inner wall of the mounting frame 3, and a camera 32 is arranged inside the U-shaped protective frame 31. A protective buffer assembly 4 is arranged at the bottom and the outside of the mounting frame 3. The protective buffer assembly 4 includes: a buffer part 41, which is arranged at the bottom of the mounting frame 3; and a folding buffer part 42, which is arranged at the bottom and the outside of the mounting frame 3, and the folding buffer part 42 is arranged outside the buffer part 41.

[0023] The buffer section 41 includes: a bottom buffer connecting column 411, which is fixedly installed at the bottom of the mounting frame 3, and there are two sets of them arranged symmetrically; a connecting crossbar frame 414, which is fixedly connected between the mounting frames 3, and there are two sets of them arranged symmetrically; an arc-shaped buffer honeycomb plate 412 is fixedly installed at the bottom of the bottom buffer connecting column 411, and a buffer pad 413 is fixedly installed at the bottom of the arc-shaped buffer honeycomb plate 412.

[0024] The bottom of the connecting crossbar frame 414 is fixedly installed with mounting plates 415, and there are two sets in total, arranged symmetrically. The bottom of the mounting plates 415 is fixedly installed with buffer dampers 416, and there are two sets in total, located at the corners. The bottom of the buffer dampers 416 is fixedly installed with buffer plates 417, and there are two sets in total, located inside the bottom buffer connecting column 411.

[0025] Furthermore, this embodiment employs a four-stage buffer system consisting of an arc-shaped buffer honeycomb plate 412, a buffer base pad 413, a buffer damper 416, and a buffer airbag 4210. The first-layer honeycomb plate absorbs most of the initial impact energy through crushing deformation. The buffer base pad further converts the impact force into deformation energy for secondary buffering. Then, the buffer damper suppresses the rebound of the fuselage through hydraulic damping effect, achieving a third energy attenuation. Finally, the buffer airbag inflates upon contact with the ground, forming the last flexible protective barrier, minimizing the residual impact energy and effectively preventing damage to the UAV body and precision payload due to severe impact. Example

[0026] Please see Figures 1-4 Furthermore, based on Embodiment 1, the folding buffer portion 42 includes: a fixed long plate 421, which is fixedly installed on the outer wall of the arc-shaped buffer honeycomb plate 412 by mounting nails, and there are two sets of them; an inflation box 4211, which is fixedly installed on the top of the drone body 1; a rotating hinge 422 is fixedly installed on the outer wall of the fixed long plate 421, and a folding thin mounting plate 423 is fixedly installed on the outer wall of the other end of the rotating hinge 422, and a fixing pin 424 is fixedly installed at equal intervals on the top of the folding thin mounting plate 423.

[0027] A small hydraulic rod seat 425 is provided below the fixed long plate 421, and the small hydraulic rod seat 425 is fixedly installed on the outer wall of the arc-shaped buffer honeycomb plate 412. A small hydraulic push rod 426 is fixedly installed on the top of the small hydraulic rod seat 425, and the top of the small hydraulic push rod 426 is fixedly connected to the bottom of the folding thin mounting plate 423.

[0028] The bottom of the folding thin mounting plate 423 is fixedly mounted with mounting posts 427, and two of them are a group. The bottom of the mounting post 427 is fixedly mounted with an anti-slip counterweight 428, and the top of the anti-slip counterweight 428 is fixedly mounted with a buffer spring 429, and the buffer spring 429 is sleeved on the outer wall of the mounting post 427.

[0029] A cushioning airbag 4210 is fixedly installed at the bottom of the folding thin mounting plate 423. An air pump is installed inside the air box 4211, and an air pump is connected to an air inflator 4212. The air inflator 4212 passes through the outer wall of the air box 4211, the top of the folding thin mounting plate 423, and extends into the airbag 4210. A sealing ring 4213 is fitted on the outer wall of the air inflator 4212, and the sealing ring 4213 is located at the top of the folding thin mounting plate 423.

[0030] Furthermore, in this embodiment, a foldable, lightweight mounting plate 423 is provided, which can be quickly folded and unfolded via a rotating hinge 422 and a small hydraulic push rod 426. In flight, the mounting plate is folded and close to the fuselage, effectively reducing air resistance and improving flight efficiency. Before landing, the hydraulic push rod quickly pushes the mounting plate to a horizontal position, expanding the support area and preparing for landing. This facilitates takeoff and landing in confined spaces. In conjunction with the anti-slip counterweight 428, which directly contacts the ground, the friction with the ground is increased, effectively preventing the drone from sliding or tipping over after landing. At the same time, the air box 4211 has a built-in air pump that inflates the buffer airbag 4210, forming a flexible protective layer around the drone, effectively mitigating the impact of a fall.

[0031] When in use, firstly, approach the landing point: the drone scans the ground with camera 32 and lidar, and the control unit calculates the optimal landing angle and path.

[0032] Next, the arc-shaped buffer honeycomb plate 412 first contacts the ground, and its honeycomb structure absorbs about 30% of the impact energy through crushing deformation. The buffer base 413 is made of high-elasticity silicone material, which further converts the vertical impact force into deformation energy and reduces the reaction force on the fuselage.

[0033] Furthermore, the piston rod of the buffer damper 416 compresses the hydraulic oil, generating damping force through the throttle orifice to suppress the rebound of the fuselage. The contact area between the buffer plate 417 and the ground is increased, dispersing the pressure to the corner areas and avoiding structural deformation caused by local overload.

[0034] Furthermore, a small hydraulic push rod 426 pushes the folding thin mounting plate 423 to unfold to a horizontal position around the rotating hinge 422, and in conjunction with the anti-slip counterweight 428, it contacts the ground. The micro-conical texture on its surface increases the coefficient of friction and prevents side slipping. The buffer spring 429 provides elasticity and locks the position of the counterweight.

[0035] Furthermore, the air pump inside the inflation box 4211 is activated, injecting nitrogen into the buffer airbag 4210 through the inflation connection pipe 4212. The airbag expands to the rated pressure within 300 milliseconds. The expanded airbag forms a ring-shaped protective ring to absorb residual kinetic energy and prevent the fuselage from directly colliding with the ground.

[0036] Emergency protection mechanism: Camera 32 and lidar monitor the fuselage tilt angle in real time. If the risk of rollover is predicted, the rotor protection mode is immediately activated. Then, the rotor is quickly deployed, and the airbags are inflated first. The air inflator box 4211 prioritizes supplying air to the cushioning airbag 4210.

[0037] The honeycomb panel uses aluminum alloy composite material, and the damper uses magnetorheological fluid to achieve a balance between energy absorption and response speed. The anti-slip counterweight has a 428 surface with a micro-conical texture to adapt to various floor materials such as sand, cement, and metal. Structural optimization: the folding structure reduces storage volume, and the application of carbon fiber composite materials makes the overall weight lighter.

[0038] Finally, it should be noted that the above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A landing protection device for unmanned aerial vehicles (UAVs), comprising a UAV body (1), characterized in that: The outer wall of the drone body (1) is fixedly installed with a display connection signal screen (2), and the bottom of the drone body (1) is fixedly installed with a mounting bracket (3) by a fixing bolt. The mounting bracket (3) is in the shape of a dispersed arch. A U-shaped protective frame (31) is fixedly installed on the top of the inner wall of the mounting bracket (3). A camera (32) is installed inside the U-shaped protective frame (31). A protective buffer assembly (4) is disposed on the bottom and the outside of the mounting frame (3); The protective buffer component (4) includes: A buffer portion (41) is provided at the bottom of the mounting bracket (3); Folding buffer portion (42) is provided at the bottom and outside of the mounting bracket (3), and the folding buffer portion (42) is provided outside the buffer portion (41).

2. The landing protection device for unmanned aerial vehicles according to claim 1, characterized in that: The buffer portion (41) includes: The bottom buffer connecting column (411) is fixedly installed at the bottom of the mounting frame (3), and there are two sets in total, arranged symmetrically. A connecting crossbar frame (414) is fixedly connected between the mounting frames (3), and there are two sets in total, arranged symmetrically; An arc-shaped buffer honeycomb plate (412) is fixedly installed at the bottom of the frame bottom buffer connecting column (411), and a buffer pad (413) is fixedly installed at the bottom of the arc-shaped buffer honeycomb plate (412).

3. The landing protection device for unmanned aerial vehicles according to claim 2, characterized in that: The bottom of the connecting crossbar frame (414) is fixedly installed with mounting light plates (415), and there are two sets in total, arranged symmetrically. The bottom of the mounting light plates (415) is fixedly installed with buffer dampers (416), and there are two sets in total, located at the corners respectively. The bottom of the buffer dampers (416) is fixedly installed with buffer plates (417), and there are two sets in total, located on the inner side of the bottom buffer connecting column (411).

4. The landing protection device for unmanned aerial vehicles according to claim 1, characterized in that: The folded buffer portion (42) includes: A fixed long plate (421) is fixedly installed on the outer wall of the arc-shaped buffer honeycomb plate (412) by mounting nails, and there are two sets of them; An air box (4211) is fixedly installed on the top of the drone body (1); A rotating hinge (422) is fixedly installed on the outer wall of the fixed long plate (421), and a folding thin mounting plate (423) is fixedly installed on the outer wall of the other end of the rotating hinge (422). Fixing pins (424) are fixedly installed at equal intervals on the top of the folding thin mounting plate (423).

5. The landing protection device for unmanned aerial vehicles according to claim 4, characterized in that: A small hydraulic rod seat (425) is provided below the fixed long plate (421), and the small hydraulic rod seat (425) is fixedly installed on the outer wall of the arc-shaped buffer honeycomb plate (412). A small hydraulic push rod (426) is fixedly installed on the top of the small hydraulic rod seat (425), and the top of the small hydraulic push rod (426) is fixedly connected to the bottom of the folding thin mounting plate (423).

6. The landing protection device for unmanned aerial vehicles according to claim 5, characterized in that: The bottom of the foldable thin mounting plate (423) is fixedly mounted with mounting posts (427), and two of them are a group. The bottom of the mounting post (427) is fixedly mounted with an anti-slip counterweight (428), and the top of the anti-slip counterweight (428) is fixedly mounted with a buffer spring (429), and the buffer spring (429) is sleeved on the outer wall of the mounting post (427).

7. A landing protection device for unmanned aerial vehicles according to claim 6, characterized in that: A buffer airbag (4210) is fixedly installed at the bottom of the folding thin mounting plate (423). An air pump is provided inside the air box (4211), and an air pump is connected to an air connection pipe (4212). The air connection pipe (4212) moves through the outer wall of the air box (4211), the top of the folding thin mounting plate (423), and extends to the inside of the buffer airbag (4210). A sealing ring (4213) is fitted on the outer wall of the air connection pipe (4212), and the sealing ring (4213) is located on the top of the folding thin mounting plate (423).

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