A drone for stable landing

Abstract

The utility model relates to an unmanned plane technical field especially is an unmanned plane of stable landing, including unmanned plane body and the machine arm of symmetrical arrangement in the outside of unmanned plane body, be equipped with the buffer assembly under the machine arm, the buffer assembly bottom fixedly connected with the shell, the shell outside is equipped with the air hole that from outside to inside penetrates the shell, the shell inside top fixedly connected with the standby battery, the standby battery bottom fixedly connected with the air pump, in the utility model, through setting up the buffer assembly, buffer oil cylinder, fixed block, round hole, limit rod, connecting rod, first sealing washer and rubber board, make unmanned plane body landing more stable, when unmanned plane body lands, rubber board contacts with ground, due to the spacing of limit rod to fixed block, connecting rod force drives fixed block to move upward, buffer oil moves downward through the round hole of fixed block inside, and buffer oil buffers fixed block to absorb the impact force when unmanned plane body lands.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a UAV that can land stably. Background Technology

[0002] A drone is an aircraft that flies without direct pilot control, relying on a remote control system or an autopilot system. A drone typically consists of an airframe, power system, control system, sensors, and communication system. In recent years, drone technology has seen continuous innovation, primarily in autonomous flight technology, improved endurance, high-precision positioning, and multi-functional payloads. In the future, drones will continue to develop in terms of intelligence, miniaturization, long endurance, and high reliability. Improvements in laws and regulations and advancements in safety technologies will promote their wider application. As a high-tech product, drones are profoundly changing our lives and work, and their development prospects are broad and their potential is enormous.

[0003] Existing drones are widely used, but they generally land using a hard landing method. This method is low-cost but not stable enough and can easily damage internal parts of the drone. In addition, drones sometimes fall into water due to various reasons (such as running out of power). Existing drones do not have the ability to float on water. Therefore, this paper proposes a drone with stable landing to address the above problems. Utility Model Content

[0004] The purpose of this invention is to provide a drone that lands stably, in order to solve the problems of unstable drone landing and drones being unable to float on water as mentioned in the background art.

[0005] To achieve the above objectives, this utility model provides the following technical solution: A stable landing drone includes a drone body and symmetrically arranged arms on the outer side of the drone body. A buffer assembly is provided below the arms. A shell is fixedly connected to the bottom end of the buffer assembly. A vent hole is opened on the outer side of the shell, penetrating from the outside to the inside. A spare battery is fixedly connected to the top of the inner side of the shell. An air pump is fixedly connected to the bottom end of the spare battery. An air inlet assembly is fixedly connected to the air outlet of the air pump. A threaded ring is fixedly connected to the bottom end of the shell. A threaded cover is screwed to the outer side of the threaded ring. A partition is fixedly connected to the inner side of the threaded cover. A second sealing ring is fixedly connected to the top end of the partition, penetrating the partition. An airbag communicating with the second sealing ring is fixedly connected to the bottom end of the partition. A baffle is fixedly connected to the bottom end of the threaded cover below the airbag.

[0006] Preferably, the buffer assembly includes a buffer oil cylinder fixedly connected to the bottom end of the arm. A fixing block is provided inside the buffer oil cylinder. A plurality of circular holes penetrating the fixing block from top to bottom are provided inside the fixing block. Limiting rods are slidably connected inside some of the circular holes. A vertically arranged connecting rod is fixedly connected to the bottom end of the fixing block. A first sealing ring is provided on the outside of the connecting rod. A rubber plate is fixedly connected to the bottom end of the connecting rod.

[0007] Preferably, the outer side of the fixing block is tightly fitted to the inner side of the buffer oil cylinder, the upper and lower ends of the limiting rod are respectively fixedly connected to the upper and lower ends of the inner side of the buffer oil cylinder, the first sealing ring is fixedly connected to the bottom end of the buffer oil cylinder, and the inner side of the first sealing ring is tightly fitted to the outer side of the connecting rod.

[0008] Preferably, the air intake assembly includes an air intake cylinder fixedly connected to the air outlet of the air pump. Both the upper and lower ends of the air intake cylinder are provided with air intake holes that penetrate from top to bottom. A vertically arranged return spring is fixedly connected to the bottom inner side of the air intake cylinder, and a sealing ball is fixedly connected to the top of the return spring.

[0009] Preferably, there are multiple vent holes, which are evenly distributed on the outer side of the outer shell. The outer side of the sealing ball is tightly fitted with the inner side of the upper air inlet, and the bottom end of the air inlet cylinder is tightly fitted with the top end of the second sealing ring.

[0010] Compared with the prior art, the beneficial effects of this utility model are: 1. In this utility model, the buffer assembly, buffer oil cylinder, fixed block, round hole, limit rod, connecting rod, first sealing ring and rubber plate make the drone body land more stably. When the drone body lands, the rubber plate contacts the ground. Due to the limit rod limiting the fixed block, the connecting rod is forced to move the fixed block upward. The buffer oil moves downward through the round hole on the inner side of the fixed block. The buffer oil buffers the fixed block, thereby absorbing the impact force when the drone body lands. 2. In this utility model, by setting up a shell, vent, backup battery, air pump, air intake assembly, air intake cylinder, air intake hole, return spring, sealing ball, threaded ring, threaded cover, partition, second sealing ring, airbag and baffle, the drone body can float on the water surface when encountering an emergency. When the drone body encounters an emergency, the drone body starts the air pump, the backup battery is used to power the air pump, the air pump inflates the airbag through the air intake assembly, the airbag expands and pushes open the baffle, and the drone body can float on the water when it lands on the water surface. Attached Figure Description

[0011] Figure 1 This is a schematic diagram of the overall structure of this utility model; Figure 2 This is a schematic diagram of the buffer component structure of this utility model; Figure 3 This is a schematic diagram of the cross-sectional structure of the outer shell of this utility model; Figure 4 This is a schematic diagram of the cross-sectional structure of the threaded cap of this utility model; Figure 5 This is a schematic diagram of the air intake assembly structure of this utility model.

[0012] In the diagram: 1. UAV body; 2. Arm; 3. Buffer assembly; 301. Buffer oil tank; 302. Fixing block; 303. Round hole; 304. Limiting rod; 305. Connecting rod; 306. First sealing ring; 307. Rubber plate; 4. Outer shell; 5. Vent hole; 6. Backup battery; 7. Air pump; 8. Air intake assembly; 801. Air intake cylinder; 802. Air intake hole; 803. Return spring; 804. Sealing ball; 9. Threaded ring; 10. Threaded cap; 11. Partition plate; 12. Second sealing ring; 13. Airbag; 14. Baffle plate. Detailed Implementation

[0013] 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.

[0014] In the description of this utility model, it should be understood that the directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this utility model. The directional terms "inner" and "outer" refer to the inner and outer contours of each component itself.

[0015] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be construed as limiting the scope of protection of this utility model.

[0016] Please see Figure 1-5 This utility model provides a technical solution: A stable landing drone includes a drone body 1 and symmetrically arranged arms 2 on the outside of the drone body 1. A buffer assembly 3 is provided below the arms 2. A shell 4 is fixedly connected to the bottom of the buffer assembly 3. A vent 5 is provided on the outside of the shell 4, penetrating from the outside to the inside. A spare battery 6 is fixedly connected to the top of the inner side of the shell 4. An air pump 7 is fixedly connected to the bottom of the spare battery 6. An air inlet assembly 8 is fixedly connected to the air outlet of the air pump 7. A threaded ring 9 is fixedly connected to the bottom of the shell 4. A threaded cover 10 is screwed to the outside of the threaded ring 9. A partition 11 is fixedly connected to the inside of the threaded cover 10. A second sealing ring 12 is fixedly connected to the top of the partition 11, penetrating the partition 11. An airbag 13 communicating with the second sealing ring 12 is fixedly connected to the bottom of the partition 11. A baffle 14 is fixedly connected to the bottom of the threaded cover 10 below the airbag 13.

[0017] The buffer assembly 3 includes a buffer oil cylinder 301 fixedly connected to the bottom end of the arm 2. A fixing block 302 is provided inside the buffer oil cylinder 301. Multiple circular holes 303 penetrate the fixing block 302 from top to bottom. Limiting rods 304 are slidably connected to the inner sides of some of the circular holes 303. A vertically arranged connecting rod 305 is fixedly connected to the bottom end of the fixing block 302. A first sealing ring 306 is provided on the outer side of the connecting rod 305. A rubber plate 307 is fixedly connected to the bottom end of the connecting rod 305. The buffer assembly 3 enables the UAV body 1 to land more stably. The outer side of the fixing block 302 is tightly fitted to the inner side of the buffer oil cylinder 301. The upper and lower ends of the limiting rod 304 are fixedly connected to the upper and lower ends of the inner side of the buffer oil cylinder 301, respectively. The first sealing ring 306 is fixedly connected to the buffer oil cylinder 301. At the bottom of 01, the inner side of the first sealing ring 306 is tightly fitted with the outer side of the connecting rod 305. The first sealing ring 306 can prevent the buffer oil from leaking out. The air intake assembly 8 includes an air intake cylinder 801 fixedly connected to the air outlet of the air pump 7. Both the upper and lower ends of the air intake cylinder 801 are provided with air intake holes 802 that pass through the air intake cylinder 801 from top to bottom. A vertically arranged return spring 803 is fixedly connected to the bottom of the inner side of the air intake cylinder 801. A sealing ball 804 is fixedly connected to the top of the return spring 803. The air intake assembly 8 can prevent the gas inside the airbag 13 from escaping. There are multiple vent holes 5. The vent holes 5 are evenly distributed on the outer side of the outer shell 4. The outer side of the sealing ball 804 is tightly fitted with the inner side of the upper air intake hole 802. The bottom of the air intake cylinder 801 is tightly fitted with the top of the second sealing ring 12.

[0018] Workflow: Before use, fully charge the drone body 1 and the spare battery 6. When the drone body 1 lands, the rubber plate 307 contacts the ground. Due to the limiting rod 304 limiting the fixed block 302, the connecting rod 305 is forced to move the fixed block 302 upward inside the buffer oil cylinder 301 at the bottom of the arm 2. The buffer oil moves downward through the round hole 303 inside the fixed block 302, buffering the fixed block 302 and absorbing the impact force when the drone body 1 lands. The first sealing ring 306 can prevent the buffer oil from leaking out. The setting of the buffer component 3 can make the drone body 1 land more stably. When the drone body 1 encounters an emergency, the air pump 7 is started by the drone body 1. The spare battery 6 is used to power the air pump 7. Outside air enters the inside of the air pump 7 through the vent 5 on the outside of the outer shell 4. The gas released by the air pump 7 pushes open the sealing ball 804, and the return spring 803 is compressed by force. The gas enters the inside of the airbag 13 through the air inlet 802 on the air inlet cylinder 801. The airbag 13 expands and pushes open the baffle 14. After the airbag 13 is full, the air pump 7 stops working. The return spring 803 returns to its original position and drives the sealing ball 804 to fit tightly against the inside of the air inlet 802 located above. The air intake assembly 8 can prevent the gas inside the airbag 13 from escaping. When the drone body 1 lands on the water, it can float on the water. After the drone body 1 is retrieved, the airbag 13 can be replaced. The threaded cap 10 is unscrewed from the outside of the threaded ring 9, and then the new threaded cap 10 is screwed onto the outside of the threaded ring 9. At this time, the top of the second sealing ring 12 on the partition 11 fits tightly against the bottom of the air inlet cylinder 801, thus completing the replacement of the airbag 13.

[0019] Contents not described in detail in this specification are existing technologies known to those skilled in the art. Standard parts used in this invention can all be purchased commercially, and irregularly shaped parts can be custom-made according to the description and drawings. The specific connection methods for each part all employ conventional methods such as bolts, rivets, and welding, which are already mature technologies. The machinery, parts, and equipment all use conventional models from the prior art, and the circuit connections also employ conventional connection methods from the prior art, which will not be detailed here.

[0020] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A stable-landing unmanned aerial vehicle (UAV), comprising a UAV body (1) and symmetrically arranged arms (2) on the outside of the UAV body (1), characterized in that: The arm (2) is provided with a buffer assembly (3) below it. The bottom end of the buffer assembly (3) is fixedly connected to a shell (4). The outer side of the shell (4) is provided with a vent hole (5) that runs from the outside to the inside of the shell (4). The top end of the inner side of the shell (4) is fixedly connected to a spare battery (6). The bottom end of the spare battery (6) is fixedly connected to an air pump (7). The air outlet of the air pump (7) is fixedly connected to an air inlet assembly (8). The bottom end of the shell (4) is fixedly connected to a threaded ring (9). The outer side of the threaded ring (9) is screwed with a threaded cover (10). The inner side of the threaded cover (10) is fixedly connected to a partition (11). The top end of the partition (11) is fixedly connected to a second sealing ring (12) that runs through the partition (11). The bottom end of the partition (11) is fixedly connected to an airbag (13) that runs through the second sealing ring (12). The bottom of the airbag (13) is provided with a baffle (14) fixedly connected to the bottom end of the threaded cover (10).

2. The unmanned aerial vehicle (UAV) with stable landing according to claim 1, characterized in that: The buffer assembly (3) includes a buffer oil cylinder (301) fixedly connected to the bottom end of the arm (2). A fixing block (302) is provided inside the buffer oil cylinder (301). A plurality of circular holes (303) are provided inside the fixing block (302) from top to bottom. A limit rod (304) is slidably connected inside some of the circular holes (303). A vertically arranged connecting rod (305) is fixedly connected to the bottom end of the fixing block (302). A first sealing ring (306) is provided on the outside of the connecting rod (305). A rubber plate (307) is fixedly connected to the bottom end of the connecting rod (305).

3. The unmanned aerial vehicle (UAV) with stable landing according to claim 2, characterized in that: The outer side of the fixing block (302) is tightly fitted to the inner side of the buffer oil cylinder (301), the upper and lower ends of the limiting rod (304) are respectively fixedly connected to the upper and lower ends of the inner side of the buffer oil cylinder (301), the first sealing ring (306) is fixedly connected to the bottom end of the buffer oil cylinder (301), and the inner side of the first sealing ring (306) is tightly fitted to the outer side of the connecting rod (305).

4. The unmanned aerial vehicle (UAV) with stable landing according to claim 1, characterized in that: The air intake assembly (8) includes an air intake cylinder (801) fixedly connected to the air outlet of the air pump (7). Both the upper and lower ends of the air intake cylinder (801) are provided with air intake holes (802) that pass through the air intake cylinder (801) from top to bottom. A vertically arranged reset spring (803) is fixedly connected to the bottom of the inner side of the air intake cylinder (801). A sealing ball (804) is fixedly connected to the top of the reset spring (803).

5. The stable landing drone according to claim 4, characterized in that: The number of vent holes (5) is multiple, and the vent holes (5) are evenly distributed on the outside of the outer shell (4). The outer side of the sealing ball (804) is closely fitted with the inner side of the upper air inlet (802), and the bottom end of the air inlet cylinder (801) is closely fitted with the top end of the second sealing ring (12).

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