Low altitude aircraft with dispensing function

Abstract

The application relates to the technical field of low-altitude aircrafts, and discloses a low-altitude aircraft with a distribution function, which comprises a low-altitude aircraft body, a winch is fixedly installed at the bottom of the low-altitude aircraft body, a steel wire rope is wound on the winch, a hanging basket is fixedly connected to one end of the steel wire rope away from the winch, and adjustable supporting mechanisms are arranged on the two sides of the hanging basket. The application has the following advantages and effects: during the low-altitude flight of the low-altitude aircraft body for conveying goods, the shaking and displacement of the hanging basket and the goods in the hanging basket can be prevented, the goods in the hanging basket can be protected, the stability during flight can be ensured, and during the process of lowering the hanging basket to the distribution point, the impact force when the goods are lowered to the ground can be effectively buffered and resolved, the hanging basket and the goods in the hanging basket can be stably landed, and the goods can be further ensured to be not damaged.

Description

Technical Field

[0001] This application relates to the field of low-altitude aircraft technology, and in particular to a low-altitude aircraft with delivery function. Background Technology

[0002] Today, as the logistics industry shifts towards precise last-mile delivery and unmanned operations, low-altitude aircraft (such as remotely controlled drones) have become core equipment for scenarios such as community retail, emergency supplies transportation, and resupply to remote areas due to their flexibility, maneuverability, and lack of ground traffic restrictions. Most mainstream delivery drones on the market currently adopt a basic structure of a low-altitude aircraft body and a cargo basket. They use winches to raise and lower ropes to achieve cargo lifting and lowering, and with the assistance of high-definition cameras, they can complete short-distance cargo transportation tasks within a kilometer radius.

[0003] While existing low-altitude aircraft with delivery capabilities can meet the basic needs of cargo delivery, at least the following shortcomings have been found in actual use: The baskets of most low-altitude aircraft with delivery capabilities are suspended from the aircraft body by only one or more ropes, lacking a restraining structure. When encountering crosswinds, acceleration, or turning during low-altitude flight, the baskets are prone to swaying, causing displacement or collision of the internal cargo. Some improvements have attempted to add internal fixing devices to the baskets, but this has not solved the swaying problem of the basket suspension structure itself, which can easily damage the cargo, especially fragile items and precision instruments. It also affects the stability during flight. Furthermore, the basket support structure of existing low-altitude aircraft with delivery capabilities is mostly fixed. When the low-altitude aircraft reaches the target location and the basket is controlled to land, it cannot effectively buffer the impact force of the basket landing, posing a risk of cargo damage due to vibration.

[0004] Therefore, we propose a low-altitude aircraft with delivery capabilities to solve the above problems. Utility Model Content

[0005] The purpose of this application is to provide a low-altitude aircraft with delivery function, which can prevent the basket and the goods inside from shaking or shifting during low-altitude cargo transportation, protect the goods inside the basket, ensure stability during flight, and effectively buffer and dissipate the impact force when the basket is lowered to the delivery point, ensuring that the basket and the goods inside land smoothly and further ensuring that the goods are not damaged.

[0006] The above-mentioned technical objective of this application is achieved through the following technical solution: a low-altitude aircraft with delivery function, comprising a low-altitude aircraft body, a winch fixedly installed at the bottom of the low-altitude aircraft body, a steel wire rope wound on the winch, a basket fixedly connected to the end of the steel wire rope away from the winch, adjustable support mechanisms provided on both sides of the basket, the adjustable support mechanism including a U-shaped seat, a rotating shaft, a motor, two legs, two support columns, two inserts and two sets of buffer foot assemblies, the U-shaped seat fixedly installed on one side outer wall of the basket, the rotating shaft rotatably installed inside the U-shaped seat, the motor fixedly installed on the front outer wall of the U-shaped seat, the output shaft end of the motor fixedly connected to the front end of the rotating shaft, one end of each of the two legs fixedly sleeved on the rotating shaft, the two support columns respectively fixedly installed on the corresponding legs, the two inserts respectively fixedly installed on the end of the corresponding support column away from the legs, a column fixedly installed at the bottom of the low-altitude aircraft body, a slot opened at the bottom end of the column, the top of the insert slidingly installed in the slot, and two sets of buffer foot assemblies respectively provided on the corresponding legs.

[0007] A further configuration of this application is as follows: the buffer support leg assembly includes a telescopic column, a support leg pad, two connecting plates, and two springs. An installation cavity is provided inside the support leg, and a through hole communicating with the installation cavity is provided at the end of the support leg away from the pivot. The telescopic column is slidably installed in the installation cavity, with one end of the telescopic column passing through the through hole. The support leg pad is fixedly installed at the end of the telescopic column located outside the support leg. The two connecting plates are respectively fixedly installed on the outer walls of both sides of the support leg and are arranged symmetrically. The two springs are both fixedly installed on the side of the support leg pad close to the support leg, and one end of each spring is fixedly connected to the corresponding connecting plate.

[0008] A further feature of this application is that: two guide rods are fixedly installed on the side of the foot pad near the outrigger, two springs are respectively sleeved on the corresponding guide rods, and guide holes are opened on one side of the two connecting plates. The ends of the two guide rods away from the foot pad slide through the corresponding guide holes.

[0009] A further provision of this application is that a limit stop is fixedly installed at the end of the guide rod away from the support foot pad.

[0010] A further feature of this application is that the buffer support assembly also includes a slider and hydraulic oil. The slider is fixedly installed at one end of the telescopic column located in the mounting cavity. The slider has multiple damping holes, and the hydraulic oil is stored in the mounting cavity.

[0011] A further provision of this application is that the outer wall of the slider is slidably fitted with the inner wall of the mounting cavity.

[0012] A further feature of this application is that wear-resistant sealing strips are fixedly installed on the four inner walls of the through hole, and the telescopic column slides and seals with the through hole through the wear-resistant sealing strips.

[0013] A further feature of this application is that an L-shaped positioning rod is fixedly installed on one outer wall of the suspended platform, located above the outrigger, with the end of the L-shaped positioning rod away from the suspended platform abutting against the outrigger.

[0014] A further feature of this application is that a positioning block located below the outriggers is fixedly installed on the outer wall of the suspended platform.

[0015] A further feature of this application is that a high-definition camera is fixedly mounted on the front side of the main body of the low-altitude aircraft.

[0016] This application includes at least one of the following beneficial technical effects: This application utilizes insert blocks that are firmly inserted into corresponding slots to prevent the basket from shaking. The cargo in the basket will not shift due to flight turbulence, thus protecting the cargo in the basket and ensuring stability during flight.

[0017] This application utilizes a cushioning support assembly to effectively buffer and mitigate the impact of goods landing during the lowering of the basket above the delivery point, ensuring a smooth landing for the basket and its contents, and further guaranteeing that the goods will not be damaged. Attached Figure Description

[0018] Figure 1 This is a front-view stereoscopic structural diagram of this embodiment.

[0019] Figure 2 This is a three-dimensional structural diagram of the winch, suspended platform, and adjustable support mechanism in this embodiment; Figure 3 This is a three-dimensional structural diagram of the adjustable support mechanism in this embodiment.

[0020] Figure 4 yes Figure 3 A schematic diagram of the partial sectional view of the main structure.

[0021] Figure 5 This is a three-dimensional structural diagram of the buffer support assembly.

[0022] In the diagram, 1. Main body of the low-altitude aircraft; 2. Winch; 3. Wire rope; 4. Suspended basket; 5. Adjustable support mechanism; 51. U-shaped seat; 52. Rotary shaft; 53. Motor; 54. Outrigger; 55. Support column; 56. Insert block; 57. Mounting cavity; 58. Telescopic column; 59. Foot pad; 510. Connecting plate; 511. Spring; 512. Guide rod; 513. Limiting block; 514. Slider; 515. Damping hole; 516. Hydraulic oil; 517. Wear-resistant sealing strip; 6. L-shaped positioning rod; 7. Positioning block; 8. Column; 9. High-definition camera. Detailed Implementation

[0023] The technical solution of this application will be clearly and completely described below with reference to specific embodiments. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0024] See Figures 1-5 This application provides a low-altitude aircraft with delivery function, including a low-altitude aircraft body 1. The low-altitude aircraft body 1 is a remotely controlled drone that can be purchased on the market or customized in a factory. It is equipped with a remote controller at the factory, allowing operators to control the low-altitude aircraft body 1 to fly at low altitudes for subsequent delivery of goods. A high-definition camera 9 is fixedly installed on the front of the low-altitude aircraft body 1. The high-definition camera 9 is used to capture images of the low-altitude aircraft body 1 during flight. The captured images can be displayed on the screen on the remote controller. A winch 2 is fixedly installed at the bottom of the main body 1 of the air-to-ground aircraft. A steel wire rope 3 is wound on the winch 2. The end of the steel wire rope 3 away from the winch 2 is fixedly connected to a basket 4. The winch 2 is used to release or reel in the steel wire rope 3, thereby adjusting the height of the basket 4. Adjustable support mechanisms 5 are provided on both sides of the basket 4. By utilizing the synergistic effect of the two sets of adjustable support mechanisms 5, the basket 4 can be stably supported on the ground when suspended below. The adjustable support mechanism 5 includes a U-shaped seat 51, a rotating shaft 52, a motor 53, two outriggers 54, and two support columns. 55. Two insert blocks 56 and two sets of buffer support leg assemblies, a U-shaped base 51 is fixedly installed on one side outer wall of the suspended platform 4, a rotating shaft 52 is rotatably installed inside the U-shaped base 51, a motor 53 is fixedly installed on the front outer wall of the U-shaped base 51, the output shaft end of the motor 53 is fixedly connected to the front end of the rotating shaft 52, one end of each of the two support legs 54 is fixedly sleeved on the rotating shaft 52, the motor 53 is used to drive the rotating shaft 52 to rotate, thereby allowing the support legs 54 to rotate around the rotating shaft 52 as the center, so that the angle of the support legs 54 can be adjusted, and two support columns 55 are respectively fixedly installed on On the corresponding outrigger 54, two inserts 56 are fixedly installed at the end of the corresponding support column 55 away from the outrigger 54. A column 8 is fixedly installed at the bottom of the low-altitude aircraft body 1. A slot is opened at the bottom end of the column 8. The top of the insert 56 is slidably installed in the slot. By using the sliding insertion and connection between the insert 56 and the slot, the basket 4 can be prevented from shaking during the low-altitude flight of the low-altitude aircraft body 1 under remote control, thereby protecting the cargo in the basket 4 and ensuring stability during flight. Two sets of buffer outrigger assemblies are respectively set on the corresponding outrigger 54.

[0025] In this embodiment, the buffer support assembly includes a telescopic column 58, a support pad 59, two connecting plates 510, and two springs 511. A mounting cavity 57 is formed inside the support leg 54. A through hole communicating with the mounting cavity 57 is formed at the end of the support leg 54 away from the rotating shaft 52. The telescopic column 58 is slidably mounted inside the mounting cavity 57, with one end of the telescopic column 58 passing through the through hole. The support pad 59 is fixedly mounted at the end of the telescopic column 58 located outside the support leg 54. The two connecting plates 510 are respectively fixedly mounted on the outer walls of both sides of the support leg 54 and are symmetrically arranged. Both springs 511 are fixedly mounted on the side of the support pad 59 closest to the support leg 54, with one end of each spring 511 fixedly connected to the corresponding connecting plate 510. The buffer support assembly also includes a slider. 514 and hydraulic oil 516 are used. The slider 514 is fixedly installed at one end of the telescopic column 58 located in the mounting cavity 57. The outer side wall of the slider 514 slides against the inner side wall of the mounting cavity 57. Multiple damping holes 515 are opened on the slider 514. The hydraulic oil 516 is stored in the mounting cavity 57. Utilizing the elastic force of the spring 511, the instantaneous vibration when the basket 4 lands can be initially absorbed. The resistance formed by the flow of the hydraulic oil 516 through the multiple damping holes 515 can slowly release the impact energy, which can effectively suppress the reciprocating bounce of the spring 511, thereby effectively buffering and dissipating the impact force when the goods are lowered and landed. This can ensure that the basket 4 and the goods inside land smoothly, which is especially suitable for the delivery of fragile items, precision instruments and other goods that are sensitive to vibration.

[0026] In this embodiment, two guide rods 512 are fixedly installed on the side of the foot pad 59 near the support leg 54. Two springs 511 are respectively sleeved on the corresponding guide rods 512. Guide holes are opened on one side of the two connecting plates 510. The ends of the two guide rods 512 away from the foot pad 59 slide through the corresponding guide holes. The sliding connection of the guide rods 512 in the guide holes plays a role in guiding the foot pad 59 and avoiding tilting due to uneven force.

[0027] In this embodiment, a limit stop 513 is fixedly installed at the end of the guide rod 512 away from the support foot pad 59. The design of the limit stop 513 can prevent the guide rod 512 from dislodging from the guide hole.

[0028] In this embodiment, wear-resistant sealing strips 517 are fixedly installed on the four inner walls of the through hole. The telescopic column 58 slides and seals with the through hole through the wear-resistant sealing strips 517. The design of the wear-resistant sealing strips 517 can effectively seal the gap between the telescopic column 58 and the through hole, preventing hydraulic oil 516 from leaking.

[0029] In this embodiment, an L-shaped positioning rod 6 located above the support leg 54 is fixedly installed on one side of the outer wall of the suspended basket 4. The end of the L-shaped positioning rod 6 away from the suspended basket 4 abuts against the support leg 54. The L-shaped positioning rod 6 can be used to limit the upward rotation angle of the support leg 54. When the support leg 54 rotates to abut against the L-shaped positioning rod 6, the support leg 54 is in a horizontal state.

[0030] In this embodiment, a positioning block 7 located below the support leg 54 is fixedly installed on the outer wall of the suspended basket 4. The positioning block 7 can limit the downward rotation angle of the support leg 54. When the support leg 54 rotates to the point of contacting the positioning block 7, the support leg 54 is in a vertical state.

[0031] In this embodiment, the motor 53 is a reversible motor. Both the winch 2 and the motor 53 are electrically connected to the internal power supply of the low-altitude aircraft body 1. The winch 2 and the motor 53 can also be remotely controlled by a remote controller. The wiring connection method and control method are mature technologies in this field and have been fully disclosed. Therefore, they will not be described in detail here.

[0032] With the above structure, the low-altitude aircraft with delivery function provided in this application, when in use, controls the winch 2 to rotate forward to gradually release the wire rope 3, and the basket 4 gradually descends under its own weight until the basket 4 descends to a suitable height or touches the ground (at which point the two adjustable support mechanisms 5 are in position). Figure 1 (In the state of being in operation), stop the operation of winch 2, and then the operator can put the goods into basket 4. After the goods are placed, control winch 2 to reverse and gradually wind up the wire rope 3, which can pull basket 4 and the goods inside it to rise. When the plug 56 at the top of the four support columns 55 is inserted into the slot at the bottom of the corresponding column 8, stop the operation of winch 2. The operator can then use the remote control to remotely control the main body 1 of the low-altitude aircraft to transport goods at low altitude. During the transport of goods, the high-definition camera 9 can capture the front view in real time and transmit it to the remote control display screen to help the operator avoid obstacles so as to accurately fly to the target delivery point. Moreover, since the plug 56 is inserted into the corresponding slot, it can prevent basket 4 from shaking. The goods in basket 4 will not be displaced due to flight turbulence, thus protecting the goods in basket 4 and ensuring stability during flight. Once the main body 1 of the low-altitude aircraft reaches the delivery point, the staff maneuvers it to hover at a suitable height. Then, they control the two motors 53 to operate. The output shaft of motor 53 drives the rotating shaft 52 to rotate, which in turn drives the outriggers 54 to rotate downwards until the outriggers 54 contact the positioning block 7. At this point, motor 53 stops, and the outriggers 54 are in a vertical position. The four buffer support leg components of the two sets of adjustable support mechanisms 5 are completely vertical and downwards, forming a stable support frame. Next, the winch 2 is started to rotate forward and release the wire rope 3. The basket 4 gradually lowers along with the wire rope 3. When the four outrigger pads 59 contact the ground, the ground reaction force pushes the telescopic column 58 to retract into the mounting cavity 57. During this process, the spring 511 is compressed and absorbs the instantaneous impact force through elastic deformation, reducing the vibration transmitted to the basket 4 and the goods placed inside. The telescopic column 58 drives the slider 514 to slide in the mounting cavity 57. The hydraulic oil 516 flows through the multiple damping holes 515 on the slider 514 to form damping resistance, slowly releasing the impact energy and suppressing the reciprocating bounce of the spring 511, thereby ensuring that the basket 4 and the goods inside land smoothly. After the basket 4 lands smoothly, the cargo inside the basket 4 can be manually removed. After the cargo is removed, the winch 2 is controlled to reverse and wind up the wire rope 3. At the same time, the two motors 53 are controlled to rotate forward and retract the outriggers 54, so that the insert block 56 can be reinserted into the corresponding slot. Then, the low-altitude aircraft body 1 can be remotely controlled to return to base.

Claims

1. A low-altitude aircraft with delivery function, characterized in that, The system includes a low-altitude aircraft body (1), a winch (2) fixedly installed at the bottom of the low-altitude aircraft body (1), a steel wire rope (3) wound on the winch (2), a basket (4) fixedly connected to the end of the steel wire rope (3) away from the winch (2), and adjustable support mechanisms (5) provided on both sides of the basket (4). The adjustable support mechanism (5) includes a U-shaped seat (51), a rotating shaft (52), a motor (53), two support legs (54), two support columns (55), two inserts (56), and two sets of buffer support leg assemblies. The U-shaped seat (51) is fixedly installed on one side of the outer wall of the basket (4), the rotating shaft (52) is rotatably installed inside the U-shaped seat (51), and the motor (53) is fixedly installed on the outer wall of the basket (4). 53) Fixedly installed on the front outer wall of the U-shaped seat (51), the output shaft end of the motor (53) is fixedly connected to the front end of the rotating shaft (52), one end of each of the two legs (54) is fixedly sleeved on the rotating shaft (52), the two support columns (55) are respectively fixedly installed on the corresponding legs (54), the two inserts (56) are respectively fixedly installed on the end of the corresponding support column (55) away from the legs (54), the bottom of the low-altitude aircraft body (1) is fixedly installed with a column (8), the bottom end of the column (8) is provided with a slot, the top of the insert (56) is slidably installed in the slot, and the two sets of buffer support leg assemblies are respectively set on the corresponding legs (54).

2. The low-altitude aircraft with delivery function according to claim 1, characterized in that: The buffer support assembly includes a telescopic column (58), a support pad (59), two connecting plates (510), and two springs (511). The support leg (54) has an installation cavity (57). The end of the support leg (54) away from the pivot (52) has a through hole that communicates with the installation cavity (57). The telescopic column (58) is slidably installed in the installation cavity (57). One end of the telescopic column (58) passes through the through hole. The support pad (59) is fixedly installed at the end of the telescopic column (58) outside the support leg (54). The two connecting plates (510) are respectively fixedly installed on the outer walls of the two sides of the support leg (54) and are arranged symmetrically. The two springs (511) are both fixedly installed on the side of the support pad (59) near the support leg (54). One end of the two springs (511) is respectively fixedly connected to the corresponding connecting plate (510).

3. The low-altitude aircraft with delivery function according to claim 2, characterized in that: Two guide rods (512) are fixedly installed on the side of the foot pad (59) near the support leg (54). Two springs (511) are respectively sleeved on the corresponding guide rods (512). Guide holes are opened on one side of the two connecting plates (510). The ends of the two guide rods (512) away from the foot pad (59) slide through the corresponding guide holes.

4. The low-altitude aircraft with delivery function according to claim 3, characterized in that: A limit stop (513) is fixedly installed at the end of the guide rod (512) away from the foot pad (59).

5. The low-altitude aircraft with delivery function according to claim 4, characterized in that: The buffer support assembly also includes a slider (514) and hydraulic oil (516). The slider (514) is fixedly installed at one end of the telescopic column (58) located in the mounting cavity (57). The slider (514) has multiple damping holes (515). The hydraulic oil (516) is stored in the mounting cavity (57).

6. The low-altitude aircraft with delivery function according to claim 5, characterized in that: The outer wall of the slider (514) slides against the inner wall of the mounting cavity (57).

7. The low-altitude aircraft with delivery function according to claim 6, characterized in that: Wear-resistant sealing strips (517) are fixedly installed on the four inner walls of the through hole, and the telescopic column (58) slides and seals with the through hole through the wear-resistant sealing strips (517).

8. The low-altitude aircraft with delivery function according to claim 1, characterized in that: An L-shaped positioning rod (6) is fixedly installed on one side of the outer wall of the suspended basket (4) above the support leg (54), and the end of the L-shaped positioning rod (6) away from the suspended basket (4) abuts against the support leg (54).

9. The low-altitude aircraft with delivery function according to claim 1, characterized in that: A positioning block (7) located below the outrigger (54) is fixedly installed on the outer wall of the suspended basket (4).

10. The low-altitude aircraft with delivery function according to claim 1, characterized in that: A high-definition camera (9) is fixedly installed on the front side of the main body (1) of the low-altitude aircraft.

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