Unmanned aerial vehicle with one-machine multi-load structure

Abstract

The utility model discloses an unmanned aerial vehicle with a multi-load structure, which relates to the technical field of unmanned aerial vehicles, and comprises an unmanned aerial vehicle main body, the unmanned aerial vehicle main body comprises a main engine, the bottom end of the main engine is provided with a transportation bin, the side wall of the main engine is fixedly connected with a plurality of groups of supporting legs, and the supporting legs are made of elastic plastics. The two sides of the main machine are each slidably connected with a set of auxiliary batteries, and a plurality of sets of buffering mechanisms are arranged between the supporting legs and the transportation bin. According to the unmanned aerial vehicle, after the transportation bin is connected with the main machine and the transportation bin is filled with goods, the weight of the whole unmanned aerial vehicle is large, impact force is transmitted to the supporting legs and the clamping blocks through the supporting strips during landing, the supporting legs are bent, the supporting rods are pushed, and then the supporting springs and friction force between the modules and the friction rods are utilized; and the impact force is buffered and consumed, so that the host is prevented from being damaged due to large impact.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), in particular to an UAV with a one-machine multi-load structure. Background Art

[0002] Due to the characteristics of low operating costs, no risk of casualties, good maneuverability, ability to fly beyond visual range, and ease and efficiency of use, drones have been successfully used in film and television aerial photography, surveying and mapping, high-voltage line inspection, geological exploration, disaster relief and rescue, pesticide spraying, highway inspection, mobile base station monitoring, fire prevention in the forestry sector, yield measurement in the agricultural sector, pest and disease monitoring and control, land and resources management, ecological environment protection, urban planning and municipal management, land use surveys, water resources development, commercial performances and other fields. More and more industries are hoping to replace traditional working methods with drones.

[0003] An existing patent (publication number: CN217673228U) discloses a multi-load UAV body structure, including a UAV frame and a UAV electronic warehouse, which is fixedly mounted on the UAV frame. The UAV frame includes support rods, and there are four support rods. The support rods are symmetrically arranged in pairs on both sides of the UAV electronic warehouse. A multi-functional mounting platform is provided between the four support rods. The multi-functional mounting platform is provided with mounting holes. The large space at the bottom of the UAV can be used to mount a variety of functional components, such as loudspeakers, cameras, high-power lighting, etc. to meet the needs of different work scenarios. This UAV is characterized by reconfigurability, multi-load, easy installation, and strong expansion capability. It can be used in many scenarios such as rescue, exploration, lighting, networking communication, logistics, etc.

[0004] However, the above technical solution still has certain defects. When the UAV is landing, it cannot achieve a perfect uniform landing when the UAV power is cut off, so the UAV will inevitably be subjected to a certain impact force when landing. When the UAV is fully loaded with cargo, the weight of the entire machine is large, resulting in an increase in the impact force of the UAV hitting the ground during landing, which makes the UAV's supporting legs easily damaged, and the impact force is transmitted to the UAV host, which can easily cause damage to the internal electronic components. For this reason, a UAV with a one-machine multi-payload structure is proposed. Utility Model Content

[0005] Based on this, the purpose of the present invention is to provide a one-machine multi-payload structure UAV to solve the technical problems raised in the above background.

[0006] To achieve the above-mentioned objectives, the present invention provides the following technical solutions: a single-machine, multi-payload structure drone, comprising a drone body, the drone body comprising a main engine, a transport compartment provided at the bottom end of the main engine, multiple sets of support legs fixedly connected to the side walls of the main engine, the support legs being made of elastic plastic, a set of secondary batteries slidably connected to each side of the main engine, and multiple sets of buffer mechanisms provided between the support legs and the transport compartment;

[0007] The buffer mechanism includes a guide rod, which is fixedly connected to the side wall of the transport bin, a support rod is slidably sleeved on the outer wall of the guide rod, a clamping block is fixedly connected to the end of the support rod, and the clamping block is slidably sleeved on the outer wall of the support leg, and the side wall of the transport bin is fixedly connected to a friction rod located next to the guide rod, and the inner wall of the support rod is slidably connected to a friction block extending to the outside of the support rod, and the friction block slides and fits on the outer wall of the friction rod.

[0008] As an optimal technical solution for the one-machine-multiple-load structure UAV of the present invention, a slide groove is provided at the bottom end of the main machine, and the transport compartment is slidably connected inside the slide groove.

[0009] As an optimal technical solution for a one-machine multi-load structure UAV of the utility model, the inner wall of the transport bin is slidably connected with two groups of limit pins extending to the transport bin, and a return spring located inside the transport bin is fixedly connected between the two groups of limit pins.

[0010] As an optimal technical solution for a one-machine, multi-load structure drone of the utility model, the side wall of the main engine is fixedly connected to multiple groups of arms, the end of each arm is fixedly connected to a group of brushless motors, and the output end of each brushless motor is fixedly connected to a group of blades.

[0011] As an optimal technical solution for a one-machine, multi-load structure UAV of the utility model, the bottom ends of the two groups of support legs on the same side are fixedly connected with support bars, the cross-section of the support bars is a downward curved arc, and the cross-section of the support legs near the top is a pentagon.

[0012] As an optimal technical solution for a one-machine multi-load structure UAV of the present invention, one end of the friction block located inside the support rod is fixedly connected to a spring sheet, and the end of the spring sheet is fixedly connected to the inner wall of the support rod.

[0013] As an optimal technical solution for a one-machine multi-load structure drone of the utility model, the top end of the support rod is fixedly connected to a support spring, the support spring is sleeved on the outer wall of the guide rod, and the top end of the support spring is fixedly connected to the top end of the guide rod.

[0014] In summary, the present invention has the following beneficial effects:

[0015] 1. After the transport compartment is connected to the main unit and filled with cargo, the weight of the entire drone is relatively large. During landing, the impact force is transmitted to the support legs and clamping blocks through the support bars, causing the support legs to bend and the support rods to be pushed. The impact force is then buffered and dissipated by the support springs and the friction between the module and the friction rod, thus preventing the main unit from being damaged by a large impact.

[0016] 2. The utility model arranges two sets of auxiliary batteries on the side wall of the main body, thereby improving the endurance of the drone body when long-distance flight is required. When long-distance flight is not required, the auxiliary batteries are removed, thereby reducing the overall weight of the drone body, making the drone body more flexible, and providing a transport compartment to expand the functions of the drone body and improve the practicality of the drone body. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the main structure of the utility model;

[0018] Figure 2 This is a schematic diagram of the bottom-up structure of the present invention;

[0019] Figure 3 This is a schematic diagram of the explosion structure of the utility model;

[0020] Figure 4 This is a schematic diagram of the main structure of the buffer structure of the present utility model;

[0021] Figure 5 This is a schematic diagram of the cross-sectional structure of the support rod of the present invention.

[0022] In the figure: 1. UAV body; 2. Buffer mechanism;

[0023] 101. Main unit; 102. Secondary battery; 103. Support arm; 104. Brushless motor; 105. Propeller blades; 106. Support legs; 107. Support bar; 108. Slide; 109. Transport compartment; 110. Limit pin.

[0024] 201. Guide rod; 202. Support rod; 203. Support spring; 204. Clamping block; 205. Friction rod; 206. Friction block; 207. Spring sheet. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. The embodiments described below with reference to the drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0026] The following describes an embodiment of the present invention based on its overall structure.

[0027] A UAV with a multi-load structure, such as Figures 1 to 5 As shown, the drone body 1 includes a main unit 101, a transport compartment 109 is provided at the bottom of the main unit 101, multiple sets of support legs 106 are fixedly connected to the side walls of the main unit 101, and the support legs 106 are made of elastic plastic. A set of secondary batteries 102 are slidably connected to both sides of the main unit 101, and multiple sets of buffer mechanisms 2 are provided between the support legs 106 and the transport compartment 109;

[0028] The buffer mechanism 2 includes a guide rod 201, which is fixedly connected to the side wall of the transport bin 109, and the outer wall of the guide rod 201 is slidably sleeved with a support rod 202, and the end of the support rod 202 is fixedly connected to a clamping block 204, which is slidably sleeved on the outer wall of the support leg 106. The side wall of the transport bin 109 is fixedly connected to a friction rod 205 located next to the guide rod 201, and the inner wall of the support rod 202 is slidably connected to a friction block 206 extending to the outside of the support rod 202, and the friction block 206 slides and fits on the outer wall of the friction rod 205. One end of the friction block 206 located inside the support rod 202 is fixedly connected to a spring sheet 207, and the end of the spring sheet 207 is fixedly connected to the inner wall of the support rod 202. The top of the support rod 202 is fixedly connected to a support spring 203, which is sleeved on the outer wall of the guide rod 201, and the top of the support spring 203 is fixedly connected to the top of the guide rod 201.

[0029] When the drone body 1 lands, the support bar 107 is subjected to the impact force, causing the support leg 106 to bend to a certain extent, and under the push of the support bar 107, the clamping block 204 drives the support rod 202 to move upward, causing the support rod 202 to compress the support spring 203. In the process of the support rod 202 moving upward, it drives the friction block 206 to move upward, so that the friction block 206 rubs against the outside of the friction rod 205, and the friction force between the friction block 206 and the friction rod 205 is consumed. The process of compression and rebound of the support spring 203 provides a flexible supporting force, avoiding the impact force of the drone being rigidly borne by the landing, and having a buffering effect.

[0030] Please refer to Figure 1 、 Figure 2 and Figure 3The inner wall of the transport bin 109 is slidably connected with two groups of limit pins 110 extending to the transport bin 109, and a return spring located inside the transport bin 109 is fixedly connected between the two groups of limit pins 110. The side wall of the main unit 101 is fixedly connected with multiple groups of support arms 103, and the end of each support arm 103 is fixedly connected with a group of brushless motors 104, and the output end of each brushless motor 104 is fixedly connected with a group of blades 105. The bottom ends of the two groups of support legs 106 on the same side are fixedly connected with support bars 107. The cross section of the support bar 107 is a downward curved arc, and the cross section of the support leg 106 near the top is a pentagon.

[0031] The special shape of the top of the support bar 107 and the support leg 106 reduces the wind resistance at the top of the support bar 107 and the top of the support leg 106, so that the blades 105 reduce the wind resistance of the support leg 106 and the support bar 107 in the process of pushing the airflow downward, thereby avoiding power loss to a certain extent. By sliding the two sets of secondary batteries 102 on both sides of the main body 101, the endurance of the drone body 1 is greatly improved, thereby improving the endurance of the drone body 1 when long-distance flight is required. When long-distance flight is not required, the secondary batteries 102 are removed, thereby reducing the overall weight of the drone body 1, making the drone body 1 more flexible. When there is no need to transport items, by pushing the two sets of limit pins 110 closer together, the limit pins 110 slide into the interior of the transport compartment 109, and then pushing the transport compartment 109 to slide out of the slide slot 108, the buffer mechanism 2 and the transport compartment 109 are separated from the drone body 1, thereby further reducing the weight of the entire machine.

[0032] During use, after the transport compartment 109 is connected to the main unit 101 and the interior of the transport compartment 109 is filled with cargo, the weight of the entire drone is relatively large. When landing, the impact force is transmitted to the support leg 106 and the clamping block 204 through the support bar 107, causing the support leg 106 to bend and the support rod 202 to be pushed. Then, the support spring 203 and the friction between the module and the friction rod 205 are used to buffer and consume the impact force, thereby preventing the main unit 101 from being damaged by a large impact. The parts not involved in the device are the same as the existing technology or can be implemented using existing technology.

[0033] Although embodiments of the present invention have been shown and described, these specific embodiments are merely explanations of the present invention and are not limitations on the present invention. The specific features, structures, materials, or characteristics described may be combined in a suitable manner in any one or more embodiments or examples. After reading this specification, those skilled in the art may make modifications, substitutions, and variations to the embodiments as needed without departing from the principles and purpose of the present invention, but as long as they are within the scope of the claims of the present invention, they are protected by patent law.

Claims

1. A multi-load UAV, comprising a UAV body (1), characterized in that: The drone body (1) comprises a main unit (101), a transport chamber (109) is provided at the bottom end of the main unit (101), a plurality of support legs (106) are fixedly connected to the side walls of the main unit (101), the support legs (106) are made of elastic plastic, a group of secondary batteries (102) are slidably connected to both sides of the main unit (101), and a plurality of buffer mechanisms (2) are provided between the support legs (106) and the transport chamber (109); The buffer mechanism (2) comprises a guide rod (201), the guide rod (201) being fixedly connected to the side wall of the transport bin (109), the outer wall of the guide rod (201) being slidably sleeved with a support rod (202), the end of the support rod (202) being fixedly connected with a clamping block (204), the clamping block (204) being slidably sleeved on the outer wall of the support leg (106), the side wall of the transport bin (109) being fixedly connected with a friction rod (205) located next to the guide rod (201), the inner wall of the support rod (202) being slidably connected with a friction block (206) extending to the outside of the support rod (202), and the friction block (206) being slidably fitted on the outer wall of the friction rod (205).

2. The UAV with a multi-load structure according to claim 1, characterized in that: A chute (108) is provided at the bottom end of the main machine (101), and the transport bin (109) is slidably connected inside the chute (108).

3. The UAV with a multi-load structure according to claim 1, characterized in that: Two groups of limit pins (110) extending to the transport bin (109) are slidably connected to the inner wall of the transport bin (109), and a return spring located inside the transport bin (109) is fixedly connected between the two groups of limit pins (110).

4. The UAV with a multi-load structure according to claim 1, characterized in that: The side wall of the main machine (101) is fixedly connected to a plurality of support arms (103), the end of each support arm (103) is fixedly connected to a group of brushless motors (104), and the output end of each brushless motor (104) is fixedly connected to a group of blades (105).

5. The UAV with a multi-load structure according to claim 1, characterized in that: The bottom ends of the two groups of support legs (106) on the same side are fixedly connected with support bars (107), the cross section of the support bar (107) is a downwardly curved arc, and the cross section of the support legs (106) at the top end is a pentagon.

6. The UAV with a multi-load structure according to claim 1, characterized in that: One end of the friction block (206) located inside the support rod (202) is fixedly connected to a spring sheet (207), and the end of the spring sheet (207) is fixedly connected to the inner wall of the support rod (202).

7. The UAV with a multi-load structure according to claim 1, characterized in that: The top end of the support rod (202) is fixedly connected to a support spring (203), the support spring (203) is sleeved on the outer wall of the guide rod (201), and the top end of the support spring (203) is fixedly connected to the top end of the guide rod (201).

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