Unmanned aerial vehicle with pod

Abstract

The invention relates to the technical field of unmanned aerial vehicle devices, in particular to an unmanned aerial vehicle with a pod, which comprises a fuselage, two ducted rotors are fixedly mounted on two sides of the upper end of the fuselage respectively, a belly is fixedly mounted at the lower end of the fuselage, and two cooling air pipes are fixedly mounted on one side of a mounting seat. Eddy current driving mechanisms are fixedly mounted in the two cooling air pipes correspondingly, and a distance adjusting lifting mechanism is slidably mounted at the lower end of each sliding way. The unmanned aerial vehicle carries a heat dissipation system formed by combining the vortex driving mechanism and the cooling air pipe, external airflow is introduced into the air inlet pipe, high-speed vortex is formed in the cooling air pipe after being accelerated by the vortex engine, heat of an oil tank, a hydraulic pump motor and other core components can be rapidly taken away, hot airflow can be discharged in time through the pressure relief air pipe and the exhaust pipe, and heat accumulation is avoided. In the aspect of load adaptability, the device can adapt to cargo hold or pod loads of different sizes and shapes. Loads can be flexibly replaced according to requirements, and the application range of industrial-grade and special-grade applications is expanded.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) device technology, and more particularly to a UAV with a pod. Background Technology

[0002] Unmanned aerial vehicles (UAVs) are unmanned aircraft controlled by radio remote control equipment or onboard computer program control systems. They can be categorized into consumer-grade, industrial-grade, and special-purpose UAVs, integrating core technologies such as flight control, power, sensing, and communication, and possessing capabilities such as autonomous flight and payload carrying. Their applications cover multiple fields: consumer-grade UAVs are used for aerial photography and entertainment; industrial-grade UAVs can achieve efficient operations such as power line inspection, agricultural plant protection, and surveying and modeling; and special-purpose UAVs play a crucial role in security monitoring, emergency rescue, and military reconnaissance, overcoming the spatial and environmental limitations of human operations. Currently, some UAVs have begun to incorporate ant colony optimization algorithms to optimize flight path planning, improving mission execution efficiency and path safety. However, hardware performance limitations still restrict the full realization of the advantages of ant colony algorithms.

[0003] Regarding heat dissipation systems, traditional drones often rely on simple air cooling or basic liquid cooling structures, resulting in low heat dissipation efficiency. Core components such as fuel tanks, hydraulic pumps, and motors are prone to heat buildup during prolonged operation, potentially leading to power failures and preventing the drone from maintaining the long-range flight path planned by the ant colony algorithm, thus affecting mission continuity. In terms of payload adaptability, existing drone payload structures are mostly fixed designs, only compatible with cargo holds or pods of specific sizes. Even with efficient material transport routes planned using ant colony algorithms, the limited payload adaptability restricts the flexibility of changing equipment, limiting application expansion in industrial and special-purpose scenarios. Furthermore, traditional support structures lack effective cushioning, making the payload susceptible to impact damage during takeoff and landing, further reducing the reliability of drone operations. Summary of the Invention

[0004] The purpose of this invention is to address the shortcomings of the prior art by proposing a drone with a pod.

[0005] To achieve the above objectives, the technical solution adopted by the present invention is as follows: a drone with a pod, comprising a fuselage, two ducted rotors fixedly mounted on the upper sides of the fuselage, a belly fixedly mounted on the lower end of the fuselage, a carrier plate fixedly mounted between the fuselage and the belly, four equally spaced partition plates fixedly mounted on the upper end of the carrier plate, an oil tank fixedly mounted between two of the middle partition plates, a mounting base fixedly mounted on the upper end of the carrier plate on one side of the oil tank, two cooling air pipes fixedly mounted on one side of the mounting base, a vortex drive mechanism fixedly mounted inside each of the two cooling air pipes, an air pipe fixing seat fixedly mounted on the upper end of the cooling air pipes, a fixed base plate fixedly mounted on the lower end of the belly, support legs fixedly mounted on the four corners of the lower end of the fixed base plate, slide rails fixedly mounted on both sides of the lower end of the fixed base plate, an adjustable distance lifting mechanism slidably mounted on the lower end of each slide rail, and a cargo hold movably mounted on the lower end of the fixed base plate.

[0006] As a preferred technical solution of the present invention, a fixed boss is fixedly installed on one side of the carrier plate, a flight control cabin is fixedly installed on the upper end of the fixed boss, a battery pack is fixedly installed on the upper end of the carrier plate on the side of the flight control cabin, a battery management module is fixedly installed on the upper end of the carrier plate on the side of the battery pack, a hydraulic pump motor is fixedly installed on the upper end of the carrier plate on the side of the fuel tank, and a liquid-cooled oil tank is fixedly installed on the side of the fuel tank and the hydraulic pump motor.

[0007] As a preferred technical solution of the present invention, the air pipe fixing seat has an air pipe clearance groove inside, an exhaust pipe is fixedly installed on one side of the upper surface of the air pipe fixing seat, the exhaust pipe is connected to the air pipe clearance groove, both cooling air pipes pass through the air pipe clearance groove, symmetrical air inlet pipes are fixedly installed on the upper left side of the air pipe fixing seat, the air inlet pipes are fixedly installed on the upper surface of the machine body, and the air inlet pipes pass through the air pipe fixing seat and connect to the interior of the cooling air pipes, and a pressure relief air pipe is fixedly installed at the outer end of each cooling air pipe.

[0008] As a preferred technical solution of the present invention, the vortex drive mechanism further includes a drive gear fixedly installed on one side of the oil tank, and vortex engines are rotatably installed inside the two cooling air pipes. Each vortex engine has a follower gear fixedly installed at its rear end, and the follower gear is located at both ends of the drive gear and meshes with it.

[0009] As a preferred embodiment of the present invention, each of the supporting legs is rotatably mounted with a support leg at its lower end, a buffer pressure rod is rotatably mounted between the rear surface and the front surface of the support leg, and a support base plate is rotatably mounted at the lower end of the support leg.

[0010] As a preferred technical solution of the present invention, the adjustable lifting mechanism further includes a telescopic rod fixedly installed on the inner side of each of the slides, an adjustable block fixedly installed at the output end of the telescopic rod, and a support rod fixedly installed at the lower end of the adjustable block.

[0011] As a preferred technical solution of the present invention, a limiting plate is fixedly installed at the lower end of the support rod, and sliding grooves are provided on both sides of the support rod. A slider is slidably installed inside the sliding groove, and an L-shaped support plate is fixedly installed on the opposite inner side of the slider.

[0012] As a preferred technical solution of the present invention, four connecting columns are installed through the four partition plates. The connecting columns are fixedly installed between two relatively outer partition plates and penetrate through the two middle partition plates. The air tube fixing seat and the carrier plate both penetrate through the partition plates.

[0013] Compared with the prior art, the present invention has the following beneficial effects: 1. In terms of heat dissipation, this UAV is equipped with a cooling system combining a vortex drive mechanism and cooling air pipes. The intake pipe draws in external airflow, which, after being accelerated by the vortex engine, forms a high-speed vortex within the cooling air pipe. This quickly removes heat from core components such as the fuel tank, hydraulic pump motor, etc. The pressure relief pipe and exhaust pipe also promptly expel hot airflow, preventing heat buildup. Compared to traditional UAVs that rely solely on air cooling or simple liquid cooling, this system enhances airflow circulation through vortexes, significantly improving heat dissipation efficiency. This effectively prevents power system failures caused by high temperatures, ensuring the stability of the UAV during long-term operation. This advantage, combined with the long-range planning capabilities of the ant colony algorithm, enables the UAV to operate sustainably and stably for long-distance missions in complex environments, such as cross-regional material transportation and large-scale inspections, without the need for frequent mid-flight landings for heat dissipation.

[0014] 2. Regarding payload adaptability, the UAV is equipped with a sliding adjustable-distance lifting mechanism. The telescopic rod drives the adjustable block to move along the slide, flexibly adjusting the lifting distance. Combined with the L-shaped and limiting plates on the support rod, it can adapt to cargo holds or pods of different sizes and shapes. Simultaneously, the buffer pressure rods at the support legs can cushion load impacts during takeoff and landing, reducing the impact of turbulence on the cargo. In contrast, traditional UAV payload mounting structures are mostly fixed designs with poor adaptability. This design allows the UAV to flexibly change payloads according to needs in logistics transportation, material delivery, and other scenarios, expanding its applicability to industrial and special-purpose applications. Combined with the scenario adaptability of the ant colony algorithm, the UAV can quickly adjust its payload status based on the real-time planned mission objectives, such as medical supply delivery in emergency rescue or equipment mounting in military reconnaissance, further improving the flexibility and efficiency of mission execution. Attached Figure Description

[0015] Figure 1This is a schematic diagram of the structure of a drone with a pod according to the present invention; Figure 2 This is a schematic diagram of another perspective of the structure of a drone with a pod according to the present invention; Figure 3 This is a partial structural diagram of an unmanned aerial vehicle (UAV) with a pod according to the present invention; Figure 4 This is a cross-sectional view of the fuselage of a drone with a pod according to the present invention; Figure 5 This is a partial structural diagram of the fuel tank of a drone with a pod according to the present invention; Figure 6 This is a schematic diagram of the air tube mounting structure for a drone with a pod according to the present invention. Figure 7 This is a cross-sectional view of the air tube mounting base for a drone with a pod according to the present invention. Figure 8 This is a schematic diagram of the fixed base plate structure of an unmanned aerial vehicle with a pod according to the present invention; Figure 9 This invention relates to a drone with a pod. Figure 8 Enlarged view of point A in the middle.

[0016] The attached diagram lists the components represented by each number as follows: 1. Fuselage; 2. Fuselage belly; 3. Exhaust pipe; 4. Air intake pipe; 5. Ducted rotor; 6. Cargo hold; 7. Fixed base plate; 8. Pressure relief pipe; 9. Cooling pipe; 10. Fixed boss; 11. Flight control cabin; 12. Partition plate; 13. Connecting column; 14. Mounting base; 15. Fuel tank; 16. Liquid-cooled fuel tank; 17. Hydraulic pump motor; 18. Battery pack; 9. Battery management module; 20. Carrier plate; 21. Drive gear; 22. Follower gear; 23. Vortex engine; 24. Support leg; 25. Support leg; 26. Support base plate; 27. Buffer pressure rod; 28. Slide rail; 29. ​​Telescopic rod; 30. Support rod; 31. Limiting support plate; 32. Slide groove; 33. Slider; 34. L-shaped support plate; 35. Air pipe fixing seat; 36. Air pipe clearance groove; 37. Adjustment block. Detailed Implementation

[0017] The following description is intended to disclose the invention and enable those skilled in the art to implement it. The preferred embodiments described below are merely examples, and other obvious variations will occur to those skilled in the art.

[0018] like Figures 1-9The UAV with a pod shown includes a fuselage 1. Two ducted rotors 5 are fixedly installed on both sides of the upper end of the fuselage 1. An underbody 2 is fixedly installed on the lower end of the fuselage 1. A carrier plate 20 is fixedly installed between the fuselage 1 and the underbody 2. Four equally spaced partition plates 12 are fixedly installed on the upper end of the carrier plate 20. A fuel tank 15 is fixedly installed between two of the middle partition plates 12. A mounting base 14 is fixedly installed on the upper end of the carrier plate 20 on one side of the fuel tank 15. Two cooling air pipes 9 are fixedly installed on one side of the mounting base 14. A vortex drive mechanism is fixedly installed inside each of the two cooling air pipes 9. An air pipe fixing seat 35 is fixedly installed on the upper end of the cooling air pipes 9. A fixed base plate 7 is fixedly installed on the lower end of the underbody 2. Support legs 24 are fixedly installed at the four corners of the lower end of the fixed base plate 7. Slide rails 28 are fixedly installed on both sides of the lower end of the fixed base plate 7. An adjustable lifting mechanism is slidably installed at the lower end of each slide rail 28. A cargo compartment 6 is movably installed on the lower end of the fixed base plate 7.

[0019] A fixed boss 10 is fixedly installed on one side of the carrier plate 20. A flight control cabin 11 is fixedly installed on the upper end of the fixed boss 10. A battery pack 18 is fixedly installed on the upper end of the carrier plate 20 on the side of the flight control cabin 11. A battery management module 19 is fixedly installed on the upper end of the carrier plate 20 on the side of the battery pack 18. A hydraulic pump motor 17 is fixedly installed on the upper end of the carrier plate 20 on the side of the fuel tank 15. A liquid-cooled fuel tank 16 is fixedly installed on the side of the fuel tank 15 and the hydraulic pump motor 17.

[0020] An oil tank 15 is installed between the two partition plates 12 in the middle position to store fuel and provide energy for the hydraulic pump motor 17 and the eddy current drive mechanism. The hydraulic pump motor 17 is equipped on one side of the oil tank 15. It is the power source of the UAV hydraulic system and is responsible for driving the hydraulic components. A liquid-cooled oil tank 16 is set next to the oil tank 15 and the hydraulic pump motor 17 to preliminarily cool the hydraulic oil of the hydraulic pump motor 17 and help maintain the normal operating temperature of the hydraulic system.

[0021] The flight control cabin 11 is installed on the fixed boss 10 on one side of the carrier plate 20. As the control core of the UAV, it can plan the flight path by combining ant colony algorithm, adjust the rotor speed and flight attitude in real time, and coordinate the work of various systems. Next to the flight control cabin 11, the battery pack 18 and the battery management module 19 are arranged in sequence. The battery pack 18 supplies power to the flight control cabin 11, hydraulic pump motor 17 and other electrical components, while the battery management module 19 monitors the power, voltage and working status of the battery pack 18 in real time to ensure stable power output.

[0022] Two cooling air pipes 9 are fixed on the mounting base 14 on one side of the fuel tank 15, which are the core channels of the UAV's efficient heat dissipation system. The upper end of the cooling air pipe 9 is fixed by the air pipe fixing seat 35. The air pipe fixing seat 35 has an air pipe clearance groove 36 inside, through which the cooling air pipe 9 passes. Two symmetrical air inlets 4 on the upper left side of the air pipe 9 pass through the upper surface of the fuselage 1 and the air pipe fixing seat 35, which are responsible for introducing external airflow. The exhaust pipe 3 on the upper surface of the air pipe fixing seat 35 is connected to the air pipe clearance groove 36 and is used to discharge hot airflow. Each cooling air pipe 9 also has a pressure relief air pipe 8 at its outer end, which can quickly release the high-pressure hot airflow in the cooling air pipe and prevent heat accumulation.

[0023] Each cooling air pipe 9 is equipped with a vortex drive mechanism, which includes a drive gear 21 fixed to one side of the oil tank 15, a vortex engine 23 rotatably mounted inside the cooling air pipe 9, and a follower gear 22 at the rear end of the vortex engine 23. The follower gear 22 meshes with the drive gear 21. When the drive gear 21 rotates, it drives the follower gear 22 to work synchronously with the vortex engine 23, accelerating the airflow introduced by the intake pipe 4 to form a high-speed vortex, which quickly removes heat from core components such as the oil tank 15 and the hydraulic pump motor 17.

[0024] The vortex drive mechanism also includes a drive gear 21 fixedly installed on one side of the oil tank 15. Two vortex engines 23 are rotatably installed inside the two cooling air pipes 9. Each vortex engine 23 has a follower gear 22 fixedly installed at its rear end. The follower gear 22 is located at both ends of the drive gear 21 and meshes with it.

[0025] The support legs 24 at the four corners of the lower end of the fixed base plate 7 are the core support for the take-off and landing of the UAV. The lower end of the support leg 24 is rotatably connected to the outrigger 25, and the lower end of the outrigger 25 is equipped with the support base plate 26 to increase the contact area with the ground and improve the stability of take-off and landing. A buffer pressure rod 27 is rotatably installed between the support leg 24 and the outrigger 25. When the UAV lands, the outrigger 25 rotates under the reaction force of the ground, and the buffer pressure rod 27 absorbs the impact force through hydraulic damping to prevent the load from being damaged by bumps and impacts. When taking off, the buffer pressure rod 27 resets and drives the outrigger 25 back to its initial position.

[0026] A set of adjustable-distance lifting mechanisms is slidably installed on each of the slide rails 28 on both sides of the lower end of the fixed base plate 7 to adapt to cargo holds 6 or pod loads of different sizes and shapes. The mechanism includes a telescopic rod 29 inside the slide rail 28, the output end of which is connected to an adjustable-distance block 37, which can drive the adjustable-distance block 37 to slide along the slide rail 28 to adjust the distance between the two lifting mechanisms; the support rod 30 at the lower end of the adjustable-distance block 37 is the main load-bearing component, and the limiting plate 31 at the lower end of the support rod 30 is used to support the bottom of the load. The slider 33 is slidably installed in the slide grooves 32 on both sides of the support rod 30. The slider 33 can move up and down with the inner L-shaped support plate 34, clamping the load from both sides to achieve stable lifting of different loads.

[0027] Four connecting posts 13 are installed through the four partition plates 12. The connecting posts 13 are fixedly installed between two relatively outer partition plates 12. The connecting posts 13 pass through the two middle partition plates 12. The air tube fixing seat 35 and the carrier plate 20 both pass through the partition plates 12.

[0028] Working principle: The UAV's flight power is provided by four ducted rotors 5 on both sides of the upper part of the fuselage 1. After the ducted rotors 5 start, they generate lift, which drives the fuselage 1 and the belly 2 to take off as a whole. The battery pack 18 on the carrier plate 20 supplies power to electrical components such as the flight control cabin 11 and the hydraulic pump motor 17. The battery management module 19 monitors the power and working status of the battery pack 18 in real time to ensure stable power output. The fuel tank 15 stores fuel to provide energy support for the hydraulic pump motor 17 and the eddy current drive mechanism. The liquid-cooled oil tank 16 provides preliminary cooling for the hydraulic oil of the hydraulic pump motor 17, helping the core components maintain normal operating temperature.

[0029] During drone operation, core components such as the fuel tank 15 and hydraulic pump motor 17 continuously generate heat. At this time, the heat dissipation system composed of the vortex drive mechanism and the cooling air pipe 9 is activated. First, the drive gear 21 rotates, driving the follower gear 22 meshing at both ends to rotate synchronously, thereby driving the vortex engine 23 inside the cooling air pipe 9 to work. External airflow enters the cooling air pipe 9 through the air intake pipe 4 on the upper surface of the fuselage 1. After being accelerated by the vortex engine 23, it forms a high-speed vortex inside the cooling air pipe 9. The vortex flows quickly past the outside of the fuel tank 15 and hydraulic pump motor 17, carrying away the heat from the surface of the components. Part of the heat-absorbing airflow is directly discharged through the pressure relief pipe 8 at the outer end of the cooling air pipe 9, and the other part is collected through the air pipe clearance groove 36 in the air pipe fixing seat 35 and discharged outside the fuselage 1 through the exhaust pipe 3, forming a complete airflow circulation and preventing heat from accumulating inside the fuselage 1.

[0030] Before mounting the cargo hold 6 or other pod loads, the adjustable lifting mechanism is first adjusted: the telescopic rods 29 on the slide rails 28 on both sides of the fixed base plate 7 extend or retract, causing the adjustable block 37 to slide along the slide rail 28, thereby adjusting the distance between the two support rods 30 to accommodate loads of different widths. Subsequently, according to the height of the load, the sliders 33 in the slide grooves 32 on both sides of the sliding support rod 30 adjust the height of the L-shaped support plate 34, so that the limiting support plate 31 supports the bottom of the load, and the L-shaped support plate 34 clamps the sides of the load from both sides, achieving stable lifting of loads of different sizes and shapes, ensuring that the load will not shift or fall off during the flight of the UAV.

[0031] When the drone lands, the lower leg 25 of the support leg 24 contacts the ground first. The reaction force from the ground causes the leg 25 to rotate around the connection point with the support leg 24. At this time, the buffer damping rod 27 between the support leg 24 and the leg 25 is compressed, absorbing the impact force during takeoff and landing through hydraulic damping, preventing the load from being damaged by bumps and impacts. The support base plate 26 increases the contact area with the ground, further improving the stability of the drone during takeoff and landing. During the takeoff phase, the buffer damping rod 27 resets, driving the leg 25 back to its initial position, preparing for subsequent flight.

[0032] The flight control cabin 11, as the control core of the UAV, can adjust the rotational speed and flight attitude of the ducted rotor 5 in real time based on the flight path planned by the ant colony algorithm, while coordinating the working status of the heat dissipation system and the pitch control mechanism. For example, in long-range material transportation missions, the heat dissipation system continuously and efficiently dissipates heat, ensuring that the UAV flies stably along the path planned by the algorithm; if it is necessary to change the work payload, the pitch control mechanism can quickly adjust to adapt to the new pod, allowing the UAV to flexibly respond to different mission requirements.

[0033] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed invention. The scope of protection claimed by the appended claims and their equivalents is defined.

Claims

1. A drone with a pod, comprising a fuselage (1), characterized in that: Two ducted rotors (5) are fixedly installed on both sides of the upper end of the fuselage (1). An underbelly (2) is fixedly installed on the lower end of the fuselage (1). A carrier plate (20) is fixedly installed between the fuselage (1) and the underbelly (2). Four equally spaced partition plates (12) are fixedly installed on the upper end of the carrier plate (20). A fuel tank (15) is fixedly installed between two of the middle partition plates (12). A mounting base (14) is fixedly installed on the upper end of the carrier plate (20) on one side of the fuel tank (15). A mounting base (14) is fixedly installed on one side of the mounting base (14). Two cooling air pipes (9) are provided, and a vortex drive mechanism is fixedly installed inside each of the two cooling air pipes (9). A pipe fixing seat (35) is fixedly installed at the upper end of the cooling air pipe (9). A fixed base plate (7) is fixedly installed at the lower end of the fuselage (2). Support legs (24) are fixedly installed at the four corners of the lower end of the fixed base plate (7). Slide rails (28) are fixedly installed on both sides of the lower end of the fixed base plate (7). An adjustable distance lifting mechanism is slidably installed at the lower end of each slide rail (28). A cargo hold (6) is movably installed at the lower end of the fixed base plate (7).

2. The unmanned aerial vehicle with a pod according to claim 1, characterized in that: A fixed boss (10) is fixedly installed on one side of the carrier plate (20). A flight control cabin (11) is fixedly installed on the upper end of the fixed boss (10). A battery pack (18) is fixedly installed on the upper end of the carrier plate (20) on the side of the flight control cabin (11). A battery management module (19) is fixedly installed on the upper end of the carrier plate (20) on the side of the battery pack (18). A hydraulic pump motor (17) is fixedly installed on the upper end of the carrier plate (20) on the side of the fuel tank (15). A liquid-cooled oil tank (16) is fixedly installed on the side of the fuel tank (15) and the hydraulic pump motor (17).

3. The unmanned aerial vehicle with a pod according to claim 1, characterized in that: The air pipe mounting base (35) has an air pipe clearance groove (36) inside. An exhaust pipe (3) is fixedly installed on one side of the upper surface of the air pipe mounting base (35). The exhaust pipe (3) is connected to the air pipe clearance groove (36). Both cooling air pipes (9) pass through the air pipe clearance groove (36). Symmetrical air inlet pipes (4) are fixedly installed on the left side of the upper end of the air pipe mounting base (35). The air inlet pipes (4) are fixedly installed on the upper surface of the fuselage (1). The air inlet pipes (4) pass through the air pipe mounting base (35) and connect to the interior of the cooling air pipes (9). A pressure relief pipe (8) is fixedly installed at the outer end of each cooling air pipe (9).

4. The unmanned aerial vehicle with a pod according to claim 1, characterized in that: The vortex drive mechanism also includes a drive gear (21) fixedly installed on one side of the oil tank (15). Both cooling air pipes (9) are rotatably installed with vortex engines (23). Each vortex engine (23) has a follower gear (22) fixedly installed at its rear end. The follower gear (22) is located at both ends of the drive gear (21) and meshes with it.

5. The unmanned aerial vehicle with a pod according to claim 1, characterized in that: Each of the support legs (24) is rotatably mounted with a support leg (25) at its lower end. A buffer pressure rod (27) is rotatably mounted between the rear surface of the support leg (24) and the front surface of the support leg (25). A support base plate (26) is rotatably mounted at the lower end of the support leg (25).

6. The unmanned aerial vehicle with a pod according to claim 1, characterized in that: The adjustable lifting mechanism also includes a telescopic rod (29) fixedly installed on the inner side of each slide (28), with an adjustable block (37) fixedly installed at the output end of the telescopic rod (29), and a support rod (30) fixedly installed at the lower end of the adjustable block (37).

7. A drone with a pod according to claim 6, characterized in that: The lower end of the support rod (30) is fixedly installed with a limiting plate (31). The support rod (30) has a sliding groove (32) on both sides. A slider (33) is slidably installed inside the sliding groove (32). An L-shaped support plate (34) is fixedly installed on the inner side of the slider (33).

8. The unmanned aerial vehicle with a pod according to claim 1, characterized in that: Four connecting columns (13) are installed through the four partition plates (12). The connecting columns (13) are fixedly installed between two relatively outer partition plates (12). The connecting columns (13) penetrate the two middle partition plates (12). The tracheal fixing seat (35) and the carrier plate (20) both penetrate the partition plates (12).

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