Novel air cylinder device of unmanned aerial vehicle engine

Abstract

The utility model relates to the technical field of engines, and discloses a novel air cylinder device of an unmanned aerial vehicle engine, which comprises a cylinder body, a cylinder skirt is fixedly connected to the lower surface of the cylinder body, a plurality of bolt holes are formed in the cylinder skirt in a penetrating manner, an exhaust passage is arranged on the outer wall of the cylinder body, and a plurality of connecting holes are formed in the outer wall of the exhaust passage in a penetrating manner. The outer wall of the cylinder body is fixedly connected with a plurality of cooling fins, and the cooling fins are in a wave shape. The lower surface of the cylinder body is fixedly connected with the cylinder skirt and provided with the bolt holes to achieve stable installation, the exhaust passage and the connecting holes are arranged on the outer wall of the cylinder body to optimize an exhaust emission path, meanwhile, the wavy cooling fin structure is adopted to greatly increase the heat dissipation area, and when an engine runs, the wavy cooling fins remarkably improve the airflow disturbance efficiency, so that the heat dissipation efficiency of the engine is improved. Heat loss is accelerated, the overheating problem of a traditional air cylinder under the high-load working condition of the unmanned aerial vehicle is effectively solved, and the service life of an engine is prolonged.

Description

Technical Field

[0001] This utility model relates to the field of engine technology, and in particular to a novel cylinder device for a drone engine. Background Technology

[0002] With the rapid development of drone technology, its application in fields such as military reconnaissance, logistics transportation, and agricultural monitoring is becoming increasingly widespread. As the core power unit of drones, the performance of the engine directly determines the drone's endurance, load efficiency, and flight stability. As a key component of the engine, the cylinder device's heat dissipation efficiency, structural strength, and lightweight level are crucial to the reliable operation of drones under extreme conditions such as high temperature and high altitude.

[0003] Currently, most drone engine cylinders use cast aluminum alloy cylinder blocks with rectangular or trapezoidal heat sinks distributed on the outer wall. Heat exchange is achieved through natural or forced air cooling. The bottom of the cylinder block is bolted to the crankcase via a flange. The internal intake and exhaust ports are straight-through. The piston top is mostly designed as a flat surface or shallow recess. This type of structure relies on the surface area of ​​the heat sink and the airflow speed for heat dissipation. The piston rings adopt a conventional rectangular ring structure. Power transmission is achieved through the classic connecting rod mechanism of piston pin, connecting rod and crankshaft.

[0004] However, UAVs often face heat dissipation bottlenecks during high-altitude, long-endurance missions. Traditional rectangular heat sinks have poor airflow guidance, and when air flows through the heat sinks, a laminar boundary layer is easily formed, resulting in low heat exchange efficiency. Especially in summer high-temperature or high-load climbing conditions, the cylinder temperature rises sharply, causing lubricating oil carbonization, piston ring sticking, and even cylinder deformation, which seriously restricts the engine's continuous operation capability and service life. Utility Model Content

[0005] To overcome the above shortcomings, this utility model provides a novel cylinder device for a drone engine, which aims to improve the poor airflow guidance of traditional rectangular heat sinks.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a novel cylinder device for a drone engine, comprising a cylinder body, a cylinder skirt fixedly connected to the lower surface of the cylinder body, a plurality of bolt holes through the interior of the cylinder skirt, an exhaust passage provided on the outer wall of the cylinder body, a plurality of connection holes through the outer wall of the exhaust passage, and a plurality of heat sinks fixedly connected to the outer wall of the cylinder body, the heat sinks being wavy in shape.

[0007] Furthermore, a mounting hole is provided through the upper surface of the cylinder block, and a spark plug is installed inside the mounting hole.

[0008] Furthermore, an air intake passage and an auxiliary air intake hole are provided through the inside of the cylinder.

[0009] Furthermore, a piston is provided inside the cylinder, and a protrusion is fixedly connected to the upper surface of the piston.

[0010] Furthermore, a compression ring and an oil ring are provided on the outer wall of the piston.

[0011] Furthermore, a connecting pin is fixedly connected inside the piston, and a connecting rod is rotatably connected inside the connecting pin.

[0012] Furthermore, a journal is fixedly connected to the inner wall of the connecting rod.

[0013] Furthermore, a crankshaft is rotatably connected to the outer wall of the journal.

[0014] This utility model has the following beneficial effects:

[0015] 1. In this utility model, a stable installation is achieved by fixing and connecting the cylinder skirt to the lower surface of the cylinder body and opening bolt holes. The exhaust passage and connection hole are set on the outer wall of the cylinder body to optimize the exhaust gas emission path. At the same time, the wave-shaped heat sink structure is adopted to greatly increase the heat dissipation area. When the engine is running, the wave-shaped heat sink significantly improves the airflow disturbance efficiency and accelerates heat dissipation, effectively solving the overheating problem of traditional cylinders under the high load conditions of UAVs and extending the service life of the engine.

[0016] 2. In this utility model, the intake passage and auxiliary intake hole inside the cylinder work together to form a dual-channel intake system. When the piston reciprocates in the cylinder, the protruding structure on its top effectively guides and compresses the mixed gas, promoting the formation of vortex. At the same time, the compression ring and oil ring on the outer wall of the piston fit tightly against the cylinder wall, ensuring the combustion chamber is sealed and effectively lubricated. Power is transmitted to the connecting rod through the connecting pin inside the piston, and then drives the crankshaft to rotate through the large end journal of the connecting rod. This optimized transmission path reduces internal friction loss and improves power transmission efficiency, making the UAV engine run more smoothly and respond more quickly. Attached Figure Description

[0017] Figure 1 This is a three-dimensional structural diagram of a novel cylinder device for an unmanned aerial vehicle engine proposed in this utility model;

[0018] Figure 2 This is a schematic diagram of the cylinder block structure of a novel cylinder device for an unmanned aerial vehicle engine proposed in this utility model;

[0019] Figure 3 This is a schematic diagram of the air intake structure of a novel cylinder device for a drone engine proposed in this utility model.

[0020] Figure 4 This is a schematic diagram of the auxiliary air intake structure of a novel cylinder device for an unmanned aerial vehicle engine proposed in this utility model;

[0021] Figure 5 This is a schematic diagram of the piston structure of a novel cylinder device for an unmanned aerial vehicle engine proposed in this utility model.

[0022] Legend:

[0023] 1. Cylinder block; 2. Cylinder skirt; 3. Bolt holes; 4. Radiator fins; 5. Exhaust passage; 6. Connecting hole; 7. Mounting hole; 8. Spark plug; 9. Intake passage; 10. Auxiliary intake port; 11. Piston; 12. Compression ring; 13. Oil ring; 14. Protrusion; 15. Connecting pin; 16. Connecting rod; 17. Journal; 18. Crankshaft. Detailed Implementation

[0024] 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.

[0025] Reference Figures 1-5This utility model provides an embodiment of a novel cylinder device for a drone engine, comprising a cylinder body 1. The cylinder body 1 is made of high-strength aluminum alloy casting, taking into account both lightweight and heat conduction requirements. A cylinder skirt 2 is fixedly connected to the lower surface of the cylinder body 1, and the extended structure enhances the bottom rigidity of the cylinder body 1, reducing the impact of thermal deformation. Multiple bolt holes 3 are evenly distributed inside the cylinder skirt 2, and high-strength bolts are used to achieve vibration suppression connection with the axle box. An exhaust passage 5 is provided on the outer wall of the cylinder body 1. The exhaust passage 5 has an optimized streamlined inner wall to reduce exhaust resistance. Multiple connection holes 6 are opened through the outer wall of the exhaust passage 5, and the flange interface ensures a sealed connection of the exhaust pipe. Multiple heat sinks 4 are fixedly connected to the outer wall of the cylinder body 1. The heat sinks 4 are radially arrayed and cover most of the surface of the cylinder body 1. The heat sinks 4 are wavy in shape, forcing airflow to generate turbulence to break through the laminar boundary layer. An installation hole 7 is opened through the upper surface of the cylinder body 1 to ensure that the spark plug electrode 8 extends into the combustion chamber in the optimal position for installation. Spark plug 8 is installed inside bore 7. Intake passage 9 is opened through the inside of cylinder 1. Auxiliary intake port 10 is opened through the inside of cylinder 1 to induce intake tumble and enhance the turbulence of the air-fuel mixture. Piston 11 is installed inside cylinder 1. The top is coated with nickel-based alloy to improve heat resistance. Protrusion 14 is fixedly connected to the upper surface of piston 11 to guide airflow to form a high-energy vortex at the end of compression. Compression ring 12 is opened on the outer wall of piston 11. It adopts a special shape sealing ring that can automatically adapt to cylinder deformation and effectively prevent high-pressure gas leakage. Oil ring 13 is opened on the outer wall of piston 11 with elastic oil scraping structure to precisely control the amount of lubricating oil on the cylinder wall, ensuring lubrication and avoiding excessive oil consumption. Connecting pin 15 is fixedly connected inside piston 11. The surface is carburized and the hardness is HRC60 or higher. Connecting rod 16 with I-shaped cross section design is rotatably connected inside connecting pin 15 to reduce weight. Journal 17 is fixedly connected to the inner wall of connecting rod 16. Crankshaft 18 is rotatably connected to the outer wall of journal 17.

[0026] Working principle: When this new type of cylinder device for UAV engines is required, the cylinder body 1 is first rigidly connected to the axle box through the bolt holes 3 inside the cylinder skirt 2 to ensure the stability of the overall structure. After the engine starts, external air enters the combustion chamber through the dual channels formed by the intake port 9 and the auxiliary intake port 10 inside the cylinder body 1, and mixes thoroughly with the atomized fuel. The piston 11 moves upward in the cylinder body 1 to compress the gas mixture, and the protrusion 14 on its top guides the airflow to form a high-intensity vortex. When the piston 11 approaches the top dead center, the spark plug 8 ignites the gas mixture in the mounting hole 7. The combustion pressure pushes the piston 11 downward. At this time, the compression ring 12 and oil ring on the outer wall of the piston 11... 13 seals the high-pressure gas in the combustion chamber and adjusts the thickness of the oil film on the cylinder wall. The reciprocating motion of the piston 11 is transmitted to the connecting rod 16 through the internal connecting pin 15. The journal 17 at the large end of the connecting rod 16 drives the crankshaft 18 to rotate and output power. The exhaust gas is efficiently discharged through the exhaust passage 5 on the outer wall of the cylinder block 1. The connecting hole 6 connects to the external exhaust pipe. At the same time, the wave-shaped heat sink 4 continuously generates turbulent disturbance in the airflow, accelerating the heat dissipation on the surface of the cylinder block 1. The extended structure of the cylinder skirt 2, together with the distributed fixing of the bolt holes 3, effectively suppresses the vibration and deformation of the cylinder block 1 under high speed conditions, ensuring an efficient heat exchange environment between the heat sink 4 and the airflow, so that the UAV engine can maintain stable output under extreme loads.

[0027] Finally, it should be noted that the above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A novel cylinder arrangement for drone engine comprising of cylinder block (1) characterized by: A cylinder skirt (2) is fixedly connected to the lower surface of the cylinder body (1). Multiple bolt holes (3) are opened through the inside of the cylinder skirt (2). An exhaust channel (5) is provided on the outer wall of the cylinder body (1). Multiple connection holes (6) are opened through the outer wall of the exhaust channel (5). Multiple heat sinks (4) are fixedly connected to the outer wall of the cylinder body (1). The heat sinks (4) are wavy in shape.

2. The new cylinder device of the UAV engine according to claim 1, characterized in that: The cylinder body (1) has a through hole (7) on its upper surface, and a spark plug (8) is installed inside the hole (7).

3. The new cylinder device of the UAV engine according to claim 1, characterized in that: An air intake passage (9) is provided through the inside of the cylinder (1), and an auxiliary air intake hole (10) is provided through the inside of the cylinder (1).

4. The new cylinder device of the UAV engine according to claim 1, characterized in that: The cylinder (1) is provided with a piston (11), and a protrusion (14) is fixedly connected to the upper surface of the piston (11).

5. The new cylinder device of the UAV engine according to claim 4, characterized in that: The piston (11) has a compression ring (12) on its outer wall and an oil ring (13) on its outer wall.

6. The new cylinder device of the UAV engine according to claim 4, characterized in that: The piston (11) is fixedly connected to a connecting pin (15), and the connecting pin (15) is rotatably connected to a connecting rod (16).

7. The new cylinder device of the UAV engine according to claim 6, characterized in that: The inner wall of the connecting rod (16) is fixedly connected to a journal (17).

8. The new cylinder device of the UAV engine according to claim 7, characterized in that: The journal (17) is rotatably connected to a crankshaft (18) on its outer wall.

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