High-altitude unmanned aerial vehicle power supercharger lubricating device

Abstract

The high-altitude unmanned aerial vehicle power supercharger lubricating device comprises a supercharger body, the supercharger body comprises a shell, the shell comprises an air compression wheel chamber and a turbine chamber which are integrally formed, and the air compression wheel chamber and the turbine chamber are connected with an air inlet pipe and a waste gas pipe correspondingly; by introducing an innovative lubricating mechanism and a waste gas heat energy utilization system, multiple technical breakthroughs are realized. Specifically, the annular oil chamber wrapping the transmission shaft is designed, the efficient circulating pump and the efficient lubricating oil tank are matched, and it is ensured that lubricating oil continuously flows and is updated in a circulating pipeline. More importantly, part of the waste gas is introduced into the sealing shell through the connecting pipe, and the circulating pipeline is heated by utilizing waste heat carried by the waste gas, so that the lubricating oil is effectively prevented from being solidified under high-altitude and low-temperature conditions, and the problem that the lubricating oil easily loses flowability in a high-altitude environment in the prior art is solved; and the operation efficiency and reliability of the supercharger are improved.

Description

Technical Field

[0001] The invention belongs to the field of unmanned aerial vehicle power boosting, and in particular relates to a lubricating device for a power booster of a high-altitude unmanned aerial vehicle. Background Art

[0002] The performance of the supercharger, a key device in existing internal combustion engines, directly affects the efficiency and stability of the entire power system. However, when the supercharger is operated in high-altitude areas, it faces a severe challenge: the temperature in high-altitude areas is usually low, especially in high-altitude environments, where the temperature can drop to dozens of degrees below zero, which makes the lubricating oil inside the supercharger easily viscous and loses fluidity.

[0003] Lubricating oil plays a vital role in the supercharger. Once the lubricating oil becomes viscous and does not flow, it will cause the supercharger to not operate normally, the engine to lose boost, power to decrease, and power to fail.

[0004] To solve this problem, existing superchargers usually use electric heating devices to preheat or keep the lubricating oil warm to ensure its fluidity in low temperature environments. However, this method not only increases the complexity and cost of the equipment, but also in actual applications, due to the power limitation and long response time of the heating device, it is often difficult to control the lubricating oil temperature, thereby affecting the power output.

[0005] Therefore, how to design a supercharger that can operate stably in a high-altitude and low-temperature environment has become an important issue that needs to be urgently solved in the current technical field. Invention content

[0006] In view of this, the present invention aims to propose a lubrication device for a high-altitude UAV power supercharger. Through a new lubrication mechanism and exhaust gas utilization system, continuous and effective lubrication of the supercharger drive shaft and bearings can be achieved, while preventing the lubricating oil from being frozen in a low temperature environment, thereby ensuring that the supercharger can operate stably and efficiently under different altitude conditions.

[0007] To achieve the above object, the technical solution created by the present invention is implemented as follows:

[0008] A high-altitude unmanned aerial vehicle power supercharger lubrication device, comprising a supercharger body, the supercharger body comprising a shell, the shell comprising an integrally formed compressor wheel chamber and turbine chamber, the compressor wheel chamber and turbine chamber are respectively connected to an intake pipe and an exhaust pipe, the compressor wheel chamber and turbine chamber are respectively provided with a compressor wheel and a turbine, the compressor wheel and the turbine are connected via a transmission shaft, bearings are provided inside the shell, the transmission shaft is installed between the bearings, sealing structures are fixedly provided on both sides of the bearings in the shell, and the shell is provided with a lubrication mechanism for lubricating the inside of the bearings;

[0009] The housing is provided with an oil chamber, which is a circular ring structure and is wrapped around the side of the transmission shaft. An oil inlet hole is penetrated through the outer side of the bearing, and the oil inlet hole is communicated with the interior of the oil chamber.

[0010] The lubrication mechanism comprises a lubricating oil tank, a circulating pump and a circulating pipeline, wherein the lubricating oil tank, the circulating pump and the oil chamber are connected to the circulating pipeline;

[0011] The shell is fixedly provided with a sealing shell on the outer side of the circulation pipeline, the exhaust pipe and the sealing shell are connected through a connecting pipe, and the sealing shell is provided with an air outlet.

[0012] Furthermore, the connecting pipe is equipped with a solenoid valve.

[0013] Furthermore, the exhaust pipe is equipped with a bypass pipe, and the bypass pipe is equipped with a bypass valve mechanism.

[0014] Furthermore, the number of the bearings is two, and the two bearings correspond to the compressor wheel and the turbine respectively. The number of the oil chambers is two, and the two oil chambers correspond to the positions of the two bearings respectively.

[0015] Furthermore, the circulation pipeline is installed with a flow rate sensor.

[0016] Compared with the prior art, the high-altitude UAV power booster lubrication device created by the present invention has the following advantages:

[0017] In the prior art, the lubricating oil inside the supercharger is easy to solidify due to the extremely low temperature environment in high altitude areas, which not only affects the normal operation of the supercharger, but also aggravates the wear of mechanical parts and reduces the stability and durability of the overall system; the present invention creates a lubrication device for a high-altitude UAV power supercharger, introduces an innovative lubrication mechanism and exhaust gas heat energy utilization system, achieves multiple technical breakthroughs, and designs an annular oil chamber that wraps the drive shaft, cooperates with an efficient circulation pump and lubricating oil tank, and ensures the continuous flow and renewal of the lubricating oil in the circulation pipeline. More importantly, part of the exhaust gas is introduced into the sealed housing through a connecting pipe, and the residual heat carried by the exhaust gas is used to heat the circulation pipeline, effectively preventing the solidification of the lubricating oil under high altitude and low temperature conditions. This series of ingenious settings not only solves the problem of easy freezing of lubricating oil in the prior art, but also improves the operating efficiency and reliability of the supercharger, ensuring its stable operation capability in various complex environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The drawings constituting part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments and descriptions of the present invention are used to explain the present invention and do not constitute an improper limitation on the present invention. In the drawings:

[0019] Figure 1 A schematic diagram of a lubricating device for a power supercharger of a high-altitude UAV according to an embodiment of the present invention;

[0020] Figure 2 A partial schematic diagram of a lubrication device for a high-altitude UAV power booster according to an embodiment of the present invention;

[0021] Figure 3 For the present invention to create the embodiment of the Figure 2 An enlarged schematic diagram of the area marked A.

[0022] Description of reference numerals:

[0023] 1. Shell; 2. Compressor chamber; 3. Turbine chamber; 4. Intake pipe; 5. Exhaust pipe; 6. Compressor; 7. Turbine; 8. Drive shaft; 9. Bearing; 10. Sealing structure; 11. Oil chamber; 12. Oil inlet hole; 13. Lubricating oil tank; 14. Circulating pump; 15. Circulating pipeline; 16. Sealed shell; 17. Connecting pipe; 18. Air outlet; 19. Solenoid valve; 20. Bypass pipe; 21. Bypass valve mechanism; 22. Flow rate sensor. DETAILED DESCRIPTION

[0024] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0025] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and the like are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", and the like may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0026] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0027] The present invention will be described in detail below with reference to the accompanying drawings and in combination with embodiments.

[0028] like Figure 1-3 As shown, a lubricating device for a high-altitude unmanned aerial vehicle power supercharger of the present invention comprises a supercharger body, the supercharger body comprises a shell 1, the shell 1 comprises an integrally formed compressor chamber 2 and a turbine chamber 3, the compressor chamber 2 and the turbine chamber 3 are respectively connected with an intake pipe 4 and an exhaust pipe 5, and the compressor chamber 2 and the turbine chamber 3 are respectively rotatably installed with a compressor 6 and a turbine 7, the compressor 6 and the turbine 7 are connected by a transmission shaft 8, when working, the exhaust gas generated by the engine is discharged through the exhaust pipe 5, the turbine 7 is driven to rotate, and the compressor 6 is driven to rotate under the transmission action of the transmission shaft 8, and the compressor 6 is driven to rotate when the compressor 6 rotates. Fresh air is sent into the engine, a bearing 9 is fixed inside the shell 1, the transmission shaft 8 is installed inside the bearing 9, the bearing 9 is used to support the transmission shaft 8, a sealing structure 10 is fixedly provided on both sides of the bearing 9 in the shell 1, and a lubrication mechanism for lubricating the inside of the bearing 9 is installed in the shell 1, and the steel balls in the bearing 9 are lubricated by the lubrication mechanism to ensure that the transmission shaft 8 can rotate smoothly.

[0029] In some embodiments, the housing 1 is fixed with an oil chamber 11, and the oil chamber 11 is used to contain lubricating oil. The oil chamber 11 is a circular ring structure, and the oil chamber 11 is wrapped around the side of the transmission shaft 8. The outer side of the bearing 9 is penetrated by an oil inlet hole 12, and the oil inlet hole 12 is connected to the interior of the oil chamber 11, so that the lubricating oil in the oil chamber 11 can enter the interior of the bearing 9 through the oil inlet hole 12, thereby lubricating the steel balls in the bearing 9. Specifically, the lubrication mechanism includes a lubricating oil tank 13, a circulating pump 14 and a circulating pipeline 15. The lubricating oil tank 13, the circulating pump 14 and the oil chamber 11 are connected in the circulating pipeline 15. The lubricating oil tank 13 is used to contain lubricating oil, and the circulating pump 14 is used to circulate the lubricating oil in the circulating pipeline 15, so that the lubricating oil keeps flowing. In some embodiments, a lubricating oil filter can also be installed in the circulating pipeline 15 to filter impurities in the oil.

[0030] It is worth mentioning that a sealing shell 16 is fixedly provided on the outer side of the circulation pipeline 15 of the shell 1. The exhaust pipe 5 is connected to the sealing shell 16 by a connecting pipe 17. The sealing shell 16 is provided with an air outlet 18. It can be understood that in a high-altitude environment, the temperature is as low as dozens of degrees below zero, which makes it easy for the lubricating fluid to freeze. Part of the exhaust gas can be discharged into the sealing shell 16 through the connecting pipe 17, and the sealing shell 16 is heated by the temperature carried by the exhaust gas, so that the lubricating oil in the circulation pipeline 15 can maintain a good flow state.

[0031] In some embodiments, the connecting pipe 17 is installed with a solenoid valve 19 , and the solenoid valve 19 is used to conveniently control the amount of exhaust gas discharged into the sealed housing 16 .

[0032] The exhaust pipe 5 is provided with a bypass pipe 20, and the bypass pipe 20 is provided with a bypass valve mechanism 21 for relieving pressure, which is the prior art and will not be described in detail here.

[0033] There are two bearings 9 , which correspond to the compressor wheel 6 and the turbine wheel 7 respectively. There are two oil chambers 11 , which correspond to the positions of the two bearings 9 respectively.

[0034] The circulation pipeline 15 is installed with a flow rate sensor 22 , and the flow rate sensor 22 is used to monitor the flow rate of the lubricating oil in the circulation pipeline 16 .

[0035] In summary, the present invention aims to realize a lubrication device for a high-altitude UAV power supercharger. Through a carefully designed lubrication mechanism and exhaust gas utilization system, it ensures that the drive shaft 8 and bearing 9 of the supercharger can be continuously and effectively lubricated in a high-altitude and low-temperature environment. At the same time, the temperature carried by the exhaust gas is used to heat the circulation pipeline 15 to prevent the lubricating oil from freezing, thereby ensuring that the supercharger can operate stably and efficiently under different altitude conditions.

[0036] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A high-altitude UAV power booster lubrication device, characterized in that: The invention comprises a supercharger body, wherein the supercharger body comprises a shell (1), wherein the shell (1) comprises an integrally formed compressor wheel chamber (2) and a turbine chamber (3), wherein the compressor wheel chamber (2) and the turbine chamber (3) are respectively connected to an intake pipe (4) and an exhaust pipe (5), wherein the compressor wheel chamber (2) and the turbine chamber (3) are respectively provided with a compressor wheel (6) and a turbine (7), wherein the compressor wheel (6) and the turbine (7) are connected via a transmission shaft (8), wherein bearings (9) are provided inside the shell (1), wherein the transmission shaft (8) is installed between the bearings (9), wherein sealing structures (10) are fixedly provided on both sides of the bearings (9) in the shell (1), and wherein the shell (1) is provided with a lubrication mechanism for lubricating the inside of the bearings (9); The housing (1) is provided with an oil chamber (11), the oil chamber (11) is a circular ring structure, and the oil chamber (11) wraps around the side of the transmission shaft (8), and an oil inlet hole (12) is penetrated through the outer side of the bearing (9), and the oil inlet hole (12) is communicated with the interior of the oil chamber (11). The lubricating mechanism comprises a lubricating oil tank (13), a circulating pump (14) and a circulating pipeline (15); the lubricating oil tank (13), the circulating pump (14) and the oil chamber (11) are connected to the circulating pipeline (15); The housing (1) is fixedly provided with a sealing housing (16) on the outside of the circulation pipeline (15); the exhaust pipe (5) and the sealing housing (16) are connected via a connecting pipe (17); and the sealing housing (16) is provided with an air outlet (18).

2. The high-altitude UAV power booster lubrication device according to claim 1 is characterized by: The connecting pipe (17) is equipped with a solenoid valve (19).

3. The high-altitude UAV power booster lubrication device according to claim 1 is characterized by: The exhaust pipe (5) is provided with a bypass pipe (20), and the bypass pipe (20) is provided with a bypass valve mechanism (21).

4. The high-altitude UAV power booster lubrication device according to claim 1 is characterized by: The number of the bearings (9) is two, and the two bearings (9) correspond to the compressor wheel (6) and the turbine wheel (7) respectively. The number of the oil chambers (11) is two, and the two oil chambers (11) correspond to the positions of the two bearings (9) respectively.

5. The high-altitude UAV power booster lubrication device according to claim 1 is characterized by: The circulation pipeline (15) is installed with a flow rate sensor (22).

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