Power output device for 45-ton aircraft tractor

Abstract

The utility model provides a kind of power output device for 45-ton airplane tractor, comprising: engine, support and heat dissipation mechanism, support is set in the bottom of engine, heat dissipation mechanism includes installation shell, mounting bracket and fan, installation shell is set on engine, mounting bracket is set inside installation shell, fan is set on mounting bracket.The power output device for 45-ton airplane tractor of the utility model embodiment, can improve the heat dissipation efficiency and lubricating effect of power output device, enhances the stability of device, prevents the failure or damage caused by overheating, prolongs the service life of engine.

Description

Technical Field

[0001] This utility model relates to the technical field of aircraft towing vehicles, and in particular to a power output device for a 45-ton aircraft towing vehicle. Background Technology

[0002] An aircraft towing vehicle is a support device used to tow aircraft on the ground at an airport. It can also be used to move large aircraft components or the aircraft itself during the aircraft manufacturing process. When towing an aircraft, a power take-off device is required to enhance the traction force on the aircraft.

[0003] When the power take-off (PTO) provides power to the aircraft towing vehicle, due to prolonged operation and the influence of the external environment, the PTO may experience problems such as overheating, vibration, or instability. This not only affects the towing effect but may also damage the towing vehicle and the aircraft. Therefore, it is necessary for staff to regularly inspect and maintain the PTO to ensure that it is in good working condition. However, this increases the workload of the staff and makes it difficult to detect and deal with problems with the PTO in a timely manner. Utility Model Content

[0004] This utility model aims to at least partially solve one of the technical problems in the above-mentioned technologies.

[0005] Therefore, one objective of this utility model is to provide a power output device for a 45-ton aircraft tractor, which can improve the heat dissipation efficiency and lubrication effect of the power output device, enhance the stability of the device, prevent failures or damage caused by overheating, and extend the service life of the engine.

[0006] To achieve the above objectives, the first aspect of this utility model provides a power output device for a 45-ton aircraft tractor, comprising: an engine, a bracket, and a heat dissipation mechanism. The bracket is disposed at the bottom of the engine, and the heat dissipation mechanism includes a mounting housing, a mounting bracket, and a fan. The mounting housing is disposed on the engine, the mounting bracket is disposed inside the mounting housing, and the fan is disposed on the mounting bracket.

[0007] In addition, the power take-off device for a 45-ton aircraft tractor proposed above according to this utility model may also have the following additional technical features: Specifically, a connecting shaft is provided on the mounting housing, and a cover plate is installed on the outer wall of the connecting shaft.

[0008] Specifically, the cover plate has ventilation holes.

[0009] Specifically, a lubrication mechanism is provided on the output shaft of the engine. The lubrication mechanism includes an oil reservoir and oil-absorbing cotton. The oil reservoir is located outside the engine. An oil filling port is opened on the outer wall of the oil reservoir, and an oil storage groove is opened on the inner wall of the oil reservoir. The oil-absorbing cotton is located inside the oil reservoir.

[0010] Specifically, the inner wall of the oil storage box has through holes.

[0011] Specifically, a pull ring is provided on the outer wall of the mounting housing.

[0012] Specifically, an isolation mesh is installed inside the mounting shell.

[0013] Compared with the prior art, the present invention has the following beneficial effects: the power output device for a 45-ton aircraft tractor improves the heat dissipation efficiency and lubrication effect of the power output device through the design of the heat dissipation mechanism and the lubrication mechanism, enhances the stability of the device, prevents failure or damage caused by overheating, and extends the service life of the engine.

[0014] Additional aspects and advantages of this invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0015] The above and / or additional aspects and advantages of this utility model will become apparent and readily understood from the following description of the embodiments taken in conjunction with the accompanying drawings, in which: Figure 1 This is a schematic diagram of a power output device for a 45-ton aircraft tractor according to an embodiment of the present invention. Figure 2 This is a schematic diagram of the heat dissipation mechanism of a power output device for a 45-ton aircraft tractor according to an embodiment of the present invention. Figure 3 This is a schematic diagram of the structure of a 45-ton aircraft tractor power output device oil reservoir and oil inlet used in conjunction with an embodiment of the present invention. Figure 4 This is a schematic diagram of the lubrication mechanism of a power output device for a 45-ton aircraft tractor according to an embodiment of the present invention.

[0016] Reference numerals: 1. Engine; 2. Bracket; 3. Cooling mechanism; 31. Mounting housing; 32. Isolation net; 33. Mounting bracket; 34. Fan; 35. Connecting shaft; 36. Cover plate; 37. Cooling hole; 4. Lubrication mechanism; 41. Oil reservoir; 42. Oil inlet; 43. Oil reservoir; 44. Through hole; 45. Oil-absorbing cotton; 5. Pull ring. Detailed Implementation

[0017] The embodiments of this utility model are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this utility model, and should not be construed as limiting this utility model.

[0018] The following description, with reference to the accompanying drawings, describes a power output device for a 45-ton aircraft tractor according to an embodiment of the present invention.

[0019] like Figures 1-4 As shown, a power output device for a 45-ton aircraft tractor according to an embodiment of the present invention includes: an engine 1, a bracket 2, and a heat dissipation mechanism 3. The bracket 2 is disposed at the bottom of the engine 1. The heat dissipation mechanism 3 includes a mounting shell 31, a mounting bracket 33, and a fan 34. The mounting shell 31 is disposed on the engine 1, the mounting bracket 33 is disposed inside the mounting shell 31, and the fan 34 is disposed on the mounting bracket 33.

[0020] A connecting shaft 35 is provided on the mounting housing 31, and a cover plate 36 is installed on the outer wall of the connecting shaft 35.

[0021] The cover plate 36 has heat dissipation holes 37.

[0022] Specifically, when engine 1 operates for an extended period, it generates a large amount of heat. If this heat is not dissipated in time, it will affect the normal operation of engine 1 and may even damage it. Through the cooling mechanism 3, the fan 34 is activated first. The fan 34 generates airflow that blows onto engine 1 through the mounting bracket 33 to dissipate heat and prevent engine 1 from being damaged due to overheating, thus extending the service life of engine 1. At the same time, the airflow is exhausted through the cooling holes 37, increasing the heat dissipation area and improving the heat dissipation efficiency. In addition, when it is necessary to repair or replace the cooling mechanism 3, the cover plate 36 is rotated. The cover plate 36 drives the connecting shaft 35 to rotate on the mounting housing 31, which opens the cover plate 36, making it easy to repair or replace the cooling mechanism 3. The operation is simple and convenient.

[0023] In one embodiment of this application, such as Figure 3 and Figure 4 As shown, a lubrication mechanism 4 is provided on the output shaft of engine 1. The lubrication mechanism 4 includes an oil reservoir 41 and an oil-absorbing cotton 45. The oil reservoir 41 is located outside the engine 1. An oil inlet 42 is provided on the outer wall of the oil reservoir 41. An oil storage groove 43 is provided on the inner wall of the oil reservoir 41. The oil-absorbing cotton 45 is located inside the oil reservoir 41.

[0024] The inner wall of the oil storage box 41 has a through hole 44.

[0025] Specifically, when engine 1 operates for a long time, the output shaft will rotate continuously. If the output shaft lacks lubrication, it will cause severe wear and may even affect the normal operation of engine 1. By setting up a lubrication mechanism 4, lubricating oil is poured from the oil inlet 42 into the oil reservoir 43. The lubricating oil in the oil reservoir 43 permeates into the oil-absorbing cotton 45 through the through hole 44. When the output shaft rotates, it comes into contact with the oil-absorbing cotton 45, which lubricates the output shaft, reduces the wear of the output shaft, and extends the service life of engine 1.

[0026] In one embodiment of this application, such as Figure 2 As shown, a pull ring 5 is provided on the outer wall of the mounting shell 31.

[0027] Understandably, the pull ring 5 facilitates the locking and opening of the cover 36 by operators, improving operational convenience. When maintenance or replacement of the heat dissipation mechanism 3 is required, operators can pull out the pull ring 5 to lock and open the cover 36.

[0028] In one embodiment of this application, such as Figure 2 As shown, an isolation net 32 ​​is installed inside the mounting housing 31.

[0029] Understandably, by setting up the isolation net 32, the airflow generated by the fan 34 can be dispersed, allowing the airflow to be blown more evenly onto the engine 1, thus improving the heat dissipation effect. At the same time, the isolation net 32 ​​can also prevent external debris from entering the cooling mechanism 3 and damaging the fan 34 and engine 1, further improving the safety and reliability of the entire power output device.

[0030] Working Principle: When engine 1 starts and operates for an extended period, it generates a significant amount of heat. At this time, the cooling mechanism 3 comes into play. Fan 34 is activated, generating airflow that passes through mounting bracket 33 and blows directly onto engine 1, effectively cooling it and preventing engine 1 from malfunctioning or being damaged due to overheating. This design not only extends the service life of engine 1 but also ensures the continuous and stable operation of the tractor. Simultaneously, the airflow is exhausted through the cooling holes 37 on cover plate 36 during the cooling process, increasing the heat dissipation area and further improving cooling efficiency. The output shaft of engine 1 rotates continuously during prolonged operation. To reduce wear on the output shaft and extend the service life of engine 1, this device is specially equipped with a lubrication mechanism 4. Operators can pour lubricating oil into the oil reservoir 43 through the oil inlet 42. The lubricating oil in the reservoir 43 then permeates through the through-hole 44 into the oil-absorbing cotton 45. When the output shaft rotates, it contacts the oil-absorbing cotton 45, thus lubricating the output shaft and effectively reducing wear. When the heat dissipation mechanism 3 needs to be repaired or replaced, the staff can easily open the cover 36 by simply pulling out the pull ring 5.

[0031] In summary, the power output device for a 45-ton aircraft tractor in this embodiment of the present invention improves the heat dissipation efficiency and lubrication effect of the power output device through the design of the heat dissipation mechanism 3 and the lubrication mechanism 4, enhances the stability of the device, prevents failure or damage caused by overheating, and extends the service life of the engine 1.

[0032] In the description of this specification, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this utility model, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0033] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0034] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A power take-off device for a 45-ton aircraft tractor, characterized in that, include: An engine (1), a bracket (2) and a heat dissipation mechanism (3) are provided. The bracket (2) is located at the bottom of the engine (1). The heat dissipation mechanism (3) includes a mounting shell (31), a mounting bracket (33) and a fan (34). The mounting shell (31) is located on the engine (1). The mounting bracket (33) is located inside the mounting shell (31). The fan (34) is located on the mounting bracket (33).

2. The power take-off device for a 45-ton aircraft tractor according to claim 1, characterized in that, A connecting shaft (35) is provided on the mounting shell (31), and a cover plate (36) is installed on the outer wall of the connecting shaft (35).

3. The power take-off device for a 45-ton aircraft tractor according to claim 2, characterized in that, The cover plate (36) has heat dissipation holes (37).

4. The power take-off device for a 45-ton aircraft tractor according to claim 1, characterized in that, The output shaft of the engine (1) is provided with a lubrication mechanism (4). The lubrication mechanism (4) includes an oil reservoir (41) and an oil-absorbing cotton (45). The oil reservoir (41) is located outside the engine (1). An oil inlet (42) is provided on the outer wall of the oil reservoir (41). An oil storage groove (43) is provided on the inner wall of the oil reservoir (41). The oil-absorbing cotton (45) is located inside the oil reservoir (41).

5. A power take-off device for a 45-ton aircraft tractor according to claim 4, characterized in that, The inner wall of the oil storage box (41) is provided with a through hole (44).

6. A power take-off device for a 45-ton aircraft tractor according to claim 2, characterized in that, A pull ring (5) is provided on the outer wall of the mounting shell (31).

7. A power take-off device for a 45-ton aircraft tractor according to claim 1, characterized in that, An isolation net (32) is installed inside the mounting housing (31).

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