Airplane propulsion transmission device

Abstract

The invention discloses an aircraft propulsion transmission device, and belongs to the technical field of aircraft power equipment. The aircraft propulsion transmission device comprises a synchronous belt, the synchronous belt is of a hollow structure, a top cover is inserted into one side of the synchronous belt, and the synchronous belt is in sliding connection with the top cover; the power transmission mechanism comprises two driving shafts, synchronous wheels are fixedly connected to the driving shafts in a sleeving mode, and the synchronous wheels are connected with the synchronous belt in an engaged mode; the lubricating pipes are arranged on the synchronous belt in a penetrating manner; the oil pumping assembly comprises an oil well pump, the end portion of the output end of the oil well pump is fixedly connected with an oil outlet pipe and an oil conveying mechanism, and the oil conveying mechanism is used for ensuring that lubricating oil is smoothly discharged through the lubricating pipe; and a leakage-proof mechanism. According to the technical scheme, the oil outlet pipes, the lubricating pipes and the oil well pump are arranged, the densely-distributed lubricating pipes can fully guarantee the lubricating uniformity, in addition, the single oil outlet pipe and the synchronous belt in the hollow state can effectively reduce the dead weight of an aircraft, and the flight performance of the aircraft can be improved.

Description

Technical Field

[0001] This application relates to the technical field of aircraft power equipment, and more specifically, to an aircraft propulsion transmission device. Background Art

[0002] With the rapid development of aerospace technology, aircraft have been more and more widely used in civilian miniaturization. For example, miniaturized manned aircraft with less than ten people are also purchased and used in more and more places.

[0003] Most miniaturized manned aircraft still rely on a propeller structure as the power for flight. During the flight of such aircraft, the stability of the propulsion transmission device is one of the most critical factors affecting its performance. For the propulsion transmission device, the lubrication effect of its internal transmission structure directly affects the flight efficiency, endurance time and reliability of the aircraft.

[0004] Although the existing technical solutions can automatically lubricate the gears and toothed belts, there are still the following defects: The lubricating oil is directly transported to the connection between the gears and the toothed belts through the main lubricating oil pipe and the auxiliary lubricating oil pipe. This method not only makes it difficult to ensure the uniform distribution of the lubricating oil, but also the output lubricating oil will drip randomly, affecting the normal operation of the internal equipment of the aircraft. In addition, the setting of multiple pipes will also increase the overall dead weight of the aircraft, affecting the flight endurance and flexibility of the aircraft. In view of this, we propose an aircraft propulsion transmission device. Summary of the Invention

[0005] Technical Problems to be Solved The purpose of this application is to provide an aircraft propulsion transmission device, which solves the technical problems that can be solved by the independent claims in the prior art and realizes the technical effects. Technical Solutions

[0006] The embodiment of this application provides an aircraft propulsion transmission device, including: A timing belt, the timing belt is provided with a hollow structure, a top cover is inserted on one side of the timing belt, and the timing belt is slidably connected to the top cover; A power transmission mechanism, the transmission mechanism includes two drive shafts, synchronous wheels are sleeved and fixed on the drive shafts, and the synchronous wheels are meshed with the timing belt; Multiple lubricating pipes, the lubricating pipes are arranged through the timing belt; An oil pumping assembly, the oil pumping assembly includes an oil pumping pump, the output end of the oil pumping pump is fixedly connected with an oil outlet pipe, and the end of the oil outlet pipe passes through one side of the top cover and extends into the inner cavity of the timing belt; An oil transmission mechanism, the oil transmission mechanism is used to ensure that the lubricating oil is discharged smoothly through the lubricating pipes; A leak prevention mechanism, the leak prevention mechanism is used to prevent the lubricating oil from leaking through the lubricating pipes.

[0007] By adopting the above technical solution, the densely arranged lubricating pipes can fully ensure the uniformity of lubrication. In addition, the single oil outlet pipe and the hollow synchronous belt can effectively reduce the dead weight of the aircraft, which is beneficial to improving the flight performance of the aircraft.

[0008] As an alternative solution of the technical solution of this application document, the oil delivery mechanism includes: an oil filling assembly, and the oil filling assembly includes: A lower pressing plate, which is installed in the inner cavity of the synchronous belt, and the lower pressing plate is in frictional contact with the inner wall of the synchronous belt; A counterweight frame, which is slidably penetrated through the top cover, and the end of the counterweight frame is fixedly connected to the lower pressing plate; An oil replenishing mechanism, which is used to automatically replenish the lubricating oil in the synchronous belt.

[0009] By adopting the above technical solution, the lubricating oil in the synchronous belt can be smoothly discharged through the lubricating pipe even if it is in a viscous state, thus ensuring the smooth progress of lubrication.

[0010] As an alternative solution of the technical solution of this application document, the oil replenishing mechanism includes: A pressure sensor, which is fixedly installed on the top cover, and the pressure sensor is electrically connected to an external control mechanism; A pressing plate, which is installed on the lower side of the counterweight frame, and a first spring is fixedly connected between the pressing plate and the counterweight frame, and the pressing plate is in abutting cooperation with the pressure sensor.

[0011] By adopting the above technical solution, lubricating oil can be automatically added into the synchronous belt.

[0012] As an alternative solution of the technical solution of this application document, the oil delivery mechanism further includes: A plurality of reinforcing rods, which are fixedly installed in the synchronous belt; A hot oil mechanism, which includes a bottom cover inserted on the other side of the synchronous belt. The upper side of the bottom cover is made of a metal material, and an electric heating plate is installed in the bottom cover.

[0013] By adopting the above technical solution, the problem that the lubricating oil becomes overly viscous or even coagulates can be avoided, effectively ensuring the smooth discharge of the lubricating oil.

[0014] As an alternative solution of the technical solution of this application document, the anti-leakage mechanism includes an oil drain valve, and the oil drain valve includes: An anti-leakage plug, which is inserted and matched with the lubricating pipe; A pushing mechanism, which is used to drive the anti-leakage plug to move linearly.

[0015] By adopting the above technical solution, not only can the waste of lubricating oil be reduced and the utilization rate of lubricating oil be improved, but also the lubricating oil can be prevented from flowing freely and polluting the internal environment of the aircraft body.

[0016] As an optional solution of the technical solution of this application document, the driving mechanism includes: A magnet group, the magnet group is installed in the synchronous belt at a position corresponding to the synchronous wheel, and the drive plate is magnetically matched with the magnet group; A driving plate, wherein the end of the anti-leakage plug is connected and fixed to the corresponding driving plate; A plurality of limiting sleeves, wherein the limiting sleeves include a fixed sleeve fixedly mounted on the synchronous belt, a sliding rod is slidably connected in the fixed sleeve, the sliding rod is fixedly connected to the driving plate, and a second spring is fixedly connected between the sliding rod and the fixed sleeve.

[0017] By adopting the above technical solution, the driving plate can smoothly drive the anti-leakage plug to move in a straight line.

[0018] As an optional solution of the technical solution of this application document, the magnet group includes a plurality of adsorption magnets, the drive plate is magnetically matched with the adsorption magnets, and the adsorption magnets are installed on both sides of the synchronous belt in an annular intermittent structure.

[0019] By adopting the above technical solution, since the adsorption magnet is arranged in an intermittent structure, the driving plate will drive the anti-leakage plug to move back and forth linearly, continuously pushing the lubricating oil to the synchronous wheel through the lubrication pipe, further ensuring smooth lubrication.

[0020] As an optional solution of the technical solution of the present application document, the anti-leakage mechanism also includes two oil receiving boxes, the oil receiving boxes are sleeved on both sides of the synchronous belt, and the oil receiving boxes are detachably mounted on the bottom cover.

[0021] By adopting the above technical solution, the oil collecting box can receive the lubricating oil remaining on the lubricating pipe, further reducing the probability of the lubricating oil dripping and contaminating other parts of the aircraft.

[0022] As an optional solution of the technical solution of this application document, the oil pump assembly includes: Oil storage barrels, An oil inlet pipe, the oil inlet pipe is passed through one side of the oil storage barrel, and the end of the oil inlet pipe is connected and fixed to the input end of the oil pump; The uniform distribution mechanism is used to ensure that the oil inlet pipe can absorb lubricating oil with uniform composition.

[0023] By adopting the above technical solution, the composition of the lubricating oil sucked into the oil inlet pipe is uniform.

[0024] As an optional solution of the technical solution of this application document, the uniform distribution mechanism includes: A receiving cylinder, which is rotatably sleeved on one side of the oil inlet pipe; A plurality of stirring pipes, which are fixedly connected to the receiving cylinder; A driving mechanism, which is used to drive the receiving cylinder to rotate; The driving mechanism includes: An installation cylinder, with a pushing pipe fixedly connected to one side of the installation cylinder; A driving impeller, which is rotatably connected inside the installation cylinder; An output pipe, which is fixedly connected between the oil inlet pipe and the installation cylinder.

[0025] By adopting the above technical solution, not only can the uniformity of the lubricating oil components inside the oil storage barrel be ensured, but also the stirring pipes can absorb the lubricating oil from different positions, avoiding the influence of uneven lubricating oil components on the lubrication effect. Beneficial effects

[0026] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages: 1. In the technical solution of the present application, by setting an oil outlet pipe, a lubricating pipe and a fuel pump, the dense lubricating pipes can fully ensure the uniformity of lubrication. In addition, the single oil outlet pipe and the hollow synchronous belt can effectively reduce the dead weight of the aircraft, which is beneficial to improving the flight performance of the aircraft.

[0027] 2. In the technical solution of the present application, by setting a lower pressing plate and a counterweight frame, the lubricating oil in the synchronous belt can smoothly drain through the lubricating pipe even if it is in a viscous state, thus ensuring the smooth progress of lubrication; at the same time, by setting a pressure sensor and a pressing plate, lubricating oil can be automatically added into the synchronous belt.

[0028] 3. In the technical solution of the present application, by setting a reinforcing rod, not only can the strength of the synchronous belt be improved, effectively preventing the synchronous belt from deforming and ensuring the normal transmission of power, but also the lower pressing plate can smoothly move up and down. At the same time, by setting a hot oil mechanism, the problem of excessive viscosity or even condensation of the lubricating oil can be avoided in cold weather.

[0029] 4. In the technical solution of the present application, by setting a magnet group, a driving plate and a plurality of limiting sleeves, while ensuring smooth lubrication, not only can the waste of lubricating oil be reduced, the utilization rate of lubricating oil be improved, but also the lubricating oil can be prevented from flowing randomly and polluting the internal environment of the aircraft body.

[0030] 5. In the technical solution of the present application, by setting a receiving cylinder, a plurality of stirring pipes and a driving mechanism, not only can the uniformity of the lubricating oil components inside the oil storage barrel be ensured, but also the stirring pipes can absorb the lubricating oil from different positions, avoiding the influence of uneven lubricating oil components on the lubrication effect. Description of the drawings

[0031] Figure 1 This is a schematic diagram of the overall structure of an aircraft propulsion transmission device disclosed in a preferred embodiment of the present application; Figure 2 This is a schematic diagram of the overall structure of a synchronous belt in a cutaway section of an aircraft propulsion transmission device disclosed in a preferred embodiment of the present application; Figure 3 This is a schematic structural diagram of an oil-filled assembly in an aircraft propulsion transmission device disclosed in a preferred embodiment of the present application; Figure 4 It is a partial structural schematic diagram of one side of a synchronous belt cut away in an aircraft propulsion transmission device disclosed in a preferred embodiment of the present application; Figure 5 A schematic top view of a partial structure of one side of a synchronous belt cut away in an aircraft propulsion transmission device disclosed in a preferred embodiment of the present application; Figure 6 A schematic diagram of a portion of the structure on one side of a driving plate in an aircraft propulsion transmission device disclosed in a preferred embodiment of the present application; Figure 7 This is a structural schematic diagram of an oil receiving box in an aircraft propulsion transmission device disclosed in a preferred embodiment of the present application; Figure 8 This is a schematic diagram of the structure of a driving mechanism in an aircraft propulsion transmission device disclosed in a preferred embodiment of the present application; Explanation of the numbers in the figure: 1. synchronous belt; 2. top cover; 3. bottom cover; 4. driving shaft; 5. oil pump assembly; 501. oil outlet pipe; 502. oil storage barrel; 503. oil pump; 504. receiving tube; 505. oil inlet pipe; 506. push tube; 507. driving impeller; 508. mounting tube; 509. stirring tube; 510. output pipe; 6. lubrication tube; 7. oil filling assembly; 701. lower pressure plate; 702. counterweight frame; 703. pressure sensor; 704. first spring; 705. pressing plate; 8. oil drain valve; 801. adsorption magnet; 802. anti-leakage plug; 803. driving plate; 804. sliding rod; 805. second spring; 806. fixing tube; 9. oil receiving box; 10. electric heating plate; 11. reinforcing rod; 12. synchronous wheel. DETAILED DESCRIPTION

[0032] In order to make the technical solutions and advantages in the embodiments of the present application more clearly understood, the exemplary embodiments of the present application are further described in detail below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present application, rather than an exhaustive list of all the embodiments. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict.

[0033] refer to Figures 1 - 8, an embodiment of the present application provides an aircraft propulsion transmission device, which includes a synchronous belt 1, a power transmission mechanism, a plurality of lubricating pipes 6, a pump oil assembly 5, an oil delivery mechanism, and a leak prevention mechanism.

[0034] Among them, the synchronous belt 1 is arranged in a hollow structure. A top cover 2 is inserted into one side of the synchronous belt 1, and the synchronous belt 1 is slidably connected to the top cover 2; the transmission mechanism includes two drive shafts 4. Synchronous wheels 12 are sleeved and fixed on the drive shafts 4, and the synchronous wheels 12 are meshed with the synchronous belt 1; the lubricating pipes 6 are penetrated through the synchronous belt 1; the pump oil assembly 5 includes a suction oil pump 503. The output end of the suction oil pump 503 is fixedly connected with an oil outlet pipe 501. The end of the oil outlet pipe 501 passes through one side of the top cover 2 and extends into the inner cavity of the synchronous belt 1; the oil delivery mechanism is used to ensure the smooth discharge of the lubricating oil through the lubricating pipes 6; the leak prevention mechanism is used to prevent the lubricating oil from leaking through the lubricating pipes 6.

[0035] During the process of power transmission by the meshing of the synchronous wheel 12 and the synchronous belt 1, under the control of an external control mechanism, the suction oil pump 503 operates, and the lubricating oil is input into the inner cavity of the synchronous belt 1 through the oil outlet pipe 501. The lubricating oil in the synchronous belt 1 will be gradually discharged through the lubricating pipes 6 to lubricate between the synchronous wheel 12 and the synchronous belt 1. The dense lubricating pipes 6 can fully ensure the uniformity of lubrication. In addition, the single oil outlet pipe 501 and the hollow synchronous belt 1 can effectively reduce the dead weight of the mechanism, which is beneficial to improving the flight performance of the aircraft.

[0036] Refer to Figure 1 、 Figure 2 、 Figure 3 and Figure 4 , for the aircraft propulsion transmission device provided by the present application, the oil delivery mechanism includes an oil filling assembly 7, and the oil filling assembly 7 includes a lower pressing plate 701, a counterweight frame 702, and an oil replenishing mechanism.

[0037] The lower pressing plate 701 is installed in the inner cavity of the synchronous belt 1, and the lower pressing plate 701 is in frictional contact with the inner wall of the synchronous belt 1; the counterweight frame 702 is slidably penetrated through the top cover 2, and the end of the counterweight frame 702 is fixedly connected to the lower pressing plate 701; the oil replenishing mechanism is used to automatically replenish the lubricating oil in the synchronous belt 1.

[0038] Under the action of the gravity of the counterweight frame 702 and the lower pressing plate 701, the lower pressing plate 701 always maintains a downward movement trend, thereby pushing the lubricating oil in the synchronous belt 1, so that the lubricating oil in the synchronous belt 1 can be smoothly discharged through the lubricating pipes 6 even if it is in a viscous state, thus ensuring the smooth progress of lubrication.

[0039] On the basis of the above solution, for the aircraft propulsion transmission device provided by the present application, the oil replenishing mechanism includes a pressure sensor 703 and a pressing plate 705.

[0040] The pressure sensor 703 is fixedly installed on the top cover 2, and the pressure sensor 703 is electrically connected to an external control mechanism; the pressing plate 705 is installed on the lower side of the counterweight frame 702, and a first spring 704 is fixedly connected between the pressing plate 705 and the counterweight frame 702, and the pressing plate 705 is in abutting cooperation with the pressure sensor 703.

[0041] As the lubricating oil inside the synchronous belt 1 continuously decreases, the counterweight frame 702 will drive the pressing plate 705 to gradually move downward, and the pressure borne by the pressure sensor 703 continuously increases. When the threshold value is reached, under the control of the external control mechanism, the oil pump 503 operates, so as to automatically add lubricating oil into the synchronous belt 1.

[0042] On the basis of the above solution, for the aircraft propulsion transmission device provided by the present application, the oil delivery mechanism further includes a plurality of reinforcing rods 11 and a hot oil mechanism.

[0043] The reinforcing rods 11 are fixedly installed inside the synchronous belt 1; the hot oil mechanism includes a bottom cover 3 inserted on the other side of the synchronous belt 1. The upper side of the bottom cover 3 is made of a metal material, and an electric heating plate 10 is installed inside the bottom cover 3.

[0044] The arrangement of the reinforcing rods 11 can not only improve the strength of the synchronous belt 1, effectively prevent the synchronous belt 1 from deforming, ensure the normal transmission of power, but also enable the lower pressing plate 701 to move up and down smoothly. In addition, the reinforcing rods 11 will move along with the synchronous belt 1, and can stir the lubricating oil inside the synchronous belt 1 to ensure the uniform composition of the lubricating oil inside the synchronous belt 1.

[0045] The electric heating plate 10 is electrically connected to a temperature sensor. When the temperature is lower than the set value, the electric heating plate 10 is started, and can heat the lubricating oil inside the synchronous belt 1, avoiding problems such as excessive viscosity or even condensation of the lubricating oil, and effectively ensuring the smooth discharge of the lubricating oil.

[0046] Refer to Figure 2 、 Figure 4 、 Figure 5 、 Figure 6 and Figure 7 For the aircraft propulsion transmission device provided by the present application, the leak prevention mechanism includes an oil drain valve 8, and the oil drain valve 8 includes a leak prevention plug 802 and a pushing mechanism.

[0047] The leak prevention plug 802 is in plug-in fit with the lubricating pipe 6; the pushing mechanism is used to drive the leak prevention plug 802 to move linearly.

[0048] On the basis of the above solution, for the aircraft propulsion transmission device provided by the present application, the pushing mechanism includes a magnet group, a driving plate 803 and a plurality of limiting sleeves.

[0049] The magnet group is installed inside the synchronous belt 1 at a position corresponding to the synchronous wheel 12, and the driving plate 803 is magnetically matched with the magnet group; the end of the anti-leakage plug 802 is connected and fixed to the corresponding driving plate 803; the limiting sleeve includes a fixed cylinder 806 fixedly installed on the synchronous belt 1, and a sliding rod 804 is slidably connected inside the fixed cylinder 806, the sliding rod 804 is connected and fixed to the driving plate 803, and a second spring 805 is fixedly connected between the sliding rod 804 and the fixed cylinder 806.

[0050] During the process of the synchronous belt 1 rotating to transmit power, when the lubrication tube 6 moves to the synchronous wheel 12, under the magnetic force of the magnet group, the driving plate 803 will drive the anti-leakage plug 802 to disengage from the lubrication tube 6. Only in this process can the lubricating oil be discharged outward through the lubrication tube 6. When the lubrication tube 6 is in other positions, under the action of the second spring 805, the anti-leakage plug 802 will automatically reset to block the lubrication tube 6, thereby preventing the lubricating oil from leaking at other positions at will. While ensuring smooth lubrication, it can not only reduce the waste of lubricating oil and improve the utilization rate of lubricating oil, but also prevent the lubricating oil from flowing at will to pollute the internal environment of the machine body.

[0051] On the basis of the above scheme, the aircraft propulsion transmission device provided by the present application comprises a magnet group including a plurality of adsorption magnets 801 , a driving plate 803 magnetically cooperates with the adsorption magnets 801 , and the adsorption magnets 801 are installed on both sides of the synchronous belt 1 in an annular intermittent structure.

[0052] Since the adsorption magnet 801 is arranged in an intermittent structure, the driving plate 803 will drive the anti-leakage plug 802 to move back and forth linearly, continuously pushing the lubricating oil through the lubricating pipe 6 to the synchronous wheel 12, further ensuring the smooth lubrication.

[0053] On the basis of the above scheme, the aircraft propulsion transmission device provided by the present application, the anti-leakage mechanism also includes two oil receiving boxes 9, the oil receiving boxes 9 are arranged on both sides of the synchronous belt 1, and the oil receiving boxes 9 are detachably installed on the bottom cover 3. The oil receiving boxes 9 can receive the lubricating oil remaining on the lubricating pipe 6, further reducing the probability of the lubricating oil dripping and contaminating other parts of the body.

[0054] Reference Figure 1 , Figure 2 and Figure 8 The aircraft propulsion transmission device provided in the present application, the oil pump assembly 5 includes an oil storage barrel 502, an oil inlet pipe 505 and a uniform distribution mechanism.

[0055] The oil inlet pipe 505 is passed through one side of the oil storage barrel 502; the end of the oil inlet pipe 505 is connected and fixed to the input end of the oil pump 503; the uniform distribution mechanism is used to ensure that the oil inlet pipe 505 can absorb lubricating oil with uniform composition.

[0056] Based on the above solution, for the aircraft propulsion transmission device provided in this application, the uniform distribution mechanism includes a receiving cylinder 504, a plurality of stirring pipes 509, and a driving mechanism.

[0057] The receiving cylinder 504 is rotatably sleeved on one side of the oil inlet pipe 505; the stirring pipes 509 are fixedly connected to the receiving cylinder 504; the driving mechanism is used to drive the receiving cylinder 504 to rotate.

[0058] During the operation of the oil extraction pump 503, under the action of the driving mechanism, the receiving cylinder 504 drives the stirring pipes 509 to rotate, which can stir the lubricating oil in the oil storage barrel 502. This can not only ensure the uniformity of the lubricating oil composition inside the oil storage barrel 502, but also enable the stirring pipes 509 to absorb the lubricating oil from different positions, avoiding the influence of uneven lubricating oil composition on the lubrication effect.

[0059] The driving mechanism includes a mounting cylinder 508, a driving impeller 507, and an output pipe 510.

[0060] One side of the mounting cylinder 508 is fixedly connected with a push pipe 506; the driving impeller 507 is rotatably connected inside the mounting cylinder 508; the output pipe 510 is fixedly connected between the oil inlet pipe 505 and the mounting cylinder 508.

[0061] When the oil extraction pump 503 is operating, a part of the lubricating oil enters the mounting cylinder 508 through the push pipe 506, impacts the driving impeller 507, enabling the receiving cylinder 504 to drive the stirring pipes 509 to rotate smoothly.

[0062] The implementation principle of the aircraft propulsion transmission device in the embodiment of this application is as follows: When the relevant technical solution transmits power to the aircraft, under the control of an external control mechanism, the oil extraction pump 503 operates, and the lubricating oil in the oil storage barrel 502 is input into the inner cavity of the synchronous belt 1 through the oil outlet pipe 501. When the lubricating pipe 6 moves to the synchronous pulley 12, under the magnetic force of the adsorption magnet 801, the driving plate 803 drives the anti-leakage plug 802 to perform reciprocating linear movement, continuously pushing the lubricating oil through the lubricating pipe 6 towards the synchronous pulley 12 to lubricate between the synchronous pulley 12 and the synchronous belt 1.

[0063] After the driving plate 803 moves away from the adsorption magnet 801, under the action of the second spring 805, the anti-leakage plug 802 will automatically reset to block the lubricating pipe 6 and prevent the lubricating oil from leaking randomly at other positions.

[0064] During the discharge of the lubricating oil, under the gravity of the counterweight frame 702 and the lower pressing plate 701, the lower pressing plate 701 always maintains a downward movement trend, thereby pushing the lubricating oil inside the synchronous belt 1, enabling the lubricating oil inside the synchronous belt 1 to be discharged smoothly through the lubricating pipe 6 even if it is in a viscous state.

[0065] As the amount of lubricating oil inside the synchronous belt 1 continuously decreases, the counterweight frame 702 drives the pressing plate 705 to gradually move downward, and the pressure borne by the pressure sensor 703 continuously increases. When the threshold value is reached, under the control of an external control mechanism, the oil pump 503 operates to automatically add lubricating oil into the synchronous belt 1.

[0066] In addition, during the operation of the oil pump 503, a part of the lubricating oil enters the installation cylinder 508 through the pushing pipe 506 to impact the driving impeller 507, and the receiving cylinder 504 drives the stirring pipe 509 to rotate, ensuring that the oil inlet pipe 505 can suck in lubricating oil with uniform composition. Continuing like this can ensure smooth lubrication between the synchronous pulley 12 and the synchronous belt 1.

[0067] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application 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 should not be construed as a limitation to the present application.

[0068] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present application, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically defined.

[0069] In the present application, unless otherwise clearly specified and limited, the terms "installation", "connection", "connection", "fixation", etc. should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection, an electrical connection, or can communicate with each other; it can be directly connected, or indirectly connected through an intermediate medium, and can be the connection inside two components or the interaction relationship between two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0070] Although the preferred embodiments of the present application have been described, those skilled in the art can make additional changes and modifications once they know the basic creative concept. Therefore, the appended claims are intended to be construed as including the preferred embodiments and all changes and modifications falling within the scope of the present application.

[0071] Obviously, those skilled in the art can make various changes and modifications to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of the claims of this application and their equivalent technologies, this application is also intended to include these modifications and variations.

Claims

1. An aircraft propulsion transmission device, characterized in that: Include: A synchronous belt (1), wherein the synchronous belt (1) is provided in a hollow structure, a top cover (2) is inserted into one side of the synchronous belt (1), and the synchronous belt (1) is slidably connected to the top cover (2); A power transmission mechanism, the transmission mechanism comprising two drive shafts (4), a synchronous wheel (12) being sleeved and fixed on the drive shaft (4), and the synchronous wheel (12) being meshingly connected with a synchronous belt (1); A plurality of lubrication pipes (6), wherein the lubrication pipes (6) are passed through the synchronous belt (1); An oil pump assembly (5), the oil pump assembly (5) comprising an oil pump (503), the output end of the oil pump (503) being fixedly connected to an oil outlet pipe (501), the end of the oil outlet pipe (501) passing through one side of the top cover (2) and extending to the inner cavity of the synchronous belt (1); An oil delivery mechanism, the oil delivery mechanism is used to ensure that the lubricating oil is smoothly discharged through the lubricating pipe (6); The anti-leakage mechanism is used to prevent the lubricating oil from leaking through the lubricating pipe (6).

2. The aircraft propulsion transmission device according to claim 1, characterized in that: The oil delivery mechanism comprises: an oil filling component (7), and the oil filling component (7) comprises: A lower pressing plate (701), the lower pressing plate (701) being installed in the inner cavity of the synchronous belt (1), the lower pressing plate (701) being in frictional contact with the inner wall of the synchronous belt (1); A counterweight frame (702), the counterweight frame (702) being slidably disposed on the top cover (2), and the end of the counterweight frame (702) being connected and fixed to the lower pressing plate (701); An oil replenishing mechanism, the oil replenishing mechanism is used to automatically replenish the lubricating oil in the synchronous belt (1).

3. The aircraft propulsion transmission device according to claim 2, characterized in that: The oil replenishing mechanism comprises: A pressure sensor (703), the pressure sensor (703) being fixedly mounted on the top cover (2), the pressure sensor (703) being electrically connected to an external control mechanism; A push plate (705) is installed on the lower side of the counterweight frame (702), a first spring (704) is fixedly connected between the push plate (705) and the counterweight frame (702), and the push plate (705) is in abutment with the pressure sensor (703).

4. The aircraft propulsion transmission device according to claim 3, characterized in that: The oil delivery mechanism also includes: A plurality of reinforcing rods (11), wherein the reinforcing rods (11) are fixedly mounted in the synchronous belt (1); A hot oil mechanism, the hot oil mechanism comprising a bottom cover (3) inserted on the other side of the synchronous belt (1), the upper side of the bottom cover (3) being made of metal material, and an electric heating plate (10) being installed in the bottom cover (3).

5. The aircraft propulsion transmission device according to claim 1, characterized in that: The anti-leakage mechanism comprises an oil drain valve (8), and the oil drain valve (8) comprises: An anti-leakage plug (802), the anti-leakage plug (802) being plug-fitted into the lubrication pipe (6); A pushing mechanism, wherein the pushing mechanism is used to drive the anti-leakage plug (802) to move linearly.

6. The aircraft propulsion transmission device according to claim 5, characterized in that: The driving mechanism comprises: A magnet group, the magnet group being mounted inside the synchronous belt (1) at a position corresponding to the synchronous wheel (12), the drive plate (803) being magnetically matched with the magnet group; A driving plate (803), wherein the end of the anti-leakage plug (802) is connected and fixed to the corresponding driving plate (803); A plurality of limiting sleeves, the limiting sleeves comprising a fixed sleeve (806) fixedly mounted on the synchronous belt (1), a sliding rod (804) slidably connected inside the fixed sleeve (806), the sliding rod (804) being fixedly connected to the driving plate (803), and a second spring (805) being fixedly connected between the sliding rod (804) and the fixed sleeve (806).

7. The aircraft propulsion transmission device according to claim 6, characterized in that: The magnet group comprises a plurality of adsorption magnets (801), the drive plate (803) and the adsorption magnets (801) are magnetically matched, and the adsorption magnets (801) are installed on both sides of the synchronous belt (1) in an annular intermittent structure.

8. The aircraft propulsion transmission device according to claim 5, characterized in that: The anti-leakage mechanism further comprises two oil receiving boxes (9), the oil receiving boxes (9) being sleeved on both sides of the synchronous belt (1), and the oil receiving boxes (9) being detachably mounted on the bottom cover (3).

9. The aircraft propulsion transmission device according to claim 1, characterized in that: The oil pump assembly (5) comprises: Oil storage barrel (502), An oil inlet pipe (505), the oil inlet pipe (505) is passed through one side of the oil storage barrel (502), and the end of the oil inlet pipe (505) is connected and fixed to the input end of the oil pump (503); The uniform distribution mechanism is used to ensure that the oil inlet pipe (505) can absorb lubricating oil with uniform composition.

10. The aircraft propulsion transmission device according to claim 9, characterized in that: The uniform distribution mechanism comprises: A receiving tube (504), the receiving tube (504) being rotatably sleeved on one side of the oil inlet pipe (505); A plurality of stirring tubes (509), wherein the stirring tubes (509) are fixedly connected to the receiving tube (504); A driving mechanism, the driving mechanism being used to drive the receiving cylinder (504) to rotate; The driving mechanism comprises: An installation cylinder (508), one side of the installation cylinder (508) being fixedly connected to a push tube (506); A driving impeller (507), wherein the driving impeller (507) is rotatably connected in the mounting cylinder (508); An output pipe (510) is fixedly connected between the oil inlet pipe (505) and the mounting tube (508).

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