A small aircraft engine tilting installation vehicle

Abstract

This invention belongs to the field of engine assembly, and specifically relates to a small aircraft engine tilting mounting vehicle, comprising a base plate, universal wheels mounted on the bottom of the base plate, a support seat slidably connected to the base plate, a fixed frame fixed on the support seat, a rotating frame mounted on the fixed frame, a rotating shaft fixedly connected through the rotating frame, and a drive assembly for driving the rotating shaft to rotate on one side of the fixed frame; a center-of-gravity self-adjusting assembly for driving the support seat to move is provided on the base plate, the center-of-gravity self-adjusting assembly including an arc-shaped gear fixedly connected to the rotating shaft. This invention allows the mounting platform to be tilted by turning a handwheel, solving the problem of ensuring the coaxiality of the engine core and reducer during the assembly of small aircraft engines, thereby improving engine assembly efficiency. It has the advantages of compact structure, ease of use, and low manufacturing cost.

Description

Technical Field

[0001] This invention belongs to the field of engine assembly, and in particular relates to a small aircraft engine tilting installation vehicle. Background Technology

[0002] An aero engine is a type of thermodynamic machinery with a precise structure and complex assembly. It is also a concentrated reflection of a country's industrial base, technological level, and comprehensive national strength. It mainly provides flight power for helicopters, fixed-wing aircraft, and autogyros.

[0003] Traditional large aero-engine assembly mainly adopts vertical assembly technology, which can well ensure the coaxiality of the engine's rotor and stator components, and also facilitates the assembly operation of workers. However, the current small engines in China are basically assembled horizontally, which makes it impossible to guarantee the coaxiality of the engine's core components and the stability and safety of the mounting vehicle are poor. Summary of the Invention

[0004] The purpose of this invention is to address the problems mentioned in the background section by providing a small aircraft engine tilting mounting vehicle.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: a small aircraft engine tilting installation vehicle, including a base plate, universal wheels installed at the bottom of the base plate, a support seat slidably connected to the base plate, a fixed frame fixed on the support seat, a rotating frame provided on the fixed frame, a rotating shaft fixedly through the rotating frame, the rotating shaft being rotatably connected to the fixed frame, and a drive assembly for driving the rotating shaft to rotate provided on one side of the fixed frame;

[0006] The base plate is equipped with a center-of-gravity self-adjusting assembly for driving the support seat to move. The center-of-gravity self-adjusting assembly includes an arc-shaped gear fixedly connected to a rotating shaft, the center of which lies on the axis of the rotating shaft. A transmission shaft is rotatably connected to the fixed frame, and a gear is fixedly connected to the upper end of the transmission shaft. The gear meshes with the transmission shaft. A threaded rod is fixedly connected to the base plate, and a threaded sleeve is rotatably connected to the support seat. The threaded sleeve and the threaded rod are threaded together. A worm gear is coaxially fixed to the threaded sleeve, and a worm is fixedly connected to the transmission shaft. The worm and the worm gear mesh with each other.

[0007] Furthermore, the drive assembly includes a worm gear reducer mounted on a fixed frame, a handwheel mounted on the input end of the worm gear reducer, a sleeve slidably connected to the output shaft of the worm gear reducer, a flat key fixed on the rotating shaft, and the sleeve sleeved on the sleeve and provided with a keyway matching the flat key.

[0008] Furthermore, an electromagnet is installed on the fixing frame, and the end of the sleeve near the electromagnet is made of permanent magnet material and is opposite to the electromagnet with the same pole. The sleeve is connected to the side wall of the worm gear reducer through a first spring.

[0009] Furthermore, the rotating shaft and the arc-shaped gear are connected by two connecting pipes, which are arranged perpendicularly to each other. Each of the two connecting pipes contains an electrical component, and the two sets of electrical components are connected in series by a wire.

[0010] Furthermore, both sets of the energizing components include a counterweight that is slidably disposed inside the connecting tube. The counterweight is connected to the end of the connecting tube via a second spring. A conductive ring is embedded in the inner wall of the connecting tube. A contact head matching the conductive ring is fixed on the counterweight. The conductive ring is electrically connected to the power supply, and the contact head is electrically connected to the electromagnet. When both contact heads are in contact with the corresponding conductive rings, the circuit of the electromagnet is turned on.

[0011] Furthermore, an installation platform is fixed on the rotating frame, and bolts for fixing the engine reducer are provided on the installation platform.

[0012] Furthermore, an oil collection box is provided below the base plate.

[0013] Furthermore, both the support base and the fixing frame are made of square tubing welded together.

[0014] Compared with existing technologies, the advantages of this small aircraft engine tilting mounting vehicle are:

[0015] 1. In this invention, the support base and fixing frame are welded from square tubes, which are lightweight, have high structural rigidity and strength, and are equipped with universal casters under the base plate to facilitate the installation of the vehicle and the transfer of the engine. The installation platform can be flipped by turning the handwheel, which solves the problem of how to ensure the coaxiality of the engine core and the reducer during the assembly of small aero engines, thereby improving the engine assembly efficiency. It has the advantages of compact structure, easy use and low manufacturing cost.

[0016] 2. By setting up a center of gravity self-adjusting component, when the engine is flipped by turning the handwheel, the support base can be moved in the opposite direction of the engine flipping direction. This ensures that the center of gravity of the engine remains within the same vertical range during the flipping process, thereby ensuring the overall stability of the installation vehicle and preventing the installation vehicle from tipping over due to the center of gravity shift caused by the engine flipping.

[0017] 3. This invention, by setting up an electromagnet, sleeve, flat key, and energizing assembly, allows the engine to be flipped by rotating the handwheel. If the handwheel rotates too fast, causing the engine's flipping angular velocity to be too large, the rotating shaft drives the connecting pipe to rotate at a high speed. This results in a large centrifugal force on the counterweight, causing both energizing heads to contact their corresponding conductive rings. This activates the electromagnet's circuit, and under the action of magnetic force, pushes the sleeve to slide on the rotating shaft, causing the flat key to disengage from the keyway. In this case, the engine cannot be flipped by rotating the handwheel, improving operational safety and protecting the engine. Attached Figure Description

[0018] Figure 1 This is a front structural schematic diagram of a small aircraft engine tilting mounting vehicle provided by the present invention;

[0019] Figure 2 yes Figure 1 Enlarged view of point A in the middle;

[0020] Figure 3 This is a side view of a small aircraft engine tilting mounting vehicle provided by the present invention;

[0021] Figure 4 yes Figure 3 Enlarged view at point B in the middle;

[0022] Figure 5 This is a schematic diagram of the internal structure of the connecting pipe in a small aircraft engine tilting installation vehicle provided by the present invention.

[0023] In the diagram, 1 is the base plate, 2 is the caster wheel, 3 is the support base, 4 is the fixed frame, 5 is the rotating frame, 6 is the rotating shaft, 7 is the arc-shaped gear, 8 is the drive shaft, 9 is the gear, 10 is the threaded rod, 11 is the threaded sleeve, 12 is the worm gear, 13 is the worm, 14 is the worm gear reducer, 15 is the handwheel, 16 is the sleeve, 17 is the flat key, 18 is the electromagnet, 19 is the first spring, 20 is the connecting pipe, 21 is the counterweight, 22 is the second spring, 23 is the conductive ring, 24 is the connector, 25 is the mounting platform, 26 is the bolt, and 27 is the oil collection box. Detailed Implementation

[0024] The following examples are for illustrative purposes only and are not intended to limit the scope of the invention.

[0025] like Figure 1-5As shown, a small aircraft engine tilting installation vehicle includes a base plate 1. Casters 2 are installed at the bottom of the base plate 1 to facilitate the installation and engine transport. An oil collection box 27 is located below the base plate 1. A support base 3 is slidably connected to the base plate 1, and a fixing frame 4 is fixed to the support base 3. Both the support base 3 and the fixing frame 4 are welded from square tubing, resulting in lightweight construction with high structural rigidity and strength. A rotating frame 5 is installed on the fixing frame 4, and an installation platform 25 is fixed to the rotating frame 5. Bolts 26 for fixing the engine reducer are installed on the installation platform 25. A rotating shaft 6 is fixed through the rotating frame 5 and rotatably connected to the fixing frame 4.

[0026] A drive assembly for driving the rotating shaft 6 is provided on one side of the fixed frame 4. The drive assembly includes a worm gear reducer 14 mounted on the fixed frame 4. A handwheel 15 is installed at the input end of the worm gear reducer 14. A sleeve 16 is slidably connected to the output shaft of the worm gear reducer 14. A flat key 17 is fixed on the rotating shaft 6. The sleeve 16 is fitted onto the sleeve 16 and is provided with a keyway that matches the flat key 17. The installation platform 25 can be rotated by turning the handwheel 15. This solves the problem of how to ensure the coaxiality of the engine core and the reducer during the assembly of small aero engines, thereby improving the engine assembly efficiency. It has the advantages of compact structure, convenient use, and low manufacturing cost.

[0027] The base plate 1 is equipped with a center-of-gravity self-adjusting assembly for driving the support base 3 to move. The center-of-gravity self-adjusting assembly includes an arc-shaped gear 7 fixedly connected to the rotating shaft 6, with the center of the arc-shaped gear 7 falling on the axis of the rotating shaft 6. A drive shaft 8 is rotatably connected to the fixed frame 4, and a gear 9 is fixedly connected to the upper end of the drive shaft 8. The gear 9 meshes with the drive shaft 8. A threaded rod 10 is fixedly connected to the base plate 1, and a threaded sleeve 11 is rotatably connected to the support base 3. The threaded sleeve 11 is threadedly engaged with the threaded rod 10. A worm gear 12 is coaxially fixed to the threaded sleeve 11, and a worm 13 is fixedly connected to the drive shaft 8. The worm 13 meshes with the worm gear 12. When the engine is flipped by turning the handwheel 15, the support base 3 can be moved synchronously in the opposite direction of the engine flipping direction. This ensures that the center of gravity of the engine remains within the same vertical range during the flipping process, thereby ensuring the overall stability of the installation vehicle and preventing the problem of the installation vehicle tipping over due to the center of gravity shift caused by the engine flipping.

[0028] An electromagnet 18 is installed on the fixed frame 4. The end of the sleeve 16 near the electromagnet 18 is made of permanent magnet material and is opposite to the electromagnet 18 with the same pole. The sleeve 16 is connected to the side wall of the worm gear reducer 14 through the first spring 19. When the first spring 19 is in its natural state, the flat key 17 is engaged with the keyway, and the worm gear reducer 14 can drive the rotating shaft 6 to rotate.

[0029] The rotating shaft 6 and the arc-shaped gear 7 are connected by two connecting pipes 20, which are perpendicular to each other. Each connecting pipe 20 contains an electrical component, which is connected in series by a wire. Each electrical component includes a counterweight 21 slidably disposed within the connecting pipe 20. The counterweight 21 is connected to the end of the connecting pipe 20 via a second spring 22. A conductive ring 23 is embedded in the inner wall of the connecting pipe 20. A connector 24 matching the conductive ring 23 is fixed on the counterweight 21. The conductive ring 23 and the electrical connector 24 are connected... The power supply is electrically connected, and the connector 24 is electrically connected to the electromagnet 18. When the second spring 22 is in its natural state, the connector 24 does not contact the corresponding conductive ring 23. Since the two connecting tubes 20 are set perpendicular to each other, during the rotation of the rotating shaft 6, one connecting tube 20 always tends to deflect in the horizontal direction. Therefore, the second spring 22 is less affected by the gravity of the counterweight 21, and the connector 24 does not contact the corresponding conductive ring 23. That is, when the engine is in a stable and slow rotation, the electromagnet is in a de-energized state.

[0030] If the handwheel 15 is turned too fast during engine rotation, resulting in an excessively high angular velocity during engine rotation, the rotating shaft 6 will cause the connecting pipe 20 to rotate too quickly. This will result in a large centrifugal force on the counterweight 21, causing both electrical contacts 24 to contact the corresponding conductive rings 23. This will activate the circuit of the electromagnet 18, which will then push the sleeve 16 to slide on the rotating shaft 6 under magnetic force. This will disengage the flat key 17 from the keyway, making it impossible to control engine rotation by turning the handwheel 15. This improves operational safety and protects the engine.

[0031] The working principle of this invention is as follows:

[0032] Push the installation vehicle to the final assembly area and turn the handwheel 15 to adjust the installation platform of the installation vehicle to a horizontal state. Install the already assembled reducer on the installation vehicle platform 25 through the mounting seat and fix it with bolts 26. When assembling the engine, the engine can be moved into the vertical assembly state by moving the handwheel 15 according to actual requirements. After completing the vertical assembly of the intake casing, combustion chamber and turbine, the engine can be moved back into the horizontal assembly state by turning the handwheel 15 in the opposite direction as needed, so as to install fuel, lubricating oil, cable accessories and pipelines.

[0033] When the engine is flipped by turning the handwheel 15, the rotating shaft 6 drives the arc-shaped gear 7 to rotate synchronously. Since the gear 9 meshes with the transmission shaft 8, the transmission shaft 8 drives the worm 13 to rotate. Since the worm 13 meshes with the worm wheel 12, the threaded sleeve 11 can rotate. Since the threaded sleeve 11 is threadedly engaged with the threaded rod 10 and the threaded rod 10 is fixed on the base plate 1, when the threaded sleeve 11 rotates, it can drive the support seat 3 to move in the opposite direction of the engine flipping direction. This ensures that the center of gravity of the engine remains within the same vertical range during the flipping process, thereby ensuring the overall stability of the installation vehicle and preventing the problem of the installation vehicle tipping over due to the shift of the center of gravity caused by the engine flipping.

[0034] If the handwheel 15 is turned too fast during engine rotation, resulting in an excessively high angular velocity during engine rotation, the rotating shaft 6 will cause the connecting pipe 20 to rotate too quickly. This will result in a large centrifugal force on the counterweight 21, causing both electrical contacts 24 to contact the corresponding conductive rings 23. This will activate the circuit of the electromagnet 18, which will then push the sleeve 16 to slide on the rotating shaft 6 under magnetic force. This will disengage the flat key 17 from the keyway, making it impossible to control engine rotation by turning the handwheel 15. This improves operational safety and protects the engine.

[0035] 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 principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A small aircraft engine tilting mounting vehicle, comprising a base plate (1), characterized in that, The bottom of the base plate (1) is equipped with casters (2), a support base (3) is slidably connected to the base plate (1), a fixed frame (4) is fixed on the support base (3), a rotating frame (5) is provided on the fixed frame (4), a rotating shaft (6) is fixed through the rotating frame (5), the rotating shaft (6) is rotatably connected to the fixed frame (4), and a drive assembly for driving the rotating shaft (6) to rotate is provided on one side of the fixed frame (4); The base plate (1) is provided with a center of gravity self-adjusting component for driving the support base (3) to move. The center of gravity self-adjusting component includes an arc-shaped toothed rod (7) fixedly connected to the rotating shaft (6). The center of the arc-shaped toothed rod (7) falls on the axis of the rotating shaft (6). A transmission shaft (8) is rotatably connected to the fixed frame (4). A gear (9) is fixedly connected to the upper end of the transmission shaft (8). The gear (9) meshes with the arc-shaped toothed rod (7). A threaded rod (10) is fixedly connected to the base plate (1). A threaded sleeve (11) is rotatably connected to the support base (3). The threaded sleeve (11) is threadedly engaged with the threaded rod (10). A worm gear (12) is coaxially fixed on the threaded sleeve (11). A worm (13) is fixedly connected to the transmission shaft (8). The worm gear (13) meshes with the worm gear (12).

2. The small aircraft engine tilting mounting vehicle according to claim 1, characterized in that, The drive assembly includes a worm gear reducer (14) mounted on a fixed frame (4), a handwheel (15) is mounted on the input end of the worm gear reducer (14), a sleeve (16) is slidably connected on the output shaft of the worm gear reducer (14), a flat key (17) is fixed on the rotating shaft (6), and the sleeve (16) is sleeved on the sleeve (16) and provided with a keyway that matches the flat key (17).

3. The small aircraft engine tilting mounting vehicle according to claim 2, characterized in that, An electromagnet (18) is installed on the fixed frame (4). The end of the sleeve (16) near the electromagnet (18) is made of permanent magnet material and is opposite to the same pole of the electromagnet (18). The sleeve (16) is connected to the side wall of the worm gear reducer (14) through the first spring (19).

4. The small aircraft engine tilting mounting vehicle according to claim 3, characterized in that, The rotating shaft (6) and the arc-shaped toothed rod (7) are connected by two connecting pipes (20), which are perpendicular to each other. Each of the two connecting pipes (20) is equipped with an electrical component, and the two sets of electrical components are connected in series by wires.

5. The small aircraft engine tilting mounting vehicle according to claim 4, characterized in that, Both sets of the energizing components include a counterweight (21) slidably disposed in the connecting tube (20). The counterweight (21) is connected to the end of the connecting tube (20) via a second spring (22). A conductive ring (23) is embedded in the inner wall of the connecting tube (20). A connector (24) matching the conductive ring (23) is fixed on the counterweight (21). The conductive ring (23) is electrically connected to the power supply. The connector (24) is electrically connected to the electromagnet (18). When both connectors (24) are in contact with the corresponding conductive ring (23), the circuit of the electromagnet (18) is turned on.

6. The small aircraft engine tilting mounting vehicle according to claim 1, characterized in that, The rotating frame (5) is fixed with an installation platform (25), and the installation platform (25) is provided with bolts (26) for fixing the engine reducer.

7. The small aircraft engine tilting mounting vehicle according to claim 1, characterized in that, An oil collection box (27) is provided below the base plate (1).

8. The small aircraft engine tilting mounting vehicle according to claim 1, characterized in that, Both the support base (3) and the fixing frame (4) are made of square tubes welded together.

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