Aircraft engine cover plate connecting structure

Abstract

The utility model discloses an aircraft engine cover plate connecting structure which comprises an aircraft engine cover plate body, a connecting block is fixedly connected to the side surface of the aircraft engine cover plate body, a T-shaped block is movably connected to the side surface of the connecting block, and clamping grooves are symmetrically formed in the side surface of the T-shaped block. A T-shaped groove is formed in the upper surface of the fixing base, and a mounting groove is formed in the side inner wall of the fixing base. Through the cooperation of the T-shaped groove and the T-shaped block of the fixing base, the fastening effect of the long bolt and the nut and the limiting effect of the inclined clamping block and the clamping groove, the aircraft engine cover plate body can be effectively prevented from loosening or falling off in the flight process of an aircraft, flight safety is guaranteed, and compared with a traditional bolt connection mode, the aircraft engine cover plate body can be effectively prevented from loosening or falling off. When the engine cover plate is disassembled and assembled, a large number of bolts do not need to be disassembled one by one, operation is simpler, more convenient and faster, the maintenance efficiency of an aircraft is greatly improved, and the downtime is shortened.

Description

Aircraft engine cover connection structure Technical Field

[0001] This utility model belongs to the field of aircraft technology, specifically relating to the connection structure of aircraft engine cover plates. Background Technology

[0002] During aircraft operation, the connection structure of the engine cover is crucial. Traditional engine cover connection structures typically use bolt or snap-fit ​​connections.

[0003] While bolted connections are relatively stable, disassembling and installing bolts during aircraft maintenance and repair requires a significant amount of time and manpower, reducing maintenance efficiency. Although snap-fit ​​connections are easier to disassemble to some extent, their stability is poor. During high-speed flight, aircraft are susceptible to loosening or even falling off due to airflow impacts and engine vibrations, seriously threatening flight safety. Therefore, an engine cover connection structure that can both ensure connection stability and facilitate quick disassembly and installation is needed. Summary of the Invention

[0004] To solve the above-mentioned technical problems, the present invention adopts a technical solution as follows: providing an aircraft engine cover plate connection structure, including an aircraft engine cover plate body, a connecting block fixedly connected to the side surface of the aircraft engine cover plate body, a T-shaped block movably connected to the side surface of the connecting block, and slots symmetrically arranged on the side surface of the T-shaped block.

[0005] A fixing base has a T-slot on its upper surface and an installation groove on its inner side wall. A guide post is movably connected to the inner side wall of the installation groove. A block is fixedly connected to one end of the guide post. A slanted locking block is fixedly connected to the side surface of the block. A vertical rod is fixedly connected to the upper surface of the block. A strong spring is fixedly connected to the side surface of the block. A long bolt is movably connected through the side surface of the fixing base. A nut is threaded onto the side surface of the long bolt.

[0006] Through the above technical solution, the cooperation between the T-slot and T-block of the fixed seat, the fastening effect of the long bolt and nut, and the limiting effect of the inclined block and slot, the loosening or falling off of the aircraft engine cover body during the flight can be effectively prevented, ensuring flight safety. Compared with the traditional bolt connection method, this utility model does not require the removal of a large number of bolts one by one when disassembling and installing the engine cover, making the operation simpler and faster, greatly improving the maintenance efficiency of the aircraft and reducing downtime.

[0007] The present invention is further configured such that a column is fixedly connected to the side surface of the connecting block, a column groove is provided on the side surface of the T-block, the column is located inside the column groove, a reinforcing rib is provided on the upper surface of the aircraft engine cover body, and a butt joint thickening is provided on the side surface of the aircraft engine cover body.

[0008] Through the above technical solution, the column groove is used to insert the column, increasing the connection strength between the connecting block and the T-block.

[0009] The present invention is further configured such that a screw is threadedly connected to the upper surface of the T-block, the side surface of the screw is threadedly connected to the column, and the connecting block, the column, the T-block and the fixing seat are all made of high-strength aluminum alloy.

[0010] The above technical solution allows the T-block and connecting block to be fixed together with screws. When the T-block is damaged, it can be removed and replaced. The high-strength aluminum alloy connecting block, column, T-block and fixing seat effectively reduce the overall weight of the aircraft while ensuring structural strength, which is conducive to improving the fuel economy and flight performance of the aircraft.

[0011] The present invention is further configured such that the upper surface of the T-shaped block is symmetrically provided with through grooves, the through grooves being connected to and penetrating the T-shaped block.

[0012] The above technical solution allows the through slot to facilitate the passage of horizontal plates.

[0013] The present invention is further configured such that a threaded hole is provided on the side surface of the T-block, and the side surface of the T-block contacts the T-groove.

[0014] The present invention is further configured such that a horizontal plate is fixedly connected to the side surface of the vertical rod, and the side surface of the horizontal plate is movably connected to the fixed seat.

[0015] Through the above technical solution, the horizontal plate and guide post work together to guide the displacement of the inclined block, while the horizontal plate after installation can restrict the position of the screws, preventing the screws from loosening and slipping during use.

[0016] The present invention is further configured such that a movable block is fixedly connected to the upper end of the vertical rod, and a through hole is provided on the side surface of the fixed base.

[0017] The present invention is further configured such that a shock-absorbing damper is fixedly connected to the bottom inner wall of the T-shaped groove, and a rubber pad is fixedly connected to the upper end of the shock-absorbing damper, the upper surface of the rubber pad being in contact with the T-shaped block.

[0018] The beneficial effects of this utility model are as follows:

[0019] By utilizing the combination of the T-slot and T-block of the fixed seat, the tightening effect of the long bolt and nut, and the limiting effect of the inclined block and slot, the engine cover body of the aircraft can be effectively prevented from loosening or falling off during the flight of the aircraft, thus ensuring flight safety. Compared with the traditional bolt connection method, this utility model eliminates the need to remove a large number of bolts one by one when disassembling and installing the engine cover, making the operation simpler and faster, greatly improving the maintenance efficiency of the aircraft and reducing downtime. Attached Figure Description

[0020] Figure 1 is a first-view structural diagram of the aircraft engine cover connection structure of this utility model;

[0021] Figure 2 is a partial structural schematic diagram of the aircraft engine cover connection structure of this utility model.

[0022] Figure 3 is an enlarged view of point A in Figure 2;

[0023] Figure 4 is a partial exploded view of the aircraft engine cover plate connection structure of this utility model.

[0024] Figure 5 is an exploded view of another part of the aircraft engine cover plate connection structure of this utility model.

[0025] Figure 6 is an enlarged view of point B in Figure 5.

[0026] Reference numerals: 1. Aircraft engine cover body; 2. Connecting block; 3. Column; 4. T-block; 5. Column groove; 6. Screw; 7. Through groove; 8. Slot; 9. Threaded hole; 10. Fixing seat; 11. Mounting groove; 12. Angled locking block; 13. Block; 14. Vertical rod; 15. Horizontal plate; 16. Guide column; 17. Strong spring; 18. Moving block; 19. Long bolt; 20. Nut; 21. Through hole; 22. Rubber pad; 23. Vibration damping; 24. Reinforcing rib; 25. Thickened joint. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the present utility model.

[0028] As shown in Figures 1-6, the aircraft engine cover connection structure of this embodiment includes an aircraft engine cover body 1, a connecting block 2 fixedly connected to the side surface of the aircraft engine cover body 1, a T-shaped block 4 movably connected to the side surface of the connecting block 2, a column 3 fixedly connected to the side surface of the connecting block 2, a column groove 5 provided on the side surface of the T-shaped block 4, the column 3 located inside the column groove 5, and a screw 6 threadedly connected to the upper surface of the T-shaped block 4, with the side surface of the screw 6 threadedly connected to the column 3.

[0029] After inserting the column 3 into the column groove 5, screw 6 into it to fix the column 3 and T-block 4 together, thus completing the connection between the connecting block 2 and the T-block 4. When the T-block 4 is damaged after long-term use, it can be removed and replaced.

[0030] The connecting block 2, column 3, T-block 4 and fixing seat 10 are all made of high-strength aluminum alloy. The side surface of the T-block 4 is symmetrically provided with slots 8, and the upper surface of the T-block 4 is symmetrically provided with through slots 7. The through slots 7 and slots 8 are connected and penetrate through the T-block 4. The upper surface of the aircraft engine cover body 1 is provided with reinforcing ribs 24, and the side surface of the aircraft engine cover body 1 is provided with butt thickening 25.

[0031] The fixing seat 10 has a T-slot on its upper surface and a threaded hole 9 on the side surface of the T-block 4. The side surface of the T-block 4 contacts the T-slot and the inner side wall of the fixing seat 10 has an installation groove 11.

[0032] The high-strength aluminum alloy connecting block 2, column 3, T-block 4 and fixed seat 10 effectively reduce the overall weight of the aircraft while ensuring structural strength, which is conducive to improving the fuel economy and flight performance of the aircraft. When the T-block 4 is installed in the T-slot of the fixed seat 10, the through slot 7 facilitates the passage of the horizontal plate 15.

[0033] A guide post 16 is movably connected to the inner side wall of the mounting groove 11. A block 13 is fixedly connected to one end of the guide post 16. An inclined locking block 12 is fixedly connected to the side surface of the block 13. A vertical rod 14 is fixedly connected to the upper surface of the block 13. A horizontal plate 15 is fixedly connected to the side surface of the vertical rod 14. The side surface of the horizontal plate 15 is movably connected to the fixing seat 10. A moving block 18 is fixedly connected to the upper end of the vertical rod 14. A through hole 21 is provided on the side surface of the fixing seat 10. A strong spring 17 is fixedly connected to the side surface of the block 13.

[0034] The mounting base 10 is fixedly installed on the engine body. When the T-block 4 is installed into the mounting base 10, the moving block 18 is moved to retract the strong spring 17. The guide post 16, the horizontal plate 15, the vertical rod 14, the block 13 and the inclined locking block 12 all move into the mounting groove 11. At this time, the T-block 4 is inserted into the T-groove to achieve the initial positioning of the aircraft engine cover plate body 1 and the engine body. After the moving block 18 is released, the strong spring 17 returns to its original position, which resets the guide post 16, the horizontal plate 15, the vertical rod 14, the block 13 and the inclined locking block 12. The inclined locking block 12 is inserted into the locking groove 8, and the lower surface of the horizontal plate 15 contacts the screw 6 to restrict the position of the screw 6.

[0035] A long bolt 19 is movably connected through the side surface of the fixed seat 10. A nut 20 is threadedly connected to the side surface of the long bolt 19. A shock-absorbing damper 23 is fixedly connected to the bottom inner wall of the T-slot. A rubber pad 22 is fixedly connected to the upper end of the shock-absorbing damper 23. The upper surface of the rubber pad 22 is in contact with the T-block 4.

[0036] After the long bolts 19 are inserted into the through holes 21 of the fixing seat 10 and the threaded holes 9 of the T-block 4 in sequence, the nuts 20 are tightened to increase the connection stability. When disassembling the aircraft engine cover body 1, compared with the traditional method of connecting a large number of bolts, this utility model does not require disassembling a large number of bolts one by one, making the operation simpler and faster, greatly improving the maintenance efficiency of the aircraft and reducing downtime. The rubber pads 22 and the shock-absorbing dampers 23 work together to play a buffering role, reducing the impact of engine vibration and airflow impact on the overall connection parts.

[0037] The working principle of this utility model is as follows: When it is necessary to install the aircraft engine cover plate body 1, firstly, insert the column 3 on the connecting block 2 into the column groove 5 on the T-block 4, and use screws 6 to fix the T-block 4 and the connecting block 2 together. Then, move the moving block 18 to cause the strong spring 17 to contract, and the guide column 16, horizontal plate 15, vertical rod 14, block 13 and inclined locking block 12 will all move into the mounting groove 11. At this time, insert the T-block 4 into the fixing seat 10 installed on the engine body, so that the T-block 4 is embedded in the fixing seat 10, realizing the initial positioning of the aircraft engine cover plate body 1 and the engine body. After releasing the moving block 18, the strong spring 17 returns to its original position, so that the guide column 16, horizontal plate 15, vertical rod 14, block 16, horizontal plate 15, vertical rod 14 and inclined locking block 12 are all moved into the mounting groove 11. 3. The inclined locking block 12 is reset and inserted into the locking slot 8. The lower surface of the horizontal plate 15 contacts the screw 6, restricting the position of the screw 6. Then, the long bolt 19 is passed through the fixed seat 10 and the T-block 4, and the nut 20 is tightened. Through the tightening action of the long bolt 19 and the nut 20, the fixed seat 10 and the T-block 4 are tightly connected together. During flight, the rubber pad 22 and the shock-absorbing damper 23 work together to play a buffering role, reducing the impact of engine vibration and airflow impact on the overall connection parts. When the engine needs to be maintained and repaired, simply unscrew the nut 20, pull out the long bolt 19, and then pry the moving block 18 to remove the T-block 4 from the fixed seat 10 to quickly disassemble the aircraft engine cover body 1.

[0038] The above description is merely an embodiment of this utility model and does not limit the patent scope of this utility model. Any equivalent structural or procedural transformations made based on the description and drawings of this utility model, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this utility model.

Claims

1. An aircraft engine cover connection structure, characterized in that: The system includes an aircraft engine cover body (1), a connecting block (2) fixedly connected to the side surface of the aircraft engine cover body (1), a T-shaped block (4) movably connected to the side surface of the connecting block (2), and slots (8) symmetrically arranged on the side surface of the T-shaped block (4); and a fixing seat (10), the upper surface of the fixing seat (10) being provided with a T-shaped groove, and an installation groove (11) being provided on the inner side wall of the fixing seat (10), the inner side wall of the installation groove (11) being movably connected to... A guide post (16) is attached, and a block (13) is fixedly connected to one end of the guide post (16). An inclined block (12) is fixedly connected to the side surface of the block (13). A vertical rod (14) is fixedly connected to the upper surface of the block (13). A strong spring (17) is fixedly connected to the side surface of the block (13). A long bolt (19) is movably connected through the side surface of the fixing seat (10). A nut (20) is threadedly connected to the side surface of the long bolt (19).

2. The aircraft engine cover plate connection structure according to claim 1, characterized in that, The side surface of the connecting block (2) is fixedly connected to a column (3), the side surface of the T-block (4) is provided with a column groove (5), the column (3) is located inside the column groove (5), the upper surface of the aircraft engine cover body (1) is provided with a reinforcing rib (24), and the side surface of the aircraft engine cover body (1) is provided with a butt joint thickening (25).

3. The aircraft engine cover connection structure according to claim 2, characterized in that, The upper surface of the T-block (4) is threaded with a screw (6), and the side surface of the screw (6) is threaded with the column (3). The connecting block (2), the column (3), the T-block (4) and the fixing seat (10) are all made of high-strength aluminum alloy.

4. The aircraft engine cover connection structure according to claim 1, characterized in that, The upper surface of the T-shaped block (4) is symmetrically provided with through grooves (7), which are connected to the slot (8) and penetrate through the T-shaped block (4).

5. The aircraft engine cover connection structure according to claim 1, characterized in that, The side surface of the T-block (4) is provided with a threaded hole (9), and the side surface of the T-block (4) is in contact with the T-groove.

6. The aircraft engine cover plate connection structure according to claim 1, characterized in that, A horizontal plate (15) is fixedly connected to the side surface of the vertical rod (14), and the side surface of the horizontal plate (15) is movably connected to the fixed seat (10).

7. The aircraft engine cover connection structure according to claim 1, characterized in that, The upper end of the vertical rod (14) is fixedly connected to a movable block (18), and the side surface of the fixed base (10) is provided with a through hole (21).

8. The aircraft engine cover connection structure according to claim 1, characterized in that, The bottom inner wall of the T-slot is fixedly connected to a shock-absorbing damper (23), and the upper end of the shock-absorbing damper (23) is fixedly connected to a rubber pad (22). The upper surface of the rubber pad (22) is in contact with the T-block (4).

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