Self-locking device for aero-engine
By designing a self-locking device for aero engines that drive the rolling and reeling components, the problems of difficult and low efficiency of pipeline fixing caused by small pawl size in the prior art are solved, and automatic locking and efficient fixing of the pipeline are achieved.
Patent Information
- Application Number
- CN202310804031.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-07-03
- Publication Date
- 2025-01-03
AI Technical Summary
The existing self-locking devices for aircraft engines are difficult to effectively clamp the pipeline due to the small size of the pawl, which leads to high difficulty in fixing, large number of use and low efficiency.
A self-locking device for aero engine including a self-locking tool, a self-locking belt, a drive reeling assembly and a fixed assembly is designed. By driving the reeling assembly, the self-locking belt is reeled and the pipe is automatically locked by using a cylinder and a raised block to lower the pipe. The difficulty of locking.
Automatic pipeline locking is realized, reducing operational difficulty and workload, and improving fixed efficiency.
Smart Images
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Abstract
Description
Technical Field
[0001] The present application relates to the technical field of aircraft engine accessories, and in particular to a self-locking device for an aircraft engine. Background Art
[0002] Aircraft engines generally use clamps to install and fix pipelines. When fixing pipelines, they must meet installation requirements such as pipeline fixation, vibration reduction, and frequency modulation. Because the reliability of the clamps will directly affect whether the pipelines can work safely and reliably, and engines often use a large number of clamps to fix pipelines, it is necessary to consider the impact of clamp installation and removal on assembly and maintainability.
[0003] The Chinese utility model patent document with announcement number CN209354762U discloses a self-locking device for an aircraft engine, including a connecting piece, a fixed clamp and a movable clamp, the fixed clamp and the movable clamp each including a connecting portion and two semi-annular movable claws, the connecting piece including a self-locking nut and a bolt, the bolt rod of the bolt passes through the connecting portion of the fixed clamp and the movable clamp, and the self-locking nut is detachably connected to the bolt rod; notches are provided on opposite sides of the connecting portion of the movable clamp, and rotating shafts are rotatably connected to the side walls of the two notches, the rotating shafts are located in the width direction of the connecting portion of the movable clamp, gears are fixedly connected to the rotating shafts, the two gears are meshed with each other, and the two movable claws of the movable clamp are respectively fixedly connected to the two rotating shafts; a ratchet is fixedly connected to one of the rotating shafts, and a ratchet is provided on the connecting portion of the movable clamp for use in conjunction with the ratchet and for preventing the upper and lower movable claws from disengaging.
[0004] When the self-locking device for aircraft engines disclosed in the above utility model patent document is used, the staff needs to manually pull the pawl to disengage it from the ratchet. Then, the handle is used to rotate the shaft counterclockwise until the fixed claw and the movable claw clamp the pipeline to complete the fixation of the pipeline. However, due to the small size of the pawl, it is difficult to clamp the pipeline, and when fixing the pipeline, a large number of pawls are required, the workload is large, and the efficiency is low. Therefore, this application proposes a self-locking device for aircraft engines that is different from the prior art to solve the above technical problems. Summary of the invention
[0005] In order to improve the above-mentioned problems that the small size of the pawls makes it difficult to clamp the pipeline, and a large number of pawls are needed to fix the pipeline, resulting in a large workload and low efficiency, the present application provides a self-locking device for an aircraft engine.
[0006] The present application provides a self-locking device for an aircraft engine, which adopts the following technical solution:
[0007] A self-locking device for an aircraft engine comprises a self-locking device, a first mounting frame is fixed to an outer wall of one side of the self-locking device, a self-locking cavity is opened inside the self-locking device, a self-locking belt is fixed to the inner wall of the self-locking cavity opened by the self-locking device, an end of the self-locking belt passes through the outer wall of the self-locking device and extends to the inner cavity of the first mounting frame, a base frame is fixed to the bottom wall position of the inner cavity of the first mounting frame, a hanging top plate is provided at the top wall position of the inner cavity of the first mounting frame, a fixing component is installed at the bottom wall position of the hanging top plate, and a driving winding and unwinding component fixed to the end position of the self-locking belt is installed at the other end of the bottom wall of the inner cavity of the first mounting frame.
[0008] By adopting the above technical solution, the pipe to be fixed is sleeved inside the self-locking belt and the self-locking device, the self-locking belt can be reeled in to an appropriate length by starting the driving winding and unwinding component, and then the fixing component is started to fix the position of the self-locking belt, thereby automatically locking the pipe and reducing the difficulty of locking the pipe.
[0009] Optionally, a plurality of locking holes are evenly arranged inside the self-locking belt.
[0010] By adopting the above technical solution, the starting fixing component and the locking hole are engaged with each other, and then with the cooperation of the base frame, the position of the engaged self-locking belt can be fixed, so that the pipeline can be automatically locked, reducing the difficulty of locking the pipeline.
[0011] Optionally, the fixing assembly includes a second mounting frame, which is fixed on the bottom wall of the lifting top plate, and a cylinder is fixed on the top wall of the inner cavity of the lifting top plate. The end of the vertical output shaft of the cylinder passes through the bottom wall of the second mounting frame and is fixed with a fixing plate, and a plurality of groups of protrusions that fit in with the locking holes are evenly fixed on the bottom wall of the fixing plate.
[0012] By adopting the above technical solution, the starting cylinder drives the fixing plate to move downward so that the protruding block can engage with the locking hole, and then the position of the self-locking belt can be fixed under the action of the base frame, so that the pipeline can be automatically locked.
[0013] Optionally, a plurality of third mounting screw holes are provided on the top wall of the inner cavity of the first mounting frame, and third mounting bolts matching the threads of the third mounting screw holes are provided on both sides of the bottom wall of the hanging top plate.
[0014] By adopting the above technical solution, the third mounting bolt is screwed to be threadedly connected with the third mounting screw hole, and then the position of the hanging top plate is moved to separate it from the first mounting frame, so that the hanging top plate and the fixing assembly can be disassembled and replaced.
[0015] Optionally, the driving winding and unwinding assembly includes a driving forward and reverse motor, which is fixed to the bottom wall of the inner cavity of the first installation frame through a pad, and a winding wheel is installed on the outside of the horizontal output shaft of the driving forward and reverse motor, and the outer wall of the winding wheel is fixed to the end position of the self-locking belt, and the end of the horizontal output shaft of the driving forward and reverse motor is rotatably connected to a positioning vertical plate through a bearing, and the bottom position of the positioning vertical plate is fixed to the bottom wall of the inner cavity of the first installation frame.
[0016] By adopting the above technical solution, the forward and reverse motors are started to drive the reel to rotate so that the self-locking belt can be reeled to an appropriate length, and the pipeline can be automatically locked.
[0017] Optionally, a battery pack is fixed to the bottom wall of the inner cavity of the first mounting frame, and a solar panel is provided on the top wall of the self-locking device. The battery pack is electrically connected to the solar panel, the driving forward and reverse motors, and the cylinder respectively.
[0018] By adopting the above technical solution, the solar energy is automatically captured by the solar panel and converted into electrical energy and stored in the battery pack, so that the battery pack can be used to provide energy for the cylinder and drive the forward and reverse motors.
[0019] Optionally, second mounting screw holes are provided at the four corners of the top wall of the self-locking device, mounting plates are provided around the top wall of the solar panel, and four groups of mounting plates are provided with second mounting bolts that match the threads of the second mounting screw holes.
[0020] By adopting the above technical solution, the second mounting bolt is screwed to separate it from the second mounting screw hole, and then the mounting plate is moved to separate it from the solar panel and the self-locking device, so that the solar panel can be disassembled and replaced.
[0021] Optionally, the front side wall of the first installation frame is rotatably connected to a door body via a hinge, and a handle is fixed to the outer wall of the door body.
[0022] By adopting the above technical solution, the door body can be flipped outward by holding the handle, making it convenient to disassemble and replace the lifting top plate and fixing components.
[0023] Optionally, a splicing frame is installed at one end of the top wall and the bottom wall of the self-locking device, and a detachable splicing plate is clamped on the two groups of splicing frames. The two side walls of the two groups of splicing plates are provided with a first mounting screw hole, and the outer walls of the two groups of splicing frames are provided with a first mounting bolt that matches the thread of the first mounting screw hole.
[0024] By adopting the above technical solution, the two sets of self-locking devices are attached to each other, and then the two sets of splicing plates are clamped in the inner cavity of the splicing frame. The first mounting bolt is screwed to be threadedly connected and fixed with the first mounting screw hole, so that the two sets of self-locking devices can be spliced together, thereby fixing the two sets of pipes to each other at the same time.
[0025] Optionally, the other ends of the top wall and the bottom wall of the self-locking device are both installed with foot blocks.
[0026] By adopting the above technical solution, the position of the self-locking device for the aircraft engine can be stably placed under the action of the splicing frame and the footing block.
[0027] In summary, the present application includes at least one of the following beneficial effects:
[0028] First, the pipe to be fixed is placed inside the self-locking belt and the self-locking device, and the forward and reverse motors are started to drive the reel to rotate so that the self-locking belt can be reeled to an appropriate length. Then, the cylinder is started to drive the fixing plate to move downward so that the protruding block can engage with the locking hole. Then, with the cooperation of the base frame, the position of the self-locking belt can be fixed, so that the pipe can be automatically locked, reducing the difficulty of locking the pipe.
[0029] Second, fit the two sets of self-locking devices together, then clamp the two sets of splicing plates in the inner cavity of the splicing frame, screw the first mounting bolt to make it threadedly connected and fixed with the first mounting screw hole, so that the two sets of self-locking devices can be spliced together, thereby fixing the two sets of pipes to each other at the same time. BRIEF DESCRIPTION OF THE DRAWINGS
[0030] Figure 1 This is a schematic diagram of the cross-sectional structure of the present application;
[0031] Figure 2 This is a schematic diagram of the front cross-sectional structure of the first installation frame of the present application;
[0032] Figure 3 This is a side view of the structure of the self-locking belt of this application;
[0033] Figure 4 This is a schematic diagram of the right side cross-sectional structure of the first installation frame of the present application;
[0034] Figure 5 This is a schematic diagram of the front view structure of the first installation frame of this application;
[0035] Figure 6 This is a schematic diagram of the top view structure of this application.
[0036] In the figure: 1. Self-locking belt; 2. Self-locking device; 3. Splicing frame; 4. First mounting screw hole; 5. First mounting bolt; 6. Foot block; 7. First mounting frame; 8. Base frame; 9. Second mounting screw hole; 10. Mounting plate; 11. Solar panel; 12. Second mounting bolt; 13. Splicing plate; 14. Locking hole; 15. Door body; 16. Handle; 17. Cylinder; 18. Second mounting frame; 19. Fixed plate; 20. Battery pack; 21. Winding wheel; 22. Third mounting bolt; 23. Lifting top plate; 24. Third mounting screw hole; 25. Positioning vertical plate; 26. Drive forward and reverse motor. DETAILED DESCRIPTION
[0037] The following is combined with Figure 1-6 This application is described in further detail.
[0038] Example 1, please refer to the attached figure in the specification Figure 1 , 2 And 3, a self-locking device for an aircraft engine, comprising a self-locking device 2, a first mounting frame 7 is fixed to the outer wall of one side of the self-locking device 2, a self-locking cavity is opened inside the self-locking device 2, a self-locking belt 1 is fixed to the inner wall of the self-locking cavity opened by the self-locking device 2, a plurality of groups of locking holes 14 are evenly opened inside the self-locking belt 1, an end of the self-locking belt 1 passes through the outer wall of the self-locking device 2 and extends to the inner cavity of the first mounting frame 7, a base frame 8 is fixed to the bottom wall position of the inner cavity of the first mounting frame 7, and a lifting top plate 23 is arranged on the top wall position of the inner cavity of the first mounting frame 7.
[0039] Please refer to the attached figure in the instruction manual Figure 2 A fixing component is installed at the bottom wall of the lifting top plate 23, and the fixing component includes a second mounting frame 18. The second mounting frame 18 is fixed on the bottom wall of the lifting top plate 23. A cylinder 17 is fixed at the top wall of the inner cavity of the lifting top plate 23. The end of the vertical output shaft of the cylinder 17 passes through the bottom wall of the second mounting frame 18 and is fixed with a fixing plate 19. The fixing plate 19 is arranged directly above the base frame 8, and a plurality of groups of protrusions that are engaged with the locking holes 14 are evenly fixed at the bottom wall of the fixing plate 19.
[0040] Please refer to the attached figure in the instruction manual Figure 4 A driving winding and unwinding assembly fixed to the end position of the self-locking belt 1 is installed at the other end of the bottom wall of the inner cavity of the first installation frame 7, and the driving winding and unwinding assembly includes a driving forward and reverse motor 26, and the driving forward and reverse motor 26 is fixed to the bottom wall of the inner cavity of the first installation frame 7 through a pad. A winding wheel 21 is installed on the outside of the horizontal output shaft of the driving forward and reverse motor 26, and the outer wall of the winding wheel 21 is fixed to the end position of the self-locking belt 1. The end of the horizontal output shaft of the driving forward and reverse motor 26 is rotatably connected to a positioning vertical plate 25 through a bearing, and the bottom position of the positioning vertical plate 25 is fixed to the bottom wall of the inner cavity of the first installation frame 7.
[0041] The specific working principle is: the pipe to be fixed is sleeved inside the self-locking belt 1 and the self-locking device 2, the forward and reverse motor 26 is started to drive the winding wheel 21 to rotate so that the self-locking belt 1 can be wound to an appropriate length, and then the cylinder 17 is started to drive the fixing plate 19 to move downward so that the protruding block can engage with the locking hole 14, and then the position of the self-locking belt 1 can be fixed with the cooperation of the base frame 8, so that the pipe can be automatically locked, reducing the difficulty of locking the pipe.
[0042] Example 2, please refer to the attached figure in the specification Figure 5 A self-locking device for an aircraft engine includes: a front side wall of a first mounting frame 7 is rotatably connected to a door body 15 through a hinge, a handle 16 is fixed to the outer wall of the door body 15, the handle 16 is vertically arranged, and an anti-slip pattern is provided on the outer wall of the handle 16; a plurality of groups of third mounting screw holes 24 are provided on the top wall of the inner cavity of the first mounting frame 7, and third mounting bolts 22 that match the threads of the third mounting screw holes 24 are penetrated at both sides of the bottom wall of the hoisting top plate 23.
[0043] The specific working principle is: hold the handle 16 to drive the door body 15 to flip outward, then screw the third mounting bolt 22 to make it threadedly connected with the third mounting screw hole 24, and then move the position of the hanging top plate 23 to separate it from the first mounting frame 7, so that the hanging top plate 23 and the fixing components can be disassembled and replaced.
[0044] Example 3, please refer to the attached figure in the specification Figure 1 , 2 And 6, a self-locking device for an aircraft engine, comprising: a battery pack 20 is fixed to the bottom wall of the inner cavity of a first mounting frame 7, the battery pack 20 is arranged at the bottom of the inner cavity of a base frame 8, a solar panel 11 is arranged on the top wall of the self-locking device 2, and the battery pack 20 is electrically connected to the solar panel 11, the driving forward and reverse motors 26 and the cylinder 17 respectively.
[0045] The specific working principle is: the solar energy is automatically captured under the action of the solar panel 11 and converted into electrical energy and stored in the battery pack 20, so that the battery pack 20 can be used to provide energy for the cylinder 17 and drive the forward and reverse motor 26.
[0046] Example 4, please refer to the attached figure in the specification Figure 2 A self-locking device for an aircraft engine includes: second mounting screw holes 9 are opened at the four corners of the top wall of the self-locking device 2, mounting plates 10 are arranged around the top wall of the solar panel 11, and second mounting bolts 12 that match the threads of the second mounting screw holes 9 are penetrated on the four groups of mounting plates 10.
[0047] The specific working principle is: screw the second mounting bolt 12 to separate it from the second mounting screw hole 9, and then move the mounting plate 10 to separate it from the solar panel 11 and the self-locking device 2, so that the solar panel 11 can be disassembled and replaced.
[0048] Example 5, please refer to the attached figure in the specification Figure 1 and 6 A self-locking device for an aircraft engine includes a splicing frame 3 installed at one end of the top wall and the bottom wall of the self-locking device 2, two groups of splicing frames 3 are clamped with detachable splicing plates 13, both side walls of the two groups of splicing plates 13 are provided with first mounting screw holes 4, and the outer walls of the two groups of splicing frames 3 are penetrated with first mounting bolts 5 that are threadably matched with the first mounting screw holes 4.
[0049] The specific working principle is: fit the two sets of self-locking devices 2 together, then clamp the two sets of splicing plates 13 in the inner cavity of the splicing frame 3, screw the first mounting bolt 5 so that it is threadedly connected and fixed with the first mounting screw hole 4, so that the two sets of self-locking devices 2 can be spliced together, so that the two sets of pipes can be fixed to each other at the same time.
[0050] Example 6, please refer to the attached figure in the specification Figure 1 and 6 A self-locking device for an aircraft engine includes a self-locking device 2, and the other ends of the top wall and the bottom wall are both equipped with a foot block 6.
[0051] The specific working principle is: under the action of the splicing frame 3 and the foot block 6, the position of the self-locking device for the aircraft engine can be stably placed.
[0052] Working principle: When using the self-locking device for aircraft engines, the pipe to be fixed is sleeved inside the self-locking belt 1 and the self-locking device 2, and the forward and reverse motor 26 is started to drive the winding wheel 21 to rotate so that the self-locking belt 1 can be wound to an appropriate length, and then the cylinder 17 is started to drive the fixing plate 19 to move downward so that the protruding block can engage with the locking hole 14, and then the position of the self-locking belt 1 can be fixed with the cooperation of the base frame 8, so that the pipe can be automatically locked, reducing the difficulty of locking the pipe, and the position of the self-locking device for aircraft engines can be stably placed under the action of the splicing frame 3 and the foot block 6.
[0053] When two groups of pipes need to be fixed together, it is only necessary to fit the two groups of self-locking devices 2 together, then engage the two groups of splicing plates 13 in the inner cavity of the splicing frame 3, and screw the first mounting bolt 5 so that it is threadedly connected and fixed with the first mounting screw hole 4, so that the two groups of self-locking devices 2 can be spliced together, thereby fixing the two groups of pipes to each other at the same time.
[0054] Hold the handle 16 to drive the door body 15 to flip outward, then screw the third mounting bolt 22 to make it threadedly connected with the third mounting screw hole 24, and then move the position of the hanging top plate 23 to separate it from the first mounting frame 7, so that the hanging top plate 23 and the fixing components can be disassembled and replaced.
[0055] Under the action of the solar panel 11, the energy of solar energy is automatically captured and converted into electrical energy and stored in the battery pack 20, so that the battery pack 20 can be used to provide energy for the cylinder 17 and drive the forward and reverse motor 26, and the second mounting bolt 12 is screwed to separate it from the second mounting screw hole 9, and then the mounting plate 10 is moved to separate it from the solar panel 11 and the self-locking device 2, so that the solar panel 11 can be disassembled and replaced.
[0056] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.
Claims
1. A self-locking device for an aircraft engine, comprising a self-locking device (2), characterized in that: A first mounting frame (7) is fixed to the outer wall of one side of the self-locking device (2), a self-locking cavity is opened inside the self-locking device (2), a self-locking belt (1) is fixed to the inner wall of the self-locking cavity opened by the self-locking device (2), the end of the self-locking belt (1) passes through the outer wall of the self-locking device (2) and extends to the inner cavity of the first mounting frame (7), a base frame (8) is fixed to the bottom wall of the inner cavity of the first mounting frame (7), a hanging top plate (23) is arranged at the top wall of the inner cavity of the first mounting frame (7), a fixing component is installed at the bottom wall of the hanging top plate (23), and a driving winding and unwinding component fixed to the end of the self-locking belt (1) is installed at the other end of the bottom wall of the inner cavity of the first mounting frame (7).
2. A self-locking device for an aircraft engine according to claim 1, characterized in that: The self-locking belt (1) is evenly provided with a plurality of groups of locking holes (14) inside.
3. A self-locking device for an aircraft engine according to claim 2, characterized in that: The fixing assembly comprises a second mounting frame (18), the second mounting frame (18) being fixed on the bottom wall of a hanging top plate (23), a cylinder (17) being fixed on the top wall of the inner cavity of the hanging top plate (23), an end of a vertical output shaft of the cylinder (17) passing through the bottom wall of the second mounting frame (18) and being fixed with a fixing plate (19), a plurality of groups of protrusions which are evenly fixed on the bottom wall of the fixing plate (19) and which are engaged with the locking holes (14).
4. The self-locking device for an aircraft engine according to claim 1, characterized in that: A plurality of third mounting screw holes (24) are provided on the top wall of the inner cavity of the first mounting frame (7), and third mounting bolts (22) threadably matched with the third mounting screw holes (24) are provided on both sides of the bottom wall of the hanging top plate (23).
5. The self-locking device for an aircraft engine according to claim 3, characterized in that: The driving winding and unwinding assembly comprises a driving forward and reverse motor (26), which is fixed to the bottom wall of the inner cavity of the first installation frame (7) through a pad, and a winding wheel (21) is installed outside the horizontal output shaft of the driving forward and reverse motor (26), and the outer wall of the winding wheel (21) is fixed to the end position of the self-locking belt (1), and the end of the horizontal output shaft of the driving forward and reverse motor (26) is rotatably connected to a positioning vertical plate (25) through a bearing, and the bottom position of the positioning vertical plate (25) is fixed to the bottom wall of the inner cavity of the first installation frame (7).
6. The self-locking device for an aircraft engine according to claim 5, characterized in that: A battery pack (20) is fixed on the bottom wall of the inner cavity of the first installation frame (7), a solar panel (11) is arranged on the top wall of the self-locking device (2), and the battery pack (20) is electrically connected to the solar panel (11), the forward and reverse driving motor (26), and the cylinder (17), respectively.
7. The self-locking device for an aircraft engine according to claim 6, characterized in that: Second mounting screw holes (9) are provided at the four corners of the top wall of the self-locking device (2), mounting plates (10) are provided at the four sides of the top wall of the solar panel (11), and second mounting bolts (12) that match the threads of the second mounting screw holes (9) are passed through the four groups of mounting plates (10).
8. The self-locking device for an aircraft engine according to claim 1, characterized in that: The front side wall of the first installation frame (7) is rotatably connected to a door body (15) via a hinge, and a handle (16) is fixed to the outer wall of the door body (15).
9. The self-locking device for an aircraft engine according to claim 1, characterized in that: A splicing frame (3) is installed at one end of the top wall and the bottom wall of the self-locking device (2), and a detachable splicing plate (13) is clamped on the two groups of the splicing frames (3). The two side walls of the two groups of the splicing plates (13) are provided with a first mounting screw hole (4), and the outer walls of the two groups of the splicing frames (3) are penetrated by a first mounting bolt (5) that matches the thread of the first mounting screw hole (4).
10. The self-locking device for an aircraft engine according to claim 9, characterized in that: The other ends of the top wall and the bottom wall of the self-locking device (2) are both provided with foot blocks (6).