Aviation mechanical part reliability life analysis pressure detection equipment

Abstract

The utility model relates to the field of aviation mechanical parts, in particular to aviation mechanical part reliability life analysis pressure detection equipment which comprises a workbench and is used for aviation mechanical part life analysis pressure detection. According to the pressure detection equipment for reliability and life analysis of the aviation mechanical part, through the arrangement of the protective cover, the sealing door, the electric heater, the hydraulic cylinder, the hydraulic pump, the connecting sleeve, the pressure sensor, the contact block, the driving signal controller and the display, the aviation mechanical part is placed on the placing plate, and the sealing door is closed; then multiple sets of electric heating devices on the two sides in the protective cover are turned on, the interior is heated through the electric heating devices, then a hydraulic pump switch is turned on, oil pressure is generated in the interior to push a hydraulic cylinder and a contact block at the lower end to press downwards, and therefore pressure detection is conducted on the mechanical parts; and data obtained by a pressure sensor above the contact block is transmitted to a driving signal controller, and then the driving signal controller transmits the data to a display for observation and analysis.

Description

Technical Field

[0001] This utility model relates to the field of aerospace mechanical components, specifically to a pressure testing device for reliability life analysis of aerospace mechanical components. Background Technology

[0002] Aviation mechanical components are important parts of aircraft and aero engines. They perform various key functions to ensure the normal operation and performance of the aircraft. The special nature of aviation requires aircraft to maintain stability and safety under extreme conditions. The lifespan of important components is directly related to the reliability and performance of the aircraft. Aviation mechanical component pressure testing equipment is a key device to ensure that aviation mechanical components can withstand predetermined pressures during the design and manufacturing process and to verify their reliability and safety.

[0003] Existing pressure testing equipment for reliability life analysis of aerospace mechanical components simply uses pressure to analyze the life of these components, but it lacks pressure testing during the heating process. Without a heating system, it is impossible to accurately simulate the working state of the components in a high-temperature environment. This leads to inaccurate assessment of component performance and lifespan, and the aging process of the components will be relatively slow, which will extend the testing time accordingly. This results in a longer R&D cycle or a slower product improvement speed.

[0004] Therefore, it is necessary to invent a pressure testing device for reliability life analysis of aerospace mechanical components to solve the above problems. Utility Model Content

[0005] The purpose of this invention is to provide a pressure testing device for reliability and life analysis of aerospace mechanical components. The device places the aerospace mechanical component requiring pressure testing on a placement plate, closes the sealed door, and then activates multiple sets of electric heaters on both sides of the protective cover to heat the interior. Next, the hydraulic pump is turned on, generating internal oil pressure that pushes the hydraulic cylinder against the lower contact block, thus performing pressure testing on the mechanical component. Data obtained from the pressure sensor above the contact block is transmitted to the drive signal controller, which then displays the data on a monitor. This combination of internal heating and the device accurately simulates the component's operating state under high-temperature conditions, improving the evaluation of component performance and lifespan. This addresses the problem of existing pressure testing devices for reliability and life analysis of aerospace mechanical components, which simply use pressure to analyze the lifespan of components without incorporating pressure testing during the heating process. Without a heating system, it is impossible to accurately simulate the component's operating state under high-temperature conditions, leading to inaccurate evaluations of component performance and lifespan. Furthermore, the aging process of the component is relatively slow, and the testing time is correspondingly extended, resulting in prolonged development cycles or slower product improvement speeds.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a pressure testing device for reliability life analysis of aerospace mechanical components, including a workbench for pressure testing of life analysis of aerospace mechanical components;

[0007] A protective cover, installed above the workbench, is used to prevent splashing. The protective cover has an external hinged door with an observation window inside. A placement plate is slidably connected to the top of the workbench and the inside of the protective cover. Electric heaters are installed on both sides of the inside of the protective cover, and protective plates are fixedly connected to the outside of the electric heaters. A temperature sensor is fixedly installed on the top side of the inside of the protective cover. Fixed rods are fixedly connected around the top of the workbench, and a top plate is fixedly connected above the fixed rods. A hydraulic cylinder is fixedly installed above the top plate, and a hydraulic pump is fixedly installed above the hydraulic cylinder. A connecting sleeve is fixedly connected to the output end of the hydraulic cylinder, and a pressure sensor is installed inside the connecting sleeve. A contact block is fixedly connected to the lower end of the pressure sensor. A drive signal controller and a display are located on the right side of the workbench.

[0008] The clamping mechanism is located inside the rear of the protective cover and is used for clamping.

[0009] Preferably, the upper two sides of the workbench are provided with sliding grooves, and sliders are slidably connected inside the sliding grooves. The lower two sides of the placement plate are fixedly connected to the sliders.

[0010] Preferably, the clamping mechanism includes a servo motor, which is fixedly mounted on the right side of the protective cover. A lead screw is fixedly connected to the output end of the servo motor, and a clamping plate is connected to the external thread of the lead screw. A limit frame is fixedly connected to the inner rear side of the sealing door.

[0011] Preferably, the external threads of the lead screw are tapped in the opposite direction, and the clamping plate slides with the limiting frame.

[0012] Preferably, the input terminal of the temperature sensor is electrically connected to the output terminal of the drive signal controller, and the input terminal of the drive signal controller is electrically connected to the electric heating output terminal.

[0013] Preferably, the input terminal of the pressure sensor is electrically connected to the output terminal of the drive signal controller, and the input terminal of the drive signal controller is electrically connected to the output terminal of the display.

[0014] The technical effects and advantages provided by this utility model in the above technical solution are as follows:

[0015] 1. By setting up a protective cover, sealing door, electric heating, hydraulic cylinder, hydraulic pump, connecting sleeve, pressure sensor, contact block, drive signal controller, and display, the aerospace mechanical component requiring pressure detection and analysis is placed on a placement plate, the sealing door is closed, and then multiple sets of electric heating on both sides inside the protective cover are turned on to heat the interior. Then, the hydraulic pump switch is turned on, causing the internal oil pressure to push the hydraulic cylinder and the lower contact block downward, thereby detecting the pressure of the mechanical component. The data obtained by the pressure sensor above the contact block is transmitted to the drive signal controller, which then transmits the data to the display for observation. This, combined with the effect of internal heating, can accurately simulate the working state of the component in a high-temperature environment, improving the evaluation of the component's performance and lifespan.

[0016] 2. The design, including the protective cover, slide, slider, placement plate, and clamping mechanism, not only facilitates the handling of aerospace mechanical parts but also enhances their stability during testing. By placing the aerospace mechanical parts on the placement plate and using the slider below the placement plate to slide in the slide inside the protective cover, it is easy to remove the placement plate and the placed aerospace mechanical parts. After the placement plate is pushed into the protective cover, the servo motor switch is turned on, driving the lead screw to rotate. The rotation of the lead screw causes the external clamping plates to move closer together, thereby clamping and fixing the aerospace mechanical parts on the placement plate to prevent shaking during testing. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this invention. For those skilled in the art, other drawings can be obtained based on these drawings.

[0018] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0019] Figure 2 This is a schematic diagram of the internal structure of the protective cover of this utility model;

[0020] Figure 3 This is a schematic diagram of the electric heating structure of this utility model;

[0021] Figure 4 This is a schematic diagram of the clamping mechanism of this utility model;

[0022] Figure 5 This is a schematic diagram of the pressure sensor structure of this utility model;

[0023] Figure 6 This is the system control flowchart of this utility model.

[0024] Explanation of reference numerals in the attached figures:

[0025] 1. Workbench; 2. Protective cover; 3. Sealed door; 4. Observation window; 5. Slide rail; 6. Slider; 7. Placement plate; 8. Electric heating; 9. Protective plate; 10. Temperature sensor; 11. Clamping mechanism; 1101. Servo motor; 1102. Lead screw; 1103. Clamping plate; 1104. Limiting frame; 12. Fixing rod; 13. Top plate; 14. Hydraulic cylinder; 15. Hydraulic pump; 16. Connecting sleeve; 17. Pressure sensor; 18. Contact block; 19. Drive signal controller; 20. Display. Detailed Implementation

[0026] To enable those skilled in the art to better understand the technical solution of this utility model, the present utility model will be further described in detail below with reference to the accompanying drawings.

[0027] This utility model provides, for example Figure 1-6 The device shown is a pressure testing equipment for reliability life analysis of aerospace mechanical components, including a workbench 1, used for pressure testing of life analysis of aerospace mechanical components.

[0028] A protective cover 2 is installed above the workbench 1 to prevent splashing. The outer hinge of the protective cover 2 is connected to a sealing door 3. An observation window 4 is provided inside the sealing door 3. A placement plate 7 is slidably connected to the top of the workbench 1 and the inside of the protective cover 2. Electric heaters 8 are provided on both sides inside the protective cover 2. A protective plate 9 is fixedly connected to the outside of the electric heaters 8. A temperature sensor 10 is fixedly installed on the top side inside the protective cover 2. Fixed rods 12 are fixedly connected around the top of the workbench 1. A top plate 13 is fixedly connected above the fixed rods 12. A hydraulic cylinder 14 is fixedly installed above the top plate 13. A hydraulic pump 15 is fixedly installed above the hydraulic cylinder 14. A connecting sleeve 16 is fixedly connected to the output end of the hydraulic cylinder 14. A pressure sensor 17 is provided inside the connecting sleeve 16. A contact block 18 is fixedly connected to the lower end of the pressure sensor 17. A drive signal controller 19 is provided on the right side of the workbench 1. A display 20 is provided on the right side of the workbench 1.

[0029] The clamping mechanism 11, located inside the rear of the protective cover 2, is used for clamping. By placing the aerospace mechanical component requiring pressure testing and analysis on the placement plate 7, and then closing the sealing door 3, multiple sets of electric heaters 8 on both sides inside the protective cover 2 are turned on to heat the interior. Then, the hydraulic pump 15 is turned on, causing internal oil pressure to push the hydraulic cylinder 14 and the lower contact block 18 downward, thereby performing pressure testing on the mechanical component. The data obtained by the pressure sensor 17 above the contact block 18 is transmitted to the drive signal controller 19, which then transmits the data to the display 20 for observation. This, combined with the effect of internal heating, can accurately simulate the working state of the component in a high-temperature environment, improving the evaluation of the component's performance and lifespan.

[0030] like Figure 1 and Figure 2 As shown, the upper two sides of the workbench 1 are provided with grooves 5, and sliders 6 are slidably connected inside the grooves 5. The lower two sides of the placement plate 7 are fixedly connected to the sliders 6. By placing the aviation mechanical parts on the placement plate 7, the sliders 6 below the placement plate 7 slide in the grooves 5 inside the protective cover 2, making it easy to remove the placement plate 7 and the placed aviation mechanical parts.

[0031] like Figure 2 and Figure 4 As shown, the clamping mechanism 11 includes a servo motor 1101, which is fixedly mounted on the right side of the protective cover 2. The output end of the servo motor 1101 is fixedly connected to a lead screw 1102, and the external thread of the lead screw 1102 is connected to a clamping plate 1103. A limit bracket 1104 is fixedly connected to the rear side of the inner side of the sealing door 3. When the placement plate 7 is pushed into the protective cover 2, the servo motor 1101 is turned on, which drives the lead screw 1102 to rotate. The rotation of the lead screw 1102 drives the external clamping plates 1103 to move closer to each other, thereby clamping and fixing the aerospace mechanical parts on the placement plate 7 to prevent shaking during the inspection process.

[0032] like Figure 4 As shown, the external threads of the lead screw 1102 tap in opposite directions, and the clamping plate 1103 slides with the limiting frame 1104. By tapping the external threads of the lead screw 1102 in opposite directions, the two sets of external clamping plates 1103 are driven to move closer to each other when the lead screw 1102 rotates, thus facilitating the clamping of aerospace mechanical parts of different sizes.

[0033] like Figure 1 , Figure 2 and Figure 6As shown, the input terminal of the temperature sensor 10 is electrically connected to the output terminal of the drive signal controller 19, and the input terminal of the drive signal controller 19 is electrically connected to the output terminal of the electric heater 8. The temperature sensor 10 inside the protective cover 2 can sense whether the internal temperature is too high. When the temperature is too high, it transmits the signal to the drive signal controller 19, which then transmits the data to the electric heater 8 to control the switch, so as to avoid the internal temperature from being too high and affecting the detection effect.

[0034] like Figure 1 , Figure 5 and Figure 6 As shown, the input terminal of the pressure sensor 17 is electrically connected to the output terminal of the drive signal controller 19, and the input terminal of the drive signal controller 19 is electrically connected to the output terminal of the display 20. The data obtained by the pressure sensor 17 above the contact block 18 is transmitted to the drive signal controller 19, and then the drive signal controller 19 transmits the data to the display 20 for observation and analysis.

[0035] The working principle of this utility model is as follows: First, connect the external power supply. Then, pull out the placement plate 7 inside the protective cover 2. Place the aerospace mechanical component requiring pressure testing on the placement plate 7. Then, push the placement plate 7 into the protective cover 2. Then, close the sealing door 3. Next, turn on the servo motor 1101 switch to drive the lead screw 1102 to rotate. Utilizing the tapping effect of the external thread of the lead screw 1102, it drives the two sets of external clamping plates 1103 to move closer together, thereby clamping and fixing the aerospace mechanical component on the placement plate 7 to prevent shaking during the testing process. Next, turn on the electric heating 8 switch to heat the inside of the protective cover 2. After the internal heating is complete, turn on the hydraulic pump 15 switch to generate oil pressure inside, pushing the hydraulic cylinder 14 and the connecting sleeve 16 below downwards. This causes the contact block 18 below the connecting sleeve 16 to contact the upper part of the aerospace mechanical component. After being squeezed, the contact block 18 contacts the pressure sensor 17. When the pressure sensor... When pressure is sensed, the data is transmitted to the drive signal controller 19. The drive signal controller 19 then transmits the signal to the display 20 for detection and analysis. When the temperature sensor 10 on the top side inside the protective cover 2 senses that the temperature is too high, it transmits the signal to the drive signal controller 19. The drive signal controller 19 then transmits the data to the electric heater 8 to control the switch, preventing the internal temperature from being too high and affecting the detection effect. Finally, after the pressure test for the life analysis of the aerospace mechanical components is completed, the hydraulic pump 15 is turned off, and the hydraulic cylinder 14 and the contact block 18 are raised and lowered. Then the electric heater 8 is turned off, the sealing door 3 is opened, and the aerospace mechanical components are released through the clamping mechanism 11. The operator, wearing gloves, pulls out the placement plate 7 and removes the aerospace mechanical components on the placement plate 7. Then the external power is cut off. This completes the use of the aerospace mechanical component reliability life analysis pressure test equipment.

[0036] The foregoing description only illustrates certain exemplary embodiments of the present invention. Undoubtedly, those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. An aircraft mechanical component reliability life analysis pressure detection apparatus, characterized by: The utility model provides a workbench (1) for aviation machinery part life analysis pressure detection, a protective cover (2) is installed above the workbench (1) for splash protection, the outside of the protective cover (2) is hingedly connected with a sealing door (3), the inside of the sealing door (3) is provided with an observation window (4), the upper side of the workbench (1) is slidably connected with a placing plate (7) inside the protective cover (2), both sides of the inside of the protective cover (2) are provided with electric heating (8), the outside of the electric heating (8) is fixedly connected with a protective plate (9), the top side of the inside of the protective cover (2) is fixedly provided with a temperature sensor (10), the upper side of the workbench (1) is fixedly connected with a fixed rod (12) around, the upper side of the fixed rod (12) is fixedly connected with a top plate (13), the upper side of the top plate (13) is fixedly provided with a hydraulic cylinder (14), the upper side of the hydraulic cylinder (14) is fixedly provided with a hydraulic pump (15), the output end of the hydraulic cylinder (14) is fixedly connected with a connecting sleeve (16), the inside of the connecting sleeve (16) is provided with a pressure sensor (17), the lower end of the pressure sensor (17) is fixedly connected with a contact block (18), the right side of the workbench (1) is provided with a drive signal controller (19), the right side of the workbench (1) is provided with a display (20). A clamping mechanism (11) is arranged on the back side of the inside of the protective cover (2) for clamping. The upper side of both sides of the workbench (1) is provided with a sliding groove (5), the inside of the sliding groove (5) is slidably connected with a sliding block (6), and both sides of the lower side of the placing plate (7) are fixedly connected with the sliding block (6).

2. The reliability life analysis pressure detection apparatus for an aeronautical machine part according to claim 1, characterized in that: The clamping mechanism (11) comprises a servo motor (1101), the servo motor (1101) is fixedly arranged on the right side of the protective cover (2), the output end of the servo motor (1101) is fixedly connected with a lead screw (1102), the outside of the lead screw (1102) is threadedly connected with a clamping plate (1103), and the inside of the back side of the sealing door (3) is fixedly connected with a limiting frame (1104).

3. The reliability life analysis pressure detection apparatus for an aeronautical machine part according to claim 1, characterized in that: The outside of the lead screw (1102) is oppositely threaded, and the clamping plate (1103) and the limiting frame (1104) limit sliding.

4. The pressure detection apparatus for reliability life analysis of an aeronautical machine part according to claim 3, characterized in that: The input end of the temperature sensor (10) is electrically connected with the output end of the drive signal controller (19), and the input end of the drive signal controller (19) is electrically connected with the output end of the electric heating (8).

5. The reliability life analysis pressure detection apparatus for an aeronautical machine part according to claim 1, characterized in that: The input end of the pressure sensor (17) is electrically connected with the output end of the drive signal controller (19), and the input end of the drive signal controller (19) is electrically connected with the output end of the display (20).

6. The reliability life analysis pressure detection apparatus for an aeronautical machine part according to claim 1, characterized in that: ​

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