Pressure resistance testing device based on aeronautical parts

Abstract

The invention relates to the technical field of pressure testing devices, in particular to an aviation part pressure resistance testing device which comprises a supporting seat, a protective shell is fixedly mounted at the upper end of the supporting seat, inlets and outlets are symmetrically formed in the two sides of the protective shell, protective doors are symmetrically mounted in the inlets and outlets, and a hydraulic oil cylinder is fixedly mounted at the upper end of the protective shell. A hydraulic oil cylinder is fixedly mounted at the upper end of the test bench, a mounting plate is fixedly mounted at the lower end of an inner rod of the hydraulic oil cylinder, a test lower pressure head is fixedly mounted at the lower end of the mounting plate, and a plurality of lifting plates are fixedly connected to the side surface of the mounting plate in an annular array. The multiple transmission mechanisms move close to the aviation part through the driving mechanism, the multiple clamping and positioning mechanisms are driven by the multiple transmission mechanisms to move close to the aviation part, at the moment, the positioning blocks in the clamping assemblies make contact with the side face of the aviation part firstly, and the multiple clamping and positioning mechanisms are matched to push the aviation part to move.

Description

Technical Field

[0001] This invention relates to the field of pressure testing equipment technology, specifically to a pressure resistance testing device for aerospace components. Background Technology

[0002] In existing technologies, some sleeve parts and cylindrical shells are often used as isolation layers to protect critical components from wear and damage. To ensure the quality of aerospace components, these components need to undergo pressure resistance tests, such as axial pressure tests, after production to check whether they meet production standards. When performing pressure tests on aerospace components, to prevent positional shifts that could prevent the components from being accurately positioned under the test head of the pressure resistance testing device, thus affecting test accuracy, a positioning device is needed to accurately position the components before the pressure resistance test is conducted.

[0003] However, existing positioning devices can only clamp and position one type of aerospace component, and cannot adjust the positioning range according to the size of different aerospace components, which greatly reduces the applicability of the device. When pressure resistance testing is required for different types of aerospace components, different testing equipment must be changed, resulting in poor adaptability and increasing testing difficulty and cost. Furthermore, after positioning the aerospace component, the existing positioning device remains firmly against the side of the component during pressure testing. When the component deforms, it can squeeze the positioning device, easily causing damage and affecting the accuracy of the aerospace component testing. Summary of the Invention

[0004] The purpose of this invention is to provide a pressure resistance testing device for aerospace components to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a pressure resistance testing device for aerospace components, comprising a support base, a protective shell fixedly installed on the upper end of the support base, inlets and outlets symmetrically opened on both sides of the protective shell, protective doors symmetrically installed inside the inlets and outlets, a hydraulic cylinder fixedly installed on the upper end of the protective shell, an mounting plate fixedly installed on the lower end of the inner rod of the hydraulic cylinder, a test pressure head fixedly installed on the lower end of the mounting plate, and multiple lifting plates fixedly connected in a circular array on the side of the mounting plate, a guide light rod inserted through the upper end of each lifting plate from top to bottom, the upper end of the guide light rod being fixedly connected to the upper end of the inner cavity of the protective shell; A test platform is fixedly installed on the upper end of the support base. A circular groove is opened at the lower end of the test platform. Multiple convex grooves are opened in a ring array at the upper end of the test platform. The lower ends of the convex grooves are connected to the circular groove. Multiple clamping and positioning mechanisms are installed in a ring array at the upper end of the test platform. A detection mechanism is installed on the side of the clamping and positioning mechanism. A driving mechanism is installed in the circular groove. Multiple transmission mechanisms are installed in a ring array at the upper end of the driving mechanism.

[0006] Preferably, the driving mechanism includes a rotating circular plate rotatably mounted in a circular groove. The upper end of the rotating circular plate has multiple arc-shaped driving grooves arranged in a ring. The rotating circular plate is driven by the motor shaft of a stepper motor fixedly mounted at the lower end of the support base. Multiple transmission mechanisms are arranged in a ring array at the upper end of the rotating circular plate.

[0007] Preferably, the transmission mechanism includes a convex slider slidably mounted in a convex groove, a connecting shaft fixedly connected to the lower end of the convex slider, a drive roller rotatably mounted on the outer side of the connecting shaft, the drive roller being mounted in an adjacent arc-shaped drive groove and being in rolling connection with the arc-shaped drive groove, and the convex slider being fixedly connected to an adjacent clamping and positioning mechanism.

[0008] Preferably, the clamping and positioning mechanism includes a movable seat fixedly installed on the upper end of the convex slider. The movable seat has symmetrical guide grooves on one side near the center of the test platform. Limiting grooves are formed on the side of the guide grooves. A clamping component is installed on the side of the movable seat near the center of the test platform. Positioning grooves are symmetrically formed on the upper end of the movable seat. A rotating groove is formed through the bottom of each positioning groove. A limiting mechanism is provided in each positioning groove. An air storage cavity is formed on the side of the movable seat away from the center of the test platform. One end of the detection mechanism is connected to one end of the air storage cavity.

[0009] Preferably, the clamping assembly includes a mounting base disposed on the side of the movable seat near the center of the test platform. A positioning block is fixedly mounted on the mounting base. A slide rod and two guide plates are fixedly connected to the side of the mounting base near the movable seat. A buffer spring is sleeved on the slide rod. The slide rod extends through the movable seat into the air storage chamber. The two guide plates are respectively inserted into adjacent guide grooves. A limit block is fixedly connected to one end of the guide plate in the guide groove. The limit block is slidably connected to the limit groove.

[0010] Preferably, the slide rod is slidably connected to the movable seat, the two ends of the buffer spring abut against the mounting base and the movable seat respectively, and the guide plate is slidably connected to the guide groove.

[0011] Preferably, the limiting mechanism includes an arc-shaped rod fixedly connected to the inner wall of the rotating groove, an upward push spring is sleeved on the arc-shaped rod, an abutment plate is rotatably installed in the positioning groove via a rotating shaft, an arc-shaped hole is opened through the upper end of the abutment plate from top to bottom, and a limiting roller is rotatably installed on the end of the abutment plate near the mounting base via a rotating shaft.

[0012] Preferably, the arc-shaped rod is inserted through the arc-shaped hole, the arc-shaped hole and the arc-shaped rod are slidably connected, the two ends of the push spring are respectively in contact with the inner side wall of the rotating groove and the lower end of the contact plate, a flipping extrusion plate is provided above the contact plate, and the upper end of the flipping extrusion plate is fixedly connected to the lifting plate.

[0013] Preferably, the detection mechanism includes a thrust piston fixedly installed at one end of the slide rod inside the air storage chamber. A sealing plug is threaded onto the open end of the air storage chamber. An air guide tube is inserted through the side of the sealing plug. An air outlet is opened at the upper end of the side of the air guide tube. A warning whistle is fixedly installed inside the air outlet. An indicator rod is movably inserted through the upper end of the air guide tube from top to bottom. The lower end of the indicator rod extends downward into the inner cavity of the air guide tube and is fixedly installed with a lifting piston. The lifting piston slides in contact with the inner wall of the air guide tube.

[0014] Compared with the prior art, the beneficial effects of the present invention are: the present invention has a reasonable structural design and strong functionality, and has the following advantages: 1. When testing aerospace components, the components are placed on the upper part of the test bench. The drive mechanism moves multiple transmission mechanisms closer to the components, which in turn move multiple clamping and positioning mechanisms closer to them. At this point, the positioning block in the clamping assembly first contacts the side of the components. The multiple clamping and positioning mechanisms work together to push the components until they are pushed to the center of the test bench. Then, the multiple clamping and positioning mechanisms work together to position the components so that they are accurately positioned directly under the test pressure head, ensuring the accuracy of subsequent tests.

[0015] 2. When performing pressure resistance tests on aerospace components, the limiting mechanism is rotated by flipping the extrusion plate. This causes the end of the contact plate near the mounting base to rotate the limiting roller upwards, separating the limiting roller from the mounting base. At this time, the limiting mechanism will not obstruct the movement of the clamping assembly towards the moving base. Simultaneously, the lower end of the test pressure head is in contact with the upper end of the aerospace component. At the same time, the clamping assembly continues to be tightly attached to the side of the aerospace component under the action of the buffer spring, thus positioning the aerospace component.

[0016] 3. During testing, the hydraulic cylinder keeps the test pressure head moving downwards, applying pressure to the aircraft parts to perform a pressure resistance test. If the aircraft parts meet the standards and do not break or deform, the testing mechanism will not issue a warning. If the aircraft parts fail to meet the standards and break or deform, the aircraft parts will push the clamping assembly closer to the moving seat, causing the slide rod to drive the thrust piston closer to the opening of the air storage chamber, thus triggering a warning from the testing mechanism to alert the staff that the aircraft parts do not meet the standards. Attached Figure Description

[0017] Figure 1 This is a three-dimensional structural view of the pressure resistance testing device for aerospace components of the present invention; Figure 2 This is a cross-sectional view of the structure of the pressure resistance testing device for aerospace components of the present invention; Figure 3 for Figure 2 Enlarged schematic diagram of the structure at point A in the middle; Figure 4 This is an exploded view of the test platform, drive mechanism, and positioning clamping mechanism of the present invention. Figure 5 This is a three-dimensional structural view of the positioning clamping mechanism and the detection mechanism of the present invention; Figure 6 This is a cross-sectional view of the positioning clamping mechanism and detection mechanism of the present invention; Figure 7 This is a cross-sectional view of the positioning and clamping mechanism of the present invention; Figure 8 This is a side sectional view of the movable seat structure of the present invention; Figure 9 This is a schematic diagram of the structure of the present invention after the flipping extrusion plate pushes the limiting mechanism downward to rotate; Figure 10 This is an exploded view of the positioning clamping mechanism and detection mechanism of the present invention.

[0018] In the diagram: 1. Support base; 11. Protective shell; 12. Hydraulic cylinder; 13. Mounting plate; 14. Test pressure head; 15. Lifting plate; 16. Tilting extrusion plate; 17. Guide rod; 2. Test platform; 21. Circular groove; 22. Convex groove; 23. Rotating circular plate; 24. Arc-shaped drive groove; 25. Convex slider; 26. Connecting shaft; 27. Drive roller; 3. Moving base; 31. Air storage chamber; 32. Guide groove 33. Limiting groove; 34. Positioning groove; 35. Rotating groove; 4. Mounting base; 41. Positioning block; 42. Slide rod; 43. Buffer spring; 44. Push piston; 45. Guide plate; 46. Limiting block; 5. Arc rod; 51. Push spring; 52. Contact plate; 53. Arc hole; 54. Limiting roller; 6. Sealing plug; 61. Air guide pipe; 62. Warning whistle; 63. Indicator rod; 64. Lifting piston. Detailed Implementation

[0019] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] Please see Figures 1 to 10 This invention provides a technical solution: a pressure resistance testing device for aerospace components, comprising a support base 1, a protective shell 11 fixedly mounted on the upper end of the support base 1, inlets and outlets symmetrically opened on both sides of the protective shell 11, protective doors symmetrically installed inside the inlets and outlets, the protective doors being slidably installed inside the inlets and outlets via guide rails, and transparent protective plates installed on the protective doors; an observation window is opened on the side of the protective shell 11 adjacent to the inlets and outlets, and a transparent protective plate is installed inside the observation window, thereby facilitating the observation of the testing conditions inside the protective shell 11 by the operator; a hydraulic cylinder 12 is fixedly mounted on the upper end of the protective shell 11, the inner rod of the hydraulic cylinder 12 extending downward into the inner cavity of the protective shell 11, and the inner rod of the hydraulic cylinder 12... A mounting plate 13 is fixedly installed at the lower end, and a test pressure head 14 is fixedly installed at the lower end of the mounting plate 13. A pressure sensor is installed on the inner side of the lower end of the test pressure head 14 to monitor the applied pressure in real time. The test pressure head 14 and the mounting plate 13 are detachably connected, which makes it easy to replace different test pressure heads 14, so that different aerospace parts can be pressure tested. Multiple lifting plates 15 are fixedly connected in a ring array on the side of the mounting plate 13. A guide light rod 17 is inserted through the upper end of each lifting plate 15 from top to bottom. The lifting plate 15 and the adjacent guide light rod 17 are slidably connected up and down. The upper end of the guide light rod 17 is fixedly connected to the upper end of the inner cavity of the protective shell 11. The mounting plate 13 moves up and down by extending and retracting the inner rod of the hydraulic cylinder 12. The mounting plate 13 drives the lifting plate 15 to slide up and down along the guide rod 17, so that the mounting plate 13 can move up and down stably. The mounting plate 13 drives the test pressure head 14 to move up and down, so that the test pressure head 14 can accurately perform pressure tests on aerospace parts and ensure the accuracy of the test. A test platform 2 is fixedly installed on the upper end of the support base 1. A circular groove 21 is opened at the lower end of the test platform 2. Multiple convex grooves 22 are opened in a ring array at the upper end of the test platform 2. The lower end of the convex grooves 22 is connected to the circular groove 21. Multiple clamping and positioning mechanisms are installed in a ring array at the upper end of the test platform 2. A detection mechanism is installed on the side of the clamping and positioning mechanism. A drive mechanism is installed in the circular groove 21. Multiple transmission mechanisms are installed in a ring array at the upper end of the drive mechanism. The multiple transmission mechanisms are respectively installed at the lower end of the multiple clamping and positioning mechanisms.

[0021] The number of lifting plates 15 is the same as the number of guide rods 17, convex grooves 22, clamping and positioning mechanisms and transmission mechanisms.

[0022] The drive mechanism moves multiple transmission mechanisms closer or further apart, which in turn moves multiple clamping and positioning mechanisms closer or further apart. The closer movement of these clamping and positioning mechanisms pushes the aerospace component to the center of the upper end of the test bench 2, ensuring that the aerospace component is accurately positioned directly below the test pressure head 14. This allows for accurate pressure resistance testing of the aerospace component. Simultaneously, the multiple clamping and positioning mechanisms work together to clamp and position the aerospace component, preventing misalignment or displacement.

[0023] Please see Figure 2 and Figure 4 The driving mechanism includes a rotating circular plate 23 rotatably installed in a circular groove 21. The upper end of the rotating circular plate 23 has multiple arc-shaped driving grooves 24 arranged in a ring. The rotating circular plate 23 is driven by the motor shaft of a stepper motor fixedly installed at the lower end of the support base 1. The motor shaft is rotatably connected to the support base 1. The upper end of the motor shaft is connected to the rotating circular plate 23 through a coupling. Multiple transmission mechanisms are arranged in a ring array on the upper end of the rotating circular plate 23.

[0024] Please see Figures 2 to 7 The transmission mechanism includes a convex slider 25 that is slidably mounted on a convex groove 22. A connecting shaft 26 is fixedly connected to the lower end of the convex slider 25. A drive roller 27 is rotatably mounted on the outer side of the connecting shaft 26. An anti-detachment plate is fixedly connected to the lower end of the connecting shaft 26. The upper end of the anti-detachment plate is in rotatable contact with the drive roller 27. The drive roller 27 is installed in an adjacent arc-shaped drive groove 24 and is in rolling connection with the arc-shaped drive groove 24. The convex slider 25 is fixedly connected to an adjacent clamping and positioning mechanism.

[0025] Initially, the drive roller 27 is located at one end of the arc-shaped drive groove 24 near the outer side. When the aerospace parts are clamped and fixed, the drive roller 27 rolls along the arc-shaped drive groove 24, causing the drive roller 27 to gradually approach the center position of the rotating circular plate 23.

[0026] The rotating disc 23 is driven to rotate by the motor shaft of the stepper motor. When the rotating disc 23 rotates, it pushes the drive roller 27 to move through the arc-shaped drive groove 24. The drive roller 27 drives the convex slider 25 to move along the convex groove 22 through the connecting shaft 26. By controlling the forward and reverse rotation of the motor shaft of the stepper motor, the convex slider 25 slides back and forth along the convex groove 22, so that multiple convex sliders 25 move closer to each other or move further away from each other. Multiple convex sliders 25 drive multiple clamping and positioning mechanisms to move closer to each other to clamp and position the aerospace parts, so that the aerospace parts are in the center position of the test platform 2, that is, directly below the test pressure head 14. Multiple convex sliders 25 drive multiple clamping and positioning mechanisms to move further away from each other to release the clamping and positioning of the aerospace parts.

[0027] Please see Figure 3 , Figures 5 to 10 The clamping and positioning mechanism includes a movable seat 3 fixedly installed on the upper end of the convex slider 25. The lower end of the movable seat 3 slides in contact with the upper end of the test platform 2. A guide groove 32 is symmetrically opened on the side of the movable seat 3 near the center of the test platform 2. A limit groove 33 is opened on the side of the guide groove 32. A clamping component is installed on the side of the movable seat 3 near the center of the test platform 2. A positioning groove 34 is symmetrically opened on the upper end of the movable seat 3. A rotating groove 35 is opened through the bottom of each positioning groove 34. A limit mechanism is provided in each positioning groove 34. An air storage cavity 31 is opened on the side of the movable seat 3 away from the center of the test platform 2. One end of the detection mechanism is connected to one end of the air storage cavity 31.

[0028] Please see Figures 5 to 10 The clamping assembly includes a mounting base 4 located on the side of the movable base 3 near the center of the test bench 2. A positioning block 41 is fixedly mounted on the mounting base 4. The mounting base 4 is an L-shaped plate, and a dovetail groove is formed on the inner side wall of the mounting base 4. A dovetail-shaped insert that matches the dovetail groove is fixedly connected to one side of the positioning block 41. When installing the positioning block 41, the dovetail-shaped insert is inserted into the dovetail groove, and then the positioning block 41 is fixed to the mounting base 4 with bolts. A sliding rod 42 and two guide plates 45 are fixedly connected to the side of the mounting base 4 near the movable base 3. Two guide plates 45 are symmetrically distributed on both sides of the slide rod 42. A buffer spring 43 is sleeved on the slide rod 42. The slide rod 42 extends through the movable seat 3 into the air storage chamber 31. The two guide plates 45 are respectively inserted into the adjacent guide grooves 32. One end of the guide plate 45 in the guide groove 32 is fixedly connected to a limiting block 46. The limiting block 46 is slidably connected to the limiting groove 33. The limiting block 46 and the limiting groove 33 cooperate to prevent the guide plate 45 from separating from the movable seat 3, thereby preventing the clamping assembly from slipping and separating from the movable seat 3.

[0029] The slide rod 42 is slidably connected to the movable seat 3, the two ends of the buffer spring 43 abut against the mounting seat 4 and the movable seat 3 respectively, the guide plate 45 is slidably connected to the guide groove 32, and the buffer spring 43 applies elastic force to the mounting seat 4.

[0030] When the clamping and positioning mechanism clamps and positions the aviation parts, multiple clamping and positioning mechanisms move close to the aviation parts. At this time, the positioning block 41 in the clamping assembly first contacts the side of the aviation parts, and the aviation parts are positioned by the cooperation of multiple clamping and positioning mechanisms. As the movable seat 3 continues to move closer to the aerospace component, the movable seat 3 drives the clamping assembly to move synchronously via the slide rod 42 and guide plate 45. Since one end of the limiting mechanism is in contact with the side of the mounting base 4, the clamping assembly and the movable seat 3 will not move closer to each other. The movable seat 3 and the clamping assembly work together to push the aerospace component until it is pushed to the center position of the test bench 2. At this point, the movable seat 3 and the clamping assembly stop moving, that is, the operation of the drive mechanism stops.

[0031] Before the aircraft parts are inspected, the limit block 46 is at the end of the limit groove 33 near the mounting base 4. At this time, the mounting base 4 and the positioning block 41 cannot move away from the movable base 3.

[0032] Please see Figures 8 to 10 The limiting mechanism includes an arc-shaped rod 5 fixedly connected to the inner wall of the rotating groove 35. An upward push spring 51 is sleeved on the arc-shaped rod 5. An abutment plate 52 is rotatably installed in the positioning groove 34 via a rotating shaft. The lower end of the abutment plate 52 contacts the bottom of the positioning groove 34. At this time, the abutment plate 52 is in a horizontal state. Through the positioning groove 34, the end of the abutment plate 52 near the mounting base 4 cannot rotate downward. An arc-shaped hole 53 is opened from top to bottom at the upper end of the abutment plate 52. A limiting roller 54 is rotatably installed at the end of the abutment plate 52 near the mounting base 4 via a rotating shaft.

[0033] The arc-shaped rod 5 is inserted through the arc-shaped hole 53, and the arc-shaped hole 53 and the arc-shaped rod 5 are slidably connected. The two ends of the push spring 51 are respectively in contact with the inner side wall of the rotating groove 35 and the lower end of the contact plate 52. The push spring 51 applies elastic force to the contact plate 52. A flip-up extrusion plate 16 is provided above the contact plate 52. The upper end of the flip-up extrusion plate 16 is fixedly connected to the lifting plate 15. The lower end of the flip-up extrusion plate 16 is provided with an extrusion slope. The arc of the arc-shaped rod 5 is adapted to the rotation path of the contact plate 52. When the contact plate 52 rotates around the axis of the rotating shaft, the contact plate 52 can move up or down along the arc-shaped rod 5.

[0034] After the positioning and clamping mechanism completes the clamping and positioning of the aviation parts, the limiting mechanism abuts against the clamping components. The mounting base 4 is limited by the cooperation of the abutting plate 52 and the limiting roller 54. At this time, the limiting roller 54 abuts against the mounting base 4, preventing the moving base 3 and the mounting base 4 from moving closer to each other. At this time, the end of the abutting plate 52 away from the mounting base 4 is below the flipping extrusion plate 16. That is, the flipping extrusion plate 16 will contact the end of the abutting plate 52 away from the mounting base 4 during the downward movement.

[0035] When pressure resistance testing is performed on aerospace components, hydraulic cylinder 12 drives lifting plate 15 and test pressure head 14 to move downward via mounting plate 13. Lifting plate 15 drives multiple flipping extrusion plates 16 to move downward. After lifting plate 15 and test pressure head 14 have moved downward a certain distance, the lower end of flipping extrusion plate 16 first contacts the end of contact plate 52 away from mounting base 4. Lifting plate 15 and test pressure head 14 continue to move downward, pushing the end of contact plate 52 away from mounting base 4 downward through flipping extrusion plate 16. At this time, the other end of contact plate 52 tilts upward, and contact plate 52 drives limit roller 54 to rotate upward. When contact plate 52 drives limit roller 54 to separate from mounting base 4, the lower end of test pressure head 14 just abuts against the upper end of aerospace component.

[0036] When the end of the contact plate 52 away from the mounting base 4 rotates downward, the arc-shaped hole 53 of the contact plate 52 slides downward along the arc-shaped rod 5, and at the same time the contact plate 52 squeezes the push spring 51. When the positioning clamping mechanism releases and resets the clamping and positioning of the aerospace parts, the flipping extrusion plate 16 is first moved upward to reset, and then the flipping extrusion plate 16 releases its downward extrusion on the contact plate 52. Under the action of the buffer spring 43, the mounting base 4 moves away from the movable base 3 until the limiting block 46 slides to the end of the limiting groove 33 near the mounting base 4. Under the action of the upward spring 51, the end of the contact plate 52 with the limiting roller 54 rotates downward until the lower end of the contact plate 52 abuts against the bottom of the positioning groove 34. At this time, the limiting roller 54 continues to abut against the mounting base 4, completing the reset.

[0037] During testing, by keeping the test pressure head 14 moving downward, pressure is applied to the aerospace parts by the test pressure head 14, thereby conducting a pressure resistance test on the aerospace parts; If the aviation parts meet the standards and do not break or deform during the test, the testing agency will not issue an early warning. If the aircraft parts fail to meet the standards and break or deform, the aircraft parts will push the clamping assembly closer to the moving seat 3, causing the slide rod 42 to be inserted into the air storage chamber 31. The slide rod 42 will drive the thrust piston 44 to move closer to the opening, thereby causing the detection mechanism to issue an early warning.

[0038] Please see Figures 4 to 10 The detection mechanism includes a thrust piston 44 fixedly installed at one end of a slide rod 42 within an air storage chamber 31. A sealing plug 6 is threadedly installed at the open end of the air storage chamber 31. An air guide tube 61 is inserted through the side of the sealing plug 6. The open end of the air storage chamber 31 has an internal thread, and the outer side of the sealing plug 6 has an external thread that matches the internal thread. The external thread on the outer side of the sealing plug 6 is threadedly connected to the internal thread. The air guide tube 61 is fixedly connected to the sealing plug 6. The upper end of the air guide tube 61 is sealed, and the lower end of the air guide tube 61 is open. One end of the air guide tube 61 communicates with the inner cavity of the air storage chamber 31. An air outlet is provided at the upper end of the side of the air duct 61. A warning siren 62 is fixedly installed inside the air outlet. Gas can enter and exit along the warning siren 62. Gas inside the air duct 61 can be discharged along the warning siren 62. External gas can also pass through the warning siren 62 and enter the air duct 61. An indicator rod 63 is movably inserted through the upper end of the air duct 61 from top to bottom. A scale is provided on the side of the indicator rod 63. The lower end of the indicator rod 63 extends downward into the inner cavity of the air duct 61 and is fixedly installed with a lifting piston 64. The lifting piston 64 slides in contact with the inner wall of the air duct 61.

[0039] The lifting piston 64 divides the inner cavity of the air duct 61 into two chambers, upper and lower. When the lifting piston 64 moves upward along the inner cavity of the air duct 61, the lifting piston 64 pushes out the gas in the upper chamber, so that the gas flows out along the warning whistle 62 on the side of the air duct 61. When the thrust piston 44 moves close to the opening, it pushes the gas in the gas storage chamber 31 into the inner cavity of the air guide tube 61. At this time, the gas pushes the lifting piston 64 to move upward, and the lifting piston 64 drives the indicator rod 63 to move upward. At the same time, the lifting piston 64 pushes the gas in the air guide tube 61 upward, so that the gas flows out along the warning whistle 62, thereby making the warning whistle 62 emit a warning sound to remind the staff that the aviation parts are not up to standard. As the thrust piston 44 pushes the gas in the gas storage chamber 31 into the air guide pipe 61, the lifting piston 64 rises. After pressure is applied to the aviation parts, the positioning and clamping mechanism does not reset, so the position of the thrust piston 44 remains unchanged. At this time, the positions of the lifting piston 64 and the indicator rod 63 also remain unchanged, making it convenient for staff to observe the rise scale of the indicator rod 63.

[0040] The higher the indicator rod 63 rises, the greater the deformation of the aircraft component.

[0041] Working principle: When testing aerospace components, the protective door on the protective shell 11 is opened, and the aerospace component is placed on the upper end of the test bench 2. The stepper motor is started, causing the drive mechanism to push multiple drive rollers 27 to move. The drive rollers 27 drive the convex slider 25 to move through the connecting shaft 26, causing multiple transmission mechanisms to move closer to the aerospace component. Through the multiple transmission mechanisms, multiple clamping and positioning mechanisms move closer to the aerospace component. At this time, the positioning block 41 in the clamping assembly first contacts the side of the aerospace component. Through the cooperation of multiple clamping and positioning mechanisms, the aerospace component is pushed to move until it is pushed to the center position of the test bench 2. At this time, the multiple clamping and positioning mechanisms are used to position the aerospace component. At this time, the moving seat 3 and the clamping assembly stop moving, that is, the operation of the drive mechanism stops.

[0042] By setting a limiting mechanism, the clamping component will not move close to the moving seat 3 when clamping and positioning aerospace parts.

[0043] When pressure resistance testing is performed on aerospace components, hydraulic cylinder 12 drives lifting plate 15 and test pressure head 14 to move downward via mounting plate 13. Lifting plate 15 drives multiple flipping extrusion plates 16 to move downward. When the lower end of flipping extrusion plate 16 contacts the end of contact plate 52 away from mounting base 4, lifting plate 15 and test pressure head 14 continue to move downward. The flipping extrusion plate 16 pushes the end of contact plate 52 near mounting base 4 and limit roller 54 to rotate upward. When contact plate 52 drives limit roller 54 to separate from mounting base 4, the limiting mechanism will not hinder the clamping assembly from moving closer to moving base 3. At the same time, the lower end of test pressure head 14 just abuts against the upper end of aerospace component.

[0044] During testing, by keeping the test pressure head 14 moving downward, pressure is applied to the aerospace parts by the test pressure head 14, thereby conducting a pressure resistance test on the aerospace parts; If the aviation parts meet the standards and do not break or deform during the test, the testing agency will not issue an early warning. If aerospace parts fail to meet standards and break or deform, the parts will push the clamping assembly closer to the moving seat 3, causing the slide rod 42 to drive the thrust piston 44 closer to the opening of the air storage chamber 31, thus triggering an early warning from the testing agency to alert the staff that the aerospace parts are not up to standard.

[0045] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A pressure resistance testing device for aerospace components, comprising a support base (1), characterized in that: A protective shell (11) is fixedly installed on the upper end of the support base (1). The protective shell (11) has symmetrical inlets and outlets on both sides. Protective doors are symmetrically installed inside the inlets and outlets. A hydraulic cylinder (12) is fixedly installed on the upper end of the protective shell (11). An installation plate (13) is fixedly installed on the lower end of the inner rod of the hydraulic cylinder (12). A test pressure head (14) is fixedly installed on the lower end of the installation plate (13). Multiple lifting plates (15) are fixedly connected in a ring array on the side of the installation plate (13). A guide light rod (17) is inserted through the upper end of each lifting plate (15) from top to bottom. The upper end of the guide light rod (17) is fixedly connected to the upper end of the inner cavity of the protective shell (11). The upper end of the support base (1) is fixedly installed with a test platform (2). The lower end of the test platform (2) is provided with a circular groove (21). The upper end of the test platform (2) is provided with a plurality of convex grooves (22) in a ring array. The lower end of the convex grooves (22) is connected to the circular grooves (21). The upper end of the test platform (2) is provided with a plurality of clamping and positioning mechanisms in a ring array. The side of the clamping and positioning mechanism is provided with a detection mechanism. The circular groove (21) is provided with a driving mechanism. The upper end of the driving mechanism is provided with a plurality of transmission mechanisms in a ring array.

2. The pressure resistance testing device for aerospace components according to claim 1, characterized in that: The driving mechanism includes a rotating circular plate (23) rotatably installed in a circular groove (21). The upper end of the rotating circular plate (23) is provided with multiple arc-shaped driving grooves (24) in a ring array. The rotating circular plate (23) is driven by the motor shaft of a stepper motor fixedly installed at the lower end of the support base (1). Multiple transmission mechanisms are installed in a ring array at the upper end of the rotating circular plate (23).

3. The pressure resistance testing device for aerospace components according to claim 2, characterized in that: The transmission mechanism includes a convex slider (25) that is slidably mounted on a convex groove (22). A connecting shaft (26) is fixedly connected to the lower end of the convex slider (25). A drive roller (27) is rotatably mounted on the outer side of the connecting shaft (26). The drive roller (27) is installed in an adjacent arc-shaped drive groove (24) and is in rolling connection with the arc-shaped drive groove (24). The convex slider (25) is fixedly connected to an adjacent clamping and positioning mechanism.

4. The pressure resistance testing device for aerospace components according to claim 3, characterized in that: The clamping and positioning mechanism includes a movable seat (3) fixedly installed on the upper end of the convex slider (25). The movable seat (3) has symmetrical guide grooves (32) on one side near the center of the test platform (2). The guide grooves (32) have limit grooves (33) on their sides. A clamping component is installed on one side of the movable seat (3) near the center of the test platform (2). The upper end of the movable seat (3) has symmetrical positioning grooves (34). A rotating groove (35) is opened through the bottom of each positioning groove (34). A limit mechanism is provided in each positioning groove (34). A gas storage chamber (31) is opened on one side of the movable seat (3) away from the center of the test platform (2). One end of the detection mechanism is connected to one end of the gas storage chamber (31).

5. The pressure resistance testing device for aerospace components according to claim 4, characterized in that: The clamping assembly includes a mounting base (4) located on the side of the movable seat (3) near the center of the test bench (2). A positioning block (41) is fixedly installed on the mounting base (4). A slide rod (42) and two guide plates (45) are fixedly connected to the side of the mounting base (4) near the movable seat (3). A buffer spring (43) is sleeved on the slide rod (42). The slide rod (42) extends through the movable seat (3) into the air storage chamber (31). The two guide plates (45) are respectively inserted into the adjacent guide grooves (32). A limit block (46) is fixedly connected to one end of the guide plate (45) in the guide groove (32). The limit block (46) is slidably connected to the limit groove (33).

6. The pressure resistance testing device for aerospace components according to claim 5, characterized in that: The slide bar (42) is slidably connected to the movable seat (3), the two ends of the buffer spring (43) abut against the mounting seat (4) and the movable seat (3) respectively, and the guide plate (45) is slidably connected to the guide groove (32).

7. The pressure resistance testing device for aerospace components according to claim 5, characterized in that: The limiting mechanism includes an arc-shaped rod (5) fixedly connected to the inner wall of the rotating groove (35). An upward push spring (51) is sleeved on the arc-shaped rod (5). A contact plate (52) is rotatably installed in the positioning groove (34) via a rotating shaft. An arc-shaped hole (53) is opened through the upper end of the contact plate (52) from top to bottom. A limiting roller (54) is rotatably installed on the end of the contact plate (52) near the mounting base (4) via a rotating shaft.

8. The pressure resistance testing device for aerospace components according to claim 7, characterized in that: The arc-shaped rod (5) is inserted through the arc-shaped hole (53), and the arc-shaped hole (53) and the arc-shaped rod (5) are slidably connected. The two ends of the push spring (51) abut against the inner side wall of the rotating groove (35) and the lower end of the contact plate (52), respectively. A flipping extrusion plate (16) is provided above the contact plate (52), and the upper end of the flipping extrusion plate (16) is fixedly connected to the lifting plate (15).

9. The pressure resistance testing device for aerospace components according to claim 5, characterized in that: The detection mechanism includes a thrust piston (44) fixedly installed at one end of the slide rod (42) inside the air storage chamber (31). A sealing plug (6) is threadedly installed at the open end of the air storage chamber (31). A guide pipe (61) is inserted through the side of the sealing plug (6). An air outlet is opened at the upper end of the side of the guide pipe (61). A warning whistle (62) is fixedly installed in the air outlet. An indicator rod (63) is movably inserted through the upper end of the guide pipe (61) from top to bottom. The lower end of the indicator rod (63) extends downward to the inner cavity of the guide pipe (61) and a lifting piston (64) is fixedly installed thereon. The lifting piston (64) slides and contacts the inner wall of the guide pipe (61) up and down.

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