Static rigidity experimental device for aeronautical parts

Abstract

The invention belongs to the technical field of static rigidity experiments, and particularly relates to an aeronautical part static rigidity experiment device which comprises a base, the top of the base is fixedly connected with a carrier plate through supporting columns, a first carrier block and a second carrier block are fixedly installed on the top of the carrier plate, a portal frame is fixed to the top of the carrier plate, and an electric push rod is fixedly installed in the middle of the top of the portal frame. A push rod of the electric push rod movably penetrates through the portal frame and is fixedly connected with a pressure sensor, the bottom of the pressure sensor is fixedly connected with a pressing plate, the outer wall of the first carrying plate is sleeved with an adaptive fence, and the outer wall of the push rod of the electric push rod is connected with the fence through a linkage assembly. In the process that an electric push rod drives a pressing plate to descend, a first rack can be synchronously driven to descend so as to act on a gear and drive the gear to rotate, and then the gear can drive a second rack to lift, so that a fence can be driven to lift in the process of pressing a part, and the part on a second carrying block is shielded; and the fence is used for protection.

Description

Technical Field

[0001] The present invention relates to the technical field of static stiffness experiments, and particularly to a static stiffness experiment device for aviation parts. Background Technique

[0002] Static stiffness detection is an important experimental means for evaluating the deformation resistance ability of materials, components or structures under static loads, and is a key link in mechanical design, structural engineering and quality control. Through static stiffness detection, it can be ensured that parts or structures meet the stiffness requirements during actual use, and avoid functional failure or safety hazards caused by excessive deformation.

[0003] During the detection of existing aviation parts, it is often necessary to detect the static stiffness of the parts, so corresponding static stiffness detection devices need to be used. Currently, when detecting the static stiffness of parts, the parts are often placed on a carrier, and then a hydraulic cylinder or an electric push rod is used to drive a pressure block to descend to press the parts, and a pressure sensor is used to monitor the pressure, and at the same time, a distance sensor is used to detect the deformation distance after being pressed. However, during the detection process, in order to test the maximum stiffness of the parts, that is, the maximum compressive ability, continuous pressure is applied. When the parts are deformed, metal debris often splashes, which is not convenient to be protected by a fence, so the splashing debris is likely to cause harm to the surrounding staff. Therefore, new technical solutions need to be designed to solve this problem. Summary of the Invention

[0004] The purpose of the present invention is to provide a static stiffness experiment device for aviation parts, which solves the problem that metal debris often splashes when the parts are deformed in the background technique, and it is not convenient to be protected by a fence, so the splashing debris is likely to cause harm to the surrounding staff.

[0005] To achieve the above purpose, the present invention provides the following technical solution: A static stiffness experiment device for aviation parts, including a base, the top of the base is fixedly connected with a carrier plate through a pillar, a first carrier block is fixedly installed on the top of the carrier plate, a through hole is opened in the middle of the top of the first carrier block and extends to the lower side of the carrier plate, a second carrier block is arranged in the through hole, a gantry is fixed on the top of the carrier plate, an electric push rod is fixedly installed in the middle of the top of the gantry, the push rod of the electric push rod movably penetrates through the gantry and is fixedly connected with a pressure sensor, the bottom of the pressure sensor is fixedly connected with a pressure plate, high-precision distance sensors are fixedly connected to both side walls of the pressure plate, a fitting fence is sleeved on the outer wall of the first carrier block, and the outer wall of the push rod of the electric push rod is connected with the fence through a linkage component.

[0006] By adopting the above technical solution, during actual use, first place the test product on the top of the second carrier block, and then start the electric push rod to drive the pressure plate to descend. During the process of the pressure plate pressing on the product, the pressure sensor can be used to feedback the pressure value, and at the same time, the high-precision distance sensor can feedback the moving distance after the pressure is generated, which is the deformation distance of the product. During the process of the pressure plate descending, the linkage component can be driven to lift the enclosure, so that the parts can be shielded by the enclosure. Therefore, when debris splashes, the enclosure can be used for protection, which is beneficial to avoiding damage to the surrounding staff caused by debris, and is also beneficial to avoiding the difficulty of cleaning up the splashed debris. When the electric push rod retracts, it can drive the linkage component to drive the enclosure to descend, which is beneficial to avoiding affecting the staff to take out the workpiece.

[0007] As a preferred embodiment of the present invention, the linkage component includes a connecting plate. The number of the connecting plates is four. The four connecting plates are respectively fixed on the four sides of the outer wall of the push rod of the electric push rod. The outer end of the connecting plate is fixedly connected with a first rack. A gear is arranged below the first rack. Both ends of the gear are movably connected with a cage. The tail end of the cage is fixed on the top of the carrier plate. A second rack is meshed with one side wall of the gear. The second rack is fixedly installed on the side wall of the enclosure.

[0008] By adopting the above technical solution, during actual use, when the push rod of the electric push rod extends, it drives the connecting plate to descend, so that the first rack can be driven to descend. After descending a certain distance, it will act on the gear, so that the gear can rotate. Furthermore, the gear can drive the second rack to move upward, so as to realize driving the enclosure to lift and shield the debris. At the same time, when the electric push rod retracts, it can drive the first rack to lift, so that the gear reverses, and the lifted second rack descends, so as to drive the enclosure to descend, which is beneficial to avoiding affecting the staff to pick up the workpiece.

[0009] As a preferred embodiment of the present invention, a cylinder is installed on one side of the top of the gantry. A piston adapted to the inner cavity of the cylinder is arranged in the cylinder. The bottom of the piston is fixedly connected with a movable rod. The tail end of the movable rod movably penetrates the gantry and is fixedly connected with the outer wall of the push rod of the electric push rod through a fixing plate. The top of the cylinder is fixedly communicated with a conduit. The conduit penetrates the first carrier block and is communicated with an annular pipe. The annular pipe is fixed on the top of the first carrier block. A plurality of uniformly distributed air outlet holes are opened on the inner wall of the annular pipe.

[0010] By adopting the above technical solution, when the electric push rod drives the pressing block to lift, it can drive the movable rod to lift, thereby driving the piston to lift, so as to push the gas in the air cylinder into the inner cavity of the annular pipe, and then blow it towards the surface of the first carrier block along the air outlet holes on the inner wall of the annular pipe, so as to blow the debris blocked by the enclosure towards the middle, so that the debris can enter the space between the first carrier block and the second carrier block, so that the debris can be collected, without the need for subsequent manual cleaning by the staff, which is beneficial to reducing the labor intensity of the staff.

[0011] As a preferred embodiment of the present invention, the four side walls of the second carrier block are fixedly connected to the inner wall of the first carrier block through connecting blocks.

[0012] By adopting the above technical solution, during use, a collection box is placed on the top of the base, so that the debris entering the space between the first carrier block and the second carrier block can fall into the collection box and be collected.

[0013] As a preferred embodiment of the present invention, a one-way intake valve is fixedly connected to the upper side of the outer wall of the air cylinder, so that during the downward movement of the piston, the air pressure balance can be ensured through the one-way intake valve.

[0014] As a preferred embodiment of the present invention, a limiting rod is fixedly connected to the top of the connecting plate, and the limiting rod movably penetrates through the gantry.

[0015] As a preferred embodiment of the present invention, the back surface of the first rack is attached to the inner wall of the gantry.

[0016] As a preferred embodiment of the present invention, rubber blocks are embedded at the four corners of the bottom of the base.

[0017] As a preferred embodiment of the present invention, both the pressure sensor and the high-precision distance sensor are electrically connected to the industrial control computer.

[0018] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0019] During the process of the electric push rod driving the pressing plate to descend in the present invention, it can synchronously drive the first rack to descend, thereby acting on the gear, driving the gear to rotate, and then the gear can drive the second rack to lift, so as to drive the enclosure to lift during the process of pressing the part, so as to form an occlusion for the part on the second carrier block, so that when debris splashes, the enclosure can be used for protection, which is beneficial to avoiding damage to the surrounding staff by the debris and is also beneficial to avoiding the difficulty of cleaning the splashed debris;

[0020] The electric push rod can lift the movable rod when driving the pressure block to lift, thereby driving the piston to lift, thereby pushing the gas in the gas cylinder into the inner cavity of the annular tube, and blowing it along the air outlet holes on the inner wall of the annular tube to the surface of the first carrier block, so that the debris blocked by the enclosure can be blown to the middle, so that the debris can enter the space between the first carrier block and the second carrier block, so that the debris can pass through the carrier plate, which is convenient for collection and does not require subsequent manual cleaning by the staff, which helps to reduce the labor intensity of the staff. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0022] Figure 1 It is a schematic diagram of the overall structure of a static stiffness test device for aviation parts of the present invention;

[0023] Figure 2 It is a front view structural schematic diagram of a static stiffness test device for aviation parts of the present invention;

[0024] Figure 3 This is a schematic diagram of the linkage assembly structure of an aviation parts static stiffness test device of the present invention;

[0025] Figure 4 This is a schematic diagram of the connection structure of an air cylinder and an electric push rod of an aviation parts static stiffness test device of the present invention;

[0026] Figure 5 It is a schematic diagram of the enlarged structure of A of a static stiffness test device for aviation parts of the present invention;

[0027] Figure 6 A schematic diagram of the cross-sectional structure of an air cylinder of a static stiffness test device for aviation parts of the present invention;

[0028] Figure 7 The present invention is a schematic diagram of a top view structure of a first carrier block, a second carrier block and a carrier plate of an aviation parts static stiffness test device.

[0029] In the figure:

[0030] 1. Base; 11. Carrier plate; 12. First carrier block; 13. Second carrier block; 14. Enclosure; 15. Electric push rod; 16. Pressure sensor; 17. Press plate; 18. High-precision distance sensor;

[0031] 2. Connecting plate; 21. First rack; 22. Gear; 23. Second rack; 24. Limiting rod;

[0032] 3. Air cylinder; 31. Conduit; 32. One-way air inlet valve; 33. Movable rod; 34. Annular tube; 35. Air outlet hole; 36. Piston. Detailed implementation manners

[0033] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments.

[0034] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0035] In the description of the present invention, it should be noted that unless otherwise clearly specified and limited, the terms "installed", "connected", and "set" should be understood in a broad sense. For example, it can be fixedly connected and set, or detachably connected and set, or integrally connected and set. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations. The models of the electrical appliances provided in the present invention are only for reference, and different models of electrical appliances with the same function can be replaced according to actual usage conditions.

[0036] Please refer to Figure 1-7 , the present invention provides a technical solution: an aviation part static stiffness experimental device, including a base 1. The top of the base 1 is fixedly connected to a carrier plate 11 through a support column. A first carrier block 12 is fixedly installed on the top of the carrier plate 11. A through hole is opened in the middle of the top of the first carrier block 12 and extends to the lower side of the carrier plate 11. A second carrier block 13 is arranged in the through hole;

[0037] A gantry is fixed on the top of the carrier plate 11. An electric push rod 15 is fixedly installed in the middle of the top of the gantry. The push rod of the electric push rod 15 movably penetrates through the gantry and is fixedly connected to a pressure sensor 16. The bottom of the pressure sensor 16 is fixedly connected to a pressing plate 17. High-precision distance sensors 18 are fixedly connected to both side walls of the pressing plate 17. A suitable enclosure 14 is sleeved on the outer wall of the first carrier block 12. The outer wall of the push rod of the electric push rod 15 is connected to the enclosure 14 through a linkage component.

[0038] It should be understood that in actual use, first place the product to be detected on the top of the second carrier block 13, and then start the electric push rod 15 to drive the pressure plate 17 to descend. During the process of the pressure plate 17 pressing on the product, the pressure sensor 16 can be used to feedback the pressure value, and at the same time, the high-precision distance sensor 18 can feedback the moving distance after the pressure is generated, which is the deformation distance of the product. During the process of the pressure plate 17 descending, the linkage component can be driven to lift the enclosure 14, so that the parts can be shielded by the enclosure 14. Thus, when debris splashes, the enclosure 14 can be used for protection, which is beneficial to avoiding damage to the surrounding staff caused by debris, and at the same time is also beneficial to avoiding the difficulty of cleaning up the splashed debris. When the electric push rod 15 retracts, it can drive the linkage component to drive the enclosure 14 to descend, which is beneficial to avoiding affecting the staff to take out the workpiece.

[0039] Furthermore, rubber blocks are embedded at the four corners of the bottom of the base 1. The setting of the rubber blocks can increase the friction during placement and use, which is beneficial to avoiding the situation of the overall device sliding.

[0040] Even further, both the pressure sensor 16 and the high-precision distance sensor 18 are electrically connected to the industrial control computer, so that the data can be fed back to the industrial control computer and further analyzed with the help of software.

[0041] As Figure 1-2 shown; the linkage component includes a connecting plate 2. The number of the connecting plates 2 is four. The four connecting plates 2 are respectively fixed on the outer walls of the four sides of the push rod of the electric push rod 15. The outer ends of the connecting plates 2 are fixedly connected with a first rack 21. A gear 22 is arranged below the first rack 21. Both ends of the gear 22 are movably connected with a cage. The tail end of the cage is fixed on the top of the carrier plate 11. A second rack 23 is meshed with one side wall of the gear 22. The second rack 23 is fixedly installed on the side wall of the enclosure 14;

[0042] It should be understood that in actual use, when the push rod of the electric push rod 15 extends, it drives the connecting plate 2 to descend, which can drive the first rack 21 to descend. After descending a certain distance, it will act on the gear 22, which can make the gear 22 rotate. Then the gear 22 can drive the second rack 23 to move upward, so as to drive the enclosure 14 to lift, so as to shield the debris. At the same time, when the electric push rod 15 retracts, it can drive the first rack 21 to lift, so that the gear 22 rotates in reverse, and the lifted second rack 23 descends, which can drive the enclosure 14 to descend, which is beneficial to avoiding affecting the staff to pick up the workpiece.

[0043] Furthermore, the back surface of the first rack 21 is attached to the inner wall of the gantry, which is beneficial to improving the stability of the first rack 21 during the lifting and lowering process.

[0044] Furthermore, a limiting rod 24 is fixedly connected to the top of the connecting plate 2. The limiting rod 24 movably penetrates through the gantry. The setting of the limiting rod 24 enables further limitation of the lifting trajectory of the connecting plate 2, which is beneficial to improving the lifting stability of the connecting plate 2.

[0045] As Figure 1-7 shown; an air cylinder 3 is installed on one side of the top of the gantry. A piston 36 adapted to the inner cavity of the air cylinder 3 is provided. A movable rod 33 is fixedly connected to the bottom of the piston 36. The tail end of the movable rod 33 movably penetrates through the gantry and is fixedly connected to the outer wall of the push rod of the electric push rod 15 through a fixing plate. The top of the air cylinder 3 is fixedly communicated with a conduit 31. The conduit 31 penetrates through the first carrier block 12 and is communicated with an annular pipe 34. The annular pipe 34 is fixed to the top of the first carrier block 12. A plurality of uniformly distributed air outlet holes 35 are formed in the inner wall of the annular pipe 34. The air outlet holes 35 are arranged obliquely downward.

[0046] It should be understood that when the electric push rod 15 drives the pressing plate 17 to lift, it can drive the movable rod 33 to lift, so as to drive the piston 36 to lift, thereby pushing the gas in the air cylinder 3 into the inner cavity of the annular pipe 34, and blowing it onto the surface of the first carrier block 12 along the air outlet holes 35 on the inner wall of the annular pipe 34, so as to blow the debris blocked by the enclosure 14 to move towards the middle, so that the debris can enter the space between the first carrier block 12 and the second carrier block 13, so that the debris can be collected, without the need for subsequent manual cleaning by the staff, which is beneficial to reducing the labor intensity of the staff.

[0047] Further, the four side walls of the second carrier block 13 are fixedly connected to the inner wall of the first carrier block 12 through connecting blocks. Thus, when in use, a collection box is placed on the top of the base 1, and the debris entering the space between the first carrier block 12 and the second carrier block 13 can fall into the collection box and be collected.

[0048] Furthermore, a one-way intake valve 32 is fixedly communicated with the upper side of the outer wall of the air cylinder 3. The setting of the one-way intake valve 32 enables the air pressure to be balanced through the one-way intake valve 32 during the descending process of the piston 36.

[0049] In summary, during the process of the electric push rod driving the pressing plate to descend, the present invention can synchronously drive the first rack to descend, thereby acting on the gear, driving the gear to rotate, and then the gear can drive the second rack to lift, so that the enclosure can be lifted during the process of pressing the parts, thereby forming an occlusion for the parts on the second carrier block. Thus, when debris splashes, the enclosure can be used for protection, which is beneficial to avoiding damage to the surrounding staff caused by debris, and is also beneficial to avoiding the difficulty of cleaning up the splashed debris; when the electric push rod drives the pressing block to lift, it can drive the movable rod to lift, thereby driving the piston to lift, and then pushing the gas in the air cylinder into the inner cavity of the annular pipe, and blowing it towards the surface of the first carrier block along the air outlet holes on the inner wall of the annular pipe, so that the debris blocked by the enclosure can be blown towards the middle, so that the debris can enter the space between the first carrier block and the second carrier block, and then the debris can pass through the carrier plate, which is convenient for collection, without the need for subsequent manual cleaning by the staff, and is beneficial to reducing the labor intensity of the staff.

[0050] In addition, all the components included in an aviation part static stiffness experimental device of the present invention are common standard parts or parts known to those skilled in the art, and their structures and principles can all be known to those skilled in the art through technical manuals or obtained through conventional experimental methods. At the idle place of this device, all the above-mentioned electrical components, which refer to power elements, electrical components, and the adapted monitoring computer and power supply, are connected through wires, and the electrical connection is completed in the order of the working sequence among the electrical components. The detailed connection means are well-known techniques in the art. The following mainly introduces the working principle and process, and no further description of the electrical control will be made.

[0051] For those skilled in the art, it is obvious that the present invention is not limited to the details of the above-mentioned exemplary embodiments, and can be implemented in other specific forms without departing from the spirit or basic characteristics of the present invention. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present invention. Any reference signs in the claims should not be regarded as limiting the claims involved.

[0052] In addition, it should be understood that although this specification is described according to embodiments, not every embodiment only contains an independent technical solution. This narrative way of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments understandable to those skilled in the art.

Claims

1. An experimental device for the static stiffness of an aviation part, comprising a base (1). The top of the base (1) is fixedly connected with a carrier plate (11) through a support column. The top of the carrier plate (11) is fixedly installed with a first carrier block (12). A through hole is formed in the middle of the top of the first carrier block (12) and extends to the lower side of the carrier plate (11). A second carrier block (13) is arranged in the through hole, and it is characterized in that: A gantry is fixed to the top of the carrier board (11). An electric push rod (15) is fixedly installed in the middle of the top of the gantry. The push rod of the electric push rod (15) movably penetrates through the gantry and is fixedly connected to a pressure sensor (16). The bottom of the pressure sensor (16) is fixedly connected to a pressing plate (17). High-precision distance sensors (18) are fixedly connected to both side walls of the pressing plate (17). A suitable enclosure (14) is sleeved on the outer wall of the first carrier block (12). The outer wall of the push rod of the electric push rod (15) is connected to the enclosure (14) through a linkage assembly.

2. The static stiffness experimental device for an aviation part according to claim 1, wherein: The linkage assembly includes connecting plates (2). The number of the connecting plates (2) is four. The four connecting plates (2) are respectively fixed to the four sides of the outer wall of the push rod of the electric push rod (15). A first rack (21) is fixedly connected to the outer end of the connecting plate (2). A gear (22) is arranged below the first rack (21). Both ends of the gear (22) are movably connected to a cage. The tail end of the cage is fixed to the top of the carrier board (11). A second rack (23) is meshed with one side wall of the gear (22). The second rack (23) is fixedly installed on the side wall of the enclosure (14).

3. The static stiffness experimental device for an aviation part according to claim 1, characterized in that: An air cylinder (3) is installed on one side of the top of the gantry. A suitable piston (36) is arranged in the inner cavity of the air cylinder (3). The bottom of the piston (36) is fixedly connected to a movable rod (33). The tail end of the movable rod (33) movably penetrates through the gantry and is fixedly connected to the outer wall of the push rod of the electric push rod (15) through a fixing plate. The top of the air cylinder (3) is fixedly communicated with a conduit (31). The conduit (31) penetrates through the first carrier block (12) and is communicated with an annular pipe (34). The annular pipe (34) is fixed to the top of the first carrier block (12). A plurality of uniformly distributed air outlet holes (35) are formed in the inner wall of the annular pipe (34).

4. An experimental device for the static stiffness of an aviation part according to claim 1, characterized in that: The four side walls of the second carrier block (13) are fixedly connected to the inner wall of the first carrier block (12) through connecting blocks.

5. The static stiffness experimental device for an aviation part according to claim 3, wherein: A one-way intake valve (32) is fixedly communicated with the upper side of the outer wall of the air cylinder (3).

6. The static stiffness experimental device for an aviation part according to claim 2, wherein: A limiting rod (24) is fixedly connected to the top of the connecting plate (2). The limiting rod (24) movably penetrates through the gantry.

7. An experimental device for the static stiffness of an aviation part according to claim 2, characterized in that: The back surface of the first rack (21) is attached to the inner wall of the gantry.

8. The static stiffness experimental device for an aviation part according to claim 1, characterized in that: Rubber blocks are embedded at the four corners of the bottom of the base (1).

9. The static stiffness experimental device for an aviation part according to claim 1, wherein: Both the pressure sensor (16) and the high-precision distance sensor (18) are electrically connected to an industrial control computer.

10. The static stiffness experimental device for an aviation part according to claim 3, wherein: The air outlet holes (35) are arranged obliquely downward.

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