A vibration test device suitable for aerospace

Abstract

The utility model discloses a vibration test device suitable for aerospace, and specifically relates to the field of aerospace test technology, wherein a rectangular frame plate is welded on the top of the test platform, and a synchronous locking assembly is installed on the inner wall of the rectangular frame plate; the synchronous locking assembly includes a linkage screw rotatably installed on the inner wall of the rectangular frame plate. The utility model adopts a synchronous locking assembly to start a reduction motor to drive the linkage screw to rotate inside the rectangular frame plate, two sleeves approach each other, and the two sleeves respectively drive two extrusion support plates to approach each other, and two rubber plates are respectively squeezed and locked at the two sides of multiple identical aerospace components, and the pressure plate can be squeezed at the top position of multiple identical aerospace components, and horizontal and vertical extrusion locking operations are realized for multiple identical aerospace components, and multiple aerospace components are tested synchronously, and the test efficiency is greatly improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aerospace testing, and more specifically, to a vibration testing device suitable for aerospace testing. Background Art

[0002] Vibration test equipment suitable for aerospace plays an important role in the aerospace field. These devices are mainly used to simulate various vibration conditions that aircraft components, satellite equipment, etc. may encounter during flight or space exploration. Through precise vibration simulation, the reliability and stability of aircraft or satellites in actual operation can be evaluated, and the performance of products in various vibration environments can be tested, including structural integrity, durability of parts, and stability of electronic equipment.

[0003] In the existing public documents, the vibration test device for aerospace with the Chinese publication number CN215492335U is provided with a vibrating mechanism. Due to the connection between the rotating plate and the movable rod, and the connection between the rotating plate and the bracket through the rotating rod to form a lever system, and the torque on the side of the crankshaft is relatively large, the frequency and vibrating force of the vibrating column are increased by increasing the output power of the motor and utilizing the lever principle, thereby meeting the test requirements. The combination of the above structures solves the problem that the excitation frequency of the existing ordinary vibration table is difficult to meet the test requirements. The vibration test device also has the following defects:

[0004] When the vibration test device conducts vibration experiments on aerospace parts, one aerospace part needs to be placed for vibration testing each time, and then another aerospace part is tested after the test. It is difficult to lock multiple aerospace parts synchronously and then implement vibration testing, which leads to a significant decrease in the efficiency of vibration testing. Utility Model Content

[0005] In order to overcome the above-mentioned defects of the prior art, the utility model provides a vibration test device suitable for aerospace.

[0006] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a vibration test device suitable for aerospace, comprising a sleeve plate, a test platform is fixedly installed on one side of the sleeve plate, a rectangular frame plate is welded on the top of the test platform, and a synchronous locking assembly is installed on the inner wall of the rectangular frame plate; the synchronous locking assembly comprises a linkage screw rotatably installed on the inner wall of the rectangular frame plate; the synchronous locking assembly also includes two sleeve blocks, a reduction motor, two extrusion support plates, two rubber plates, a sleeve support plate, an electric cylinder and a pressure plate; the two sleeve blocks are threadedly arranged on the outer wall of the linkage screw, the two sleeve blocks are arranged equidistantly from front to back, and the reduction motor is fixed on one side of the rectangular frame plate and drives the linkage screw to rotate, the two extrusion support plates are respectively located on one side of the two sleeve blocks and are fixedly connected, the two rubber plates are respectively bonded to the inner walls of the two extrusion support plates, the sleeve support plate is fixed on the top of an extrusion support plate, the electric cylinder is fixed on the inner wall of the sleeve support plate and close to its top, and the pressure plate is fixedly installed on the output end of the electric cylinder.

[0007] Preferably, the two sleeve blocks are both threadedly connected to the linkage screw, and the two threads on the outer wall of the linkage screw are opposite and symmetrical; the two sleeve blocks are both slidably connected to the inner wall of the rectangular frame plate, and the two extruded support plates are symmetrically arranged about the middle of the linkage screw, and the vertical cross-sectional shapes of the two extruded support plates are both set to L-shaped, the extruded support plates and the rubber plates are both slidably connected to the rectangular frame plate, and the outer wall of the rectangular frame plate is polished and ground, and the inner wall of the sleeve plate is connected to two guide columns, and a support base is fixedly installed at the bottom end of the guide columns.

[0008] When the upper structure is in use, multiple identical aerospace devices are placed on the top of the test platform, the reduction motor is started to drive the linkage screw to rotate inside the rectangular frame plate, and the two sleeve blocks are close to each other under the action of the thread transmission force. The two extrusion support plates can drive the two rubber plates to move, and the two rubber plates are respectively squeezed and locked at the positions on both sides of the multiple identical aerospace devices, and can synchronously achieve lateral locking of the multiple identical aerospace devices. The sleeve support plate provides support force for the electric cylinder, and the pressure plate can be squeezed at the top position of the multiple identical aerospace devices.

[0009] A guide vibration mechanism is provided on one side of the sleeve plate; the guide vibration mechanism also includes a connecting shaft, a sleeve rod, a linkage shaft, a rotating block, a driving motor, and a V-shaped support plate; the connecting shaft is fixed on one side of the sleeve plate, the sleeve rod is located on the outer wall of the connecting shaft and is rotatably connected, the linkage shaft is rotatably installed on the inner wall of the sleeve rod and is located above the connecting shaft, the rotating block is welded on one end of the linkage shaft, the driving motor is coaxially installed on one side of the rotating block, the rotating block is located at the output end of the driving motor and is transmission connected, and the V-shaped support plate is arranged between the driving motor and the guide column, the two guide columns are both slidably connected to the sleeve plate, the outer walls of the two guide columns are polished and ground, the two guide columns and the driving motor are fixedly connected to the V-shaped support plate, and the cross-sectional shape of the V-shaped support plate is V-shaped.

[0010] When the upper structure is in use, two guide columns are used to provide support force for the V-shaped support plate, the driving motor drives the rotating block to rotate, the linkage shaft reciprocates from bottom to top, the linkage shaft carries the sleeve rod to vibrate reciprocatingly from bottom to top, the sleeve rod can also make the sleeve plate vibrate, and the sleeve plate drives multiple identical aerospace devices on the test platform to vibrate vertically.

[0011] Technical effects and advantages of the utility model:

[0012] 1. The utility model adopts a synchronous locking component, starts the reduction motor to drive the linkage screw to rotate inside the rectangular frame plate, the two sleeve blocks approach each other, the two sleeve blocks respectively drive the two extrusion support plates to approach each other, the two rubber plates are respectively squeezed and locked at the two sides of multiple identical aerospace components, the pressure plate can be squeezed at the top position of multiple identical aerospace components, and the horizontal and vertical extrusion locking operations are realized for multiple identical aerospace components, and multiple aerospace components are tested synchronously, and the test efficiency is greatly improved;

[0013] 2. The utility model adopts a driving motor to drive the rotating block to rotate, and the rotating block carries the linkage shaft to rotate. The linkage shaft carries the sleeve rod to reciprocate from bottom to top, and the sleeve plate presses the outer walls of the two guide pillars to achieve up and down reciprocating vibration. Multiple identical aerospace components can realize vibration tests in specified positions and accurately perform vertical vibration tests. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 The utility model is a schematic diagram of the structure of a vibration test device suitable for aerospace.

[0015] Figure 2 It is a schematic diagram of the local structure of the connection between the rectangular frame plate and the linkage screw rod of the utility model.

[0016] Figure 3 The utility model is a schematic diagram of the main plane structure of a vibration test device suitable for aerospace.

[0017] Figure 4 The utility model is a schematic diagram of a bottom-up structure of a vibration test device suitable for aerospace.

[0018] Figure 5 It is a schematic diagram of the partial structure of the connection between the support base and the guide column of the utility model.

[0019] Figure 6 It is a schematic diagram of the partial structure of the connection between the linkage shaft and the sleeve rod of the utility model.

[0020] The accompanying drawings are marked as follows: 1. sleeve plate; 2. test platform; 3. rectangular frame plate; 4. linkage screw; 5. sleeve block; 6. reduction motor; 7. extrusion support plate; 8. rubber plate; 9. sleeve support plate; 10. electric cylinder; 11. pressure plate; 12. guide column; 13. support base; 14. connecting shaft; 15. sleeve rod; 16. linkage shaft; 17. rotating block; 18. drive motor; 19. V-shaped support plate. DETAILED DESCRIPTION

[0021] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0022] As attached Figure 1-6 A vibration test device suitable for aerospace is shown, and a synchronous locking assembly is provided on the vibration test device suitable for aerospace. The setting of the synchronous locking assembly can realize lateral and vertical extrusion locking operations on multiple identical aerospace components, and test multiple aerospace components simultaneously, and the test efficiency is greatly improved. The specific structural setting of the synchronous locking assembly is as follows:

[0023] In this technology, as shown in the attached Figure 1-3As shown, the synchronous locking assembly includes a linkage screw 4 rotatably mounted on the inner wall of the rectangular frame plate 3; the synchronous locking assembly also includes two sleeve blocks 5, a reduction motor 6, two extrusion support plates 7, two rubber plates 8, a sleeve support plate 9, an electric cylinder 10 and a pressing plate 11; the two sleeve blocks 5 are threadedly arranged on the outer wall of the linkage screw 4, the two sleeve blocks 5 are arranged equidistantly from front to back, and the reduction motor 6 is fixed on one side of the rectangular frame plate 3 and drives the linkage screw 4 to rotate, the two extrusion support plates 7 are respectively located on one side of the two sleeve blocks 5 and are fixedly connected, the two rubber plates 8 are respectively bonded to the inner walls of the two extrusion support plates 7, the sleeve support plate 9 is fixed on the top of one extrusion support plate 7, the electric cylinder 10 is fixed on the inner wall of the sleeve support plate 9 and close to its top, and the pressing plate 11 is fixedly mounted on the output end of the electric cylinder 10;

[0024] When the aerospace vibration test device of this embodiment is used, multiple identical aerospace components are placed on the top of the test platform 2 and located in the gap between the two rubber plates 8. The reduction motor 6 is started to drive the linkage screw 4 to rotate inside the rectangular frame plate 3. The linkage screw 4 drives the two sleeve blocks 5 to move closer to each other under the action of the thread transmission force. The two sleeve blocks 5 respectively drive the two extrusion support plates 7 to move closer to each other. The two extrusion support plates 7 can drive the two rubber plates 8 to move. The two rubber plates 8 are respectively squeezed and locked at the two sides of the multiple identical aerospace components, and can synchronously realize lateral locking of the multiple identical aerospace components. At the same time, the electric cylinder 10 is started to drive the pressure plate 11 to squeeze downward, and the sleeve support plate 9 provides support force to the electric cylinder 10, so that the pressure plate 11 can be squeezed at the top position of the multiple identical aerospace components.

[0025] In this technology, as shown in the attached Figure 4-6 As shown, the inner wall of the sleeve plate 1 is connected to two guide pillars 12, and a support base 13 is fixedly installed at the bottom end of the guide pillars 12; a guide vibration mechanism is provided on one side of the sleeve plate 1; the guide vibration mechanism also includes a connecting shaft 14, a sleeve rod 15, a linkage shaft 16, a rotating block 17, a driving motor 18, and a V-shaped support plate 19; the connecting shaft 14 is fixed to one side of the sleeve plate 1, the sleeve rod 15 is located on the outer wall of the connecting shaft 14 and is rotatably connected, and the linkage shaft 16 is rotatably installed on the inner wall of the sleeve rod 15 and is located above the connecting shaft 14, and the rotating block 17 is provided on the inner wall of the sleeve rod 15. The moving block 17 is welded to one end of the linkage shaft 16, the driving motor 18 is coaxially installed on one side of the rotating block 17, the rotating block 17 is located at the output end of the driving motor 18 and is drivingly connected, and the V-shaped support plate 19 is arranged between the driving motor 18 and the guide column 12, the two guide columns 12 are slidably connected to the sleeve plate 1, the outer walls of the two guide columns 12 are polished, the two guide columns 12 and the driving motor 18 are fixedly connected to the V-shaped support plate 19, and the cross-sectional shape of the V-shaped support plate 19 is V-shaped;

[0026] According to the upper structure, when conducting a vibration test, the two guide columns 12 provide support force to the V-shaped support plate 19, and the V-shaped support plate 19 provides stable support for the drive motor 18. The drive motor 18 drives the rotating block 17 to rotate, and the rotating block 17 carries the linkage shaft 16 to rotate. The linkage shaft 16 reciprocates from bottom to top, and the linkage shaft 16 carries the sleeve rod 15 to reciprocate and vibrate from bottom to top. While the sleeve rod 15 reciprocates from bottom to top, the sleeve rod 15 can also make the sleeve plate 1 vibrate. The sleeve plate 1 presses the outer walls of the two guide columns 12 to achieve up and down reciprocating vibration. The sleeve plate 1 drives multiple identical aerospace devices on the test platform 2 to vibrate, and the support base 13 can provide reliable support force to the guide column 12.

[0027] The contents not described in detail in the specification belong to the prior art known to those skilled in the art, and the model parameters of each electrical appliance are not specifically limited, and conventional equipment can be used. In this technical solution, the electrical control components not mentioned are not shown in the figure because they belong to the prior art and will not be described here.

[0028] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A vibration test device suitable for aerospace, comprising a sleeve plate (1), a test platform (2) fixedly mounted on one side of the sleeve plate (1), a rectangular frame plate (3) welded to the top of the test platform (2), characterized in that: The inner wall of the rectangular frame plate (3) is installed with a synchronous locking assembly; The synchronous lock assembly comprises a linkage screw (4) rotatably mounted on the inner wall of the rectangular frame plate (3); The synchronous lock assembly also includes two sleeve blocks (5), a reduction motor (6), two extrusion support plates (7), two rubber plates (8), a sleeve support plate (9), an electric cylinder (10) and a pressure plate (11); The two sleeve blocks (5) are threadedly arranged on the outer wall of the linkage screw (4), the two sleeve blocks (5) are arranged equidistantly from front to back, and the reduction motor (6) is fixed on one side of the rectangular frame plate (3) and drives the linkage screw (4) to rotate, the two extrusion support plates (7) are respectively located on one side of the two sleeve blocks (5) and are fixedly connected, the two rubber plates (8) are respectively bonded to the inner walls of the two extrusion support plates (7), the sleeve support plate (9) is fixed to the top of an extrusion support plate (7), the electric cylinder (10) is fixed to the inner wall of the sleeve support plate (9) and close to its top, and the pressure plate (11) is fixedly installed at the output end of the electric cylinder (10).

2. A vibration test device suitable for aerospace according to claim 1, characterized in that: The two sleeve blocks (5) are both threadedly connected to the linkage screw rod (4), and the two threads on the outer wall of the linkage screw rod (4) are opposite and symmetrically arranged; The two sleeve blocks (5) are both slidably connected to the inner wall of the rectangular frame plate (3).

3. A vibration test device suitable for aerospace according to claim 1, characterized in that: The two extrusion support plates (7) are symmetrically arranged about the middle of the linkage screw rod (4), and the vertical cross-section shapes of the two extrusion support plates (7) are both set to be L-shaped.

4. A vibration test device suitable for aerospace according to claim 1, characterized in that: The extruded support plate (7) and the rubber plate (8) are both slidably connected to the rectangular frame plate (3), and the outer wall of the rectangular frame plate (3) is polished and ground.

5. The vibration test device suitable for aerospace according to claim 1, characterized in that: The inner wall of the sleeve plate (1) is connected to two guide pillars (12), and a support base (13) is fixedly installed at the bottom end of the guide pillars (12); A guide vibration mechanism is provided on one side of the sleeve plate (1); The guide vibration mechanism also includes a connecting shaft (14), a sleeve rod (15), a linkage shaft (16), a rotating block (17), a driving motor (18), and a V-shaped support plate (19); The connecting shaft (14) is fixed on one side of the sleeve plate (1); the sleeve rod (15) is located on the outer wall of the connecting shaft (14) and is rotatably connected; the linkage shaft (16) is rotatably mounted on the inner wall of the sleeve rod (15) and is located above the connecting shaft (14); the rotating block (17) is welded to one end of the linkage shaft (16); the driving motor (18) is coaxially mounted on one side of the rotating block (17); the rotating block (17) is located at the output end of the driving motor (18) and is rotatably connected; and the V-shaped support plate (19) is arranged between the driving motor (18) and the guide column (12).

6. A vibration test device suitable for aerospace according to claim 5, characterized in that: The two guide pillars (12) are both slidably connected to the sleeve plate (1), and the outer walls of the two guide pillars (12) are both polished and ground.

7. The vibration test device suitable for aerospace according to claim 5, characterized in that: The two guide pillars (12) and the drive motor (18) are fixedly connected to the V-shaped support plate (19), and the cross-sectional shape of the V-shaped support plate (19) is V-shaped.

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