A vibration test fixture for aerospace equipment

Abstract

The present invention relates to the technical field of aerospace equipment vibration test tooling, and discloses a vibration test tooling for aerospace equipment, including an impact assembly installed in the middle of a frame, aerospace shells placed on a plurality of placement racks, a pump air assembly installed on the top outer wall of a mobile rack, a ring kit connected to the pump air assembly, and a brush and a micrometer installed on the ring kit. The present invention moves the ring kit to squeeze the telescopic tube, and then the gas inside the telescopic tube is discharged through the air pipe, a spring is used to reset the telescopic tube, so that the telescopic tube is refilled with air, and the exhausted air is blown out through the air holes of the ring body and blown to the outer wall surface of the aerospace shell, blowing off the dust on the outer wall surface of the aerospace shell, thereby reducing the influence of the dust on the outer wall surface on the micrometer detection.

Description

Technical Field

[0001] The invention relates to the technical field of vibration testing tooling for aerospace equipment, and in particular to a vibration testing tooling for aerospace equipment. Background Art

[0002] The vibration test fixture for aerospace equipment is a specially designed device used to simulate and test the vibration environment that aerospace equipment may encounter during launch and flight. These vibration environments may include severe vibrations during rocket launches and micro-vibrations during on-orbit operation. The purpose of the vibration test fixture is to ensure that aerospace equipment can maintain structural integrity and function properly under these extreme conditions. During the design and manufacturing process of aerospace equipment, a series of environmental and performance tests are required to ensure that it can work properly in a real space environment. Vibration testing is an important part of these tests. It simulates the vibration environment generated during rocket launches and on-orbit operations to evaluate the structural strength and reliability of the equipment. Vibration testing under negative pressure is to simulate the actual working conditions of aerospace equipment in the vacuum environment of space. This test is particularly important for equipment that will be directly deployed in a space environment, because the vacuum environment will affect the performance of the material, such as thermal expansion, gas release, etc. By performing vibration testing in a negative pressure environment, the performance and life of the equipment can be more accurately evaluated;

[0003] With current technology, after a vibration test on the shell of aerospace equipment, it is usually necessary to use a micrometer to test the flatness of the shell to ensure its structural integrity and performance. However, during the vibration of the shell of aerospace equipment, dust and impurities that may exist on its top surface are not completely shaken off. The dust or impurities attached to the shell will affect the accuracy of the test results to a certain extent. Summary of the invention

[0004] The purpose of the present invention is to provide a vibration test fixture for aerospace equipment to solve the problems raised in the above background technology.

[0005] In order to solve the above technical problems, the present invention is achieved through the following technical solutions:

[0006] The present invention is a vibration test tool for aerospace equipment, comprising a vehicle frame, a mobile frame and a lifting assembly, wherein the vehicle frame is provided with a plurality of first slide grooves, a plurality of second slide grooves, a plurality of placement frames and brackets;

[0007] The moving frame is slidably connected to the two second slide grooves, and the lifting assembly is installed on the top of the moving frame;

[0008] The two first slide grooves are respectively slidably connected with a sliding frame, the two sliding frames are respectively at two ends of the frame, and a bidirectional screw is connected between the two sliding frames;

[0009] A cylinder is installed on the sliding frame, and the tops of the two sliding frames are slidably connected with support components respectively, and the output end of the cylinder is connected to the support component;

[0010] A striking assembly is installed in the middle of the frame;

[0011] A plurality of the placement racks are provided with aerospace shells;

[0012] A pump air assembly is installed on the top outer wall of the mobile frame, an annular sleeve is connected to the pump air assembly, and a brush and a micrometer are installed on the annular sleeve;

[0013] The purpose of the above arrangement is to place the aerospace shell on the placement rack, adjust the sliding rack and the brace assembly through the bidirectional screw, adjust the two brace assemblies to the two ends of the frame, and then adjust the moving rack to adjust the lifting assembly, lift the bidirectional screw through the lifting assembly and the lifting rope, and then move it between the two brace assemblies;

[0014] By adjusting the two support components, close to the ports of the aerospace shell, supporting the two ports of the aerospace shell, touching the outer wall of the aerospace shell through the impact component, performing a vibration test on the aerospace shell, and then rotating the aerospace shell, touching another position of the aerospace shell, and then performing another vibration test;

[0015] After the test, the flatness of the outer wall of the aerospace shell is tested by moving the annular kit. During the test, the annular kit moves to drive the pump air assembly to operate. The pump air assembly first blows off the dust on the outer wall of the aerospace shell, and then the annular kit drives the brush to clean the outer wall of the aerospace shell, and then the micrometer tests the outer wall of the aerospace shell.

[0016] Furthermore, the lifting assembly includes a first motor and a roller, the first motor is mounted on the outer wall of the mobile frame, the two rollers are rotatably connected to the top of the mobile frame, and the output end of the first motor is connected to one of the rollers;

[0017] The two rollers are respectively connected with gears, and the two gears are meshed with each other;

[0018] The outer walls of the two drums are respectively connected with cables, the bottom ends of the two cables are connected with blocks, and the bottom of the blocks is rotatably connected with hooks;

[0019] The purpose of the above arrangement is to drive the roller to rotate through the output end of the first motor, and at the same time drive the gear to rotate, the two gears mesh with each other and rotate in opposite directions, and the cables on the two rollers are retracted and released, thereby lifting and lowering the block and the hook.

[0020] Furthermore, the bidirectional screw is provided with two threads, the two threads are symmetrical on the outer wall of the bidirectional screw, and the bidirectional screw is respectively threadedly connected to the sliding frame;

[0021] The purpose of the above setting is that the setting of the bidirectional screw bidirectional thread, when the bidirectional screw is rotated, drives and adjusts the two sliding frames at the same time, and the symmetrical threads make the two sliding frames approach or move away from each other, thereby driving the two support components to approach or move away from each other.

[0022] Furthermore, the support assembly includes a support frame, the output end of the cylinder passes through the top of the sliding frame and extends to the top of the sliding frame, the lower surface of the support frame is connected to the output end of the cylinder, the two ends of the support frame are respectively slidably connected to the sliding frame, and one end of the support frame is connected to a circular body;

[0023] The purpose of the above arrangement is to control the lifting and lowering of the support assembly through the output end of the cylinder, so as to adjust the height of the aerospace shell, thereby adjusting the distance between the aerospace shell and the impact assembly, and thus adjusting the vibration test.

[0024] Furthermore, a second motor is installed on the outer wall of the circular body, the output end of the second motor passes through the circular body, a driving gear is installed on the output end of the second motor, a driven gear is rotatably connected at the center of the circular body, and the driving gear and the driven gear are meshed with each other;

[0025] Four sliders are slidably connected to the circular body, an arc groove is provided on the outer wall of the driven gear, and one end of the slider extends to the inner side of the arc groove;

[0026] The purpose of the above-mentioned setting is that the output end of the second motor drives the driving gear to rotate, and the driving gear and the driven gear are meshed with each other, driving the driven gear to rotate, and the arc groove arc surface on the driven gear drives the slider, thereby controlling the four sliders to move on the circular body. When the four sliders move outward at the same time, the inner wall of the port of the aerospace shell is supported, thereby fixing the aerospace shell.

[0027] Furthermore, a third motor is installed at the bottom of the frame, the output end of the third motor passes through the frame and extends to the top of the frame, a rotating disk is installed on the output end of the third motor, a plurality of ramp blocks are installed on the upper surface of the rotating disk, a U-shaped frame is slidably connected to both ends of the bracket, the bottom end of the U-shaped frame moves on the upper surface of the ramp block, and a convex block is installed on the upper surface of the U-shaped frame;

[0028] The purpose of the above arrangement is that the output end of the third motor drives the rotating disk and the ramp block to rotate, the ramp block gradually lifts the U-shaped frame and the protrusion, and the U-shaped frame slides up and down on the bracket.

[0029] Further, the pump air assembly includes a long tube, the long tube is installed on the outer wall of the mobile frame, a sliding groove is provided at the bottom of the long tube, a telescopic tube is installed inside the long tube, a spring is installed inside the telescopic tube, and an air pipe is connected to the outer wall of the telescopic tube;

[0030] The purpose of the above arrangement is to move the annular kit to squeeze the telescopic tube, and then the gas inside the telescopic tube is discharged through the air pipe. The spring is used to reset the telescopic tube so that the telescopic tube is refilled with air.

[0031] Furthermore, the annular kit includes a sliding rod, the top of the sliding rod is slidably connected to the inner wall of the long tube through the long tube sliding groove, the air pipe is connected to the sliding rod, the bottom of the sliding rod is connected to the ring body, and the inner wall of the ring body is provided with a plurality of air holes;

[0032] A moving block is slidably connected to the inner wall of the ring body, and the micrometer is installed on the moving block;

[0033] The purpose of the above arrangement is to discharge the exhausted air through the air holes of the ring body to the outer wall surface of the aerospace shell, and adjust the moving block and the micrometer to test the flatness of the outer wall of the aerospace shell.

[0034] Furthermore, a brush is threadedly connected to the moving block;

[0035] The purpose of the above-mentioned setting is that when the moving block and the micrometer make circular motion on the ring body, the outer wall of the aerospace shell is cleaned. A brush is connected to the thread. During the movement, the outer wall of the aerospace shell is first cleaned by the brush, thereby reducing the influence of dust on the surface of the aerospace shell on the micrometer test.

[0036] Furthermore, the outer walls of several of the sliders are respectively provided with notches, annular rubbers are provided between several of the notches, and a tube body is provided on one of the circular bodies;

[0037] The purpose of the above-mentioned setting is that after the inner wall of the port of the aerospace shell is propped up by the slider, the set groove is used to install the annular rubber, the outer wall of the annular rubber is tightly fitted with the inner wall of the aerospace shell, and the inner wall of the annular rubber is tightly fitted with the outer wall of the circular body, thereby closing the port of the aerospace shell to form a cavity, in which a tube body is provided on one of the circular bodies, and the tube body is connected with the cavity, and the tube body is used to connect the air pump through a pipeline. The air pump adopts the existing YN1680*2-50L model. The air pump is used to evacuate or inflate the cavity, so that a pressurized or negative pressure state is formed inside the cavity, so as to perform vibration test on the aerospace shell under pressurized and negative pressure states, so as to obtain test results under different states.

[0038] The present invention has the following beneficial effects:

[0039] (1) The present invention uses a movable annular kit to squeeze the telescopic tube, and then the gas inside the telescopic tube is discharged through the air pipe. The spring is used to reset the telescopic tube so that the telescopic tube is refilled with air. The discharged air is blown out through the air holes of the ring body and blown toward the outer wall surface of the aerospace shell, blowing off the dust on the outer wall surface of the aerospace shell, thereby reducing the influence of the dust on the outer wall surface on the micrometer detection.

[0040] (2) The present invention provides a brush so that when the moving block and the micrometer make a circular motion on the ring body, the outer wall of the aerospace shell is cleaned. The brush is threadedly connected. During the movement, the outer wall of the aerospace shell is first cleaned by the brush, thereby further reducing the influence of dust on the surface of the aerospace shell on the micrometer test.

[0041] (3) The present invention arranges an annular rubber and a tube body. After the inner wall of the port of the aerospace shell is propped up by a slider, a groove is arranged for installing the annular rubber. The outer wall of the annular rubber is tightly fitted with the inner wall of the aerospace shell, and the inner wall of the annular rubber is tightly fitted with the outer wall of the circular body, thereby closing the port of the aerospace shell to form a cavity, wherein a tube body is arranged on one of the circular bodies, and the tube body is connected with the cavity. The tube body is used to connect an air pump through a pipeline. The air pump adopts the existing YN1680*2-50L model. The air pump is used to evacuate or inflate the cavity, so that a pressurized or negative pressure state is formed inside the cavity, so that the aerospace shell is subjected to vibration test under pressurized and negative pressure states, thereby obtaining test results under different states.

[0042] Of course, any product implementing the present invention does not necessarily need to achieve all of the advantages described above at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for describing the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0044] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0045] Figure 2 It is a schematic diagram of the lifting assembly and the mobile frame of the present invention;

[0046] Figure 3 It is a schematic diagram of the lifting assembly of the present invention;

[0047] Figure 4 It is a schematic diagram of the pump gas assembly and the annular kit of the present invention;

[0048] Figure 5 For the present invention Figure 4 The structural diagram at A in the middle;

[0049] Figure 6 It is a schematic diagram of the frame structure of the present invention;

[0050] Figure 7 Schematic diagram of the components for attacking the present invention;

[0051] Figure 8 The support assembly of the present invention is shown in FIG. Figure 1 ;

[0052] Fig. 9 The support assembly of the present invention is shown in FIG. Figure 2 ;

[0053] Fig.10 A schematic diagram of the support assembly of the present invention Figure 1 ;

[0054] Fig.11 A schematic diagram of the support assembly of the present invention Figure 2 ;

[0055] Fig.12 This is a schematic diagram of the annular rubber structure of the present invention;

[0056] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0057] In the figure: 1, frame; 101, first slide; 102, second slide; 103, placement rack; 104, bracket; 2, mobile rack; 3, lifting assembly; 301, first motor; 302, roller; 303, cable; 304, gear; 305, block; 306, hook; 4, sliding rack; 5, cylinder; 6, support assembly; 601, support rack; 602, circular body; 603, driving gear; 604, driven gear; 605, arc groove; 606, slider; 6060, notch; 607, second motor; 7, attack assembly; 701, third motor; 702, rotating disk; 703, ramp block; 704, U-shaped frame; 705, bump; 8, pump air assembly; 801, long tube; 802, telescopic tube; 803, spring; 804, air pipe; 9, annular kit; 901, sliding rod; 902, ring body; 9020, air hole; 903, moving block; 10, bidirectional screw; 11, aerospace shell; 12, brush; 13, micrometer; 14, annular rubber; 15, tube body. DETAILED DESCRIPTION

[0058] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention. Example 1

[0059] The present invention is a vibration test tool for aerospace equipment, such as Figure 1 - Fig.10 As shown, it includes a vehicle frame 1, a moving frame 2 and a lifting assembly 3, and the vehicle frame 1 is provided with a plurality of first slide grooves 101, a plurality of second slide grooves 102, a plurality of placement racks 103 and a bracket 104;

[0060] The moving frame 2 is slidably connected to the two second slide grooves 102, and the lifting assembly 3 is installed on the top of the moving frame 2;

[0061] The two first slide grooves 101 are respectively slidably connected with a sliding frame 4, the two sliding frames 4 are respectively at two ends of the frame 1, and a bidirectional screw rod 10 is connected between the two sliding frames 4;

[0062] The sliding frame 4 is provided with a cylinder 5, and the tops of the two sliding frames 4 are respectively slidably connected with a support assembly 6, and the output end of the cylinder 5 is connected to the support assembly 6;

[0063] A striking assembly 7 is installed in the middle of the frame 1;

[0064] A plurality of placement racks 103 are provided with aerospace shells 11;

[0065] A pump assembly 8 is installed on the top outer wall of the mobile frame 2, and an annular sleeve 9 is connected to the pump assembly 8, and a brush 12 and a micrometer 13 are installed on the annular sleeve 9;

[0066] In this embodiment, the purpose of the above arrangement is to place the aerospace shell 11 on the placement rack 103, adjust the sliding rack 4 and the support assembly 6 through the bidirectional screw 10, adjust the two support assemblies 6 to the two ends of the frame 1, and then adjust the moving rack 2 to adjust the lifting assembly 3, lift the bidirectional screw 10 through the lifting assembly 3 and the lifting rope, and then move it between the two support assemblies 6;

[0067] By adjusting the two support components 6, close to the ports of the aerospace shell 11, the two ports of the aerospace shell 11 are supported, and the outer wall of the aerospace shell 11 is touched by the impact component 7, and the aerospace shell 11 is subjected to a vibration test, and then the aerospace shell 11 is rotated, and another position of the aerospace shell 11 is touched, and then the vibration test is performed again;

[0068] After the test, the flatness of the outer wall of the aerospace shell 11 is tested by moving the annular kit 9. During the test, the annular kit 9 ​​moves to drive the pump air component 8 to operate. The pump air component 8 first blows off the dust on the outer wall of the aerospace shell 11, and then the annular kit 9 ​​drives the brush 12 to clean the outer wall of the aerospace shell 11, and then the micrometer 13 tests the outer wall of the aerospace shell 11.

[0069] As an implementation method, Figure 2 - Figure 3 As shown, further:

[0070] The lifting assembly 3 includes a first motor 301 and a roller 302. The first motor 301 is installed on the outer wall of the mobile frame 2. The two rollers 302 are rotatably connected to the top of the mobile frame 2 respectively. The output end of the first motor 301 is connected to one of the rollers 302.

[0071] The two rollers 302 are respectively connected with gears 304, and the two gears 304 are meshed with each other;

[0072] The outer walls of the two drums 302 are respectively connected with cables 303, the bottom ends of the two cables 303 are connected with blocks 305, and the bottom of the blocks 305 is rotatably connected with hooks 306;

[0073] In this embodiment, the purpose of the above-mentioned arrangement is to drive the roller 302 to rotate through the output end of the first motor 301, and at the same time drive the gear 304 to rotate, the two gears 304 are meshed and rotated with each other, and the two gears 304 rotate in opposite directions, so as to retract and release the cables 303 on the two rollers 302, thereby lifting and lowering the block 305 and the hook 306.

[0074] As an implementation method, Figure 1 As shown, further:

[0075] The bidirectional screw 10 is provided with two threads, which are symmetrical on the outer wall of the bidirectional screw 10, and the bidirectional screw 10 is threadedly connected to the sliding frame 4 respectively;

[0076] In this embodiment, the purpose of the above-mentioned setting is that the setting of the bidirectional thread of the bidirectional screw 10 drives and adjusts the two sliding frames 4 at the same time when the bidirectional screw 10 is rotated. The symmetrical thread allows the two sliding frames 4 to move closer to or away from each other, thereby driving the two support components 6 to move closer to or away from each other.

[0077] As an implementation method, Figure 8 - Fig. 9 As shown, further:

[0078] The support assembly 6 includes a support frame 601. The output end of the cylinder 5 passes through the top of the sliding frame 4 and extends to the top of the sliding frame 4. The lower surface of the support frame 601 is connected to the output end of the cylinder 5. Both ends of the support frame 601 are respectively slidably connected to the sliding frame 4. One end of the support frame 601 is connected to a circular body 602.

[0079] In this embodiment, the purpose of the above arrangement is to control the lifting and lowering of the support assembly 6 through the output end of the cylinder 5, so as to adjust the height of the aerospace shell 11, thereby adjusting the distance between the aerospace shell 11 and the impact assembly 7, and thus adjusting the vibration test.

[0080] As an implementation method, Figure 8 - Fig. 9 As shown, further:

[0081] A second motor 607 is installed on the outer wall of the circular body 602, and the output end of the second motor 607 passes through the circular body 602. A driving gear 603 is installed on the output end of the second motor 607. A driven gear 604 is rotatably connected to the center of the circular body 602, and the driving gear 603 and the driven gear 604 are meshed with each other.

[0082] Four sliders 606 are slidably connected to the circular body 602, an arc groove 605 is provided on the outer wall of the driven gear 604, and one end of the slider 606 extends to the inner side of the arc groove 605;

[0083] In this embodiment, the purpose of the above-mentioned setting is that the output end of the second motor 607 drives the driving gear 603 to rotate, and the driving gear 603 and the driven gear 604 are meshed with each other, driving the driven gear 604 to rotate, and the arc surface of the arc groove 605 on the driven gear 604 drives the slider 606, thereby controlling the four sliders 606 to move on the circular body 602. When the four sliders 606 move outward at the same time, the inner wall of the port of the aerospace shell 11 is supported, thereby fixing the aerospace shell 11.

[0084] As an implementation method, Figure 7 As shown, further:

[0085] A third motor 701 is installed at the bottom of the frame 1, and the output end of the third motor 701 passes through the frame 1 and extends to the top of the frame 1. A rotating disk 702 is installed on the output end of the third motor 701, and a plurality of ramp blocks 703 are installed on the upper surface of the rotating disk 702. U-shaped frames 704 are slidably connected at both ends of the bracket 104, and the bottom end of the U-shaped frame 704 moves on the upper surface of the ramp block 703. A convex block 705 is installed on the upper surface of the U-shaped frame 704.

[0086] In this embodiment, the purpose of the above arrangement is that the output end of the third motor 701 drives the rotating disk 702 and the ramp block 703 to rotate, and the ramp block 703 gradually lifts the U-shaped frame 704 and the protrusion 705, and the U-shaped frame 704 slides up and down on the bracket 104.

[0087] As an implementation method, Figure 4 As shown, further:

[0088] The pump air assembly 8 includes a long tube 801, which is mounted on the outer wall of the mobile frame 2, a sliding groove is provided at the bottom of the long tube 801, a telescopic tube 802 is installed inside the long tube 801, a spring 803 is installed inside the telescopic tube 802, and an air pipe 804 is connected to the outer wall of the telescopic tube 802;

[0089] In this embodiment, the purpose of the above arrangement is to move the annular sleeve 9 to squeeze the telescopic tube 802, and then the gas inside the telescopic tube 802 is discharged through the air pipe 804, and the spring 803 is used to reset the telescopic tube 802 to allow the telescopic tube 802 to be refilled with air.

[0090] As an implementation method, Figure 4 As shown, further:

[0091] The annular kit 9 ​​includes a sliding rod 901, the top of the sliding rod 901 passes through the sliding groove of the long tube 801 and is slidably connected to the inner wall of the long tube 801, the air pipe 804 is connected to the sliding rod 901, and the bottom of the sliding rod 901 is connected to the ring body 902, and a plurality of air holes 9020 are arranged on the inner wall of the ring body 902;

[0092] A moving block 903 is slidably connected to the inner wall of the ring body 902, and the micrometer 13 is installed on the moving block 903;

[0093] In this embodiment, the purpose of the above-mentioned setting is that the exhausted air is blown out through the air hole 9020 of the ring body 902, blown to the outer wall surface of the aerospace shell 11, and the dust on the outer wall surface of the aerospace shell 11 is blown off. The moving block 903 and the micrometer 13 are adjusted to test the flatness of the outer wall of the aerospace shell 11.

[0094] As an implementation method, Figure 5 As shown, further:

[0095] The moving block 903 is threadedly connected with a brush 12;

[0096] In this embodiment, the purpose of the above-mentioned setting is that when the moving block 903 and the micrometer 13 make circular motion on the ring body 902, the outer wall of the aerospace shell 11 is cleaned. A brush 12 is threadedly connected. During the movement, the outer wall of the aerospace shell 11 is first cleaned by the brush 12, thereby reducing the influence of dust on the surface of the aerospace shell 11 on the test of the micrometer 13. Example 2

[0097] As an implementation method, Fig.11 - Fig.12 As shown, further:

[0098] The outer walls of the plurality of sliders 606 are respectively provided with notches 6060 , and annular rubbers 14 are provided between the plurality of notches 6060 , and a tube 15 is provided on one of the circular bodies 602 ;

[0099] In this embodiment, the purpose of the above-mentioned setting is that after the inner wall of the port of the aerospace shell 11 is propped up by the slider 606, the set groove 6060 is used to install the annular rubber 14, and the outer wall of the annular rubber 14 is tightly fitted with the inner wall of the aerospace shell 11, and the inner wall of the annular rubber 14 is tightly fitted with the outer wall of the circular body 602, thereby closing the port of the aerospace shell 11 to form a cavity, wherein a tube body 15 is provided on one of the circular bodies 602, and the tube body 15 is connected to the cavity, and the tube body 15 is used to connect the air pump through a pipeline, and the air pump adopts the existing YN1680*2-50L model, and the air pump is used to evacuate or inflate the cavity, so that a pressurized or negative pressure state is formed inside the cavity, so that the aerospace shell 11 is subjected to vibration testing under pressurized and negative pressure states, thereby obtaining test results under different states.

[0100] Working principle: Place the aerospace shell 11 on the placement frame 103, adjust the sliding frame 4 and the support assembly 6 through the bidirectional screw 10, adjust the two support assemblies 6 to the two ends of the frame 1, and then adjust the mobile frame 2 to adjust the lifting assembly 3, drive the roller 302 to rotate through the output end of the first motor 301, and drive the gear 304 to rotate at the same time, the two gears 304 mesh with each other and rotate in opposite directions, and retract the cables 303 on the two rollers 302, so as to lift and lower the block 305 and the hook 306, and the hook 306 lifts the aerospace shell 11 through the lifting rope;

[0101] The sliding frame 4 and the support assembly 6 are adjusted by the bidirectional screw 10, and the two support assemblies 6 are adjusted to the two ports of the aerospace shell 11. The output end of the second motor 607 drives the driving gear 603 to rotate, and the driving gear 603 and the driven gear 604 are meshed with each other, driving the driven gear 604 to rotate. The arc surface of the arc groove 605 on the driven gear 604 drives the slider 606, thereby controlling the four sliders 606 to move on the circular body 602. When the four sliders 606 move outward at the same time, the inner wall of the port of the aerospace shell 11 is propped up, thereby fixing the aerospace shell 11;

[0102] The output end of the third motor 701 drives the rotating disk 702 and the ramp block 703 to rotate, and the ramp block 703 gradually lifts the U-shaped frame 704 and the protrusion 705, and the U-shaped frame 704 slides up and down on the bracket 104, and the protrusion 705 continuously touches the aerospace shell 11, so that the aerospace shell 11 itself vibrates, and the support assembly 6 is controlled to rise and fall through the output end of the cylinder 5, so as to adjust the height of the aerospace shell 11, thereby adjusting the distance between the aerospace shell 11 and the impact assembly 7, and thus adjusting the vibration test;

[0103] After the vibration ends, the sliding rod 901 is moved, and the top of the sliding rod 901 squeezes the telescopic tube 802, and then the gas inside the telescopic tube 802 is discharged through the air pipe 804. The spring 803 is used to reset the telescopic tube 802, so that the telescopic tube 802 is refilled with air, and the exhausted air is blown out through the air hole 9020 of the ring body 902, and blown to the outer wall surface of the aerospace shell 11, and the dust on the outer wall surface of the aerospace shell 11 is blown off. The moving block 903 and the micrometer 13 are adjusted to test the flatness of the outer wall of the aerospace shell 11;

[0104] When the moving block 903 and the micrometer 13 make a circular motion on the ring body 902, the outer wall of the aerospace shell 11 is cleaned. The brush 12 is threadedly connected. During the movement, the outer wall of the aerospace shell 11 is first cleaned by the brush 12, thereby reducing the influence of dust on the surface of the aerospace shell 11 on the test of the micrometer 13;

[0105] After the inner wall of the port of the aerospace shell 11 is propped up by the slider 606, the groove 6060 is set for installing the annular rubber 14, and the outer wall of the annular rubber 14 is tightly fitted with the inner wall of the aerospace shell 11, and the inner wall of the annular rubber 14 is tightly fitted with the outer wall of the circular body 602, thereby closing the port of the aerospace shell 11 to form a cavity, wherein a tube body 15 is provided on one of the circular bodies 602, and the tube body 15 is connected with the cavity, and the tube body 15 is used to connect the air pump through a pipeline, and the air pump adopts the existing YN1680*2-50L model, and the air pump is used to evacuate or inflate the cavity, so that a pressurized or negative pressure state is formed inside the cavity, so as to perform vibration test on the aerospace shell 11 under pressurized and negative pressure states, so as to obtain test results under different states.

[0106] The preferred embodiments of the present invention disclosed above are only used to help explain the present invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to the specific implementation methods described. Obviously, many modifications and changes can be made according to the content of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well. The present invention is limited only by the claims and their full scope and equivalents.

Claims

1. A vibration test fixture for aerospace equipment, comprising a frame (1), a mobile frame (2) and a lifting assembly (3), characterized in that: The frame (1) is provided with a plurality of first slide grooves (101), a plurality of second slide grooves (102), a plurality of placement racks (103) and a bracket (104); The movable frame (2) is slidably connected to the two second slide grooves (102), and the lifting assembly (3) is installed on the top of the movable frame (2); The two first sliding grooves (101) are respectively slidably connected to sliding frames (4), the two sliding frames (4) are respectively located at two ends of the vehicle frame (1), and a bidirectional screw rod (10) is connected between the two sliding frames (4); A cylinder (5) is mounted on the sliding frame (4), and the tops of the two sliding frames (4) are respectively slidably connected to support assemblies (6), and the output end of the cylinder (5) is connected to the support assemblies (6); A striking assembly (7) is installed in the middle of the frame (1); A plurality of the placement racks (103) are provided with aerospace shells (11); A pump assembly (8) is installed on the top outer wall of the mobile frame (2), an annular sleeve (9) is connected to the pump assembly (8), and a brush (12) and a micrometer (13) are installed on the annular sleeve (9); The lifting assembly (3) comprises a first motor (301) and a roller (302), wherein the first motor (301) is mounted on the outer wall of the moving frame (2), and the two rollers (302) are rotatably connected to the top of the moving frame (2), respectively, and the output end of the first motor (301) is connected to one of the rollers (302); The two rollers (302) are respectively connected to a gear (304), and the two gears (304) are meshed with each other; The outer walls of the two rollers (302) are respectively connected with cables (303), the bottom ends of the two cables (303) are connected with blocks (305), and the bottom of the blocks (305) is rotatably connected with hooks (306); The pump air assembly (8) comprises a long tube (801), the long tube (801) is mounted on the outer wall of the mobile frame (2), a sliding groove is provided at the bottom of the long tube (801), a telescopic tube (802) is installed inside the long tube (801), a spring (803) is installed inside the telescopic tube (802), and an air pipe (804) is connected to the outer wall of the telescopic tube (802); The annular kit (9) comprises a sliding rod (901), the top of the sliding rod (901) is slidably connected to the inner wall of the long tube (801) through a sliding groove of the long tube (801), the air pipe (804) is connected to the sliding rod (901), the bottom of the sliding rod (901) is connected to a ring body (902), and a plurality of air holes (9020) are provided on the inner wall of the ring body (902); A moving block (903) is slidably connected to the inner wall of the ring body (902), and the micrometer (13) is mounted on the moving block (903).

2. The vibration test fixture for aerospace equipment according to claim 1, characterized in that: The bidirectional screw (10) is provided with two threads, the two threads are symmetrical on the outer wall of the bidirectional screw (10), and the bidirectional screw (10) is respectively threadedly connected to the sliding frame (4).

3. The vibration test fixture for aerospace equipment according to claim 2, characterized in that: The support assembly (6) comprises a support frame (601), the output end of the cylinder (5) passes through the top of the sliding frame (4) and extends to the top of the sliding frame (4), the lower surface of the support frame (601) is connected to the output end of the cylinder (5), the two ends of the support frame (601) are respectively slidably connected to the sliding frame (4), and one end of the support frame (601) is connected to a circular body (602).

4. The vibration test fixture for aerospace equipment according to claim 3, characterized in that: A second motor (607) is mounted on the outer wall of the circular body (602); the output end of the second motor (607) passes through the circular body (602); a driving gear (603) is mounted on the output end of the second motor (607); a driven gear (604) is rotatably connected to the center of the circular body (602); the driving gear (603) and the driven gear (604) are meshed with each other; Four sliding blocks (606) are slidably connected to the circular body (602), an arc-shaped groove (605) is provided on the outer wall of the driven gear (604), and one end of the sliding block (606) extends to the inner side of the arc-shaped groove (605).

5. The vibration test fixture for aerospace equipment according to claim 4, characterized in that: A third motor (701) is installed at the bottom of the vehicle frame (1); an output end of the third motor (701) passes through the vehicle frame (1) and extends to the top of the vehicle frame (1); a rotating disk (702) is installed on the output end of the third motor (701); a plurality of inclined blocks (703) are installed on the upper surface of the rotating disk (702); U-shaped frames (704) are slidably connected at both ends of the bracket (104); the bottom end of the U-shaped frame (704) moves on the upper surface of the inclined block (703); and a convex block (705) is installed on the upper surface of the U-shaped frame (704).

6. The vibration test fixture for aerospace equipment according to claim 5, characterized in that: A brush (12) is threadedly connected to the moving block (903).

7. The vibration test fixture for aerospace equipment according to claim 6, characterized in that: Notches (6060) are respectively arranged on the outer walls of the plurality of sliding blocks (606), annular rubbers (14) are arranged between the plurality of notches (6060), and a tube body (15) is arranged on one of the circular bodies (602).

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