Aerospace cable vibration test tool

Abstract

The utility model provides a spaceflight cable vibration test tool, comprising an electric test bench and a suspension bracket, the electric test bench is provided with a bench surface, the bench surface is fixedly provided with a clamping assembly, the clamping assembly fixes an insertion block on the bench surface, the insertion block is provided with a cable insertion port, and the cable insertion port is provided with a cable insertion hole. And the cable plugging port on the plugging block is connected with one end of a spaceflight cable. Compared with the prior art, the beneficial effects of the utility model are that one end of a spaceflight cable is plugged through the cable plugging port on the plugging block, and the other end of the spaceflight cable passes through the suspension bracket and is pressed by the auxiliary clamping assembly, that is, the pressing of the other end of the spaceflight cable is completed through the pressing plate and the first rubber pad layer at the bottom of the pressing plate; the spaceflight cable suspension device ensures that the spaceflight cables are kept in a stable suspension state, prevents the suspended spaceflight cables from falling off to affect the vibration test of the spaceflight cables, avoids contact friction between the spaceflight cables, and plays a certain role in protecting the spaceflight cables.

Description

Technical Field

[0001] This utility model is a vibration testing fixture for aerospace cables, belonging to the field of cable testing. Background Technology

[0002] Vibration testing has become an important means of verifying the reliability of aerospace, aviation, shipbuilding, and ground-based military and civilian equipment. It is mainly used to verify the adaptability of the entire equipment and its components under expected or specified vibration conditions, and to assess whether the equipment can operate normally and meet usage requirements under vibration conditions. Aerospace cable vibration testing is primarily conducted on an electromagnetic vibration table. Its working principle involves the interaction between a constant magnetic field and a coil carrying a certain alternating current within the magnetic field, thereby generating a specific excitation force. During vibration testing, accelerometers are typically attached to the product and tooling, and connected to a controller via communication cables. The controller corrects the output waveform based on the collected feedback signals, ultimately achieving closed-loop control.

[0003] In existing technologies, when conducting vibration tests on aerospace cables, the aerospace cables are typically coiled and mounted on a fixture, which is then connected to a vibration table to complete the test. Since aerospace cables are inherently soft, the pulling and friction during vibration testing may damage the surface coating and connectors. Therefore, this application proposes a suspended cable type aerospace cable vibration test fixture to avoid the damage to the cable coating and connectors caused by the traditional method of coiling the cable on the fixture during vibration testing. Utility Model Content

[0004] In view of the shortcomings of the existing technology, the purpose of this utility model is to provide a vibration testing fixture for aerospace cables.

[0005] To achieve the above objectives, this utility model is implemented through the following technical solution:

[0006] A vibration testing fixture for aerospace cables includes an electric test bench and a suspension frame. The electric test bench has a table surface, on which a clamping assembly is fixedly mounted. The clamping assembly fixes a connector block to the table surface. The connector block has a cable connector that connects to one end of an aerospace cable. The other end of the aerospace cable passes through the suspension frame. The suspension frame has an auxiliary clamping assembly that clamps the other end of the aerospace cable. The number of auxiliary clamping assemblies is even, with two auxiliary clamping assemblies forming a group corresponding to the connector block. Each auxiliary clamping assembly includes a pressure plate, and a soft rubber pad is fixedly mounted on the bottom end of the pressure plate.

[0007] Furthermore, the secondary clamping assembly also includes a U-shaped frame fixed on the suspension frame, with multiple through rods passing through the U-shaped frame. The pressure plate is fixed at the bottom end of each through rod, and a number of reset members equal to the number of through rods are provided between the top end of the pressure plate and the inner top end of the U-shaped frame.

[0008] Furthermore, the reset element is a spring, which is sleeved on the outside of the corresponding through rod, and a handle plate is fixedly provided at the top of the through rod.

[0009] Furthermore, vertical grooves are provided on both inner sides of the U-shaped frame, and sliders extending into the vertical grooves are fixed on both end side walls of the pressure plate.

[0010] Furthermore, the suspension frame is fixedly equipped with multiple through-tubes through which the aerospace cables pass.

[0011] Furthermore, there are multiple clamping components, each corresponding to a connector block. Each clamping component includes two vertical plates fixed on the table surface, with a double-axis lead screw passing through between the vertical plates. Both ends of the double-axis lead screw are threaded with threaded plates, and the inner surface of the threaded plates is provided with a soft rubber pad layer.

[0012] Furthermore, a manual turntable is fixedly provided at one end of the dual-axis lead screw, and the manual turntable is in contact with the outer side of one of the vertical plates. A bearing is sleeved at the other end of the dual-axis lead screw, and the bearing is fixed to the outer side of the other vertical plate.

[0013] Furthermore, a traction rod is fixed between the vertical plates, penetrating the threaded plate, and a dust cover is installed on the table surface via metal hinges.

[0014] The beneficial effects of this utility model are:

[0015] The connector blocks are fixed to the table surface by the clamping components, thus completing the fixation of connector blocks of different specifications for vibration testing of cables of different specifications. At the same time, the connector blocks are easy to install and disassemble, making it convenient to replace aging or damaged connector blocks.

[0016] One end of the aerospace cable is plugged into the cable connector on the connector block, and the other end of the aerospace cable passes through the suspension frame and is clamped by the secondary clamping assembly. That is, the clamping of the other end of the aerospace cable is completed by the pressure plate and the rubber pad layer at its bottom, which ensures that the aerospace cable remains in a stable suspended state, prevents the suspended aerospace cable from falling and affecting the vibration test of the aerospace cable, and avoids contact and friction between the aerospace cables, thus playing a certain protective role for the aerospace cable. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This application shows a front view of a vibration testing fixture for aerospace cables.

[0019] Figure 2 A schematic diagram of the clamping assembly of a vibration testing fixture for aerospace cables according to this application is shown;

[0020] Figure 3 A schematic diagram of the secondary clamping assembly of a vibration testing fixture for aerospace cables according to this application is shown;

[0021] Figure 4 A schematic diagram of the dust cover of a vibration testing fixture for aerospace cables according to this application is shown.

[0022] In the diagram: 1. Electric test bench; 2. Suspension frame; 3. Tabletop; 4. Connector block; 5. Cable connector; 6. Aerospace cable; 7. U-shaped frame; 8. Through rod; 9. Pressure plate; 10. Handle plate; 11. Vertical slide groove; 12. Rubber pad layer one; 13. Through cylinder; 14. Vertical plate; 15. Double-axis lead screw; 16. Threaded plate; 17. Rubber pad layer two; 18. Manual turntable; 19. Bearing; 20. Traction rod; 21. Spring; 22. Dust cover. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0024] Please see Figure 1-4This utility model provides a technical solution: a vibration testing fixture for aerospace cables, including an electric test bench 1 and a suspension frame 2. The electric test bench 1 has a table surface 3, and a clamping assembly is fixedly provided on the table surface 3. The clamping assembly fixes a connector block 4 on the table surface 3. The connector block 4 is provided with a cable connector 5. The cable connector 5 on the connector block 4 connects to one end of an aerospace cable 6. The other end of the aerospace cable 6 passes through the suspension frame 2, and the suspension frame 2 is provided with a secondary clamping assembly for clamping the other end of the aerospace cable 6. The number of secondary clamping assemblies is even, and every two secondary clamping assemblies form a group, corresponding to the connector block 4. The secondary clamping assembly includes a pressure plate 9, and a soft rubber pad layer 12 is fixedly provided at the bottom end of the pressure plate 9.

[0025] See Figure 1-2 The auxiliary clamping assembly also includes a U-shaped frame 7 fixed to the suspension frame 2. Multiple through rods 8 are threaded through the U-shaped frame 7. A pressure plate 9 is fixed to the bottom end of each through rod 8. A number of reset members, equal in number to the through rods 8, are provided between the top end of the pressure plate 9 and the inner top end of the U-shaped frame 7. Each reset member is a spring 21, sleeved on the outer side of the corresponding through rod 8. A handle plate 10 is fixed to the top end of each through rod 8. Vertical sliding grooves 11 are provided on both inner sides of the U-shaped frame 7. The pressure plate... Both ends of the 9 are fixed with sliders extending into the vertical groove 11. The suspension frame 2 is fixed with multiple through tubes 13 for the aerospace cable 6 to pass through. The operator can lift the lifting handle 10 to drive the connected through rod 8 to rise, thus driving the pressure plate 9 to rise. During the rise of the pressure plate 9, the spring 21 is compressed. Subsequently, the spring 21 returns to its original position and extends, driving the pressure plate 9 to press down on the end of the cable, thus fixing the other end of the cable and ensuring the suspension stability of the cable to improve the test efficiency.

[0026] See Figure 1 , Figure 3 and Figure 4The clamping assemblies are numerous and correspond one-to-one with the connector blocks 4. Each clamping assembly includes two vertical plates 14 fixed on the table surface 3. A double-axis lead screw 15 passes between the vertical plates 14. Both ends of the double-axis lead screw 15 are threaded with threaded plates 16. The inner surface of the threaded plates 16 is provided with a soft rubber pad layer 17. A manual turntable 18 is fixed to one end of the double-axis lead screw 15. The manual turntable 18 is in contact with the outer surface of one of the vertical plates 14. A bearing 19 is sleeved on the other end of the double-axis lead screw 15. The bearing 19 is fixed... On the outer side of another vertical plate 14, a traction rod 20 is fixed between the vertical plates 14, passing through the threaded plate 16. A dust cover 22 is installed on the table surface 3 via metal hinges. The operator can manually rotate the manual turntable 18 to rotate the double-axis lead screw 15, thus causing the two threaded plates 16 to move relative to each other. Therefore, the threaded plates 16 cooperate with the inner rubber pad layer 17 to clamp the mating block 4, making disassembly convenient and avoiding the need for screw installation, which would otherwise require tools to complete the disassembly. The dust cover covers the table surface, and the table surface is kept dust-free when the equipment is not in use.

[0027] In practice, the connector block 4 is fixed to the table surface 3 using the clamping components, thus fixing connector blocks 4 of different specifications for vibration testing of cables of different specifications. The connector block 4 is easy to install and disassemble, facilitating the replacement of aged or damaged connector blocks 4. One end of the aerospace cable 6 is plugged into the cable connector 5 on the connector block 4, and the other end of the aerospace cable 6 passes through the suspension frame 2 and is pressed down by the auxiliary clamping components. Specifically, the pressure plate 9 and its bottom rubber pad 12 press down the other end of the aerospace cable 6, ensuring the aerospace cable 6 remains in a stable suspended state and preventing it from falling and affecting the vibration test. This also prevents the aerospace cables 6 from contacting and rubbing against each other, providing a certain degree of protection for the aerospace cable 6.

[0028] Although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A spaceflight cable vibration test tool, characterized by: Including electric test bench (1) and suspension frame (2), the electric test bench (1) has table top (3) on it, the table top (3) is fixed with clamping assembly, the clamping assembly is fixed on the table top (3) with connector block (4), the connector block (4) is provided with cable connector (5), the cable connector (5) on the connector block (4) is connected with one end of aerospace cable (6), the other end of the aerospace cable (6) passes through the suspension frame (2), and the suspension frame (2) is provided with vice clamping assembly for clamping the other end of the aerospace cable (6), the number of the vice clamping assembly is double, every two vice clamping assemblies are a group, and correspond to the connector block (4), the vice clamping assembly includes pressing plate (9), the bottom end of the pressing plate (9) is fixed with soft rubber pad (12).

2. The space cable vibration test fixture of claim 1, wherein: The vice clamping assembly further includes U-shaped frame (7) fixed on the suspension frame (2), a plurality of through rods (8) are provided on the U-shaped frame (7), the bottom end of the through rod (8) is fixed with the pressing plate (9), and the top end of the pressing plate (9) and the inner top end of the U-shaped frame (7) are provided with reset members equal to the number of the through rod (8).

3. The space cable vibration test fixture of claim 2, wherein: The reset member is a spring (21), the spring (21) is sleeved on the outer side of the corresponding through rod (8), and the top end of the through rod (8) is fixed with a handle plate (10).

4. The space cable vibration test fixture of claim 3, wherein: The inner two sides of the U-shaped frame (7) are provided with vertical sliding grooves (11), and the two end side walls of the pressing plate (9) are fixed with sliding blocks extending into the vertical sliding grooves (11).

5. The space cable vibration test fixture of claim 4, wherein: A plurality of through cylinders (13) for the aerospace cable (6) to pass through are fixed on the suspension frame (2).

6. The space cable vibration test fixture of claim 5, wherein: The number of the clamping assembly is multiple, and it corresponds to the connector block (4) one by one, the clamping assembly includes two vertical plates (14) fixed on the table top (3), a double-shaft screw rod (15) is provided between the vertical plates (14), both ends of the double-shaft screw rod (15) are threadedly provided with threaded plates (16), and the inner side of the threaded plate (16) is provided with soft rubber pad (17).

7. The space cable vibration test fixture of claim 6, wherein: One end of the double-shaft screw rod (15) is fixed with a manual rotary disc (18), the manual rotary disc (18) is arranged in contact with the outer side of one of the vertical plates (14), the other end of the double-shaft screw rod (15) is sleeved with a bearing (19), and the bearing (19) is fixed on the outer side of the other vertical plate (14).

8. The space cable vibration test fixture of claim 7, wherein: The vertical plates (14) are fixed with a traction rod (20) penetrating through the threaded plates (16), and a dust cover (22) is installed on the table top (3) through a metal hinge.

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