Device and method for testing characteristic parameters of a vibration damper in an airborne optoelectronic device vibration damping system

Abstract

The application discloses a kind of testing device and method for the characteristic parameters of vibration damper in airborne optoelectronic equipment damping system.The testing method comprises the following steps: connecting test base with vibration table;Connecting support with test base and vibration damper connector;Connecting vibration damper connector with support and the pair of vibration damper to be tested;Connecting load simulation with the pair of vibration damper to be tested;Installing the pair of vibration damper to be tested with testing device and fixing to vibration table;Fixing acceleration sensor;Performing broadband harmonic response acceleration sweep excitation;Obtaining natural resonant frequency and amplification of the pair of vibration damper;Solving axial stiffness, lateral stiffness and damping equation of the pair of vibration damper to be tested;Replacing the pair of vibration damper and repeating solving;Simultaneously solving axial stiffness, lateral stiffness and damping of single vibration damper.The method has good effect on testing characteristic parameters of vibration damper, strong practicability, and is worth promoting.

Description

Device and Method for Testing Vibration Damper Characteristic Parameters in Airborne Optoelectronic Equipment Vibration Reduction Systems Technical Field

[0001] This invention belongs to the field of vibration damper technology, and relates to a device and method for testing the characteristic parameters of vibration dampers in an airborne optoelectronic equipment vibration damping system. In particular, it uses a three-dimensional layout vibration damping unit in airborne optoelectronic equipment such as aviation optoelectronics to reduce disturbances acting on the mission sensors or the entire equipment, thereby realizing the mission functions and performance of the equipment system. Background Technology

[0002] Airborne optoelectronic equipment, such as optoelectronic devices, installed on aviation platforms needs to perform its mission functions and performance while withstanding dynamic loads such as three-dimensional vibration and impact in space. This is typically achieved using planar or spatially arranged vibration damping units to reduce disturbances to the mission sensors or the entire equipment. Consequently, there are specific requirements for the characteristic parameters and consistency of the vibration dampers within these units. Before the vibration dampers are developed and installed, their characteristic parameters and consistency must be tested and accepted. Given the three-dimensional layout characteristics of aviation equipment, the vibration dampers within the unit must be tested for their dynamic axial linear stiffness, lateral linear stiffness, lateral torsional stiffness, structural damping, and deviations in the characteristic parameters of each damper. Summary of the Invention

[0003] (a) Purpose of the invention

[0004] The purpose of this invention is to provide a testing device and method for the characteristic parameters of vibration dampers in airborne optoelectronic equipment vibration reduction systems.

[0005] (II) Technical Solution

[0006] To address the aforementioned technical problems, this invention provides a testing device for the characteristic parameters of vibration dampers in airborne optoelectronic equipment vibration reduction systems. The testing device is mounted on a vibration table 1 and includes a frame 2, a vibration damper connector 3, a vibration damper under test 4, a load connector 5, a load 6, a slider 7, a baffle 8, and a circular block 9. The frame 2 serves as the testing base, and the slider 7 serves as the support. The vibration table 1 is kept horizontal. The frame 2 is a cuboid frame. On its six faces, the bottom surface connecting to the vibration table 1 is not provided with a rectangular groove. The bottom surface of the frame 2 is horizontally fitted to the table surface of the vibration table 1 and fixed with countersunk bolts. The top, front, back, left, and right sides of the frame 2 each have a rectangular groove. The rectangular grooves on the left and right sides of the frame 2 form sliding grooves between the bottom and top surfaces. Slider 7 is installed in each of these two sliding grooves. The slider 7 is a cuboid slider with rounded corners. Circular grooves are provided on the outer surfaces of both sliders 7, and circular blocks 9 are installed in these grooves. A threaded hole is opened in the center, and a connecting rod is installed in the threaded hole; rectangular baffles 8 are respectively set on the left and right outer sides of the frame 2, and the outer end of the connecting rod passes through the baffle 8 through the threaded connection. The baffle 8 blocks the slider 7; when the left and right sides of the frame 2 are closed, the baffle 8 and the frame 2 are aligned and fixedly installed according to the hole position; two damper connectors 3 are respectively connected to the corresponding sliders 7 by countersunk screws; the interface between the damper connector 3 and the damper under test 4 is a replaceable interface. When the damper connector 3 is connected to the damper under test 4, the corresponding hole position is selected and fixed with screws; the load connector 5 is a cuboid column structure with a threaded hole on one end. The damper under test 4 and the load connector 5 are fixedly connected by screws according to the hole alignment; the other end of the load connector 5 is connected to the load 6. The load 6 is placed on the load connector 5 and fixed to the load connector 5 with screws. There are threaded holes on the load surface, and counterweights can be installed according to the actual load size.

[0007] An axial stiffness / damping test is performed by fixing an acceleration sensor along the rotational axis of the damper pair under test on load 6; a lateral stiffness / damping test is performed by fixing an acceleration sensor along the lateral axis of the damper pair under test on load 6.

[0008] Based on the above-mentioned testing device, the present invention also provides a method for testing the characteristic parameters of a vibration damper in an airborne optoelectronic equipment vibration reduction system, the process of which is as follows:

[0009] First, install the testing equipment, then fix the acceleration sensor, and begin testing the first pair of shock absorbers to be tested.

[0010] During the axial stiffness / damping test of the first pair of vibration dampers under test, an acceleration sensor was fixed on the load 6 along the rotational axis of the first pair of vibration dampers under test; during the lateral stiffness test of the first pair of vibration dampers under test, an acceleration sensor was fixed on the load 6 along the lateral axis of the first pair of vibration dampers under test; then, a broadband harmonic response acceleration sweep frequency excitation was performed on the vibration table 1 and the testing device to obtain the amplitude-frequency response curve, and then the circular frequency and amplification of the first pair of vibration dampers under test were obtained.

[0011] The lateral and axial stiffness of the first set of dampers under test can be obtained by inverse solving Equation 1.

[0012] (1)

[0013] Where ω is the angular frequency, K is the stiffness, and m is the mass.

[0014] The damping of the first pair of dampers under test can be obtained by inverse solution of Formula 2.

[0015] (2)

[0016] Where λ is the magnification, ω is the angular frequency, and m is the mass. For damping.

[0017] The first pair of vibration dampers under test, which has already been tested, is disassembled and replaced with the second pair. An acceleration sensor is installed according to the testing method of the first pair of vibration dampers under test. A broadband harmonic response acceleration sweep frequency excitation is performed on the vibration table 1 to obtain the amplitude-frequency response curve and the circular frequency and amplification of the second pair of vibration dampers under test. The lateral stiffness, axial stiffness and damping of the second pair of vibration dampers are then calculated using formulas 1 and 2.

[0018] Repeatedly replace the vibration damper pairs under test, and test all the vibration dampers in pairs to obtain the axial stiffness, lateral stiffness and damping of multiple sets of vibration damper pairs under test.

[0019] By combining the above equations, we obtain a set of equations for the axial stiffness, lateral stiffness, and damping of each tested vibration damper. Solving the set of equations yields the axial stiffness, lateral stiffness, and damping of a single vibration damper.

[0020] Assuming there are n vibration dampers under test, and all vibration dampers are tested in pairs, at least n combinations are required to solve for the parameters of each vibration damper. The lateral stiffness of a single vibration damper under test is defined as k1, k2, ..., k n Axial stiffness is defined as , ... Damping is defined as c1, c2...c nThe lateral stiffness of the n pairs of vibration dampers under test, after being combined in pairs, is defined as K1, K2...K. n Axial stiffness is defined as , ... Damping is defined as , ... .

[0021] The lateral stiffness equation set 3, the axial stiffness equation set 4, and the damping equation set 5 are established as follows:

[0022] (3)

[0023] (4)

[0024] (5)

[0025] The lateral stiffness k1, k2...k of n individual vibration dampers can be obtained by solving the problem. n axial stiffness , ... and damping c1, c2...c n .

[0026] (III) Beneficial Effects

[0027] The device and method for testing the characteristic parameters of vibration dampers in the airborne optoelectronic equipment vibration reduction system provided by the above technical solution have the following advantages:

[0028] 1. The test of characteristic parameters such as axial stiffness, lateral stiffness and damping of vibration dampers was realized, which has positive supporting significance for the verification of characteristic parameters and assembly matching of vibration dampers developed and procured.

[0029] 2. The vibration damper testing device and method proposed in this invention have the advantages of strong versatility and ease of operation. They can be applied to the characteristic inspection and procurement acceptance of vibration dampers used in various precision airborne optoelectronic equipment and other industry equipment products, meet the requirements of accurate application of vibration damper components in equipment systems, ensure the full realization of the performance of equipment vibration damping systems, and generate good technical effects and economic benefits. Attached Figure Description

[0030] Figure 1. Flowchart of the test device installation and testing method;

[0031] Figure 2. Schematic diagram of the testing device;

[0032] Figure 3. Schematic diagram of the test device;

[0033] Figure 4. Schematic diagram of axial stiffness test;

[0034] Figure 5. Schematic diagram of lateral stiffness test. Detailed Implementation

[0035] To make the objectives, contents, and advantages of the present invention clearer, the specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples.

[0036] As shown in Figures 1 and 2, in this embodiment, the vibration damper characteristic parameter testing device for the vibration reduction system of airborne optoelectronic equipment is installed on a vibration table 1. The testing device includes a frame 2, a vibration damper connector 3, a vibration damper under test 4, a load connector 5, a load 6, a slider 7, a baffle 8, and a circular block 9. The frame 2 serves as the test base, and the slider 7 serves as the support. The vibration table 1 is kept horizontal. The frame 2 is a cuboid frame. On the six faces of the frame 2, the bottom surface connecting to the vibration table 1 is not provided with rectangular grooves. The bottom surface of the frame 2 is horizontally attached to the table surface of the vibration table 1 and fixed with countersunk bolts. The top, front, back, left, and right sides of frame 2 have five rectangular slots. The rectangular slots on the left and right sides of frame 2 form sliding grooves between the bottom and top surfaces. Slider 7 is installed in each of these two sliding grooves. Slider 7 is a cuboid slider with rounded corners on all four sides. Circular grooves are formed on the outer surfaces of both sliders 7. Circular blocks 9 are installed in the grooves. A threaded hole is formed in the center of each circular block 9, and a connecting rod is installed in the threaded hole. Rectangular baffles 8 are set on the left and right outer sides of frame 2. The outer end of the connecting rod passes through the baffles 8 through a threaded connection, and the baffles 8 hold the sliders 7 in place. The frame 2 is then rotated left and right. When the part is closed, the baffle 8 and frame 2 are aligned and fixed according to the hole positions; the two damper connectors 3 are respectively connected to the corresponding sliders 7 by screws. In order to prevent the screw heads from affecting the installation of the damper, countersunk screws are used. After aligning the holes, the screws are tightened with a screwdriver. It is necessary to ensure that the surface of the screw head is on the same plane as or lower than the surface of the damper connector; the interface between the damper connector 3 and the damper 4 under test is a replaceable interface. When connecting the damper connector 3 and the damper 4 under test, the corresponding hole positions are selected according to the actual size of the damper. The load is fixedly connected with screws. The load connector 5 is a cuboid column structure with a threaded hole on one end. The damper under test 4 and the load connector 5 are fixedly connected with screws by aligning the holes. The other end of the load connector 5 is connected to the load 6. The load 6 rests on the load connector 5. The load 6 and the load connector 5 are fixed with screws. The load simulation component has specific structural quality characteristics. It should be installed with the load 6 on top and the load connector 5 on the bottom to prevent the screws from bearing too much tension. There are threaded holes on the load surface, and counterweights can be installed according to the actual load size.

[0037] As shown in Figures 1 and 3, the testing method in this embodiment includes the following steps:

[0038] S1. After installing the test device, fix the test device and the vibration damper assembly to be tested onto the vibration table, fix the acceleration sensor, fix the acceleration sensor on the load simulation part along the rotation axis of the vibration damper during the axial stiffness / damping test of the vibration damper, fix the acceleration sensor on the load simulation part along the side of the vibration damper during the lateral stiffness / damping test of the vibration damper assembly.

[0039] In this step, the assembly results are installed with the vibration damper to be tested and the test device and fixed to the vibration table. Two vibration dampers are symmetrically installed in the test device and symmetrically combined with the load respectively to eliminate the influence of torsional stiffness caused by rotational inertia on the measurement results. Then the test device and the vibration damper to be tested are assembled and fixed to the vibration table.

[0040] S2. Based on the assembly results in step S1, perform wideband harmonic response acceleration sweep frequency excitation on the measuring device;

[0041] S3. Based on the data acquisition results in step S2, obtain the inherent resonant frequency and amplification of the vibration damper pair;

[0042] S4. Based on the results in step S3, obtain the axial stiffness, lateral stiffness, and damping equations of the damper pair to be tested using the resonant frequency and transmissivity formulas.

[0043] S5. Replace the damper pairs and test all the dampers to be tested in pairs. Repeat steps S2-S4 to obtain the axial stiffness, lateral stiffness and damping equations of multiple sets of reducer pairs.

[0044] S6. By combining the equations in step S5, we obtain the axial stiffness, lateral stiffness, and damping equations for each tested reducer. Solving the equations yields the axial stiffness, lateral stiffness, and damping of a single reducer.

[0045] The specific implementation process of the above testing method is as follows:

[0046] First, install the testing equipment, then fix the acceleration sensor, and begin testing the first pair of shock absorbers to be tested.

[0047] During the axial stiffness / damping test of the first pair of vibration dampers under test, an acceleration sensor was fixed on the load 6 along the rotational axis of the first pair of vibration dampers under test; during the lateral stiffness / damping test of the first pair of vibration dampers under test, an acceleration sensor was fixed on the load 6 along the lateral axis of the first pair of vibration dampers under test; then, a broadband harmonic response acceleration sweep frequency excitation was performed on the vibration table 1 and the testing device to obtain the amplitude-frequency response curve, and then the circular frequency and amplification of the first pair of vibration dampers under test were obtained.

[0048] The lateral and axial stiffness of the first set of dampers under test can be obtained by inverse solving Equation 1.

[0049] (1)

[0050] Where ω is the angular frequency, K is the stiffness, and m is the mass.

[0051] The damping of the first pair of dampers under test can be obtained by inverse solution of Formula 2.

[0052] (2)

[0053] Where λ is the magnification, ω is the angular frequency, and m is the mass. For damping.

[0054] The first pair of vibration dampers under test, which has already been tested, is disassembled and replaced with the second pair. An acceleration sensor is installed according to the testing method of the first pair of vibration dampers under test. A broadband harmonic response acceleration sweep frequency excitation is performed on the vibration table 1 to obtain the amplitude-frequency response curve and the circular frequency and amplification of the second pair of vibration dampers under test. The lateral stiffness, axial stiffness and damping of the second pair of vibration dampers are then calculated using formulas 1 and 2.

[0055] Repeatedly replace the vibration damper pairs under test, and test all the vibration dampers in pairs to obtain the axial stiffness, lateral stiffness and damping of multiple sets of vibration damper pairs under test.

[0056] By combining the above equations, we obtain a set of equations for the axial stiffness, lateral stiffness, and damping of each tested vibration damper. Solving the set of equations yields the axial stiffness, lateral stiffness, and damping of a single vibration damper.

[0057] Assuming there are n vibration dampers under test, and all vibration dampers are tested in pairs, at least n combinations are required to solve for the parameters of each vibration damper. The lateral stiffness of a single vibration damper under test is defined as k1, k2, ..., k n Axial stiffness is defined as , ... Damping is defined as c1, c2...c n The lateral stiffness of the n pairs of vibration dampers under test, after being combined in pairs, is defined as K1, K2...K. n Axial stiffness is defined as , ... Damping is defined as , ... .

[0058] The lateral stiffness equation set 3, the axial stiffness equation set 4, and the damping equation set 5 are established as follows:

[0059] (3)

[0060] (4)

[0061] (5)

[0062] The lateral stiffness k1, k2...k of n individual vibration dampers can be obtained by solving the problem. n axial stiffness , ... and damping c1, c2...c n .

[0063] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method for testing the characteristic parameters of a vibration damper in an airborne optoelectronic equipment vibration reduction system, characterized in that, The process includes the following steps: S1. Install the test device and fix the test device and the damper to be tested onto the vibration table. The test device includes a frame (2), a damper connector (3), the damper to be tested (4), a load connector (5), a load (6), a slider (7), a baffle (8), and a round block (9). The frame (2) is installed on the vibration table (1). The rectangular grooves on the left and right sides of the frame (2) form a sliding groove between the bottom and top surfaces. The sliders (7) are installed in the two sliding grooves respectively. The outer surfaces of the two sliders (7) are all A circular groove is provided, and a circular block (9) is installed in the groove. A threaded hole is provided in the center of the circular block (9), and a connecting rod is installed in the threaded hole. Rectangular baffles (8) are provided on the left and right outer sides of the frame (2). The outer end of the connecting rod passes through the baffle (8) by a threaded connection. The baffle (8) blocks the slider (7). Two damper connectors (3) are connected to the corresponding sliders (7) by screws. The interface between the damper connector (3) and the damper under test (4) is a replaceable interface. The damper connector (3) and the damper under test (4) are connected by screws. The load connector (5) is a rectangular column structure with a threaded hole on one end. The damper under test (4) and the load connector (5) are fixedly connected by screws through hole alignment. The other end of the load connector (5) is connected to the load (6), which rests on the load connector (5). The load (6) and the load connector (5) are fixed by screws. An acceleration sensor is fixed on the load (6) along the rotation axis of the damper under test for axial stiffness / damping testing. An acceleration sensor is fixed on the load (6) along the rotation axis of the damper under test for axial stiffness / damping testing. Lateral fixed acceleration sensors are used to perform lateral stiffness / damping tests on the damper pair; For axial stiffness / damping tests, acceleration sensors are fixed along the rotational axis of the damper on the load; for lateral stiffness / damping tests, acceleration sensors are fixed along the side of the damper on the load; S2, based on the assembly results in step S1, a wideband harmonic response acceleration sweep frequency excitation is performed on the measuring device; S3, based on the data acquisition results in step S2, the natural resonant frequency and amplification of the damper pair are obtained; S4. Based on the results in step S3, obtain the axial stiffness, lateral stiffness, and damping equations of the damper pair under test using the resonant frequency and transmissivity formulas; S5. Replace the damper pair, and test all dampers under test in pairs, repeating steps S2-S4 to obtain the axial stiffness, lateral stiffness, and damping equations of multiple reducer pairs; S6. Combine the equations from step S5 to obtain the axial stiffness, lateral stiffness, and damping equations for each reducer under test, and solve the equations to obtain the axial stiffness, lateral stiffness, and damping of a single reducer; In step S6, assuming the number of dampers under test is n, test all dampers under test in pairs. To obtain the parameters of each damper under test, at least n combinations are required; the lateral stiffness of a single damper under test is defined as k1, k2...k n Axial stiffness is defined as 、 …… Damping is defined as c1, c2...c n The lateral stiffness of the n pairs of vibration dampers under test, after being combined in pairs, is defined as K1, K2...K. n Axial stiffness is defined as 、 …… Damping is defined as 、 、…… The lateral stiffness equations (3), axial stiffness equations (4), and damping equations (5) are established as follows: （3） （4） (5) Solve for the lateral stiffness k1, k2...k of the n individual dampers. n axial stiffness 、 …… and damping c1, c2...c n .

2. The method for testing the characteristic parameters of the vibration damper in the airborne optoelectronic equipment vibration reduction system as described in claim 1, characterized in that, The frame (2) is a cuboid frame. On the six faces of the frame (2), the bottom surface connecting to the vibration table (1) is not cut with a rectangular groove. The bottom surface of the frame (2) is horizontally attached to the table surface of the vibration table (1) and fixed with countersunk bolts.

3. The method for testing the characteristic parameters of the vibration damper in the airborne optoelectronic equipment vibration reduction system as described in claim 2, characterized in that, The slider (7) is a cuboid slider with rounded chamfers at all four corners.

4. The method for testing the characteristic parameters of the vibration damper in the airborne optoelectronic equipment vibration reduction system as described in claim 3, characterized in that, The two damper connectors (3) are respectively connected to the corresponding sliders (7) by countersunk screws. The screw head surface of the countersunk screw is on the same plane as or below the surface of the damper connector (3).

5. The method for testing the characteristic parameters of the vibration damper in the airborne optoelectronic equipment vibration reduction system as described in claim 4, characterized in that, The interface between the damper connector (3) and the damper under test (4) is a replaceable interface. When connecting the damper connector (3) and the damper under test (4), select the corresponding hole position according to the actual size of the damper and fix it with screws.

6. The method for testing the characteristic parameters of a vibration damper in an airborne optoelectronic equipment vibration reduction system as described in claim 5, characterized in that, In steps S3 and S4, the vibration table (1) and the testing device are subjected to broadband harmonic response acceleration sweep frequency excitation to obtain the amplitude frequency response curve, and then the circular frequency and amplification of the damper pair under test are obtained; the lateral stiffness and axial stiffness of the first pair of dampers under test are solved by formula (1). (1) Where ω is the angular frequency, K is the stiffness, and m is the mass; the damping of the first pair of dampers to be tested is obtained by inverse solution of formula (2); (2) Where λ is the magnification, ω is the angular frequency, and m is the mass. For damping.

7. The method for testing the characteristic parameters of a vibration damper in an airborne optoelectronic equipment vibration reduction system as described in claim 6, characterized in that, In step S5, the damper pair to be tested is replaced, an acceleration sensor is installed, and the vibration table (1) is subjected to broadband harmonic response acceleration sweep frequency excitation to obtain the amplitude frequency response curve and the circular frequency and amplification of the second pair of dampers to be tested. The lateral stiffness, axial stiffness and damping of the second set of dampers are then calculated using formulas (1) and (2).

8. The application of a method for testing the characteristic parameters of a vibration damper in an airborne optoelectronic equipment vibration reduction system according to any one of claims 1-7 in the field of vibration damper technology.

Images