Movable dual-axis control device and thermal modal test system

Abstract

The application discloses a movable double-shaft control device and a thermal modal test system. The movable double-shaft control device comprises a hanging rack arranged horizontally and suspended; the bottom surface of the hanging rack is connected with the top surface of the guide rail body of a first screw linear guide rail distributed horizontally; the lower part of the guide rail body of the first screw linear guide rail is provided with a first slider capable of sliding left and right horizontally; the bottom surface of the first slider is connected with the top surface of the guide rail body of a second screw linear guide rail distributed longitudinally; the lower part of the guide rail body of the second screw linear guide rail is provided with a second slider capable of sliding forward and backward longitudinally; the second slider is fixedly connected with the top of a laser vibration tester mounting rack; and the laser vibration tester mounting rack is provided with a laser vibration tester. Through the movable double-shaft system, the laser vibration tester can be safely, reliably and efficiently moved, the laser vibration tester is dynamically moved to multiple modal parameter response measuring points on a test piece, and then the modal test of the test piece under a high-temperature environment is completed, so that the application has great practical significance.

Description

Technical Field

[0001] This invention relates to the field of thermal modal testing technology in aerospace structural testing, and in particular to a movable dual-axis control device and a thermal modal testing system. Background Technology

[0002] With the development of hypersonic vehicles, the vehicle structure will be subjected to extreme high temperature environments exceeding 1400℃ during high-speed flight. Its structural characteristics exhibit significant temperature dependence. Excessive temperature may cause changes in structural modal parameters, thereby affecting the safety and reliability of the entire system.

[0003] Accurately obtaining the structural characteristics of aircraft at high temperatures has become a critical problem that urgently needs to be solved in aerospace engineering. Obtaining structural modal parameters (such as natural frequencies, configuration, and damping ratio) under high-temperature conditions is a core means of evaluating the risk of thermo-vibrational coupling failure.

[0004] However, existing thermal modal testing techniques face technical bottlenecks:

[0005] Firstly, there is a limitation in the measurement method: in extreme high-temperature environments (1400℃), contact sensors cannot function, while traditional red laser displacement sensors, which use a 650nm wavelength red laser, are completely obscured by the spontaneous emission of the test piece at high temperatures, causing the signal-to-noise ratio to drop below -20dB, making it impossible to acquire test signals. Therefore, a laser vibrometer based on Doppler interferometry is needed to obtain the structural modal parameters of the test piece under high-temperature conditions (such as natural frequencies, array configuration, and damping ratio).

[0006] For laser vibrometers, in order to measure the structural modal parameters of test specimens, the position of the laser vibrometer probe needs to be adjusted outside the high-temperature environment. The existing laser vibrometer probe position adjustment scheme is a manual adjustment scheme, which is slow and takes a long time (e.g., more than 3 minutes) for a single manual adjustment and positioning. Given that when the test temperature reaches 1400℃, the test specimen will undergo oxidation thickening (>50μm) and material creep within 10 minutes, resulting in modal drift of the test specimen exceeding 2Hz, which seriously affects the accuracy of the test.

[0007] Secondly, there is the challenge of spatial interference: the optical probes of laser vibrometers are generally larger than 130mm, while the effective testing area of ​​a typical aircraft panel test piece is only 500*500mm. When the spacing between measuring points is 100mm, the arrangement of multiple probes will cause physical interference.

[0008] Thirdly, there is the issue of high hardware costs: Currently, the price of a single commonly used German Polytec laser vibration meter is as high as 500,000 to 800,000 yuan. A typical aircraft panel test piece modal test requires 10 to 50 modal parameter response measurement points. If multiple laser vibration meters are used for parallel measurement, the hardware cost will exceed 10 million yuan, far exceeding the affordability of most test units.

[0009] Therefore, there is an urgent need to develop a technology that can solve the above-mentioned technical problems. Summary of the Invention

[0010] The purpose of this invention is to address the technical deficiencies of existing technologies by providing a movable dual-axis control device and a thermal modal testing system.

[0011] Therefore, the present invention provides a movable dual-axis control device, which includes a horizontally suspended bracket;

[0012] The bottom surface of the bracket is connected to the top surface of the guide rail body of the first horizontally distributed linear guide rail;

[0013] The lower part of the guide rail body of the first lead screw linear guide has a first slider that can slide horizontally left and right;

[0014] The bottom surface of the first slider is connected to the top surface of the guide rail body of the longitudinally distributed second lead screw linear guide rail;

[0015] The lower part of the guide rail body of the second lead screw linear guide has a second slider that can slide longitudinally back and forth;

[0016] The second slider is fixedly connected to the top of the laser vibrometer mounting bracket;

[0017] A laser vibration meter is installed on the laser vibration meter mounting bracket.

[0018] In addition, the present invention provides a thermal modal testing system, which includes a movable dual-axis control device as described above, and a laser vibration meter;

[0019] A laser vibrometer is mounted on the laser vibrometer bracket of the movable dual-axis control device.

[0020] As can be seen from the technical solutions provided by the present invention above, compared with the prior art, the present invention provides a movable dual-axis control device and a thermal modal testing system. The design is scientific. The movable dual-axis system can safely, reliably and efficiently move the laser vibrometer (specifically a single-point laser vibrometer), thereby controlling the laser vibrometer to dynamically move to multiple modal parameter response measurement points (i.e., response points of modal measurement, also known as modal parameter response points) on the test piece, and thus complete the modal testing of the test piece in a high-temperature environment, which has significant practical significance.

[0021] The modal testing system of this invention is a user-friendly, versatile, and low-cost high-temperature modal testing system. Its application solves the technical difficulties of existing technologies in high-temperature modal testing of test specimens, overcoming the challenges of difficult and costly measurement methods in high-temperature environments. It also achieves versatility by allowing configuration of any test bench and laser vibrometer, and is reusable. This invention is not limited to thermal modal testing; it can also be applied to high-temperature vibration, high-temperature noise, and other tests, enabling multi-point signal acquisition with a single device, thus saving on testing costs.

[0022] After testing, the thermal modal testing system provided by this invention is a thermal modal testing system suitable for ultra-high temperature environments of high-speed aircraft, which is beneficial to meeting the measurement requirements of modal characteristics of thermal protection structures of high Mach aircraft under extreme aerodynamic and thermal load conditions. Attached Figure Description

[0023] Figure 1 A front view of a movable dual-axis control device with a laser vibrometer installed, provided by the present invention;

[0024] Figure 2 A bottom view of a movable dual-axis control device with a laser vibrometer installed, provided by the present invention;

[0025] Figure 3 This is a schematic diagram illustrating the working principle of one embodiment of a thermal modal testing system provided by the present invention.

[0026] Figure 4 This is a schematic diagram showing the distribution of modal parameter response points (i.e., thermal modal test response measurement points) of the test specimen in one embodiment of a thermal modal testing system provided by the present invention.

[0027] In the diagram: 1 is the hanger, 2 is the first lead screw linear guide (i.e., the X-axis guide), 3 is the second lead screw linear guide (i.e., the Y-axis guide), 4-1 is the first slider, and 4-2 is the second slider;

[0028] 5-1 is the first servo motor; 5-2 is the second servo motor;

[0029] 6-1 is the first photoelectric sensor switch; 6-2 is the second photoelectric sensor switch;

[0030] 7 is the laser vibration meter mounting bracket, 8 is the laser vibration meter, 9 is the test piece, 10 is the fixed mounting hole, and 11 is the modal parameter response point. Detailed Implementation

[0031] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0032] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0033] In the description of this patent, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "setting" should be interpreted broadly. For example, they can refer to a fixed connection or setting, a detachable connection or setting, or an integral connection or setting. Those skilled in the art can understand the specific meaning of the above terms in this patent according to the specific circumstances.

[0034] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0035] See Figures 1 to 4 The present invention provides a movable dual-axis control device, including a horizontally suspended bracket 1;

[0036] The bottom surface of the bracket 1 is connected to the top surface of the guide rail body of the first horizontally distributed linear guide rail (i.e., X-axis guide rail) 2.

[0037] The first lead screw linear guide 2 has a first slider 4-1 that can slide horizontally left and right at the lower part of the guide body (i.e., X-axis profile);

[0038] The bottom surface of the first slider 4-1 is connected to the top surface of the guide rail body of the longitudinally distributed second lead screw linear guide (i.e., Y-axis guide) 3.

[0039] The lower part of the guide rail body (i.e., Y-axis profile) of the second lead screw linear guide rail 3 has a second slider 4-2 that can slide longitudinally back and forth;

[0040] The second slider 4-2 is fixedly connected to the top of the laser vibration meter mounting bracket 7;

[0041] A laser vibration meter 8 is installed on the laser vibration meter mounting bracket 7.

[0042] In this invention, specifically, the top of the bracket 1 is provided with a plurality of evenly distributed mounting holes;

[0043] The bracket 1 is connected to the external test bench by screws.

[0044] It should be noted that, in this invention, the surface of the bracket 1 has evenly distributed mounting holes, which can be combined and installed with any test bench, thus having versatility.

[0045] In this invention, specifically, a first servo motor 5-1 is provided at the right end of the first lead screw linear guide 2;

[0046] The power output end (i.e., power output shaft) on the left side of the first servo motor 5-1 is linked to one end of the lead screw in the first lead screw linear guide 2 to drive the lead screw to rotate (specifically, it can be linked by common methods such as gears or couplings, which are common existing connection methods and will not be described in detail here).

[0047] The first lead screw linear guide 2 has a first slider 4-1 installed on the lead screw.

[0048] It should be noted that, driven by the first servo motor 5-1, the first slider 4-1 can move laterally left and right on the lead screw of the first lead screw linear guide 2 (i.e., move along the X-axis).

[0049] In this invention, specifically, a second servo motor 5-2 is provided at the front end of the second lead screw linear guide rail 3;

[0050] The power output end (i.e., power output shaft) of the second servo motor 5-2 is linked to one end of the lead screw in the second lead screw linear guide rail 3 to drive the lead screw to rotate (specifically, it can be linked by common methods such as gears or couplings, which are common existing connection methods and will not be described in detail here).

[0051] The second lead screw linear guide 3 is equipped with a second slider 4-1.

[0052] It should be noted that, driven by the second servo motor 5-2, the second slider 4-2 can move longitudinally back and forth on the lead screw of the second lead screw linear guide 3 (i.e., move along the Y-axis).

[0053] In practice, both the first servo motor 5-1 and the second servo motor 5-2 are AC servo motors.

[0054] It should be noted that the first slider and the first servo motor, and the second slider and the second servo motor are all connected through a transmission mechanism. The transmission mechanism may include gears and lead screws. Based on the number of pulses required for one rotation of the motor in one direction and the distance the slider moves for one rotation of the motor in one direction, the slider can be controlled to complete high-precision movement through electronic pulse signals.

[0055] It should be noted that the first lead screw linear guide (i.e., the X-axis guide) 2 and the second lead screw linear guide (i.e., the Y-axis guide) are both existing, mature, and well-known ball screw linear guides, and will not be described in detail here.

[0056] In this invention, specifically, the projections of the central axis of the first lead screw linear guide (i.e., the X-axis guide) 2 and the central axis of the second lead screw linear guide (i.e., the Y-axis guide) 3 onto the horizontal plane intersect perpendicularly.

[0057] In this invention, the first lead screw linear guide 2 and the second lead screw linear guide 3 are installed in a cross orthogonal configuration, and can be moved to any point under the dual coordinate system, thereby enabling linear, rectangular, and circular movement.

[0058] In this invention, specifically, the laser vibration meter mounting bracket 7 has multiple threaded holes for fixing the laser vibration meter 8.

[0059] It should be noted that, in this invention, the laser vibration meter 8 is mounted on the laser vibration meter bracket 7, enabling the laser vibration meter to achieve linear motion, rectangular motion, etc.

[0060] It should be noted that, in this invention, the first lead screw linear guide 2 and the second lead screw linear guide 3 form a basic motion frame via the first slider 4-1, which can provide movement at any coordinate point along both axes. The sliders on the first lead screw linear guide 2 and the second lead screw linear guide 3 are connected to the corresponding servo motors via a transmission mechanism (e.g., a lead screw), enabling high-precision movement on the X-axis profile of the first lead screw linear guide 2 and the Y-axis profile of the second lead screw linear guide 3, respectively.

[0061] In this invention, specifically, a first photoelectric sensor switch 6-1 is provided on the bottom surface of the guide rail body of the first lead screw linear guide rail 2;

[0062] The first photoelectric sensor switch 6-1 is used to detect the specific position of the first slider 4-1 on the first lead screw linear guide rail 2;

[0063] A second photoelectric sensor switch 6-2 is provided on the bottom surface of the guide rail body of the second lead screw linear guide rail 3;

[0064] The second photoelectric sensor switch 6-2 is used to detect the specific position of the second slider 4-2 on the second lead screw linear guide rail 3.

[0065] It should be noted that, in this invention, the first photoelectric sensor switch 6-1 and the second photoelectric sensor switch 6-2 are photoelectric calibration switches, arranged on the guide body (i.e., the X-axis profile) of the first lead screw linear guide 2 and the guide body (i.e., the Y-axis profile) of the second lead screw linear guide 3. They can provide real-time feedback on the slider's position and further correct positional deviations. By combining the position of the transmission mechanism (e.g., the lead screw) with the position correction, positioning accuracy can be maintained even during rapid movement.

[0066] In practice, the first photoelectric sensor switch 6-1 and the second photoelectric sensor switch 6-2 are located at the mechanical zero position. Each time the device is turned on, the photoelectric sensor switches can feed back the slider position to the motion control system to calibrate the position coordinates of the corresponding slider.

[0067] Therefore, in this invention, the mechanical position of the two sliders can be fed back through two photoelectric sensor switches, and the accuracy of each test point (i.e., the modal parameter response measurement point to be moved to) can be ensured through real-time adjustment.

[0068] In a specific implementation of this invention, the movable dual-axis control device of this invention further includes a motion control system;

[0069] Motion control system, including motion control chip;

[0070] The motion control chip is connected to the control terminals of the first photoelectric sensor switch 6-1, the second photoelectric sensor switch 6-2, the first servo motor 5-1, and the second servo motor 5-2, respectively. It is used to acquire, in real time, the specific positions of the first slider 4-1 on the first lead screw linear guide 2 and the second slider 4-2 on the second lead screw linear guide 3 via the first photoelectric sensor switch 6-1 and the second photoelectric sensor switch 6-2. Furthermore, it sends control signals to control the operation of the first servo motor 5-1 and the second servo motor 5-2, so that under the drive of the first servo motor 5-1, the first slider 4-1 moves laterally left and right on the lead screw of the first lead screw linear guide 2 (i.e., moves along the X-axis), and under the drive of the second servo motor 5-2, the second slider 4-2 moves longitudinally forward and backward on the lead screw of the second lead screw linear guide 3 (i.e., moves along the Y-axis), until the movement position of the second slider 4-2 reaches the predetermined test position (e.g., the modal parameter response measurement point, i.e., the response point of modal measurement).

[0071] It should be noted that the coordinates of the pre-required test position include the horizontal coordinate and the vertical coordinate. The horizontal coordinate can be determined by the first photoelectric sensor switch 6-1, and the vertical coordinate can be determined by the second photoelectric sensor switch 6-2.

[0072] In practice, the motion control chip can be a programmable logic controller (PLC), a central processing unit (CPU), a digital signal processor (DSP), or a microcontroller (MCU).

[0073] It should be noted that the motion control system of this invention can have both automatic and manual modes. By moving two sliders on the guide body of the first linear guide 2 (i.e., the X-axis profile) and the guide body of the second linear guide 3 (i.e., the Y-axis profile), respectively, the laser vibrometer 8 can be quickly and accurately positioned to the response point coordinates of modal measurement, completing modal measurement in an ultra-high temperature (1400℃) environment. The motion control system includes an LCD display, a motion control chip, etc., with a minimum data unit of 0.001mm and a maximum speed limit of ±9000mm / min.

[0074] Based on the above, the present invention provides a movable dual-axis control device, see [link to related document]. Figure 3 , Figure 4 The present invention also provides a thermal modal testing system, including a movable dual-axis control device as described above, and a laser vibration meter 8;

[0075] The laser vibration meter 8 is mounted on the laser vibration meter bracket 7 of the movable dual-axis control device;

[0076] The laser vibration meter 8 is used to measure the structural modal parameters (such as natural frequency, array shape and damping ratio) at multiple modal parameter response points on the test piece 9.

[0077] In specific implementation, the laser vibrometer 8 and the movable dual-axis control device are used to form the modal response testing system in the thermal modal testing system of the present invention. Specifically, the laser vibrometer 8 can be a laser vibrometer from Polytec, Germany.

[0078] In specific implementation, the thermal modal testing system of the present invention also includes a vibration excitation system;

[0079] The excitation system includes a vibration table and a power amplifier;

[0080] The test piece 9 is placed on the surface of the vibration table;

[0081] The vibration table is used to simulate a vibration environment for test piece 9.

[0082] It should be noted that the vibration table is also connected to a power amplifier, which drives the electromagnetic vibration table to generate vibration. This is a conventional technology and will not be elaborated upon here. The excitation system uses an electrically powered vibration table with closed-loop control for excitation.

[0083] In specific implementation, the thermal modal testing system of the present invention also includes a heating system;

[0084] The heating system includes a sealed test chamber and multiple quartz lamps located inside the test chamber;

[0085] Test piece 9 is located in the test chamber;

[0086] The quartz lamp is used to apply thermal load to test specimen 9.

[0087] It should be noted that the heating system provides simulated thermal load to test piece 9 through radiant heating of the quartz lamp.

[0088] In specific implementation, the thermal modal testing system of the present invention also includes a modal analysis system;

[0089] The modal analysis system, connected to the laser vibrometer 8, is used to collect the acceleration response signal output by the laser vibrometer 8, and then analyze and obtain the structural modal parameters (including natural frequency, configuration and damping ratio) of the test piece 9 (e.g., the panel of an aircraft) at high temperature.

[0090] It should be noted that, for the present invention, the modal analysis system is an existing, well-known, and technically mature signal processing system, such as the Siemens SimCenter TestLab SCM2E05 acquisition and analysis system.

[0091] It should be noted that, for this invention, for test piece 9, a vibration table is used to apply basic excitation, a quartz lamp to apply thermal load, and a laser vibrometer 8 is combined with a movable dual-axis control device. The laser vibrometer 8 sequentially measures the acceleration response signals at predetermined modal parameter response points (e.g., 25 modal parameter response points) on the structure of test piece 9. (See...) Figure 4 Then, the transfer function under high temperature is calculated based on the existing modal analysis system, and the structural modal parameters of the test piece 9 (e.g., the wall panel of an aircraft) under high temperature are analyzed.

[0092] To better understand the technical solution of the present invention, the key role of the present invention in thermal modal testing will be explained below with reference to specific embodiments.

[0093] Example

[0094] Test piece 9 is a composite material wall panel. The purpose of conducting high-temperature modal tests on it is to obtain typical structural modal parameters under thermal conditions and to carry out ground-based thermal modal tests.

[0095] Implementation plan: See Figure 3 The thermal modal testing system includes an excitation system, a heating system, a modal response testing system, and a modal analysis system. A vibration table was used to apply foundation excitation, a quartz lamp to apply thermal load, and a laser vibrometer combined with a movable dual-axis control device was used. The laser vibrometer 8 sequentially measured the acceleration response signals at 25 modal parameter response points on the structure of the test specimen 9. (See attached diagram). Figure 4 Then, the transfer function under high temperature is calculated based on the existing modal analysis system, and the structural modal parameters under high temperature are analyzed.

[0096] In terms of specific implementation, the thermal modal testing system provided by this invention has the following specific implementation steps:

[0097] The first step is to determine the coordinates of the 25 modal parameter response points 11 on the test piece 9 before the test begins, for example (0,0), (0,10)..., and input them sequentially into the movable dual-axis control device (specifically the motion control system);

[0098] The second step is to rigidly fix the test piece 9 to the vibration table using the existing clamps;

[0099] The third step involves heating the test piece 9 to the target temperature of 1400℃ using a quartz lamp heating system at a rate of 3℃ / s.

[0100] Fourth step: Once the temperature of test piece 9 has stabilized at the target temperature, turn on the vibration table for excitation;

[0101] Step 5: Turn on the laser vibrometer 8;

[0102] Step 6: Activate the movable dual-axis control device and measure the time domain response signal (i.e., acceleration response signal) of 25 modal parameter response points 11 in sequence according to the previously input coordinates. The acquisition time for a single test point is 3 seconds.

[0103] The seventh step involves rapidly moving the laser vibrometer 8 using a movable dual-axis control device, which can complete the acquisition of signals at all measurement points (i.e., 25 modal parameter response points 11) within 2 minutes.

[0104] The eighth step involves the modal analysis system analyzing the acquired time-domain response signal (i.e., acceleration response signal) to obtain the structural modal parameters of the test piece 9 (e.g., the wall panel of an aircraft) at high temperatures, thus completing the thermal modal test.

[0105] In practice, the test piece 9 is also provided with multiple mounting holes 10 around its four edges, and screws are passed through the mounting holes 10 to connect it to external installation equipment (such as the fuselage of an aircraft).

[0106] 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 principle 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 movable dual-axis control device, characterized in that, Including horizontally suspended hanging brackets (1); The bottom surface of the hanger (1) is connected to the top surface of the guide rail body of the first horizontally distributed linear guide rail (2); The lower part of the guide body of the first lead screw linear guide (2) has a first slider (4-1) that can slide horizontally left and right. The bottom surface of the first slider (4-1) is connected to the top surface of the guide rail body of the longitudinally distributed second lead screw linear guide (3); The lower part of the guide body of the second lead screw linear guide (3) has a second slider (4-2) that can slide longitudinally back and forth. The second slider (4-2) is fixedly connected to the top of the laser vibration meter mounting bracket (7); A laser vibration meter (8) is installed on the laser vibration meter mounting bracket (7); The right end of the first lead screw linear guide (2) is equipped with a first servo motor (5-1). The power output end on the left side of the first servo motor (5-1) is linked to one end of the lead screw in the first lead screw linear guide (2); The first lead screw linear guide (2) has a first slider (4-1) on it. The front end of the second lead screw linear guide (3) is equipped with a second servo motor (5-2). The power output end of the second servo motor (5-2) is linked to one end of the lead screw in the second lead screw linear guide (3) to drive the lead screw to rotate. The second lead screw linear guide (3) is equipped with a second slider (4-2). The projections of the central axis of the first lead screw linear guide (2) and the central axis of the second lead screw linear guide (3) on the horizontal plane intersect perpendicularly. The bottom surface of the first lead screw linear guide (2) is provided with a first photoelectric sensor switch (6-1). The first photoelectric sensor switch (6-1) is used to detect the specific position of the first slider (4-1) on the first lead screw linear guide (2); A second photoelectric sensor switch (6-2) is provided on the bottom surface of the guide rail body of the second lead screw linear guide (3). The second photoelectric sensor switch (6-2) is used to detect the specific position of the second slider (4-2) on the second lead screw linear guide (3).

2. The movable dual-axis control device as described in claim 1, characterized in that, The top of the bracket (1) is provided with multiple evenly distributed mounting holes; The bracket (1) is connected to the external test bench by screws.

3. The movable dual-axis control device as described in claim 1, characterized in that, It also includes a motion control system; Motion control system, including motion control chip; The motion control chip is connected to the control terminals of the first photoelectric sensor switch (6-1), the second photoelectric sensor switch (6-2), the first servo motor (5-1), and the second servo motor (5-2), respectively. It is used to obtain the specific position of the first slider (4-1) on the first lead screw linear guide (2) and the specific position of the second slider (4-2) on the second lead screw linear guide (3) in real time through the first photoelectric sensor switch (6-1) and the second photoelectric sensor switch (6-2). It also sends control signals to control the operation of the first servo motor (5-1) and the second servo motor (5-2), so that the first slider (4-1) moves laterally left and right on the lead screw of the first lead screw linear guide (2) under the drive of the first servo motor (5-1), and the second slider (4-2) moves longitudinally back and forth on the lead screw of the second lead screw linear guide (3) under the drive of the second servo motor (5-2), until the movement position of the second slider (4-2) reaches the pre-required test position.

4. A thermal modal testing system, characterized in that, Includes a movable dual-axis control device as described in any one of claims 1 to 3, and a laser vibrometer (8). The laser vibration meter (8) is mounted on the laser vibration meter mounting bracket (7) of the movable dual-axis control device.

5. The thermal modal testing system as described in claim 4, characterized in that, It also includes a vibration system and a heating system; The excitation system includes a vibration table and a power amplifier. The test piece (9) is placed on the surface of the vibration table; A vibration table is used to simulate a vibration environment for the test specimen (9); The heating system includes a sealed test chamber and multiple quartz lamps located inside the test chamber; Test specimen (9) is located in the test chamber; A quartz lamp is used to apply a thermal load to the test specimen (9).

6. The thermal modal testing system as described in claim 5, characterized in that, It also includes a modal analysis system; The modal analysis system is connected to the laser vibration meter (8) and is used to collect the acceleration response signal output by the laser vibration meter (8) and then analyze and obtain the structural modal parameters of the test piece (9) at high temperature.

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