High-temperature vibration device suitable for carbon fiber resin matrix composite large-scale structural components

Abstract

Provided in the present invention is a high-temperature vibration device suitable for carbon fiber resin matrix composite large-scale structural components, comprising: a carbon fiber resin matrix composite large-scale structural component, a variable-diameter support device, an oxyacetylene blowtorch, a threaded push rod, a support body, a base adapter plate, a laser vibrometer, a support frame, a vibration measurement port, a vent valve, a platinum-rhodium thermocouple, and a vibration table. The carbon fiber resin matrix composite large-scale structural component is fixed on the support body of the vibration table, the oxyacetylene blowtorch moves and extends to one end of the carbon fiber resin matrix composite large-scale structural component, and the variable-diameter support device fixes the oxyacetylene blowtorch inside the carbon fiber resin matrix composite large-scale structural component. The blowtorch is used to provide a high-temperature ablation thermal environment, the vibration table is used to fixedly connect the support body and provide random vibration excitation, and the laser vibrometer collects vibration signals through a high-temperature vibration chamber. The present invention provides a testing means for high-temperature vibration modal testing of carbon fiber resin matrix composite large-scale structural components under aerospace flight environments.

Description

High-temperature vibration device for large carbon fiber resin-based composite structural components Technical Field

[0001] This invention relates to the field of testing large carbon fiber resin matrix composite structural components in aerospace flight environments, and particularly to a high-temperature vibration device suitable for large carbon fiber resin matrix composite structural components. Background Technology

[0002] Carbon fiber reinforced polymer (CFRP) composites are widely used in aerospace, automotive, and other industries due to their high strength, high modulus, lightweight, corrosion resistance, and good thermal stability. Currently, large, critical structural components such as aircraft wings, tail fins, engine fan blades, rocket casings, and nozzles are all made of CFRP. However, with the rapid development of hypersonic vehicles, the high-temperature vibration modal changes of large CFRP structural components under extreme and complex flight environments have become a growing research focus. Especially for CFRP, extreme aerodynamic and high-temperature environments severely affect their performance. Uneven thermal stress causes high-temperature modal changes in structural components, directly impacting the stability and safety of the aircraft. Furthermore, ground-based modal testing to simulate the real extreme high-temperature vibration flight environment of aircraft presents significant challenges. Therefore, it is urgent to build a high-temperature vibration device suitable for large CFRP structural components to closely simulate real flight conditions using ground-based atmospheric environments, enabling accurate prediction of the high-temperature modes of large CFRP structural components and guiding and verifying the design feasibility of aircraft under extreme flight environments.

[0003] Currently, high-temperature vibration modal studies of carbon fiber resin matrix composites (CFRP) typically employ radiant heating methods such as quartz lamps to create an extreme high-temperature environment. However, this uniformly heated environment cannot accurately simulate the uneven ablation conditions encountered during aircraft flight. Furthermore, the melting point of materials like quartz lamps limits the ability of these heating devices to stably provide temperatures above 1400°C. In real flight environments, large CFRP structural components operate in a micro-oxygen environment, posing a challenge to ground-based atmospheric simulations. Additionally, CFRP composites generate significant amounts of gas under extreme high-temperature conditions, potentially impacting the health of vibration measurement and experimental personnel. Therefore, researchers urgently need to develop high-temperature vibration devices suitable for large CFRP structural components to accurately simulate the micro-oxygen and uneven ablation conditions encountered during extreme aircraft flight, providing a safe and reliable experimental environment for personnel and enabling precise acquisition of high-temperature vibration modes of large CFRP structural components under aerospace flight conditions. Summary of the Invention

[0004] To address the aforementioned issues, this invention discloses a high-temperature vibration device suitable for large carbon fiber resin matrix composite structural components. This device can provide a non-uniform heating environment of over 1200°C and micro-oxygen conditions for large carbon fiber resin matrix composite structural components. Simultaneously, it enables accurate acquisition of high-temperature vibration modes of large carbon fiber resin matrix composite structural components and provides a safe and stable operating environment for operators. This device provides a testing method for the stability and design feasibility of large carbon fiber resin matrix composite structural components in aerospace flight environments.

[0005] The technical solution of this invention is: a high-temperature vibration device suitable for large carbon fiber resin matrix composite structural components, comprising: a large carbon fiber resin matrix composite structural component, a variable diameter support device, an oxyacetylene torch, a threaded top rod, a support body, a base adapter plate, a slide rail, a sliding truss I, a sliding truss II, a laser vibration meter, a support frame, a vibration measuring port, a vent valve, a platinum-rhodium thermocouple, a vibration table, a high-temperature furnace door, a high-temperature vibration chamber, a fume extractor, a hollow shaft, a high-temperature support plate, and a linkage rod; the support body is fixed to the vibration table surface by high-temperature bolts passing through the base adapter plate; the large carbon fiber resin matrix composite structural component is nested in a conical clamp of the support body; rotating the threaded top rod on the outer side of the conical clamp stabilizes and fixes the large carbon fiber resin matrix composite structural component; the vibration table applies a random excitation signal to provide random vibration; the oxyacetylene torch... Fixed to the right side of the high-temperature vibration chamber, a variable-diameter support device is nested within the inner wall of the oxyacetylene torch. The oxyacetylene torch and the variable-diameter support device are fixed to one side of the large carbon fiber resin-based composite material structure. The sliding hollow shaft of the variable-diameter support device drives the expansion of eight linkage rods, expanding eight high-temperature support plates to the inner wall of the large carbon fiber resin-based composite material structure. The flame from the oxyacetylene torch passes through the variable-diameter support device and ablates the inner wall of the large carbon fiber resin-based composite material structure, providing a high-temperature ablation environment above 1200℃. The smoke extractor on the left side of the high-temperature vibration chamber effectively absorbs smoke, providing a safe and stable experimental environment. The laser vibrometer on the top of the high-temperature vibration chamber illuminates the large carbon fiber resin-based composite material structure through the vibration measurement port, collecting high-temperature vibration modal data of the large carbon fiber resin-based composite material structure and obtaining high-temperature vibration modal parameters.

[0006] Because this invention is applicable to high-temperature vibration testing of large carbon fiber resin-based composite structural components, the vibration table is connected to the support body via high-temperature bolts passing through the base adapter plate. The support body consists of a base, a support plate, reinforcing ribs, and a conical clamp. The support plate is welded to the middle of the support body base, and two reinforcing ribs are distributed on both sides of the support plate to provide stable support. A conical clamp is welded to the upper end of the support plate. Threaded push rod holes are opened at 60° intervals around the outer wall of the conical clamp. The large carbon fiber resin-based composite structural component is nested in the conical clamp. Without damaging the integrity of the large carbon fiber resin-based composite structural component, the threaded push rods are rotated and high-temperature adhesive is used to stably fix the large carbon fiber resin-based composite structural component to the inner wall of the conical clamp. The vibration table applies random excitation and transmits the excitation signal to the large carbon fiber resin-based composite structural component.

[0007] Since this invention is applicable to high-temperature ablation testing of large carbon fiber resin matrix composite structural components, changing the flame nozzle diameter of the oxyacetylene torch to adapt to changes in the large carbon fiber resin matrix composite structural components with different diameters is time-consuming and labor-intensive, affecting the experimental process. The variable-diameter support device described in this invention consists of a hollow shaft, connecting rods, and high-temperature support plates. The hollow shaft slides within the outer wall of the oxyacetylene torch, and eight connecting rods are fixed to the hollow shaft with eight high-temperature support plates arranged circumferentially. Sliding the hollow shaft of the variable-diameter support device drives the eight connecting rods to expand, causing the eight high-temperature support plates to expand to the inner wall of the large carbon fiber resin matrix composite structural component. The expansion angle of the high-temperature support plates changes in a timely manner according to the inner diameter of the large carbon fiber resin matrix composite structural component. The variable-diameter support device is made of high-temperature alloy steel to meet the ablation temperature requirements, providing stable flame ablation conditions for large carbon fiber resin matrix composite structural components with varying diameters.

[0008] This invention is applicable to high-temperature ablation testing of large carbon fiber resin-based composite structural components. Under extreme thermal ablation conditions, these components generate large amounts of smoke and harmful gases, posing risks to the laser vibration measurement optical path and the health of laboratory personnel. The smoke extraction device of this invention is located on the left side of the high-temperature vibration chamber. A square slot is provided on the left side of the chamber to accommodate the dimensions of the smoke extraction device. Under extreme ablation conditions, the lateral suction of the device effectively extracts the smoke and guides the direction of flame ablation to a certain extent, providing a safe, stable, and effective testing environment.

[0009] Because this invention is applicable to simulating the real flight environment of large carbon fiber resin-based composite structural components in a ground environment, the simulation of ablation conditions and airflow erosion is effectively solved by using an oxy-acetylene torch for flame jetting and flame velocity adjustment. The ventilation valve described in this invention is installed on the right side of the high-temperature vibration chamber. The ventilation valve introduces inert gases such as argon, enabling a micro-oxygen environment and reducing the generation of ablation fumes under the protection of the gas.

[0010] This invention is applicable to high-temperature vibration modal testing of large structural components made of carbon fiber resin matrix composites. The laser vibration meter described in this invention is bolted to the intersection of sliding truss one and sliding truss two. The sliding trusses move laterally and longitudinally on slide rails. According to the vibration measurement point requirements, the trusses slide the laser vibration meter to the designated area for high-temperature vibration modal data acquisition.

[0011] The platinum-rhodium thermocouple meets the temperature measurement requirements of over 1200℃. It passes through the right-side disc of the high-temperature vibration chamber and connects to the support body to the large carbon fiber resin-based composite material structural component and the external data acquisition instrument of the high-temperature vibration chamber to measure the temperature of the large carbon fiber resin-based composite material structural component.

[0012] The Φ510m circular groove is opened at the bottom of the high-temperature vibration chamber, closely matching the dimensions of the vibration table surface to provide vibration margin, and the surrounding gaps are filled with heat insulation cotton.

[0013] The high-temperature furnace door is located at the front end of the high-temperature vibration box, which facilitates the clamping of large carbon fiber resin-based composite structural components.

[0014] The 300mm×300mm×50mm square groove is located on the left side of the high-temperature vibration chamber, closely fitting the outer dimensions of the fumigation machine to absorb the smoke generated by ablation.

[0015] The Φ60mm circular hole is located on the right side of the high-temperature vibration chamber, through which the oxyacetylene flame torch provides a high-temperature ablation environment.

[0016] The 200mm×30mm×50mm vibration measuring port is located on the top of the high-temperature vibration chamber and is made of fiberglass that can withstand 1200℃.

[0017] Working principle of the invention:

[0018] A high-temperature bolt is used to fix the support base and base adapter plate to the vibration table surface. A large carbon fiber resin-based composite material structural component is fixed inside the large carbon fiber resin-based composite material structural component by rotating the external threaded rod of the conical clamp and applying high-temperature adhesive. The vibration table applies random excitation, transmitting the vibration excitation signal to the large carbon fiber resin-based composite material structural component. An oxyacetylene torch is fixed to one end of the large carbon fiber resin-based composite material structural component through the high-temperature vibration chamber. A hollow shaft of a variable-diameter support device is slidably fixed to the outer wall of the oxyacetylene torch. The other end drives a linkage rod through the sliding hollow shaft, expanding the high-temperature support plate to the inner wall of the large carbon fiber resin-based composite material structural component, providing a high-temperature ablation thermal environment above 1200℃. Platinum-rhodium thermocouples pass through the right-side disc and support body of the high-temperature vibration chamber, connecting the large carbon fiber resin-based composite material structural component to a data acquisition instrument outside the high-temperature vibration chamber to monitor the temperature change of the large carbon fiber resin-based composite material structural component during ablation. An inert gas is introduced through the vent valve on the right side of the high-temperature vibration chamber to simulate the micro-oxygen environment under flight conditions. A smoke extraction device, positioned on the left side of the high-temperature vibration chamber, absorbs the smoke generated by the ablation of large carbon fiber resin-based composite structural components and guides the direction of flame ablation, providing a safe and stable experimental environment. A laser vibrometer is fixedly mounted on a support frame at the top of the high-temperature vibration chamber. A sliding truss is moved to the vibration measurement point, and a laser beam passes through the measurement port to irradiate the large carbon fiber resin-based composite structural component, collecting high-temperature vibration modal parameters. This invention can simulate the uneven ablation and micro-oxygen environment of large carbon fiber resin-based composite structural components during flight in a safe and stable ground-based experimental environment. It also enables accurate testing of the high-temperature ablation vibration modes of large carbon fiber resin-based composite structural components, providing experimental means for assessing the stability and design feasibility of large carbon fiber resin-based composite structural components in aerospace flight environments.

[0019] The advantages of this invention compared to the prior art are:

[0020] (1) Currently, most high-temperature vibration modal testing devices are built using radiant heating methods such as quartz lamps to create an extreme high-temperature thermal environment. The uniform heating environment cannot accurately simulate the uneven ablation during aircraft flight. Furthermore, heating equipment such as quartz lamps is limited by the melting point of quartz materials and cannot stably provide a high-temperature thermal environment above 1400℃. At the same time, excitation equipment such as vibrators cannot provide stable thrust for large carbon fiber resin-based composite structural components, affecting the stability of high-temperature thermal vibration modal data acquisition. This invention uses a fixed oxyacetylene flame torch that moves through the interior of the high-temperature vibration chamber to one end of the large carbon fiber resin-based composite structural component. It is fixed to the inner wall of the carbon fiber resin-based composite material by a variable-diameter support device, providing a stable flame ablation condition and overcoming the limitations of quartz lamp heating equipment. The vibration table is fixed to the support body by high-temperature bolts. Random excitation signals are applied to the large carbon fiber resin-based composite structural component fixed to the support body through the vibration table. The laser vibrometer at the top of the high-temperature vibration chamber collects high-temperature vibration modal data through the vibration measurement port. The advantages of this invention are that it can provide a relatively stable non-uniform ablation environment above 1200℃ and overcome the limitations of current high-temperature thermal vibration equipment, thereby enabling the acquisition of high-temperature vibration modal data for large carbon fiber resin matrix composite structural components.

[0021] (2) This invention is applicable to the clamping of large carbon fiber resin-based composite structural parts with different outer diameters. The support body of this invention consists of a base, a support plate, reinforcing ribs, and a conical clamp. Without damaging the integrity of the large carbon fiber resin-based composite structural part, the large carbon fiber resin-based composite structural part is nested and glued inside the conical clamp. The threaded push rods distributed circumferentially at 60° on the conical clamp are rotated to adapt to changes in the outer diameter of the large carbon fiber resin-based composite structural part.

[0022] (3) This invention is applicable to the ablation test of large carbon fiber resin-based composite material structural parts with different inner diameters. A variable diameter support device is used to adapt to the change of inner diameter of the large carbon fiber resin-based composite material structural parts. It consists of a hollow shaft, a linkage rod and a high-temperature support plate. The hollow shaft slides on the outer wall of the oxyacetylene torch, which drives the linkage rod to expand the high-temperature support plate to the inner wall of the large carbon fiber resin-based composite material structural parts. The flame of the oxyacetylene torch passes through the variable diameter support device and adheres to the high-temperature support plate to ablate the inner wall of the large carbon fiber resin-based composite material structural parts, ensuring the stability of the ablation.

[0023] (4) This invention can provide a safe and stable experimental environment and simulate a micro-oxygen flight environment. A ventilation valve is installed on the right side of the high-temperature vibration chamber, allowing inert gases such as argon to be introduced and expelling air from the chamber, thus achieving a micro-oxygen environment and reducing the generation of ablation smoke under the protection of the protective gas. A smoke extractor is located on the left side of the high-temperature vibration chamber, with a square slot on the left side to accommodate the smoke extractor's dimensions. Under extreme ablation conditions, the lateral suction of the smoke extractor effectively extracts smoke and guides the direction of flame ablation to a certain extent, providing a safe, stable, and effective testing environment.

[0024] (5) Traditional accelerometers suffer from problems such as the influence of extreme ablation temperatures on vibration modal data acquisition and the accelerometer detachment caused by the accelerometer leads being wrapped around the high-temperature vibration chamber. In this invention, a laser vibration meter is arranged on the top of the high-temperature vibration chamber. The laser passes through the high-temperature fiberglass vibration measuring port to irradiate the outer surface of the large carbon fiber resin-based composite material structural component to obtain high-temperature vibration modal parameters.

[0025] (6) Since high-temperature vibration modal data requires the acquisition of multiple measurement points to meet the requirements of vibration mode measurement points, the present invention arranges sliding truss one and sliding truss two on the top of the high-temperature vibration chamber, and the laser vibration meter is fixedly installed on the truss. According to the measurement point requirements, the sliding truss slides laterally and longitudinally on the slide rail to realize the acquisition of multi-point modal data of large carbon fiber resin-based composite material structural components. Attached Figure Description

[0026] Figure 1 is a front view of the present invention;

[0027] Figure 2 is a rear view of the present invention;

[0028] Figure 3 is a top view of the present invention;

[0029] Figure 4 is a cross-sectional view of the present invention;

[0030] Figure 5 is an enlarged view of the support body and variable diameter support device of the present invention.

[0031] Figure 6 is a side view of the support body and variable diameter support device of the present invention.

[0032] Figure 7 is a diagram of the support assembly of the present invention. Detailed Implementation

[0033] The present invention will be further illustrated below with reference to the accompanying drawings and specific embodiments. It should be understood that the following specific embodiments are for illustrative purposes only and are not intended to limit the scope of the invention. It should be noted that the terms "front," "rear," "left," "right," "up," and "down" used in the following description refer to directions in the accompanying drawings, and the terms "inner" and "outer" refer to directions toward or away from the geometric center of a specific component, respectively.

[0034] As shown in Figures 1, 2, 3, 4, 5, and 6, the present invention comprises a large carbon fiber resin-based composite material structural component 1, a variable diameter support device 2, an oxyacetylene torch 3, a threaded top rod 4, a support body 5, a base adapter plate 6, a slide rail 7, a sliding truss I 8, a sliding truss II 9, a laser vibration meter 10, a support frame 11, a vibration measuring port 12, a vent valve 13, a platinum-rhodium thermocouple 14, a vibration table 15, a high-temperature furnace door 16, a high-temperature vibration box 17, a fume extractor 18, a hollow shaft 19, a high-temperature support plate 20, and a linkage rod 21.

[0035] The base of the support body 5 and the base adapter plate 6 are fixed to the vibration table surface using high-temperature bolts. The external threaded rod 4 of the rotating conical clamp is used to glue the large carbon fiber resin-based composite material structural component 1 with high-temperature adhesive, thus fixing the large carbon fiber resin-based composite material structural component 1 inside the conical clamp of the support body 5. The vibration table 15 applies random excitation and transmits the vibration excitation signal to the large carbon fiber resin-based composite material structural component 1. The oxyacetylene torch 3 passes through the high-temperature vibration box 17 and is fixed to one end of the large carbon fiber resin-based composite material structural component 1. One end of the variable diameter support device 2 is slidably fixed to the outer wall of the oxyacetylene torch 3, and the other end drives the linkage rod 21 to move through the sliding hollow shaft 19, expanding the high-temperature support plate 20 to the inner wall of the large carbon fiber resin-based composite material structural component 1, providing a high-temperature ablation thermal environment of over 1200°C. High-temperature platinum-rhodium thermocouples 14 pass through the right-side disc and support 5 of the high-temperature vibration chamber 17, connecting the large carbon fiber resin composite structure 1 to the data acquisition instrument outside the high-temperature vibration chamber 17 to monitor the temperature change of the large carbon fiber resin composite structure during ablation. Inert gas is introduced through the vent valve 13 on the right side of the high-temperature vibration chamber 17 to simulate the micro-oxygen environment under flight conditions. A smoke extraction device 18 on the left side of the high-temperature vibration chamber 17 absorbs the smoke generated by the ablation of the large carbon fiber resin composite structure 1 and guides the direction of flame ablation, providing a safe and stable experimental environment. A laser vibration meter 10 is fixedly installed on the support frame 11 at the top of the high-temperature vibration chamber 17. The laser passes through the vibration measurement port 12 to irradiate the large carbon fiber resin composite structure 1, collecting high-temperature vibration modal parameters.

[0036] Since high-temperature vibration modal data requires multi-point acquisition to meet the requirements of mode shape measurement points, this invention provides a laser vibration meter with transverse and longitudinal through holes at the top and middle. A sliding truss 8 passes through the transverse through hole, and a sliding truss 9 passes through the longitudinal through hole at the top of the high-temperature vibration chamber. The laser vibration meter is fixedly installed using sliding truss 8 and sliding truss 9. According to the measurement point requirements, sliding truss 8 and sliding truss 9 slide laterally and longitudinally on slide rails to reach the specified measurement point positions, completing the modal data acquisition.

[0037] The technical means disclosed in this invention are not limited to those disclosed in the above embodiments, but also include technical solutions composed of any combination of the above technical features.

Claims

1. A high-temperature vibration device suitable for large structural components made of carbon fiber resin matrix composites, characterized in that: The system includes a large carbon fiber resin-based composite material structural component (1), a variable-diameter support device (2), an oxyacetylene torch (3), a threaded top rod (4), a support body (5), a base adapter plate (6), a laser vibration meter (10), a support frame (11), a vibration port (12), a vent valve (13), a platinum-rhodium thermocouple (14), a vibration table (15), a high-temperature furnace door (16), a high-temperature vibration chamber (17), and a fumigation machine (18). The vibration table (15) is equipped with a high-temperature vibration chamber (17). A sliding truss is provided on the top of the high-temperature vibration chamber (17). The support body (5) is fixed to the surface of the vibration table (15) by high-temperature bolts passing through the base adapter plate (6). The large carbon fiber resin-based composite material structural component (1) is fixed and nested inside the support body (5) by the threaded top rod (4). The vibration table (15) provides random excitation to the large carbon fiber resin-based composite material structural component (1). A thermocouple (14) passes through the support (5) and the surface of the large carbon fiber resin composite material structure (1) and is connected to an external data acquisition instrument. An oxyacetylene torch (3) is fixed and nested inside the large carbon fiber resin composite material structure (1) by a variable diameter support device (2). An inert gas is introduced into the right side of the high temperature vibration chamber (17) through a ventilation valve (13) to simulate the micro-oxygen environment in the high temperature flight environment of the large carbon fiber resin composite material structure, and a smoke machine (18) is connected to the left side to absorb the smoke generated by the ablation of the large carbon fiber resin composite material structure. A vibration measuring port (12) is opened at the upper end of the vibration chamber (17), and the laser of the laser vibration meter (10) installed on the sliding truss penetrates the vibration measuring port (12) and is projected onto the upper surface of the large carbon fiber resin composite material structure to collect high temperature vibration modal data of the large carbon fiber resin composite material structure.

2. The high-temperature vibration device for large carbon fiber resin matrix composite structural components according to claim 1, characterized in that: The support body (5) consists of a base (51), a support plate (52), reinforcing ribs (53), and a conical clamp (54). The base (51) has 6 threaded holes and is fixed to the vibration table (15) by passing high-temperature bolts through the base adapter plate (6). The support plate (52) is welded to the middle of the base (51), and two reinforcing ribs (53) are distributed on both sides of the support plate (52). The upper end of the support plate (52) is welded to the conical clamp (54). Threaded top rod holes are opened every 60° along the circumference of the conical clamp (51). Rotating the threaded top rods fixes the large carbon fiber resin-based composite material structural parts inside the conical clamp.

3. The high-temperature vibration device for large carbon fiber resin matrix composite structural components according to claim 1, characterized in that: The oxyacetylene torch (3) is fixed to one end of the large carbon fiber resin-based composite material structure (1). The variable diameter support device (2) is nested on the outer wall of the oxyacetylene torch (3). The variable diameter support device consists of a hollow shaft (19), a linkage rod (21), and a high-temperature support plate (20). The hollow shaft (19) is nested on the outer wall of the oxyacetylene torch (3). Eight linkage rods (21) are fixed on the hollow shaft (19). Eight high-temperature support plates (20) are arranged circumferentially on the eight linkage rods (21). The hollow shaft (19) slides on the outer wall of the oxyacetylene torch (3) to drive the eight linkage rods (21) to move, so that the eight high-temperature support plates (20) expand to the inner wall of the large carbon fiber resin-based composite material structure (1). Adjusting the sliding distance of the hollow shaft (19) is suitable for flame ablation of large carbon fiber resin-based composite material structures with different diameters.

4. The high-temperature vibration device for large carbon fiber resin matrix composite structural components according to claim 1, characterized in that: The bottom of the high-temperature vibration box (17) is provided with a circular groove of Φ510mm, which fits closely with the table size of the vibration table (15) to provide vibration margin; a high-temperature furnace door (16) is provided on the front side of the high-temperature vibration box (17); a square groove of 300mm×300mm×50mm is provided on the left side of the high-temperature vibration box (17), which fits closely with the outer dimensions of the smoke extractor (18).

5. The high-temperature vibration device for large carbon fiber resin matrix composite structural components according to claim 1, characterized in that: A Φ60mm circular hole is opened on the right side of the high temperature vibration chamber (17). The oxyacetylene torch (3) passes through the circular hole and is fixed to one end of the large carbon fiber resin-based composite material structural component (1) to provide a high temperature ablation environment. A 200mm×30mm×50mm vibration measuring port (12) is opened on the top of the high temperature vibration chamber (17). The vibration measuring port (12) is made of fiberglass that can withstand 1200℃.

6. The high-temperature vibration device for large carbon fiber resin matrix composite structural components according to claim 1, characterized in that: The platinum-rhodium thermocouple (14) passes through the right side of the high-temperature vibration chamber (17) and the support (5) to measure the temperature of the large carbon fiber resin-based composite structural component (1).

7. The high-temperature vibration device for large carbon fiber resin matrix composite structural components according to claim 1, characterized in that: The sliding truss is fixed to the top of the high-temperature vibration box (17), and it consists of a support frame (11), a slide rail (7), a sliding truss one (8) and a sliding truss two (9). The sliding truss one (8) and the sliding truss two (9) are fixedly installed through the top and middle through holes of the laser vibration meter (10) and slide laterally and longitudinally on the slide rail.

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