High-temperature vibration device suitable for large structural parts of carbon fiber resin matrix composite

Abstract

The application provides a high-temperature vibration device suitable for a carbon fiber resin matrix composite large structure, which comprises a carbon fiber resin matrix composite large structure, a variable-diameter supporting device, an oxyacetylene torch, a threaded ejector rod, a supporting body, a base adapter plate, a laser vibration tester, a supporting frame, a vibration measuring port, a breather valve, a platinum-rhodium thermocouple and a vibration table. The carbon fiber resin matrix composite large structure is fixed on the supporting body of the vibration table, the oxyacetylene torch moves to one end of the carbon fiber resin matrix composite large structure, and the variable-diameter supporting device fixes the oxyacetylene torch in the carbon fiber resin matrix composite structure. The high-temperature ablation thermal environment is provided by the oxyacetylene torch, the random vibration excitation is provided by the vibration table fixedly connected with the supporting body, and the laser vibration tester collects vibration signals through the high-temperature vibration box. The application provides a test method for high-temperature vibration modal testing of the carbon fiber resin matrix composite large structure under the flight environment of aviation and aerospace.

Description

TECHNICAL FIELD

[0001] The application relates to the field of testing of large carbon fiber resin matrix composite structural parts in aerospace flight environments, and particularly relates to a high-temperature vibration device suitable for large carbon fiber resin matrix composite structural parts

[0002] Carbon fiber resin matrix composites are widely used in the fields of aerospace, automobile industry and the like due to high strength, high modulus, light weight, corrosion resistance and good thermal stability. At present, large key structural parts such as aircraft wings, tail wings, engine fan blades, rocket shells and nozzles are manufactured by using carbon fiber resin matrix composites. However, with the rapid development of hypersonic vehicles, the high-temperature vibration mode change rule of the large carbon fiber resin matrix composite structural parts in extreme complex flight environments has become the research focus of more and more scholars. In particular, for carbon fiber resin matrix composites, the extreme aerodynamic environment and high-temperature environment seriously affect the performance of the carbon fiber resin matrix composites, and the non-uniform thermal stress causes the high-temperature mode change of the structural parts, directly affecting the stability and safety of the vehicles. Meanwhile, it is challenging to simulate the real extreme high-temperature vibration flight environment of the vehicles by ground mode testing, and therefore it is urgent to build a high-temperature vibration device suitable for the large carbon fiber resin matrix composite structural parts to simulate the real working conditions of the flight environment in the ground atmospheric environment, accurately predict the high-temperature mode of the large carbon fiber resin matrix composite structural parts, and guide and verify the design feasibility of the vehicles in the extreme flight environment.

[0003] At present, the high-temperature vibration mode device of the carbon fiber resin matrix composites is built by using a quartz lamp and the like to form an extreme high-temperature environment, and the uniform heating environment cannot accurately simulate the non-uniform ablation in the flight process of the vehicles. In addition, due to the limitation of the melting point of quartz and the like, the heating equipment such as the quartz lamp cannot stably provide a high-temperature thermal environment of 1400 DEG C or above. Moreover, the large carbon fiber resin matrix composite structural parts work in a micro-oxygen environment in the real flight environment, which brings certain challenges to the simulation of the ground atmospheric environment. In addition, the carbon fiber resin matrix composites will generate a large amount of gas in the extreme high-temperature environment, which will affect the health of the vibration measurement and experimental personnel. Therefore, a large number of researchers urgently need to build a high-temperature vibration device suitable for the large carbon fiber resin matrix composite structural parts, accurately simulate the real working conditions of the micro-oxygen and non-uniform ablation in the extreme flight environment of the vehicles, and provide a safe and reliable experimental environment for the experimental personnel, so as to accurately collect the high-temperature vibration mode of the large carbon fiber resin matrix composite structural parts in the aerospace flight environment. SUMMARY

[0004] To solve the above problems, the application discloses a high-temperature vibration device suitable for a large carbon fiber resin matrix composite structure, which can provide a non-uniform heating environment above 1200 DEG C and a micro-oxygen working condition for the large carbon fiber resin matrix composite structure, accurately collect high-temperature vibration modes of the large carbon fiber resin matrix composite structure, and provide a safe and stable implementation environment for operators, thereby providing a test means for the stability and design feasibility of the large carbon fiber resin matrix composite structure under an aerospace flight environment.

[0005] The technical solution of the application is:

[0006] The high-temperature vibration device suitable for the large carbon fiber resin matrix composite structure comprises a large carbon fiber resin matrix composite structure, a variable-diameter supporting device, an oxyacetylene torch, a threaded ejector rod, a supporting body, a base adapter plate, a slide rail, a slide truss I, a slide truss II, a laser vibration tester, a supporting frame, a vibration measuring port, a breather valve, a platinum-rhodium thermocouple, a vibration table, a high-temperature furnace door, a high-temperature vibration box body, a smoke suction machine, a hollow shaft, a high-temperature supporting sheet and a linkage connecting rod. The supporting body is fixed on the vibration table surface through high-temperature bolts penetrating through the base adapter plate, the large carbon fiber resin matrix composite structure is nested in the conical clamp of the supporting body, the threaded ejector rod outside the rotating conical clamp stably fixes the large carbon fiber resin matrix composite structure, the vibration table applies a random excitation signal to provide random vibration; the oxyacetylene torch is fixed on the right side of the high-temperature vibration box, the variable-diameter supporting device is nested in the inner wall of the oxyacetylene torch, the oxyacetylene torch and the variable-diameter supporting device are fixed on one side of the large carbon fiber resin matrix composite structure, the hollow shaft of the slide variable-diameter supporting device drives eight linkage connecting rods to expand, eight high-temperature supporting sheets are expanded to the inner wall of the large carbon fiber resin matrix composite structure, the oxyacetylene torch sprays a flame to ablate the inner wall of the large carbon fiber resin matrix composite structure, and a high-temperature ablation environment above 1200 DEG C is provided; the smoke suction machine on the left side of the high-temperature vibration box effectively absorbs smoke to provide a safe and stable experimental environment; the laser vibration tester on the top of the high-temperature vibration box irradiates the large carbon fiber resin matrix composite structure through the vibration measuring port to collect high-temperature vibration mode data of the large carbon fiber resin matrix composite structure and obtain high-temperature vibration mode parameters.

[0007] Further, the vibration table is connected with the support body through high-temperature bolts penetrating through the base adapter plate, the support body is composed of a base, a support plate, reinforcing ribs and a conical clamp, the support plate is welded in the middle of the base of the support body, two reinforcing ribs are distributed on both sides of the support plate to play a stabilizing supporting role, the upper end of the support plate is welded with the conical clamp, the outer wall of the conical clamp is provided with threaded ejector pin holes at intervals of 60° in the circumferential direction, the large-sized carbon fiber resin matrix composite structure is nested in the conical clamp, and the large-sized carbon fiber resin matrix composite structure is stably fixed to the inner wall of the conical clamp by rotating the threaded ejector pin and high-temperature glue bonding without damaging the integrity of the large-sized carbon fiber resin matrix composite structure; and the vibration table applies random excitation to transmit the excitation signal to the large-sized carbon fiber resin matrix composite structure.

[0008] Further, for different calibers of the large-sized carbon fiber resin matrix composite structure, it is time-consuming and laborious to replace the oxyacetylene torch flame jet caliber to adapt to the change of the large-sized carbon fiber resin matrix composite structure, which affects the progress of the experiment. The caliber changing support device comprises a hollow shaft, linkage connecting rods and high-temperature support pieces, the hollow shaft is nested in the outer wall of the oxyacetylene flame gun to slide, eight linkage connecting rods are fixed to the hollow shaft and eight high-temperature support pieces are arranged in the circumferential direction. By sliding the caliber changing support device hollow shaft, eight linkage connecting rods are expanded to make eight high-temperature support pieces expand to the inner wall of the large-sized carbon fiber resin matrix composite structure, and the expansion angle of the high-temperature support piece is changed in time according to the caliber size of the inner wall of the large-sized carbon fiber resin matrix composite structure. The caliber changing support device is made of high-temperature alloy steel to meet the ablation temperature requirement, and provides stable flame ablation working conditions for the caliber changing large-sized carbon fiber resin matrix composite structure.

[0009] Further, a large amount of smoke and harmful gas is generated under the ablation of the large-sized carbon fiber resin matrix composite structure in an extreme thermal environment, which brings certain harm to the optical path of the laser vibration measurement and the health of laboratory personnel. The smoke suction machine of the present application is located on the left side of the high-temperature vibration box, a square groove is formed on the left side of the high-temperature vibration box to match the outer shape size of the smoke suction machine, under the condition of extreme ablation, the smoke suction machine effectively sucks out the smoke and to some extent guides the flame ablation direction, providing a safe, stable and effective test environment.

[0010] Since the present application is applicable to simulate the real flight environment of the large-sized carbon fiber resin matrix composite structure in the ground environment, the ablation working condition and the airflow scouring simulation are effectively solved by the oxyacetylene torch flame jet and the flame flow rate adjustment. The breather valve of the present application is installed on the right side of the high-temperature vibration box body, the breather valve is connected with inert gases such as argon, so that a micro-oxygen environment can be realized and the generation of ablation smoke is reduced under the action of the protective gas.

[0011] The laser vibration measuring instrument is fixedly installed at the intersection of the first sliding truss and the second sliding truss, the sliding trusses move horizontally and longitudinally on the slide rails, according to the demand of vibration measuring points, the trusses slide the laser vibration measuring instrument to the specified area to collect high-temperature vibration modal data.

[0012] The platinum-rhodium thermocouple meets the temperature measuring demand above 1200 DEG C, passes through the right side of the high-temperature vibration box, the carbon fiber resin matrix composite large structural member connected with the support body and the high-temperature vibration box, and connects the data acquisition instrument outside the high-temperature vibration box to measure the temperature of the carbon fiber resin matrix composite large structural member.

[0013] The Φ510m circular groove is arranged at the bottom of the high-temperature vibration box, is closely matched with the size of the vibration table surface, provides vibration margin, and is filled with heat insulation cotton at the surrounding gap.

[0014] The high-temperature furnace door is arranged at the front end of the high-temperature vibration box, and is convenient for clamping the carbon fiber resin matrix composite large structural member.

[0015] The 300mm*300mm*50mm square groove is arranged at the left side of the high-temperature vibration box, is closely matched with the outer size of the smoke suction machine, and absorbs the smoke generated by ablation.

[0016] The Φ60mm circular hole is arranged at the right side of the high-temperature vibration box, the oxygen-ethyne flame spray gun passes through the circular hole to provide a high-temperature ablation environment.

[0017] The 200mm*30mm*50mm vibration measuring port is arranged at the top of the high-temperature vibration box, and the vibration measuring port is composed of glass steel which can withstand 1200 DEG C.

[0018] The working principle of the present application is as follows:

[0019] High temperature bolt is used for fixing the support base and the base adapter plate on the vibration table surface, the rotating conical clamp outer thread top rod and the high temperature glue are used for fixing the large carbon fiber resin matrix composite structure, the vibration table is used for applying random excitation, and the vibration excitation signal is transmitted to the large carbon fiber resin matrix composite structure, the oxygen ethylene torch is fixed to one end of the large carbon fiber resin matrix composite structure through the high temperature vibration box, the variable caliber support device hollow shaft is slidably fixed to the outer wall of the oxygen ethylene torch, the other end is driven by the linkage connecting rod to move, the high temperature support sheet is expanded to the inner wall of the large carbon fiber resin matrix composite structure, and the high temperature ablation thermal environment above 1200 DEG C is provided, the platinum rhodium thermocouple is respectively passed through the high temperature vibration box right side gear disc and the support body, the data acquisition instrument outside the large carbon fiber resin matrix composite structure and the high temperature vibration box is connected, and the temperature change of the large carbon fiber resin matrix composite structure in the ablation process is monitored, the inert gas is introduced into the high temperature vibration box right side air valve, the micro-oxygen environment in the flight environment is simulated, the smoke machine is used for absorbing the smoke generated by the ablation of the large carbon fiber resin matrix composite structure on the left side of the high temperature vibration box and guiding the ablation direction of the flame, and a safe and stable experimental environment is provided, the laser vibration tester is fixedly installed on the support frame on the top of the high temperature vibration box, the sliding truss is slid to the vibration measuring point, the laser passes through the vibration measuring port and irradiates the large carbon fiber resin matrix composite structure, and the high temperature vibration modal parameter is collected.

[0020] Compared with the prior art, the present application has the beneficial effects that:

[0021] (1) At present, most of the high-temperature vibration modal testing devices are built by using quartz lamps and other radiation heating methods to form an extreme high-temperature thermal environment, and a uniform heating environment cannot accurately simulate the non-uniform ablation during the flight of the aircraft. And the heating equipment such as quartz lamp is limited by the melting point of quartz material, and cannot stably provide a high-temperature thermal environment above 1400 DEG C. At the same time, the excitation device such as the exciter cannot provide a stable thrust for the carbon fiber resin matrix composite large structure, which affects the stability of the high-temperature thermal vibration modal data acquisition. The fixed oxygen acetylene flame spray gun moves through the high-temperature vibration box body to one end of the carbon fiber resin matrix composite large structure, is fixed to the inner wall of the carbon fiber resin matrix composite through the variable-diameter supporting device, a stable flame ablation working condition is provided, and the limitation of the quartz lamp heating equipment is overcome. The vibration table is fixedly connected with the support body through high-temperature bolts, a random excitation signal is applied to the carbon fiber resin matrix composite large structure fixed by the support body through the vibration table, and the laser of the laser vibration meter on the top of the high-temperature vibration box body passes through the vibration measuring port to acquire high-temperature vibration modal data. The present application has the advantages that a non-uniform ablation environment above 1200 DEG C can be stably provided, the limitation of the performance of the current high-temperature thermal vibration equipment is overcome, and the high-temperature vibration modal data of the carbon fiber resin matrix composite large structure can be collected.

[0022] (2) The present application is suitable for clamping the carbon fiber resin matrix composite large structure under different outer diameters. The support body of the present application is composed of a base, a support plate, a reinforcing rib and a conical clamp. Under the premise of not damaging the integrity of the carbon fiber resin matrix composite large structure, the carbon fiber resin matrix composite large structure is nested and glued in the conical clamp, and the threaded jacks distributed at an angle of 60 degrees around the conical clamp are rotated to adapt to the change of the outer diameter of the carbon fiber resin matrix composite large structure.

[0023] (3) The present application is suitable for ablation testing of carbon fiber resin matrix composite large structures under different inner diameters. The variable-diameter supporting device is used to adapt to the change of the inner diameter of the carbon fiber resin matrix composite large structure, which is composed of a hollow shaft, a linkage connecting rod and a high-temperature supporting sheet. The hollow shaft slides on the outer wall of the oxygen acetylene spray gun, drives the linkage connecting rod to move and expand the high-temperature supporting sheet to the inner wall of the carbon fiber resin matrix composite large structure, the oxygen acetylene flame spray gun sprays through the variable-diameter supporting device, adheres to the high-temperature supporting sheet and ablates the inner wall of the carbon fiber resin matrix composite large structure, and ensures the stability of ablation.

[0024] (4) The application can provide a safe and stable experimental environment and realize the simulation of micro-oxygen flight environment. The ventilation valve is installed on the right side of the high-temperature vibration box, and inert gases such as argon are introduced to exclude the air inside the box, so that the micro-oxygen environment is realized and the generation of ablation smoke is reduced under the action of protective gas. The smoke suction machine is located on the left side of the high-temperature vibration box, and a square groove is opened on the left side of the high-temperature vibration box to match the size of the smoke suction machine. In the case of extreme ablation, the transverse suction force of the smoke suction machine effectively sucks out the smoke and to some extent guides the ablation direction of the flame, providing a safe, stable and effective test environment.

[0025] (5) Because the traditional acceleration sensor collects vibration modal data, which is affected by the extreme ablation temperature, and the acceleration lead wire is wound in the high-temperature vibration box, which causes the acceleration sensor to fall off and other problems. The laser vibration meter is arranged on the top of the high-temperature vibration box, the laser passes through the high-temperature glass steel vibration measuring port to irradiate the outer surface of the large carbon fiber resin matrix composite structure, and the high-temperature vibration modal parameters are obtained.

[0026] (6) Because the high-temperature vibration modal data needs to be collected by multiple measuring points to meet the vibration mode measuring point requirement. The sliding truss one and the sliding truss two are arranged on the top of the high-temperature vibration box, and the laser vibration meter is fixedly installed on the truss. According to the measuring point requirement, the sliding truss slides horizontally and vertically on the slide rail, realizing the multi-measuring point modal data collection of the large carbon fiber resin matrix composite structure. BRIEF DESCRIPTION OF DRAWINGS

[0027] Figure 1 It is a front view of the application;

[0028] Figure 2 It is a rear view of the application;

[0029] Figure 3 It is a top view of the application;

[0030] Figure 4 It is a sectional view of the application;

[0031] Figure 5 It is an enlarged view of the support body and the variable-diameter support device of the application;

[0032] Figure 6 It is a side view of the support body and the variable-diameter support device of the application;

[0033] Figure 7 It is a combination view of the support body of the application. DETAILED DESCRIPTION

[0034] The present application is further illustrated by the following description and accompanying drawings. It is to be understood that the following description is merely illustrative of the present application and does not limit the scope of the present application. It is to be understood that the terms "front", "back", "left", "right", "top" and "bottom" used in the following description refer to the directions in the drawings. The terms "inner" and "outer" refer to the directions towards or away from the geometric center of a particular component.

[0035] As shown in Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 , the high-temperature vibration device for large carbon fiber resin matrix composite structures of the present embodiment comprises a carbon fiber resin matrix composite large structure 1, a variable-diameter support device 2, an oxyacetylene torch 3, a threaded ejector pin 4, a support body 5, a base adapter plate 6, a slide rail 7, a sliding truss 1 8, a sliding truss 2 9, a laser vibration meter 10, a support frame 11, a vibration measurement 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 smoke absorber 18, a hollow shaft 19, a high-temperature support sheet 20, and a linkage connecting rod 21.

[0036] The base of the support body 5 and the base adapter plate 6 are fixed on the vibration table surface by high-temperature bolts. The threaded ejector pin 4 is rotated and the carbon fiber resin matrix composite large structure 1 is glued to the support body 5. The carbon fiber resin matrix composite large structure 1 is fixed in the conical clamp of the support body 5. The vibration table 15 applies random excitation and transmits the vibration excitation signal to the carbon fiber resin matrix composite large structure 1. The oxyacetylene torch 3 is fixed to one end of the carbon fiber resin matrix composite large structure 1 through the high-temperature vibration box 17. The variable-diameter support device 2 is slidably fixed to the outer wall of the oxyacetylene torch 3 at one end and moves the linkage connecting rod 21 through the sliding hollow shaft 19 at the other end, expanding the high-temperature support sheet 20 to the inner wall of the carbon fiber resin matrix composite large structure 1 to provide a high-temperature ablation thermal environment above 1200°C. The high-temperature platinum-rhodium thermocouple 14 passes through the right side of the high-temperature vibration box 17 and the support body 5, connecting the data acquisition instrument of the carbon fiber resin matrix composite large structure 1 and the high-temperature vibration box 17 to monitor the temperature change of the carbon fiber resin matrix composite large structure during ablation. The vent valve 13 on the right side of the high-temperature vibration box 17 is connected to inert gas to simulate the micro-oxygen environment in the flight environment. The smoke absorber 18 absorbs the smoke generated by the ablation of the carbon fiber resin matrix composite large structure 1 on the left side of the high-temperature vibration box 17 and guides the direction of the flame ablation to provide a safe and stable experimental environment. The laser vibration meter 10 is fixedly installed on the support frame 11 at the top of the high-temperature vibration box 17. The laser passes through the vibration measurement port 12 to irradiate the carbon fiber resin matrix composite large structure 1 to collect high-temperature vibration modal parameters.

[0037] Since high-temperature vibration mode data needs to be collected by multiple measuring points, the vibration mode measuring point requirement is met; the transverse and longitudinal through holes are arranged on the top and middle parts of the laser vibration tester, the sliding truss one 8 passes through the transverse through hole, the sliding truss two 9 passes through the longitudinal through hole, and the laser vibration tester is fixedly installed by the sliding truss one 8 and the sliding truss two 9. According to the measuring point requirement, the sliding truss one 8 and the sliding truss two 9 slide transversely and longitudinally on the slide rail, reach the specified measuring point position, and complete the mode data collection.

[0038] The technical means disclosed in the scheme of the present application is not limited to the technical means disclosed in the above-mentioned embodiments, but also includes the technical solutions composed of any combination of the above technical features.

Claims

1. Suitable for high temperature vibration device of large structural parts of carbon fiber resin matrix composite materials, characterized by: The invention comprises a large carbon fiber resin-based composite material structure (1), a variable-caliber support device (2), an oxyacetylene flamethrower (3), a threaded top rod (4), a support body (5), a base adapter plate (6), a laser vibrometer (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), and a smoking machine (18); a high-temperature vibration box (17) is provided on the vibration table (15); a sliding truss is provided on the top of the high-temperature vibration box (17); the support body (5) is fixed to the top of the vibration table (15) by high-temperature bolts passing through the base adapter plate (6). On the surface, the large-scale structural member (1) of carbon fiber resin-based composite material is fixedly embedded in the interior of the support body (5) by a threaded push rod (4), the vibration table (15) provides random excitation to the large-scale structural member (1) of carbon fiber resin-based composite material, the platinum-rhodium thermocouple (14) passes through the support body (5) and the surface of the large-scale structural member (1) of carbon fiber resin-based composite material, and is connected to an external data acquisition instrument, the oxyacetylene flame spray gun (3) is fixedly embedded in the interior of the large-scale structural member (1) of carbon fiber resin-based composite material by a variable-caliber support device (2), and inert gas is introduced into the right side of the high-temperature vibration box (17) through the vent valve (13) to simulate the carbon fiber resin-based composite material. The micro-oxygen environment of the large structural member of the carbon fiber resin-based composite material in the high-temperature flight environment is connected to the left side of the smoking machine (18); the smoke generated by the ablation of the large structural member of the carbon fiber resin-based composite material is absorbed, and the upper end of the vibration box (17) is provided with a vibration measuring port (12), wherein the laser of the laser vibrometer (10) installed on the sliding truss penetrates the vibration measuring port (12) and is projected onto the upper surface of the large structural member of the carbon fiber resin-based composite material, and the high-temperature vibration modal data of the large structural member of the carbon fiber resin-based composite material is collected; the oxyacetylene flame blasting gun (3) is fixed to one end of the large structural member of the carbon fiber resin-based composite material (1), the variable-caliber support device (2) is nested in the outer wall of the oxyacetylene flame blasting gun (3), and the variable-caliber support device (2) is embedded in the outer wall of the oxyacetylene flame blasting gun (3). The diameter support device consists of a hollow shaft (19), a linkage connecting rod (21) and a high-temperature support plate (20), the hollow shaft (19) is nested on the outer wall of the oxyacetylene flame blasting gun (3), and eight linkage connecting rods (21) are fixed on the hollow shaft (19), wherein eight high-temperature support plates (20) are arranged circumferentially on the eight linkage connecting rods (21); the hollow shaft (19) slides on the outer wall of the oxyacetylene flame blasting gun (3) to drive the eight linkage connecting 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), and the sliding distance of the hollow shaft (19) is adjusted to be suitable for flame ablation of large carbon fiber resin-based composite material structures with different diameters.

2. The high-temperature vibration device for large carbon fiber resin-based composite material structures according to claim 1, characterized in that: The support body (5) is composed of a base (51), a support plate (52), a reinforcing rib (53) and a conical fixture (54). Six threaded holes are opened on the base (51) and fixed to the vibration table (15) by high-temperature bolts passing 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 conical fixture (54) is welded to the upper end of the support plate (52), and threaded push rod holes are opened every 60 degrees along the circumference of the conical fixture (54). The threaded push rod is rotated so that the large carbon fiber resin-based composite material structure is fixed inside the conical fixture.

3. The high-temperature vibration device for large carbon fiber resin-based composite material structures according to claim 1, characterized in that: The bottom of the high-temperature vibration box (17) is provided with a circular groove of Φ510 mm, which closely matches the table size of the vibration table (15) to provide a vibration margin; the front side of the high-temperature vibration box (17) is provided with a high-temperature furnace door (16); the left side of the high-temperature vibration box (17) is provided with a square groove of 300 mm×300 mm×50 mm, which closely matches the outer size of the smoker (18).

4. The high-temperature vibration device for large carbon fiber resin-based composite material structures according to claim 1, characterized in that: A Φ60mm circular hole is provided on the right side of the high-temperature vibration box (17), and an oxyacetylene torch (3) is passed through the circular hole and fixed to one end of the large carbon fiber resin-based composite material structure (1) to provide a high-temperature ablation environment; a 200mm×30mm×50mm vibration measuring port (12) is provided on the top of the high-temperature vibration box (17), and the vibration measuring port (12) is made of glass fiber reinforced plastic that can withstand 1200°C.

5. The high-temperature vibration device for large carbon fiber resin-based composite material structures according to claim 1, characterized in that: The platinum-rhodium thermocouple (14) passes through the right side of the high-temperature vibration box (17) and the support body (5) to measure the temperature of the large carbon fiber resin-based composite material structure (1).

6. The high-temperature vibration device for large carbon fiber resin-based composite material structures according to claim 1, characterized in that: The sliding truss is fixed to the top of the high-temperature vibration box (17), and is composed of a support frame (11), a slide rail (7), a sliding truss 1 (8) and a sliding truss 2 (9); the sliding truss 1 (8) and the sliding truss 2 (9) respectively pass through the top and middle through holes of the laser vibrometer (10) and slide horizontally and vertically on the slide rail respectively.

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