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

Abstract

The invention provides a high-temperature vibration device suitable for a carbon fiber resin-based composite material large-scale structural member. The high-temperature vibration device comprises the carbon fiber resin-based composite material large-scale structural member, a variable-caliber supporting device, an oxyacetylene flame gun, a threaded ejector rod, a supporting body, a base adapter plate, a laser vibration meter, a supporting frame, a vibration measuring opening, a vent valve, a platinum-rhodium thermocouple and a vibration table. The carbon fiber resin matrix composite large-scale structural part is fixed to a supporting body of the vibration table, the oxyacetylene flame gun moves to extend to one end of the carbon fiber resin matrix composite large-scale structural part, and the aperture supporting device fixes the oxyacetylene flame gun into the carbon fiber resin matrix composite large-scale structural part. The flame gun provides a high-temperature ablation thermal environment, the vibration table is fixedly connected with the supporting body to provide random vibration excitation, the laser vibration meter penetrates through the high-temperature vibration box body to collect vibration signals, and a testing means is provided for high-temperature vibration mode testing of the carbon fiber resin matrix composite large-scale structural member in the aerospace flight environment.

Description

Technical Field

[0001] The present invention relates to the field of testing large-scale structural parts of carbon fiber resin-based composite materials in an aerospace flight environment, and in particular to a high-temperature vibration device suitable for large-scale structural parts of carbon fiber resin-based composite materials. Carbon fiber resin-based composite materials are widely used in aerospace, automotive and other fields due to their high strength, high modulus, light weight, corrosion resistance and good thermal stability. At present, large key structural parts such as aircraft wings, tails, engine fan blades, rocket shells, nozzles, etc. are made of carbon fiber resin-based composite materials. However, with the rapid development of hypersonic vehicles, the high-temperature vibration modal change law of large structural parts of carbon fiber resin-based composite materials in extremely complex flight environments has become the research focus of more and more scholars. Especially for carbon fiber resin-based composite materials, extreme aerodynamic environments and high-temperature environments seriously affect the performance of carbon fiber resin-based composite materials. Uneven thermal stress causes high-temperature modal changes in structural parts, which directly affects the stability and safety of aircraft. At the same time, ground modal testing to simulate the real extreme high-temperature vibration flight environment of aircraft is challenging. Therefore, it is urgent to build a high-temperature vibration device suitable for large structural parts of carbon fiber resin-based composite materials, so as to simulate the real working conditions of the flight environment with the ground atmospheric environment, realize the accurate prediction of the high-temperature modal of large structural parts of carbon fiber resin-based composite materials, and guide and verify the design feasibility of aircraft in extreme flight environments.

[0002] At present, the high-temperature vibration modal device of carbon fiber resin-based composite materials is built by using quartz lamps and other radiation heating methods to form an extreme high temperature environment. The uniformly heated environment cannot accurately simulate the uneven ablation during the flight of the aircraft. At the same time, due to the limitations of the melting point of materials such as quartz, heating equipment such as quartz lamps cannot stably provide a high-temperature thermal environment above 1400°C. In addition, large structural parts of carbon fiber resin-based composite materials work in a micro-oxygen environment in a real flight environment, which brings certain challenges to the simulation of the ground atmospheric environment. In addition, carbon fiber resin-based composite materials will produce a large amount of gas in an extremely high temperature environment, which will have a certain impact on vibration measurement and the health of experimental personnel. Therefore, a large number of researchers urgently need to build a high-temperature vibration device suitable for large structural parts of carbon fiber resin-based composite materials, realize the accurate simulation of the real working conditions of micro-oxygen and uneven ablation in the extreme flight environment of the aircraft, and provide a safe and reliable experimental environment for experimental staff to realize the accurate acquisition of high-temperature vibration modes of large structural parts of carbon fiber resin-based composite materials in aerospace flight environments. Summary of the invention

[0003] To solve the above problems, the present invention discloses a high temperature vibration device suitable for large structural parts of carbon fiber resin-based composite materials. The device can provide a non-uniform heating environment and micro-oxygen conditions above 1200°C for large structural parts of carbon fiber resin-based composite materials, while achieving accurate collection of high temperature vibration modes of large structural parts of carbon fiber resin-based composite materials and providing a safe and stable implementation environment for operators. The device provides a test means for the stability and design feasibility of large structural parts of carbon fiber resin-based composite materials in aerospace flight environments.

[0004] The technical solution of the present invention is: A high-temperature vibration device suitable for large-scale structural parts of carbon fiber resin-based composite materials, comprising: large-scale structural parts of carbon fiber resin-based composite materials, a variable-caliber support device, an oxyacetylene flamethrower, a threaded push rod, a support body, a base adapter plate, a slide rail, a sliding truss one, a sliding truss two, a laser vibrometer, 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 box, a smoking machine, a hollow shaft, a high-temperature support sheet and a linkage connecting rod; the support body is fixed to the surface of the vibration table through a high-temperature bolt passing through the base adapter plate, the large-scale structural parts of carbon fiber resin-based composite materials are nested in the conical fixture of the support body, the threaded push rod outside the rotating conical fixture stably fixes the large-scale structural parts of carbon fiber resin-based composite materials, and the vibration table applies a random excitation signal to provide random vibration; the oxyacetylene flamethrower is fixed to the high-temperature vibration table. On the right side of the moving box, the variable-caliber support device is embedded in the inner wall of the oxyacetylene flamethrower. The oxyacetylene flamethrower and the variable-caliber support device are fixed on one side of the large structural part of carbon fiber resin-based composite materials. The hollow shaft of the variable-caliber support device is slid to drive the expansion of 8 linkage rods, and the 8 high-temperature support plates are expanded to the inner wall of the large structural part of carbon fiber resin-based composite materials. The oxyacetylene flamethrower sprays flames through the variable-caliber support device to ablate the inner wall of the large structural part of carbon fiber resin-based composite materials, providing a high-temperature ablation environment of more than 1200°C; the smoking machine on the left side of the high-temperature vibration box effectively absorbs smoke and provides a safe and stable experimental environment; the laser vibrometer on the top of the high-temperature vibration box irradiates the large structural part of carbon fiber resin-based composite materials through the vibration measuring port, collects the high-temperature vibration modal data of the large structural part of carbon fiber resin-based composite materials, and obtains the high-temperature vibration modal parameters.

[0005] Furthermore, the vibration table is connected to the support body through high-temperature bolts passing through the base adapter plate. The support body is composed of a base, a support plate, reinforcement ribs and a conical clamp. The support plate is welded to the middle part of the base of the support body. Two reinforcement ribs are distributed on both sides of the support plate to play a stable support role. The conical clamp is welded on the upper end of the support plate. The outer wall of the conical clamp has threaded push rod holes every 60° in the circumferential direction. The large structural part of carbon fiber resin-based composite material is nested in the conical clamp. Under the premise of not destroying the integrity of the large structural part of carbon fiber resin-based composite material, the threaded push rod and high-temperature glue are rotated to stably fix the large structural part of carbon fiber resin-based composite material to the inner wall of the conical clamp. The vibration table applies random excitation to transmit the excitation signal to the large structural part of carbon fiber resin-based composite material.

[0006] Furthermore, for large-scale structural parts of carbon fiber resin-based composite materials of different calibers, changing the flame spray caliber of the oxyacetylene flame spray gun to adapt to the change of large-scale structural parts of carbon fiber resin-based composite materials is time-consuming and labor-intensive, which affects the progress of the experiment. The variable-caliber support device described in the present invention is composed of a hollow shaft, a linkage connecting rod and a high-temperature support sheet. The hollow shaft is nested in the outer wall of the oxyacetylene flame spray gun for sliding. 8 linkage connecting rods are fixed to the hollow shaft and 8 high-temperature support sheets are arranged in a circumferential direction. The sliding hollow shaft of the variable-caliber support device drives the expansion of the 8 linkage connecting rods, so that the 8 high-temperature support sheets expand to the inner wall of the large-scale structural part of carbon fiber resin-based composite materials. The expansion angle of the high-temperature support sheet changes in time with the caliber size of the inner wall of the large-scale structural part of carbon fiber resin-based composite materials. The variable-caliber support devices are all made of high-temperature alloy steel to meet the ablation temperature requirements and provide stable flame ablation conditions for large-scale structural parts of variable-caliber carbon fiber resin-based composite materials.

[0007] Furthermore, large carbon fiber resin-based composite material structures will produce a lot of smoke and harmful gases under extreme thermal environment ablation, which will cause certain harm to the optical path of laser vibration measurement and the health of laboratory personnel. The smoking machine of the present invention 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 external dimensions of the smoking machine. Under extreme ablation conditions, the lateral suction of the smoking machine effectively sucks out the smoke and guides the flame ablation direction to a certain extent, providing a safe, stable and effective testing environment.

[0008] Since the present invention is suitable for simulating the real flight environment of large carbon fiber resin-based composite material structures with ground environment, the simulation of ablation conditions and airflow scouring is effectively solved by flame spraying of an oxyacetylene flamethrower and flame flow rate regulation. The vent valve of the present invention is installed on the right side of the high-temperature vibration box, and the vent valve is introduced with inert gas such as argon, so that a micro-oxygen environment can be achieved and the generation of ablation smoke can be reduced under the action of protective gas.

[0009] The laser vibrometer of the present invention is fixedly installed at the intersection of the sliding truss 1 and the sliding truss 2 by bolts. The sliding truss moves horizontally and vertically on the slide rail. According to the requirements of the vibration measurement point, the truss slides the laser vibrometer to the designated area to collect high-temperature vibration modal data.

[0010] The platinum-rhodium thermocouple meets the temperature measurement requirements above 1200°C, passes through the law wheel on the right side of the high-temperature vibration box and the support body to connect the large structural parts of carbon fiber resin-based composite materials and the data acquisition instrument outside the high-temperature vibration box to measure the temperature of the large structural parts of carbon fiber resin-based composite materials.

[0011] A Φ510m circular groove is opened at the bottom of the high-temperature vibration box, which closely matches the size of the vibration table surface to provide vibration margin, and the surrounding gaps are filled with insulation cotton.

[0012] The high-temperature furnace door is arranged at the front end of the high-temperature vibration box, so as to facilitate clamping of large structural parts of carbon fiber resin-based composite materials.

[0013] The 300mm×300mm×50mm square groove is opened on the left side of the high-temperature vibration box, which fits closely with the outer dimensions of the smoking machine and absorbs the smoke generated by ablation.

[0014] A Φ60mm circular hole is opened on the right side of the high-temperature vibration box, and an oxyacetylene flame spray gun passes through the circular hole to provide a high-temperature ablation environment.

[0015] The 200mm×30mm×50mm vibration measuring port is opened on the top of the high-temperature vibration box, and the vibration measuring port is made of fiberglass that can withstand 1200℃.

[0016] Working principle of the present invention: The high-temperature bolts are passed through the support base and the base adapter plate to be fixed on the vibration table surface, the external threaded push rod of the conical fixture is rotated and the large structural part of carbon fiber resin-based composite material is glued with high-temperature glue, and the large structural part of carbon fiber resin-based composite material is fixed in the conical fixture. The vibration table applies random excitation to transmit the vibration excitation signal to the large structural part of carbon fiber resin-based composite material. The oxyacetylene flame spray gun passes through the high-temperature vibration box and is fixed to one end of the large structural part of carbon fiber resin-based composite material. The hollow shaft of the variable-caliber support device is slidably fixed to the outer wall of the oxyacetylene flame spray gun. The other end drives the linkage connecting rod to move through the sliding hollow shaft, and the high-temperature support sheet is expanded to the inner wall of the large structural part of carbon fiber resin-based composite material to provide a high-temperature ablation thermal environment above 1200°C. The platinum-rhodium thermocouple passes through the right side of the high-temperature vibration box and the support body, respectively, and connects the large structural part of carbon fiber resin-based composite material and the data acquisition instrument outside the high-temperature vibration box to monitor the temperature change of the large structural part of carbon fiber resin-based composite material during the ablation process. The ventilation valve on the right side of the high-temperature vibration box is introduced with inert gas to simulate the micro-oxygen environment in the flight environment. The smoking machine absorbs the smoke generated by the ablation of large structural parts of carbon fiber resin-based composite materials on the left side of the high-temperature vibration box and guides the direction of flame ablation, providing a safe and stable experimental environment. The laser vibrometer is fixedly installed on the support frame on the top of the high-temperature vibration box. The sliding truss is slid to the vibration measurement point. The laser passes through the vibration measurement port to irradiate the large structural parts of carbon fiber resin-based composite materials to collect high-temperature vibration modal parameters. The present invention can simulate the uneven ablation and micro-oxygen environment of large structural parts of carbon fiber resin-based composite materials during flight in a safe and stable experimental environment on the ground, and realize accurate testing of high-temperature ablation vibration modes of large structural parts of carbon fiber resin-based composite materials, providing experimental means for the stability and design feasibility of large structural parts of carbon fiber resin-based composite materials in aerospace flight environments.

[0017] Compared with the prior art, the present invention has the following beneficial effects: (1) At present, most high-temperature vibration modal test devices are constructed by using quartz lamps and other radiation heating methods to form an extreme high-temperature thermal environment. The uniform heating environment cannot accurately simulate the uneven ablation during the flight of the aircraft. In addition, due to the limitations of the melting point of quartz materials, heating equipment such as quartz lamps cannot stably provide a high-temperature thermal environment above 1400°C. At the same time, since excitation equipment such as exciters cannot provide stable thrust for large-scale structural parts of carbon fiber resin-based composite materials, the stability of high-temperature thermal vibration modal data acquisition is affected. The present invention fixes the oxyacetylene flame spray gun through the interior of the high-temperature vibration box to move to one end of the large-scale structural part of the carbon fiber resin-based composite material, and fixes it to the inner wall of the carbon fiber resin-based composite material through a variable-caliber support device, providing a stable flame ablation working condition and overcoming the limitations of the quartz lamp heating equipment. The vibration table is fixedly connected to the support body by high-temperature bolts, and the random excitation signal is applied by the vibration table to the large-scale structural part of the carbon fiber resin-based composite material fixed to the support body. The laser vibrometer on the top of the high-temperature vibration box passes through the vibration measuring port to collect high-temperature vibration modal data. The advantages of the present invention are that it can provide a relatively stable non-uniform ablation environment above 1200°C, overcome the limitations of the current high-temperature thermal vibration equipment performance, and realize the collection of high-temperature vibration modal data of large structural parts of carbon fiber resin-based composite materials.

[0018] (2) The present invention is suitable for clamping large carbon fiber resin-based composite material structures with different outer diameters. The support body of the present invention is composed of a base, a support plate, reinforcing ribs and a conical clamp. Under the premise of not destroying the integrity of the large carbon fiber resin-based composite material structure, the large carbon fiber resin-based composite material structure is nested and glued in the conical clamp, and the threaded ejector rods distributed 60° in the circumferential direction of the conical clamp are rotated to adapt to the change of the outer diameter of the large carbon fiber resin-based composite material structure.

[0019] (3) The present invention is applicable to the ablation test of large-scale structural parts of carbon fiber resin-based composite materials under different inner diameters. A variable-diameter support device is used to adapt to the change of the inner diameter of large-scale structural parts of carbon fiber resin-based composite materials. The device is composed of a hollow shaft, a linkage connecting rod and a high-temperature support sheet. The hollow shaft slides on the outer wall of the oxyacetylene flame spray gun, driving the linkage connecting rod to move and expand the high-temperature support sheet to the inner wall of the large-scale structural parts of carbon fiber resin-based composite materials. The flame of the oxyacetylene flame spray gun passes through the variable-diameter support device, adheres to the high-temperature support sheet, and ablates the inner wall of the large-scale structural parts of carbon fiber resin-based composite materials to ensure the stability of ablation.

[0020] (4) The present invention can provide a safe and stable experimental environment and achieve the simulation of a 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 exhaust the air inside the box, so that a micro-oxygen environment can be achieved and the generation of ablation smoke can be reduced under the action of protective gas. The smoking machine is located on the left side of the high-temperature vibration box. A square groove is opened on the left side of the high-temperature vibration box to match the external dimensions of the smoking machine. Under extreme ablation conditions, the lateral suction of the smoking machine effectively sucks out the smoke and guides the flame ablation direction to a certain extent, providing a safe, stable and effective test environment.

[0021] (5) The vibration modal data collected by traditional acceleration sensors are affected by extreme ablation temperature and the acceleration lead wire is entangled in the high-temperature vibration box, which causes the acceleration sensor to fall off. In the present invention, a laser vibrometer is arranged on the top of the high-temperature vibration box. 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 structure to obtain the high-temperature vibration modal parameters.

[0022] (6) Since high-temperature vibration modal data needs to be collected at multiple measuring points, the vibration type measurement point requirements are met. The present invention arranges sliding trusses 1 and 2 on the top of the high-temperature vibration box, and the laser vibrometer is fixedly installed on the trusses. According to the measurement point requirements, the sliding trusses slide horizontally and vertically on the slide rails to achieve multi-measurement point modal data collection of large carbon fiber resin-based composite material structures. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a front view of the present invention; Figure 2 It is a rear view of the present invention; Figure 3 A top view of the present invention; Figure 4 is a cross-sectional view of the present invention; Figure 5 It is an enlarged view of the support body and the variable-caliber support device of the present invention; Figure 6 It is a side view of the support body and the variable-caliber support device of the present invention; Figure 7 It is a support assembly diagram of the present invention. DETAILED DESCRIPTION

[0024] The present invention is further explained below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the following specific embodiments are only used to illustrate the present invention and are not used to limit the scope of the present invention. It should be noted that the words "front", "rear", "left", "right", "upper" and "lower" used in the following description refer to directions in the accompanying drawings, and the words "inner" and "outer" refer to directions toward or away from the geometric center of a specific component, respectively.

[0025] like Figure 1, Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 As shown, the high-temperature vibration device of the present embodiment is applicable to large-scale structural members of carbon fiber resin-based composite materials, including a large-scale structural member 1 of carbon fiber resin-based composite materials, a variable-caliber support device 2, an oxyacetylene flamethrower 3, a threaded push rod 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 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, a smoking machine 18, a hollow shaft 19, a high-temperature support sheet 20 and a linkage connecting rod 21.

[0026] The support body 5 base and the base adapter plate 6 are fixed to the vibration table surface by high temperature bolts, the external threaded push rod 4 of the conical fixture is rotated and the large structure 1 of the carbon fiber resin-based composite material is glued with high temperature glue, and the large structure 1 of the carbon fiber resin-based composite material is fixed in the conical fixture of the support body 5. The vibration table 15 applies random excitation to transmit the vibration excitation signal to the large structure 1 of the carbon fiber resin-based composite material. The oxyacetylene flame spray gun 3 is fixed to one end of the large structure 1 of the carbon fiber resin-based composite material through the high temperature vibration box 17, and one end of the variable caliber support device 2 is slidably fixed to the outer wall of the oxyacetylene flame spray gun 3, and the other end drives the linkage connecting rod 21 to move through the sliding hollow shaft 19, so as to expand the high temperature support sheet 20 to the inner wall of the large structure 1 of the carbon fiber resin-based composite material, and provide a high temperature ablation thermal environment above 1200°C. The high-temperature platinum-rhodium thermocouple 14 passes through the law wheel and the support body 5 on the right side of the high-temperature vibration box 17, respectively, and connects the large-scale structural part 1 of the carbon fiber resin-based composite material with the data acquisition instrument 17 outside the high-temperature vibration box to monitor the temperature change of the large-scale structural part of the carbon fiber resin-based composite material during the ablation process. The ventilation valve 13 on the right side of the high-temperature vibration box 17 introduces inert gas to simulate the micro-oxygen environment in the flight environment. The smoking machine 18 on the left side of the high-temperature vibration box 17 absorbs the smoke generated by the ablation of the large-scale structural part 1 of the carbon fiber resin-based composite material and guides the direction of flame ablation, providing a safe and stable experimental environment. The laser vibrometer 10 is fixedly installed on the support frame 11 on the top of the high-temperature vibration box 17. The laser passes through the vibration measuring port 12 to irradiate the large-scale structural part 1 of the carbon fiber resin-based composite material to collect high-temperature vibration modal parameters.

[0027] Since high-temperature vibration modal data needs to be collected at multiple measuring points to meet the vibration type measuring point requirements, the present invention opens transverse and longitudinal through holes at the top and middle of the laser vibrometer, arranges a sliding truss 1 8 on the top of the high-temperature vibration box to pass through the transverse through hole, and a sliding truss 2 9 passes through the longitudinal through hole, and the laser vibrometer is fixedly installed by the sliding truss 1 8 and the sliding truss 2 9. According to the measuring point requirements, the sliding truss 1 8 and the sliding truss 2 9 slide transversely and longitudinally on the slide rail to reach the specified measuring point position to complete the modal data collection.

[0028] The technical means disclosed in the scheme of the present invention are not limited to the technical means disclosed in the above-mentioned implementation mode, but also include technical schemes composed of any combination of the above technical features.

Claims

1. Applicable to high temperature vibration device for large structural parts of carbon fiber resin-based composite materials, characterized by: The invention comprises a large-scale structural member of a carbon fiber resin-based composite material (1), a variable-caliber support device (2), an oxyacetylene flamethrower (3), a threaded push 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 table surface of the vibration table (15) through the base adapter plate (6); the large-scale structural member of a carbon fiber resin-based composite material (1) is fixedly embedded in the support body (5) by the threaded push rod (4); the vibration table (15) provides random excitation to the large-scale structural member of a carbon fiber resin-based composite material (1); the platinum-rhodium thermocouple (14) provides random excitation to the large-scale structural member of a carbon fiber resin-based composite material (1); The electric couple (14) passes through the support body (5) and the surface of the large carbon fiber resin-based composite material structure (1) and is connected to an external data acquisition device. The oxyacetylene flame spray gun (3) is fixedly embedded in the large carbon fiber resin-based composite material structure (1) by the variable-caliber support device (2). Inert gas is introduced into the right side of the high-temperature vibration box (17) through the ventilation valve (13) to simulate the micro-oxygen environment of the large carbon fiber resin-based composite material structure in the high-temperature flight environment, and the left side is connected to the smoke machine (18); smoke generated by the ablation of the large carbon fiber resin-based composite material structure is absorbed. A vibration measuring port (12) is provided at the upper end of the vibration box (17), 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 carbon fiber resin-based composite material structure, so as to collect high-temperature vibration modal data of the large carbon fiber resin-based composite material structure.

2. The high temperature vibration device for large carbon fiber resin-based composite material structures according to claim 1 is 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 provided on the base (51) and are 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). 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). Threaded push rod holes are provided at intervals of 60° along the circumferential direction of the conical fixture (51). 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 oxyacetylene flame spray gun (3) is fixed to one end of a large carbon fiber resin-based composite material structure (1); the variable-caliber support device (2) is embedded in the outer wall of the oxyacetylene flame spray gun (3); the variable-caliber support device comprises a hollow shaft (19), a linkage connecting rod (21) and a high-temperature support sheet (20); the hollow shaft (19) is embedded in the outer wall of the oxyacetylene flame spray gun (3); eight linkage connecting rods (21) are fixed to the hollow shaft (19); eight high-temperature support sheets (20) are arranged in a circumferential direction on the eight linkage connecting rods (21); the hollow shaft (19) slides on the outer wall of the oxyacetylene flame spray gun (3) to drive the eight linkage connecting rods (21) to move, so that the eight high-temperature support sheets (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 calibers.

4. 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 dimensions of the smoking machine (18).

5. The high temperature vibration device for large carbon fiber resin-based composite material structures according to claim 1, characterized in that: A Φ60 mm circular hole is provided on the right side of the high-temperature vibration box (17), and an oxyacetylene flame spray gun (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 200 mm×30 mm×50 mm 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.

6. The high temperature vibration device for large carbon fiber resin matrix 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).

7. 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) are respectively passed through the top and middle through holes of the laser vibrometer (10) to fix the sliding truss 1 (8) and the sliding truss 2 (9) so as to slide horizontally and vertically on the slide rail.

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