High-temperature vibration modal test device for variable-cross-section carbon fiber resin matrix composite

Abstract

Provided in the present invention is a high-temperature vibration modal test device for a variable-cross-section carbon fiber resin matrix composite. The high-temperature vibration modal test device comprises a triangular serrated slide rail, a high-temperature steel sliding bayonet, a sliding furnace door, a water cooling conduit, a dual-axis slide rail, a thermal insulation chamber, an infrared radiation heating array, a sheet-type armored thermocouple, an observation port, a tapped threaded rod, a tapped threaded fixture, a ceramic force transmission rod, a vibration exciter, a laser vibrometer, a vibration measurement port, a mechanical pump and an exhaust valve. A variable-cross-section test piece for a carbon fiber resin matrix composite is fixed to the high-temperature steel sliding bayonet, and is fixed to the tapped threaded fixture by means of the dual-axis slide rail. When a high-temperature vibration modal test is performed, the infrared radiation heating array provides a high-temperature thermal environment, the vibration exciter is connected to the tapped threaded fixture to provide random vibration, and thermal modal measurement is performed by means of the laser vibrometer. The present invention provides a test means for the high-temperature vibration modal test of the variable-cross-section carbon fiber resin matrix composite in an aerospace flight environment.

Description

High temperature vibration modal test device for variable cross-section carbon fiber resin matrix composites Technical Field

[0001] The invention relates to the field of aerospace, and in particular to a high-temperature vibration modal experimental device for a variable-section carbon fiber resin-based composite material. Background Art

[0002] Resin-based composites are widely used in the automotive, transportation, and aviation industries due to their lightweight, high strength, high stiffness, and excellent corrosion resistance. Currently, composite materials account for 20-50% of the total weight of advanced aircraft worldwide, primarily in wings, fuselages, turbine blades, satellite antenna covers, fairings, and rocket engines. However, with the advancement of hypersonic vehicle research, increasing research interest has emerged in the performance of resin-based composite components under extreme flight conditions. In particular, the intense aerodynamic loads and high temperatures (above 1000°C) generated during flight generate uneven thermal deformation and stress within the material structure, causing changes in structural stiffness and modal properties, which in turn affect the stability and controllability of the aircraft during flight. Therefore, it is imperative to develop a high-temperature vibration modal testing facility to simulate the vibration and thermal environments experienced during flight. High-temperature modal testing of carbon fiber resin-based composite components under various thermomechanical coupling conditions is crucial for determining the high-temperature vibration modal parameters and guiding the feasibility of aircraft designs under these extreme flight conditions.

[0003] At present, most of the high-temperature vibration modal devices are built for alloy structural parts, and only a small number of them are used to carry out modal tests on carbon fiber resin-based composite materials. However, they have not yet been able to conduct thermal modal experiments in environments above 1000°C. In addition, the high temperature environment that existing carbon fiber resin-based composite structural parts are subjected to during flight is higher than 1000°C, and the maximum temperature resistance of high-temperature acceleration sensors is 650°C. Therefore, the traditional method of attaching acceleration sensors to the surface of the material to obtain dynamic vibration signals is no longer applicable. At the same time, when carbon fiber resin-based composite materials are heated at high temperatures, the resin will decompose and produce a large amount of gas, which has a great impact on the experimental environment and the health of the experimenters. Therefore, researchers urgently need to build a high-temperature modal test device that can perform high-temperature modal testing on carbon fiber resin-based composite materials at temperatures above 1000°C and develop a method that can obtain high-temperature modal parameters in a safe and controllable experimental environment.

[0004] Summary of the Invention

[0005] To solve the above problems, the present invention discloses a high-temperature vibration modal experimental device suitable for variable-section carbon fiber resin-based composite materials. The device can provide a thermal vibration high-temperature environment of more than 1000°C for the carbon fiber resin-based composite material test piece while obtaining the change law of the high-temperature vibration modal response, and can form a closed space to effectively process the decomposition gas, providing a stable, safe and reliable experimental environment. The device provides an experimental basis for the stability and design feasibility of variable-section carbon fiber resin composite structural parts in aerospace flight environments.

[0006] A variable-section carbon fiber resin-based composite material high-temperature vibration modal experimental device comprises: a variable-section carbon fiber resin-based composite material test piece, a triangular zigzag slide rail, a high-temperature steel sliding bayonet, a sliding furnace door, a water-cooling pipe, a biaxial slide rail, an insulation box, an infrared radiation heating array, a thin-film armored thermocouple, an observation port, a tapping threaded rod, a tapping threaded fixture, a ceramic force transmission rod, an excitation source, a laser vibrometer, a vibration measuring port, a mechanical pump, an exhaust valve, a first connecting rod, a second connecting rod, a first Falun disk, and a second Falun disk; the variable-section carbon fiber resin-based composite material test piece is fixed to the sliding furnace door via steel bolts, the triangular zigzag slide rail, and the high-temperature steel sliding bayonet to form a cantilever structure;

[0007] The sliding furnace door sends the variable-section carbon fiber resin-based composite material test piece to the tapping thread fixture through a dual-axis slide rail, and clamps one end of the variable-section carbon fiber resin-based composite material test piece; the excitation source applies random vibration to the variable-section carbon fiber resin-based composite material through a high-temperature resistant ceramic force transmission rod and a tapping thread fixture; an infrared radiation heating array is arranged on the upper end of the variable-section carbon fiber resin-based composite material test piece, which can provide a high temperature of more than 1000°C, simulating the real environment of single-sided high-temperature heating during flight; on the top of the insulation box, a laser vibrometer passes through the infrared radiation lamp tubes through the vibration measuring port and acts on the variable-section carbon fiber resin-based composite material test piece, measures the high-temperature vibration response of the variable-section carbon fiber resin-based composite material test piece, and obtains the high-temperature modal parameters.

[0008] The middle part of the sliding furnace door of the present invention is fixedly connected to a triangular serrated slide rail, and the high-temperature steel bayonet on the triangular serrated slide rail horizontally fixes and clamps one end of a variable-section carbon fiber resin-based composite material test piece. The dual-axis slide rail slides the variable-section carbon fiber resin-based composite material test piece horizontally fixed and clamped on the sliding furnace door to the tapping thread fixture in the middle of the box. The tapping thread fixture clamps the other end of the variable-section carbon fiber resin-based composite material test piece, and the tapping thread fixture is fixedly connected to the ceramic force transmission rod.

[0009] Since the present invention is suitable for variable-section carbon fiber resin-based composite material test pieces, triangular serrated slide rails with a side length of 400 mm and symmetrically distributed up and down are fixedly connected on the sliding furnace door by steel bolts, and the high-temperature sliding bayonet is fixed and slides through the serrated slide rails. Two high-temperature sliding bayonet are fixed on each triangular serrated single-sided slide rail, and six high-temperature sliding bayonet are distributed on one triangular serrated slide rail. The triangular serrated slide rails symmetrically distributed up and down are spaced 20 mm apart, which can stably clamp flat parts and conical parts, etc. Triangular water-cooling ducts are installed on the periphery of the two triangular serrated slide rails to continuously cool the triangular serrated slide rails. The high-temperature sliding bayonet is made of chromium-aluminum alloy steel that can withstand high temperatures of 1400°C to ensure the stability of clamping in a high-temperature environment.

[0010] Since the present invention needs to provide a high-temperature environment of more than 1000°C for the variable-section resin-based composite material, the carbon fiber resin-based composite material will produce a large amount of irritating gases and smoke when heated and burned in the high-temperature environment, which will have a certain impact on the experimental environment and the health of the experimenters. The mechanical pump and exhaust valve described in the present invention are respectively installed on both sides of the insulation box body, the first wheel fixes the mechanical pump at the lower end of one side of the insulation box body, and the second wheel fixes the exhaust valve at the upper end of one side of the insulation box body. During the high-temperature experiment, inert gas argon is continuously introduced from the mechanical pump to place the entire box body in a protective gas to prevent the carbon fiber resin-based composite material from burning. At the same time, the protective gas introduced from the lower end gradually accumulates and discharges the large amount of irritating gases and smoke generated during heating from the exhaust valve, providing a safe and stable experimental environment.

[0011] Due to the particularity of variable-section carbon fiber resin-based composite materials, it is not appropriate to use a bolt and nut locking method to fix them to the exciter to provide random vibration. This method is easy to damage the internal structure of the carbon fiber resin-based composite material and affect the accuracy of high-temperature modal testing. Under the premise of not destroying the overall structure of the variable-section carbon fiber resin-based composite material test piece, the present invention applies excitation to the variable-section carbon fiber resin-based composite material test piece through a high-temperature resistant ceramic force transmission rod and a tapping thread clamp. The tapping thread clamp is composed of a tapping thread rod, a bolt and a bayonet. It is rigidly connected to the high-temperature resistant ceramic rod through a bolt. The bolt rod can be rotated to adjust the horizontal distance between the clamp and the variable-section carbon fiber resin-based composite material test piece, thereby fixing one end of the variable-section carbon fiber resin-based composite material test piece.

[0012] Because the present invention requires vibration excitation for a variable-section carbon fiber resin-based composite test piece, a high-temperature ceramic rod is connected to the exciter through a 25mm stepped opening at the bottom of the insulated box. This stepped opening effectively ensures the rod's upward and downward movement margin during excitation. The rod has a diameter of 23mm, ensuring stiffness and strength under high-temperature testing. A force sensor is mounted on its external extension to record the force applied by the exciter during vibration.

[0013] The double-axis slide rail connects the sliding furnace door and the heat preservation box body in a sliding manner. The double-axis slide rail is installed on both sides of the bottom of the heat preservation box body and is composed of 4 high-strength steel connecting rods, which can slide the furnace door stably and quickly.

[0014] The thin-sheet armored thermocouple can withstand high temperatures of 1200°C. It passes through four Φ4mm small holes evenly distributed on the first and second law wheel disks to connect to a temperature recorder to measure the temperature of the upper and lower surfaces of the variable-section carbon fiber resin-based composite material test piece.

[0015] The 200mm×25mm×50mm vibration measuring port is opened on the top outside the heat preservation box, and the vibration measuring port is made of glass fiber reinforced plastic that can withstand 2000°C.

[0016] The 200mm x 200mm x 50mm observation port, made of fiberglass reinforced plastic (FRP) that can withstand temperatures up to 2000°C, is located on the back of the insulation box. Opening the port allows for an adjustable tapping fixture to secure one end of a variable-section carbon fiber resin-based composite test piece and observe its changes during high-temperature vibration measurement.

[0017] Working principle of the present invention:

[0018] The sliding furnace door features 12 symmetrical, high-temperature sliding bayonets secured by steel bolts, suitable for clamping flat and conical carbon fiber composite (CFRP) components. A dual-axis slide rail transports the variable-section CFRP test piece to a tapping fixture for one-end support. Parallel infrared radiation heating arrays arranged at the top of the insulated chamber provide radiant heating exceeding 1000°C to the top surface of the variable-section CFRP test piece, simulating the extreme aerodynamic thermal environment experienced during actual flight. A vibrator, utilizing a high-temperature ceramic dowel rod and tapping fixture, provides vibration testing on the variable-section CFRP test piece, creating a coupled thermal-vibration environment.

[0019] Since traditional acceleration sensors cannot work properly in extremely high temperature environments, a laser vibrometer laser is used to pass through the vibration measuring port and an infrared radiation heating array to measure the vibration of the variable cross-section carbon fiber resin-based composite material to obtain high-temperature vibration modal parameters. The mechanical pump on the outside of the insulation box continuously introduces inert gas argon to ensure that the variable cross-section carbon fiber resin-based composite material test piece is tested at high temperature in a protective gas to prevent combustion. The exhaust valve continuously discharges the smoke and irritating gas generated by the high-temperature test to provide a stable and safe experimental environment. The present invention can realize thermal vibration coupling testing of variable cross-section carbon fiber resin-based composite material test pieces in a safe and stable experimental environment, and provide a test means for the stability and design feasibility of variable cross-section carbon fiber resin composite material structures in an aerospace flight environment.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] (1) The vast majority of existing experimental technologies are aimed at alloy structural parts, and only a small number of them are used to conduct modal tests on carbon fiber resin-based composite materials. However, most of them are tested at 400℃-600℃, and thermal modal experiments have not yet been conducted in an environment above 1000℃. At the same time, due to the particularity of carbon fiber resin-based composite materials, it is not suitable to drill holes on the surface of the material and use bolts and nuts to lock it. This method is easy to damage the internal structure of the carbon fiber resin-based composite material and affect the accuracy of high-temperature modal testing. The present invention uses an infrared radiation heating array to simulate an extreme aerodynamic thermal environment above 1000℃ for a variable-section carbon fiber resin-based composite material test piece. The exciter applies random vibration to the variable-section carbon fiber resin-based composite material test piece through a ceramic force transmission rod and a tapping thread fixture to simulate a thermal vibration coupling environment. The laser vibrometer laser passes through the vibration measuring port and the infrared radiation heating array to measure the vibration of the variable-section carbon fiber resin-based composite material to obtain high-temperature vibration modal parameters. The advantage of the present invention is that it can carry out high-temperature modal test experiments above 1000°C without destroying the overall structure of the carbon fiber resin-based composite material, providing a test means for the stability and design feasibility of variable-section carbon fiber resin composite structural parts in aerospace flight environments.

[0022] (2) The present invention is applicable to carbon fiber resin-based composite material test pieces of different cross-sections. Triangular zigzag rails are symmetrically distributed up and down on the sliding furnace door, fixedly connected by steel bolts. Each triangular zigzag rail has six high-temperature steel sliding bayonets, which can slide freely on the triangular zigzag rails. The twelve high-temperature steel sliding bayonets can be arranged arbitrarily to accommodate the clamping of carbon fiber resin-based composite material test pieces of different cross-sections.

[0023] (3) The present invention is suitable for vibration testing of carbon fiber resin-based composite material test pieces of different lengths. A tapping thread fixture is used to fix the front end of the variable-section carbon fiber resin-based composite material test piece. The tapping thread fixture is composed of a tapping thread rod, a bolt, and a bayonet. The front end of the tapping thread rod is fixedly connected to the bayonet. Rotating the tapping thread rod can adjust the bayonet position to match the clamping structure. The exciter performs vibration testing on the carbon fiber resin-based composite material test pieces of different lengths through the ceramic force transmission rod and the tapping thread fixture.

[0024] (4) The present invention can provide a safe and stable experimental environment. Since carbon fiber resin-based composite materials will produce a large amount of irritating gases and smoke when heated and burned in a high-temperature environment, it will have a certain impact on the experimental environment and the health of the experimenters. The mechanical pump on the outside of the thermal insulation box of the present invention continuously introduces inert gas argon to ensure that the variable-section carbon fiber resin-based composite material test pieces are tested at high temperature in a protective gas to prevent combustion. The exhaust valve continuously discharges the smoke and irritating gases generated by the high-temperature test, detects the gas concentration in the thermal insulation box, and provides a stable and safe experimental environment.

[0025] (5) Since the steel triangular zigzag slide rail needs to withstand thermal loads in extreme environments, high temperature environments will affect its stiffness and strength. The present invention welds a steel water-cooling pipe on the edge of the triangular zigzag slide rail. During the experiment, flowing water is passed through the water-cooling pipe to cool the triangular zigzag slide rail, ensuring that the triangular zigzag slide rail works normally during high-temperature testing.

[0026] (6) Since the maximum temperature tolerance of current high-temperature acceleration sensors is 650°C, they cannot operate normally in extreme thermal environments. The present invention adopts a laser vibration measurement method, opens a fiberglass vibration measurement port that can withstand 2000°C on the top of the box, and uses a laser vibrometer to perform vibration testing on a variable-section carbon fiber resin-based composite test piece to obtain high-temperature vibration dynamic response parameters. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] FIG1 is a front view of the present invention;

[0028] FIG2 is a rear view of the present invention;

[0029] FIG3 is a side view of the present invention;

[0030] FIG4 is a cross-sectional view of the present invention;

[0031] FIG5 is an enlarged view of the clamp of the present invention. DETAILED DESCRIPTION

[0032] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. It should be understood that the following specific embodiments are intended only to illustrate the present invention and are not intended to limit the scope of the present 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 "inward" and "outward" refer to directions toward or away from the geometric center of a particular component, respectively.

[0033] As shown in Figures 1, 2, 3, 4 and 5, the present invention consists of a triangular serrated slide rail 1, a high-temperature steel sliding bayonet 2, a sliding furnace door 3, a water-cooling pipe 4, a dual-axis slide rail 5, an insulation box 6, an infrared radiation heating array 7, a thin-film armored thermocouple 8, an observation port 9, a tapping threaded rod 10, a tapping threaded fixture 11, a ceramic force transmission rod 12, an excitation source 13, a laser vibrometer 14, a vibration measuring port 15, a mechanical pump 16, an exhaust valve 17, a connecting rod 18, a connecting rod 2 19, a Falun disk 1 20 and a Falun disk 2 21.

[0034] The variable-section carbon fiber resin-based composite material test piece (flat or conical) is fixed to the sliding furnace door 3 via a triangular zigzag slide 1 and a high-temperature steel sliding bayonet 2, forming a cantilever structure. A water-cooling duct 4 is welded around the triangular zigzag slide 1 to cool the triangular zigzag slide 1 by introducing flowing water. The variable-section carbon fiber resin-based composite material test piece (flat or conical) is transported to an insulated box 6 by a dual-axis slide 5. An infrared radiation heating array 7 is installed at the upper end of the variable-section carbon fiber resin-based composite material test piece (flat or conical) to provide a high temperature of over 1000°C. Thin-film armored thermocouples 8 pass through the law wheels on both sides of the insulated box 6 and are attached to the upper and lower surfaces of the variable-section carbon fiber resin-based composite material test piece (flat or conical). The surface and back temperatures of the test piece are monitored in real time, simulating the extreme aerodynamic thermal environment during actual flight. Through the observation port 9 on the back of the insulated box 6, a tapping threaded rod 10 and tapping threaded fixture 11 are adjusted to clamp one end of the variable-section carbon fiber resin-based composite test piece (flat or conical). The lower end of the tapping threaded rod 10 is connected to a ceramic force transmission rod 12 and an excitation source 13, which provide random vibration to the variable-section carbon fiber resin-based composite test piece (flat or conical), simulating the vibration state of the test piece during actual flight. A laser vibrometer 14 measures the vibration of the variable-section carbon fiber resin-based composite test piece (flat or conical) through the vibration measurement port 15 to obtain modal parameters under extreme thermal-vibration coupling conditions.

[0035] Since the high temperature environment in which the variable cross-section carbon fiber resin-based composite material test piece (flat piece or conical piece) is located is above 1000°C, the variable cross-section carbon fiber resin-based composite material test piece (flat piece or conical piece) will produce a large amount of smoke in an extremely high temperature thermal environment. Therefore, a mechanical pump 16 and an exhaust valve 17 are provided on both sides of the thermal insulation box 6. The mechanical pump 16 introduces inert gas argon, so that the entire thermal insulation box 5 is filled with an inert atmosphere. During the experiment, the mechanical pump 16 and the exhaust valve 17 continue to work to avoid the generation of a large amount of smoke and the occurrence of combustion. The present invention can realize the thermal vibration coupling test of the variable cross-section carbon fiber resin-based composite material test piece in a safe and stable experimental environment, and provide a test means for the stability and design feasibility of the variable cross-section carbon fiber resin composite material structural parts in the aerospace flight environment.

[0036] The technical means disclosed in the solution of the present invention are not limited to the technical means disclosed in the above-mentioned embodiment, but also include technical solutions composed of any combination of the above technical features.

Claims

1. Variable cross-section carbon fiber resin matrix composite high-temperature vibration mode test device, characterized in that: Including: Variable cross-section carbon fiber resin matrix composite test piece, triangular serrated slide rail (1), high-temperature steel sliding bayonet (2), sliding furnace door (3), water-cooled conduit (4), biaxial slide rail (5), heat preservation box (6), infrared radiation heating array (7), thin-film sheathed thermocouple (8), tapped threaded rod (10), tapped thread fixture (11), ceramic force transmission rod (12), vibration exciter (13), laser vibrometer (14), vibration measurement port (15), mechanical pump (16) and exhaust valve (17); the sliding furnace door (3) is slidably connected to the biaxial slide rail (5), the center of the sliding furnace door (3) is connected to the high-temperature steel sliding bayonet (2) through a fixed steel bolt, and the variable cross-section carbon fiber resin matrix composite test piece is horizontally fixed; the biaxial slide rail (5) transports and fixes the variable cross-section carbon fiber resin matrix composite test piece to the tapped thread fixture (11), the ceramic force transmission rod (12) extends outside the heat preservation box (6) and is connected to the vibration exciter (13), an infrared radiation heating array (7) is installed at a position 30 - 40 mm above the upper surface of the variable cross-section carbon fiber resin matrix composite test piece, thin-film sheathed thermocouples (8) are installed on the upper and lower surfaces of the variable cross-section carbon fiber resin matrix composite test piece and connected to a temperature recorder (8) outside the heat preservation box, inert gas is introduced into the heat preservation box (6) through the mechanical pump (16) and the exhaust valve (17), a vibration measurement port (15) is opened at the top of the heat preservation box (6), and the laser of the laser vibrometer (14) penetrates through the vibration measurement port (15) and the infrared radiation heating array (7) and projects onto the upper surface of the variable cross-section carbon fiber resin matrix composite test piece to measure the vibration high-temperature mode of the variable cross-section carbon fiber resin matrix composite test piece.

2. The high-temperature vibration mode test device for variable cross-section carbon fiber resin matrix composite materials according to claim 1, characterized in that: On the sliding furnace door (3), two upper and lower symmetric triangular serrated slide rails (1) are fixedly connected by steel bolts. There are 2 high-temperature steel sliding bayonets (2) on each of the three single sides of each triangular serrated slide rail (1), and a total of 6 high-temperature steel sliding bayonets (2) are installed on the three sides. The high-temperature steel sliding bayonets (2) are tightly nested and matched with the serrated slide rail; the variable cross-section carbon fiber resin matrix composite test piece is fixed on the sliding furnace door (3) through the triangular serrated slide rail (1) and the high-temperature steel sliding bayonet (2) to form a cantilever structure.

3. The variable cross-section carbon fiber resin matrix composite material high-temperature vibration mode test device according to claim 1, characterized in that: A water-cooled conduit (4) is welded around the triangular serrated slide rail (1) to cool the triangular serrated slide rail (1) by introducing flowing water.

4. The variable cross-section carbon fiber resin matrix composite material high-temperature vibration mode test device according to claim 1, wherein: The biaxial slide rail (5) connects the sliding furnace door (3) and the heat preservation box body (6) and is composed of 4 connecting rods. The connecting rod one (18) on the single-side slide rail is nested and slidably connected in the connecting rod two (19). The length of each connecting rod is 400 mm, and the total length of the slide rail is 600 mm.

5. The variable cross-section composite material high-temperature vibration mode test device according to claim 1, characterized in that: Each infrared radiation lamp tube is arranged at an interval of 50 mm on the top of the heat preservation box (6), and the laser of the laser vibrometer (14) passes through the space between the infrared radiation lamp tubes and acts on the variable cross-section carbon fiber resin matrix composite test piece.

6. The variable cross-section carbon fiber resin matrix composite material high-temperature vibration mode test device according to claim 1, wherein: The described ceramic load transfer bar (12) is connected by a steel bolt to a tapping thread fixture (11) and is arranged inside the heat preservation box body (6). The tapping thread fixture (11) consists of a tapping threaded rod, a bolt, and a bayonet. The front end of the tapping threaded rod is fixedly connected to the bayonet, and by rotating the tapping threaded rod, the position of the bayonet can be adjusted to cooperate with clamping the front end of the variable cross-section carbon fiber resin matrix composite test piece.

7. The variable cross-section carbon fiber resin matrix composite material high-temperature vibration modal test device according to claim 1, characterized in that: The size of the vibration measurement port (15) is 200mm×25mm×50mm, and the vibration measurement port (15) is made of fiberglass that can withstand 2000°C; a Φ25mm stepped hole is opened at the bottom of the heat preservation box (6), and the ceramic load transfer bar (12) passes through the stepped hole and is rigidly connected to the tapping threaded rod, providing a margin for up and down vibration for the ceramic load transfer bar.

8. The high-temperature vibration mode test device for variable cross-section carbon fiber resin matrix composite materials according to claim 1, wherein: An observation port with a size of 200mm×200mm×50mm is opened on the back of the heat preservation box (6), and the observation port is made of fiberglass that can withstand 2000°C.

9. The high-temperature vibration mode test device for variable cross-section carbon fiber resin matrix composite materials according to claim 1, characterized in that: The mechanical pump (16) and the exhaust valve (17) are respectively installed on both sides of the heat preservation box (6). The first flange (20) fixes the mechanical pump at the lower end on one side of the heat preservation box (6), and the second flange (21) fixes the exhaust valve (17) at the upper end on one side of the heat preservation box (6). Four Φ4mm small holes are evenly distributed on the first flange and the second flange, and the thermocouple passes through the small holes to connect the upper and lower surfaces of the variable cross-section carbon fiber resin matrix composite test piece and the temperature recorder outside the heat preservation box.

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