CN118050145A - High-temperature vibration mode clamp for carbon fiber resin matrix composite - Google Patents
High-temperature vibration mode clamp for carbon fiber resin matrix composite Download PDFInfo
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- CN118050145A CN118050145A CN202410273783.4A CN202410273783A CN118050145A CN 118050145 A CN118050145 A CN 118050145A CN 202410273783 A CN202410273783 A CN 202410273783A CN 118050145 A CN118050145 A CN 118050145A
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- 239000002131 composite material Substances 0.000 title claims abstract description 85
- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 83
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 83
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 83
- 239000011159 matrix material Substances 0.000 title claims abstract description 79
- 239000011347 resin Substances 0.000 title claims abstract description 79
- 229920005989 resin Polymers 0.000 title claims abstract description 79
- 238000012360 testing method Methods 0.000 claims abstract description 63
- 239000000919 ceramic Substances 0.000 claims abstract description 21
- 238000010438 heat treatment Methods 0.000 claims abstract description 19
- 230000005855 radiation Effects 0.000 claims abstract description 18
- 239000002184 metal Substances 0.000 claims abstract description 12
- 239000000463 material Substances 0.000 claims abstract description 8
- 239000000805 composite resin Substances 0.000 claims abstract description 4
- 230000005284 excitation Effects 0.000 abstract description 10
- 230000008859 change Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 4
- 238000004154 testing of material Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000009529 body temperature measurement Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000004080 punching Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 229910000714 At alloy Inorganic materials 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000003763 carbonization Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000009941 weaving Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/025—Measuring arrangements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/027—Specimen mounting arrangements, e.g. table head adapters
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
- G01N25/20—Investigating or analyzing materials by the use of thermal means by investigating the development of heat, i.e. calorimetry, e.g. by measuring specific heat, by measuring thermal conductivity
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- Pathology (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Immunology (AREA)
- General Health & Medical Sciences (AREA)
- Manufacturing & Machinery (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Reinforced Plastic Materials (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a high-temperature vibration mode clamp for a carbon fiber resin matrix composite, which comprises an infrared radiation heating array, a supporting plate, a sliding supporting frame, a sheet type armoured thermocouple, a carbon fiber resin matrix composite test piece, a sliding clamp, a supporting chute, a ceramic rod, a high-temperature baffle, a sliding supporting plate, a metal bracket, a high-temperature sliding block, a vibration exciter and a high-temperature threaded ejector rod. During high-temperature vibration mode test, one end of a carbon fiber resin matrix composite test piece is fixed on the sliding support frame, the other end of the carbon fiber resin matrix composite test piece is clamped by the ceramic rod connected sliding clamp, the infrared radiation heating array provides a high-temperature environment for the carbon fiber resin matrix composite test piece, and the vibration exciter is connected with the ceramic rod to provide random excitation for the carbon fiber resin matrix composite test piece. The clamping scheme is provided for testing the high-temperature vibration mode of the composite material in the aerospace flight environment on the premise of not damaging the carbon fiber resin-based composite material.
Description
Technical Field
The invention relates to the field of high-temperature environment vibration mode testing of flight components, in particular to a high-temperature vibration mode clamp for a carbon fiber resin matrix composite.
Background
With the development of science and technology, carbon fiber resin matrix composite materials are widely applied to the aspects of aerospace, transportation, automobile manufacturing and the like due to the unique physical and chemical properties of the carbon fiber resin matrix composite materials. In particular, in the field of aerospace, the composite material is processed and manufactured into key parts of a large-sized aircraft due to light weight, high strength and good corrosion resistance, and plays a role in importance. However, with the rapid development of high overspeed aircrafts, the ablation resistance and vibration fatigue damage resistance of carbon fiber resin matrix composite materials under severe high-temperature flying environments are increasingly focused by researchers. Particularly, the structural performance of the carbon fiber resin matrix composite aircraft is changed under the vibration action of a high-temperature environment, and the stability and the service life of the aircraft are directly influenced by the modal dynamic change under the high-temperature vibration, so that scientific researchers need to perform high-temperature vibration tests on the carbon fiber resin matrix composite, perform good simulation prediction on test components in the flying process of the high-temperature environment on the ground, and perform research on the damage mechanism of the flying components by the high-temperature vibration.
In order to accurately acquire the vibration mode parameters of the test member, the structural integrity is ensured as a primary condition, and particularly for the carbon fiber resin matrix composite material, the special manufacturing process of the carbon fiber resin matrix composite material leads to large differences between the internal structure and the metal material, and the layering thickness and layering angle of the fiber can influence the vibration mode parameters, so that punching and fixing cannot be carried out on the surface of the material, and the structural integrity is damaged. Meanwhile, under the action of high-temperature environment above 1000 ℃, the structural performance of the carbon fiber resin matrix composite material is changed severely, the carbonization of the material is serious, and the overall rigidity is reduced, so that a certain challenge is brought to the stable clamping of the carbon fiber resin matrix composite material test piece. Therefore, research and development of a high-temperature vibration mode test fixture for the carbon fiber resin matrix composite is needed, a high-temperature environment of more than 1000 ℃ can be provided stably, the carbon fiber resin matrix composite can be clamped stably, the integrity of the material is not damaged, the accurate acquisition of the high Wen Motai parameters of the test piece is realized, and an experiment and a clamping method are provided for the vibration mode data acquisition of the carbon fiber resin matrix composite flying components in the aerospace high-temperature flying environment.
Disclosure of Invention
In order to solve the problems, the invention discloses a high-temperature vibration mode clamp for a carbon fiber resin matrix composite, which can be used for stably clamping a flying component under the premise of not damaging the carbon fiber resin matrix composite when a high-temperature vibration mode of the flying component is tested at a temperature of more than 1000 ℃ in the aerospace field, so as to obtain the accurate vibration mode dynamic change rule of the flying component, and provide experiments and clamping means for the data acquisition of the vibration mode of the flying component of the carbon fiber resin matrix composite under the aerospace high-temperature flight environment.
The high-temperature vibration mode clamp for the carbon fiber resin-based composite material comprises an infrared radiation heating array, a supporting plate, a sliding supporting frame, a thin-sheet type armored thermocouple, a carbon fiber resin-based composite material test piece, a ceramic rod, a sliding supporting plate, a metal bracket, a high-temperature sliding block, a vibration exciter and a high-temperature threaded ejector rod; the sliding support frame is in sliding connection with the metal support through a high-temperature sliding block; the support plate is arranged at one end of the sliding support frame; the upper end is provided with a hole groove, one end of the infrared radiation heating array is fixed in the hole groove of the supporting plate, and the other end of the infrared radiation heating array is fixed on the hole groove of the sliding supporting plate; the carbon fiber resin matrix composite material test piece is arranged on the sliding support frame, and one end of the carbon fiber resin matrix composite material test piece is connected with the sliding clamp assembly; the upper surface and the lower surface of the carbon fiber resin matrix composite test piece are attached to the thin-sheet type armored thermocouple; the sheet type armoured thermocouple is externally connected with a temperature acquisition instrument; the vibration exciter is connected with the sliding clamp assembly through a high-temperature ceramic rod.
The vibration exciter transmits an excitation source to the sliding clamp through the high-temperature ceramic rod, and random excitation is applied to the carbon fiber resin matrix composite material; the support plate and the sliding support plate fixedly support the infrared radiation heating array to slide up and down between the metal brackets, heat the upper surface of the carbon fiber resin matrix composite, and simulate the high-temperature environment in the real flight process.
Further, the sliding clamp assembly comprises a supporting chute and a sliding clamp; the support chute is fixedly provided with a nested sliding clamp. The sliding fixture can be horizontally adjusted along the supporting sliding groove, the high-temperature threaded ejector rod passes through the sliding fixture, and when in clamping, the sliding fixture is rotated to be suitable for clamping carbon fiber resin matrix composite test pieces with different thickness and variable cross sections.
Further, bolt holes are formed in the sliding support frame, and adjusting grooves are formed in two ends of the support plate; the adjusting bolts penetrate through the adjusting grooves to be locked and arranged in the bolt holes.
Further, the high-temperature baffle is positioned between the extending end of the high-temperature ceramic rod and the vibration exciter, a round hole with the diameter of 12mm is formed in the middle of the high-temperature baffle, and the high-temperature ceramic rod penetrates through the round hole in the middle of the high-temperature baffle to be connected with the vibration exciter. The high-temperature baffle integrally wraps the vibration exciter shell, so that the vibration exciter is prevented from being influenced by high-temperature environment.
Further, the sliding support plate is slidably arranged on the metal bracket.
Further, rectangular hole grooves with the length of 350mm and the height of 10mm are formed in the middle of the cross beam of the sliding support frame, a support is arranged at the lower end of each rectangular Kong Caokong groove, and high-temperature threaded ejector rods are arranged on the support at intervals of 40mm to support the bottom of a carbon fiber resin matrix composite test piece.
Further, two ends of the high-temperature armored thermocouple are respectively fixed in the oval hole grooves on the sliding support frame, the sheet-type armored thermocouple can withstand 1200 ℃ high-temperature environments and is respectively and evenly attached to the upper surface and the lower surface of the carbon fiber resin matrix composite test piece, the temperature data acquisition instrument is connected to the outside, and the temperature change of the carbon fiber resin matrix composite test piece is monitored in real time. .
The high-temperature ceramic rod has the diameter of 10mm and the length of 250mm, and is integrally and fixedly connected with the supporting chute in a penetrating way; and transmitting an excitation source to the sliding clamp through the high-temperature ceramic rod, and applying random excitation to the carbon fiber resin matrix composite.
The principle of the invention is as follows: the middle of the sliding support frame is clamped at one end of the carbon fiber resin matrix composite material testing piece by the high-temperature threaded ejector rod, the support plate is connected with two ends of the sliding support frame by the high-temperature bolts, the upper end of the support plate is fixedly connected with one end of the infrared radiation heating array, the other end of the infrared radiation heating array is fixedly supported by the hole groove at the upper end of the sliding support plate, the upper surface of the carbon fiber resin matrix composite material testing piece is heated, the thermal environment in the real flight process is simulated, the thin-sheet type armoured thermocouple penetrates through the oval hole groove of the sliding support frame, the upper surface and the lower surface of the carbon fiber resin matrix composite material testing piece are respectively subjected to temperature measurement, the temperature data acquisition instrument is externally connected, and the temperature change is detected in real time. And simultaneously, the other end of the carbon fiber resin matrix composite test piece is clamped by the two ends of the sliding clamp on the supporting chute, and the two ends of the carbon fiber resin matrix composite test piece are fixedly supported. The vibration exciter is connected with the high-temperature ceramic rod, penetrates through the high-temperature baffle plate and is connected with the supporting chute and the sliding clamp, and random excitation is provided for one end of the carbon fiber resin matrix composite material. The invention can provide a thermal-force-vibration coupling test condition under the condition of not damaging the whole of the carbon fiber resin matrix composite test piece, and provides a clamping scheme for testing the high-temperature vibration mode of the composite material in the aerospace flight environment.
Compared with the prior art, the invention has the beneficial effects that:
(1) Most of the existing high-temperature vibration test fixtures aim at alloy structural members, only a small part of the existing high-temperature vibration test fixtures are used for researching the design of the composite material high-temperature vibration fixture, and most of the existing high-temperature vibration test fixtures need to be perforated on the surface of the material, and vibration equipment is connected to provide excitation. But punching on the surface of the composite material not only damages the integrity of the structural member, but also can change the weaving structure of the composite material, thereby affecting the accuracy of obtaining parameters of high Wen Motai. According to the invention, the sliding clamp and the sliding support frame are used for stably clamping under the condition that the integral structure of the carbon fiber resin matrix composite test piece is not damaged, and the random excitation signal is stably transmitted to the sliding clamp through the high-temperature ceramic rod, so that random vibration is provided for the carbon fiber resin matrix composite test piece, and the vibration change rule in the flying environment is simulated.
(2) The invention is suitable for providing different thermal environments for the carbon fiber resin matrix composite test piece, the supporting plate is connected to the two ends of the sliding supporting frame by the high-temperature bolts in a sliding way, the upper end of the supporting plate is provided with the hole slots for fixedly supporting one end of the infrared radiation heating array, the other end of the supporting plate is provided with the hole slots for fixedly supporting the other end of the supporting plate, and the irradiation area is changed by moving the height of the infrared radiation heating array so as to adjust the heating environment of the carbon fiber resin matrix composite.
(3) The invention is suitable for high-temperature vibration test of carbon fiber resin matrix composite test pieces with different lengths, different thicknesses and different cross sections. The two ends of the sliding support frame can slide along the peripheral metal support frame, so that the clamping of the carbon fiber resin matrix composite test pieces with different lengths is ensured. The sliding fixture on the sliding support chute can clamp carbon fiber resin matrix composite test pieces with different cross sections, and the high-temperature threaded ejector rod on the sliding fixture is rotated to adapt to the carbon fiber resin matrix composite test pieces with different thicknesses.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a partial overall schematic of the present invention;
FIG. 3 is a front view of the present invention;
Fig. 4 is a schematic view of the clamp of the present invention.
Detailed Description
The present invention is further illustrated in the following drawings and detailed description, which are to be understood as being merely illustrative of the invention and not limiting the scope of the 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 drawings, and the words "inner" and "outer" refer to directions toward or away from, respectively, the geometric center of a particular component.
As shown in fig. 1,2, 3 and 4, the invention is composed of an infrared radiation heating array 1, a supporting plate 2, a sliding supporting frame 3, a thin-sheet type armoured thermocouple 4, a carbon fiber resin matrix composite material test 5, a sliding clamp 6, a supporting chute 7, a ceramic rod 8, a high-temperature baffle 9, a sliding supporting plate 10, a metal bracket 11, a high-temperature sliding block 12, a vibration exciter 13 and a high-temperature threaded ejector rod 14.
The clamp designed by the embodiment is suitable for clamping and fixing carbon fiber resin matrix composite test pieces with different thicknesses and different lengths on the premise of not damaging the integrity of the carbon fiber resin matrix composite. One end of the carbon fiber resin matrix composite test piece 5 penetrates through the middle truss of the sliding support frame 3, and the high-temperature threaded ejector rod 14 of the middle truss of the sliding support frame 3 is rotated to fix one end of the carbon fiber resin matrix composite test piece 5. The two ends of the sliding support frame 3 can be fixed on the outer metal support 11 in a sliding way by the high-temperature sliding blocks 12, and the sliding support frame 3 can move along the metal support 11 and is suitable for fixing test pieces with different lengths. The other end of the carbon fiber resin matrix composite 5 is placed on the supporting chute 7, the sliding clamps 6 at the two ends of the supporting chute 7 are moved to be suitable for test pieces with different lengths, the threaded ejector rods on the sliding clamps 6 are rotated, and the threaded ejector rods are adjusted to be suitable for the carbon fiber resin matrix composite test pieces with different thicknesses.
The clamp is suitable for collecting modal data in high-temperature environments. The sliding support frame 3 is locked by high-temperature bolts and connected with the support plate 2, the support plate 2 is perforated with an infrared radiation heating array 1, the other end of the infrared radiation heating array 1 is perforated with a hole and is placed on the sliding support plate 10, the two support plates fixedly support the infrared radiation heating array 1, the infrared radiation heating array 1 provides a high-temperature environment with the temperature of more than 1000 ℃ for the upper surface of the carbon fiber resin matrix composite test piece 5, and the thin-sheet armoured thermocouple 4 passes through the middle elliptical hole grooves at the two ends of the sliding support frame 3 and is attached to the upper surface and the lower surface of the carbon fiber resin matrix composite test piece 5, so that temperature measurement is carried out on the upper surface and the lower surface. The vibration exciter 13 is connected with the supporting chute 7 through the high-temperature baffle 9 by the high-temperature ceramic rod 8, and transmits a random excitation signal to one end of the carbon fiber resin matrix composite test piece 5, so that the thermal-force-vibration environment coupling simulation in the real flight process is realized.
The middle part of the cross beam of the sliding support frame can clamp a carbon fiber resin matrix composite test piece with the length of 350mm and the thickness of less than 10mm, the other end of the cross beam of the sliding support frame can be fixed at two ends of the sliding clamp and the thickness of the high-temperature threaded ejector rod is adjusted, the vibration exciter provides random excitation for one end of the carbon fiber resin matrix composite test piece through the high-temperature ceramic rod, stable clamping and vibration are ensured to be provided on the premise of not damaging the integrity of the carbon fiber resin matrix composite, and the testing precision of high-temperature vibration modal parameters is improved.
The invention can provide accurate modal test under the condition of not damaging the structure of the carbon fiber resin matrix composite test piece, two ends of the carbon fiber resin matrix composite test piece 5 are stably clamped by the sliding support frame 3 and the sliding clamp 6 on the support chute 7, a random signal such as sine, impact explosion and the like is applied by adjusting the vibration exciter 13, the support chute 7 is connected with the ceramic rod 8 to provide fixed frequency or sweep frequency test for the carbon fiber resin matrix composite test piece 5, the front 5-order modal frequency of the carbon fiber resin matrix composite test piece 5 is ensured to normally occur, and the high-temperature vibration modal parameters of the carbon fiber resin matrix composite test piece 5 are acquired by means of software processing.
The technical means disclosed by the scheme of the invention is not limited to the technical means disclosed by the embodiment, and also comprises the technical scheme formed by any combination of the technical features.
Claims (8)
1. The high-temperature vibration mode clamp for the carbon fiber resin-based composite material is characterized in that: the device comprises an infrared radiation heating array (1), a supporting plate (2), a sliding supporting frame (3), a sheet type armored thermocouple (4), a carbon fiber resin matrix composite material test piece (5), a ceramic rod (8), a sliding supporting plate (10), a metal bracket (11), a high-temperature sliding block (12), a vibration exciter (13) and a high-temperature threaded ejector rod (14); the sliding support frame (3) is in sliding connection with the metal support frame (11) through a high-temperature sliding block (12); the supporting plate (2) is arranged at one end of the sliding supporting frame (3); the upper end is provided with a hole groove, one end of the infrared radiation heating array is fixed in the hole groove of the supporting plate (2), and the other end of the infrared radiation heating array is fixed on the hole groove of the sliding supporting plate (10); the carbon fiber resin matrix composite material test piece (5) is arranged on the sliding support frame (3) and one end of the carbon fiber resin matrix composite material test piece is connected with the sliding clamp assembly; the upper surface and the lower surface of the carbon fiber resin matrix composite material test piece (5) are attached to the thin-sheet type armored thermocouple (4); the thin-sheet armoured thermocouple (4) is externally connected with a temperature acquisition instrument; the vibration exciter (13) is connected with the sliding clamp assembly through the high-temperature ceramic rod (8).
2. The carbon fiber resin matrix composite high temperature vibration mode clamp according to claim 1, wherein: the sliding clamp assembly comprises a supporting chute (7) and a sliding clamp (6); two ends of the supporting chute (7) are provided with sliding clamps (6) in a sliding manner; the top of each sliding clamp (6) is rotatably provided with a threaded ejector rod.
3. The carbon fiber resin matrix composite high temperature vibration mode clamp according to claim 1, wherein: bolt holes are formed in the sliding support frames (3), and adjusting grooves are formed in two ends of the support plates (2); the adjusting bolts penetrate through the adjusting grooves to be locked and arranged in the bolt holes.
4. The carbon fiber resin matrix composite high temperature vibration mode clamp according to claim 1, wherein: the vibration exciter (13) is positioned in the high-temperature baffle plate (9).
5. The carbon fiber resin matrix composite high temperature vibration mode clamp according to claim 1, wherein: the sliding support plate (10) is arranged on the metal bracket (11) in a sliding manner.
6. The carbon fiber resin matrix composite high temperature vibration mode clamp according to claim 1, wherein: rectangular hole grooves with the length of 350mm and the height of 10mm are formed in the middle of a cross beam of the sliding support frame (3), a support is arranged at the lower end of each rectangular Kong Caokong groove, high-temperature threaded ejector rods are arranged on the support every 40mm, and the bottom of a carbon fiber resin matrix composite test piece (5) is supported.
7. The carbon fiber resin matrix composite high temperature vibration mode clamp according to claim 1, wherein: wherein, two ends of the high-temperature armored thermocouple (4) are respectively fixed in the elliptical hole grooves on the sliding support frame (3).
8. The carbon fiber resin matrix composite high temperature vibration mode clamp according to claim 1, wherein: the diameter of the high-temperature ceramic rod (8) is 10mm, the length of the high-temperature ceramic rod is 250mm, and the high-temperature ceramic rod is integrally penetrated and fixedly connected with the supporting chute (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410273783.4A CN118050145A (en) | 2024-03-11 | 2024-03-11 | High-temperature vibration mode clamp for carbon fiber resin matrix composite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410273783.4A CN118050145A (en) | 2024-03-11 | 2024-03-11 | High-temperature vibration mode clamp for carbon fiber resin matrix composite |
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| Publication Number | Publication Date |
|---|---|
| CN118050145A true CN118050145A (en) | 2024-05-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410273783.4A Pending CN118050145A (en) | 2024-03-11 | 2024-03-11 | High-temperature vibration mode clamp for carbon fiber resin matrix composite |
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| Country | Link |
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| CN (1) | CN118050145A (en) |
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- 2024-03-11 CN CN202410273783.4A patent/CN118050145A/en active Pending
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