CN116448442A - Force thermal coupling analysis test system and method for C/SiC material multilayer thermal protection structure - Google Patents
Force thermal coupling analysis test system and method for C/SiC material multilayer thermal protection structure Download PDFInfo
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- 238000012360 testing method Methods 0.000 title claims abstract description 140
- 230000008878 coupling Effects 0.000 title claims abstract description 36
- 238000010168 coupling process Methods 0.000 title claims abstract description 36
- 238000005859 coupling reaction Methods 0.000 title claims abstract description 36
- 238000004458 analytical method Methods 0.000 title claims abstract description 25
- 239000000463 material Substances 0.000 title claims abstract description 20
- 239000011204 carbon fibre-reinforced silicon carbide Substances 0.000 title claims abstract description 19
- 238000000034 method Methods 0.000 title claims abstract description 9
- 238000004088 simulation Methods 0.000 claims abstract description 30
- 238000009826 distribution Methods 0.000 claims abstract description 21
- 239000011153 ceramic matrix composite Substances 0.000 claims abstract description 15
- 239000004964 aerogel Substances 0.000 claims abstract description 8
- 230000005855 radiation Effects 0.000 claims abstract description 8
- 238000010998 test method Methods 0.000 claims abstract description 5
- 238000005259 measurement Methods 0.000 claims description 11
- 239000000919 ceramic Substances 0.000 claims description 10
- 238000009413 insulation Methods 0.000 claims description 5
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- 238000013461 design Methods 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
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- 230000006978 adaptation Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000004321 preservation Methods 0.000 description 2
- 239000003870 refractory metal Substances 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012512 characterization method Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000691 measurement method Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/18—Performing tests at high or low temperatures
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0001—Type of application of the stress
- G01N2203/0003—Steady
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0016—Tensile or compressive
- G01N2203/0019—Compressive
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/003—Generation of the force
- G01N2203/0032—Generation of the force using mechanical means
- G01N2203/0033—Weight
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0676—Force, weight, load, energy, speed or acceleration
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0682—Spatial dimension, e.g. length, area, angle
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0694—Temperature
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
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Abstract
The invention discloses a force thermal coupling analysis test system and a force thermal coupling analysis test method for a C/SiC material multilayer thermal protection structure. The heat load simulation module controls the power output of the transformer to heat up through signals; in the test, a thermocouple is used for measuring the temperature distribution of the inner wall surface of the innermost layer of the test piece during radiation heating, and the thermal boundary condition of the test piece is obtained; the pressure load module is used for simulating by placing loads with different masses above the test piece; the data acquisition module can collect deformation data generated by the test piece under the action of force-thermal coupling conditions and temperature distribution data of the outer wall surface of the rigid aerogel layer of the test piece. The invention can obtain the distribution characteristics and the change rules of the temperature field and the strain field of the multilayer heat protection structure under different pressure loads and different temperature loads, and provides a principle test verification method of an analysis model for the multilayer heat protection structure of the ceramic matrix composite material.
Description
Technical Field
The invention belongs to the technical field of engineering thermophysics, and particularly relates to a C/SiC material multilayer thermal protection structure force thermal coupling analysis test system and method.
Background
The combustion temperature of the advanced ramjet engine can reach more than 2500K, the temperature of the inner wall surface of the combustion chamber also exceeds 2000K, and an effective heat protection structure is needed to ensure the safe operation of the combustion chamber and the spray pipe extension section thereof. The heat protection structure of the ramjet engine combustion chamber often adopts a multi-layer material structure, and comprises a burning-resistant layer, a bearing layer, a heat insulation layer, an outer shell body and the like from inside to outside along the radial direction, wherein the burning-resistant layer of the innermost layer is required to directly bear the ultrahigh gas temperature in the combustion chamber, and strict requirements are put on the temperature resistance of the burning-resistant layer. The C/SiC ceramic matrix composite has been widely used in the field of engine combustion chambers due to its excellent properties of high specific strength, high specific modulus, high temperature resistance, ablation resistance, etc. Compared with refractory metal materials used in the past engine combustion chambers, the C/SiC composite material has the following main advantages: the cooling system is not needed, and the structural design of the engine is simplified; the specific strength and the specific rigidity are high (the density is 1/4-1/3 of that of refractory metal), and the thermal shock resistance and the creep resistance are good; the working temperature is improved, and the oxidation resistance is better. The preparation and application research of the C/SiC composite material is greatly developed in the United states, germany, france, china and Japan, so that the C/SiC composite material is widely used as the material of the engine combustion chamber and the jet pipe extension section.
Aiming at the ceramic matrix composite multilayer thermal protection structure, because of different physical parameters of materials of each layer, the temperature distribution and structural deformation of the ceramic matrix composite multilayer thermal protection structure show non-uniform and nonlinear complex characteristics along the axial direction, the radial direction and the circumferential direction of the engine, a ceramic matrix composite multilayer thermal protection structure force-thermal coupling analysis model is required to be established, force-thermal coupling response characteristic analysis is carried out, and corresponding multilayer thermal protection structure matching design research is carried out. The method comprises the steps of determining the accuracy of a ceramic matrix composite multilayer thermal protection structure force thermal coupling analysis model, and providing a powerful analysis tool for force thermal coupling response characteristic analysis and matching design. Therefore, the invention researches a simulation characterization method of thermal load and pressure load of the thermal protection structure aiming at the accuracy verification requirement of the ceramic matrix composite multilayer thermal protection structure force thermal coupling analysis model, establishes a principle test method of the ceramic matrix composite multilayer thermal protection structure force thermal coupling response characteristic, and provides a principle verification platform for the multilayer thermal protection structure force thermal coupling analysis model.
Disclosure of Invention
In order to study the heat distribution and structural deformation characteristics of the whole structure of the multi-layer heat protection structure of the engine combustion chamber under the force-heat coupling condition, the invention provides a C/SiC material multi-layer heat protection structure force-heat coupling analysis test system and a method, and force-heat coupling characteristic test research is carried out on a typical multi-layer heat protection structure unit model test piece of the combustion chamber, and the heat load and pressure load environments of the engine combustion chamber are simulated.
In order to achieve the technical purpose, the technical scheme of the invention is as follows:
the C/SiC material multilayer thermal protection structure force thermal coupling analysis test system comprises a test piece, a thermal load simulation module, a pressure load simulation module and a data acquisition module;
the test piece is a multi-layer heat protection structure, and the multi-layer heat protection structure comprises a ceramic matrix composite heat protection plate and a rigid aerogel heat insulation plate;
the thermal load simulation module heats the test piece in a thermal radiation mode through an electric heating ceramic resistance plate;
the pressure load simulation module is used for performing pressure load simulation by placing weights with different masses above the test piece;
and the data acquisition module acquires temperature and pressure load data born by the inner surface and the outer surface of the test piece, and temperature distribution and deformation data of the outer surface of the test piece under the force-thermal load coupling condition.
Preferably, in the thermal load simulation module, the electrically heated ceramic resistor plate is connected with a transformer, and a feedback thermocouple is further arranged on the inner surface of the test piece to collect the temperature of the inner surface of the test piece.
Preferably, in the pressure load simulation module, when weights with different masses are placed on the outer surface of the test piece, the objective table support is only installed at the center position of the test piece, so that the influence of the weights with different masses on the temperature and deformation measurement of the outer surface of the test piece is avoided.
Preferably, in the data acquisition module, data are acquired in a non-contact measurement mode.
Preferably, the temperature born by the inner surface and the outer surface of the test piece and the temperature of the outer surface of the test piece under the force-thermal load coupling condition are obtained through a thermal infrared imager temperature test system; and the deformation data test of the test piece is obtained by a lamb optical digital image strain test system.
The C/SiC material multilayer thermal protection structure force thermal coupling analysis test method comprises the following steps:
1) Obtaining a test piece;
2) Building a test system, wherein the test system comprises a test piece, a thermal load simulation module, a pressure load simulation module and a data acquisition module;
3) And testing the test piece through the test system to obtain temperature distribution and deformation data of the outer surface of the test piece under the force-thermal load coupling condition.
The beneficial effects brought by adopting the technical scheme are as follows:
(1) According to the invention, the thermal load simulation module and the pressure load simulation module simulate the thermal load environment of the multi-layer thermal protection structure unit assembly of the engine combustion chamber, so that the temperature load and the pressure load can be accurately controlled, further the temperature and pressure boundary data of the multi-layer thermal protection structure under the test working condition can be accurately extracted, and the thermal load simulation module and the pressure load simulation module are used for the boundary conditions of the force thermal coupling analysis model of the multi-layer thermal protection structure of the engine combustion chamber.
(2) The data acquisition module acquires the surface strain distribution characteristics of the test piece by using the non-contact type lamb optical digital image test system, and compared with a strain gauge electrical measurement method, the strain test system can extract the strain data of a target area in the test piece and has no influence of surface temperature change on the strain data; according to the invention, the data acquisition module acquires the temperature distribution of the surface of the test piece by using the thermal infrared imager, so that the integral temperature distribution characteristic of the surface of the test piece can be acquired more truly and effectively. Data support is provided for temperature field and strain field distribution characteristic exploration of the multi-layer heat protection structure of the engine combustion chamber.
Drawings
FIG. 1 is a schematic view of the structure of the test device of the present invention;
FIG. 2 is a cloud image of temperature distribution taken by a thermal infrared imager;
fig. 3 is a cloud image of stress distribution taken and calculated by the DIC non-contact strain measurement system.
Description of the embodiments
The technical scheme of the invention is described in detail below with reference to the accompanying drawings and examples.
Examples: and (3) carrying out principle test on the force thermal coupling response characteristics of the ceramic matrix composite multilayer thermal protection structure.
The test system comprises a thermal load simulation module, a pressure load simulation module, a data acquisition module and a test piece. The test piece box body is fixed in a mode that the fixed base adopts the clamping plate, the thermal load simulation module is heated through signal control voltage, the heating ceramic plate in the system heats the test piece in a radiation heating mode, meanwhile, the thermocouple can test the inner surface temperature of the test piece, and signals are fed back to the control box so as to reach the set heating temperature. In the test, a thermocouple is combined with a heat flow meter to measure the temperature distribution and the local heat flow value of the inner wall surface during radiation heating, and the temperature and the heat flow data are displayed on a data panel of a temperature inspection instrument and a heat flow meter which are matched for use, so that the thermal boundary condition of a test piece can be accurately obtained. The pressure load simulation module above the test piece applies pressure load to the test piece through standard weights with different masses, simulates the pressure load applied to the test piece, deformation data generated by the test piece under the action of force-heat coupling conditions can be collected into matched software by the strain test system in the data acquisition module, and the temperature distribution of the outer wall surface of the test piece is acquired by the thermal infrared imager in the data acquisition system and records the test data. A schematic of the test system is shown in fig. 1.
The thermal load simulation module consists of a ceramic heating plate, a temperature feedback control box, a test piece fixing and mounting bracket. In the experimental study, a heating effect of fuel gas on the multilayer heat protection structure of the multi-layer structure combustion chamber is simulated by adopting a radiation heating mode of the ceramic heating plate. The temperature feedback control box is used for setting a temperature through the operation panel, heating the ceramic heating plate by utilizing high-voltage electricity, and carrying out radiation heat transfer on the test piece by the ceramic heating plate so as to achieve the purpose of heating the test piece. The temperature feedback thermocouple is arranged at the most middle part of the test piece, and is used for monitoring and feeding back the temperature of the inner wall surface of the whole test piece, converting a temperature signal into an electric signal and feeding back the electric signal to the control box, and when the temperature exceeds the set temperature, the control box is powered off.
The heating mode in the test is a ceramic plate radiation heating mode, and compared with the actual environment of a passive thermal protection combustion chamber of a scramjet engine, the pressure load generated by high-temperature airflow on the wall surface during combustion is lack, so that the standard weight is added on the outer wall surface of a test piece in the test, different pressure loads are applied to the test piece by changing the weight mass, and as the green rigid aerogel layer can break and lose efficacy and the like under the influence of gravity load, the rigid aerogel layer is taken out when the pressure load is applied, and the gravity load is directly applied on the C/SiC layer. Weights on the outer wall surface are respectively 10kg,15kg and 20 kg.
The temperature testing system consists of an infrared thermal imager, an armored thermocouple and a plurality of paths of temperature inspection instruments, and the temperature measuring instruments adopted in the test are FLIR A615 infrared thermal imager, MT-X multi-path temperature inspection instruments and armored thermocouples which are used as temperature measuring sensors. The FLIR A615 thermal infrared imager has 640' -480 pixel resolution, the spatial resolution is 0.68mrad, the wavelength range is 7.5-14mm, the testing temperature range is 300-2000 ℃ and the testing precision is +/-2%; the thermocouple temperature measuring range is 0-1000 ℃, and the testing precision is +/-0.75%.
In the test, a digital image measuring system (DIC test system) of a road-and-science optical technology company is adopted to test the surface strain of a test piece, the road-and-science optical measuring system is widely applied to global industrial manufacturing processes, and the test system can meet various requirements of the test piece in specific application functions such as vibration analysis, temperature correlation measurement, deformation tracking, expansion test, tensile test, bending test and the like. The technology is an algorithm for comparing the related points of the images, and the displacement and strain distribution of the object surface can be calculated by the method. The strain measurement range is 0.005% -2000%, the strain measurement precision is 0.005%, and the test temperature range is-100 ℃ -1500 ℃.
In the test, the ceramic matrix composite heat protection plate, the rigid aerogel layer heat insulation plate and the combined connection structure of the ceramic matrix composite heat protection plate and the rigid aerogel layer heat insulation plate are respectively fixed on the box body, the fixing base applies fixing constraint to four sides of the box body in a clamping plate mode, and then the test is carried out according to specific test working conditions. The working conditions of the force load in the test are divided into 0kg,10kg,15kg and 20kg, the temperature load is divided into 550 ℃, 650 ℃ and 750 ℃, and the influence condition of the stress-thermal coupling condition of the test piece in different temperature and pressure loads is further simulated.
And (3) turning on a power switch of the temperature simulation system and the data acquisition system, calibrating each instrument, shooting an image of the original test piece when the original test piece is not deformed by using the DIC non-contact strain measurement system, and recording deformation data.
The test piece is under no pressure load, and is only affected by boundary temperature load: the temperature of the temperature control box is set to 550 ℃, 650 ℃ and 750 ℃, along with the rising of the temperature, the thermocouple feeds back the heating temperature of the outer wall surface and the temperature of the control box, when the heating temperature reaches the set temperature, the temperature in the thermocouple and the temperature in the control box are kept constant, the test piece is subjected to heat preservation and heating, after the test environment is stable, stress strain data of the surface of the test piece under various working conditions are obtained through a DIC non-contact strain measurement system, and the temperature distribution data of the surface of the test piece under various working conditions are obtained through shooting by an infrared thermal imager.
When the test piece is affected by temperature load and different pressure loads: after the test under the three working conditions without pressure load is completed, carrying out a force-heat coupling load test on the test piece, taking out the rigid aerogel layer, directly applying a gravity load on the C/SiC layer, respectively increasing the loads with the mass of 10kg,15kg and 20kg on the outer layer, and simultaneously respectively applying the temperature load with the temperature of 550 ℃, 650 ℃ and 750 ℃ on the test piece. After a period of heat preservation and heating are carried out, after test data are stable, stress strain data of the surface of the test piece under each working condition are obtained through a DIC non-contact strain measurement system, temperature distribution data of the surface of the test piece under each working condition are obtained through shooting through a thermal infrared imager, the result of the temperature data obtained through shooting is shown in a graph 2, and the result of stress shooting is shown in a graph 3.
Based on the principle test method established by the invention, force-heat coupling characteristic test research can be carried out on the ceramic matrix composite material multilayer heat protection structure plate, the distribution characteristics and change rules of temperature fields and strain fields of the multilayer heat protection structure under different pressure loads and different temperature loads can be obtained, and the principle test verification method of an analysis model is provided for the application of the ceramic matrix composite material multilayer heat protection structure in aerospace high-temperature components.
The foregoing is only a preferred embodiment of the invention, it being noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the present invention, and such modifications and adaptations are intended to be comprehended within the scope of the invention.
Claims (6)
- C/SiC material multilayer thermal protection structure force thermal coupling analysis test system, its characterized in that: the device comprises a test piece, a thermal load simulation module, a pressure load simulation module and a data acquisition module;the test piece is a multi-layer heat protection structure, and the multi-layer heat protection structure comprises a ceramic matrix composite heat protection plate and a rigid aerogel heat insulation plate;the thermal load simulation module heats the test piece in a thermal radiation mode through an electric heating ceramic resistance plate;the pressure load simulation module is used for performing pressure load simulation by placing weights with different masses above the test piece;and the data acquisition module acquires temperature and pressure load data born by the inner surface and the outer surface of the test piece, and temperature distribution and deformation data of the outer surface of the test piece under the force-thermal load coupling condition.
- 2. The C/SiC material multilayer thermal protection structure force thermal coupling analysis test system of claim 1, wherein: in the thermal load simulation module, the electric heating ceramic resistor plate is connected with a transformer, and the inner surface of the test piece is also provided with a feedback thermocouple for collecting the temperature of the inner surface of the test piece.
- 3. The C/SiC material multilayer thermal protection structure force thermal coupling analysis test system of claim 1, wherein: in the pressure load simulation module, when weights with different qualities are placed on the outer surface of the test piece, the objective table bracket is only installed at the center position of the test piece, so that the influence of the weights with different qualities on the temperature and deformation measurement of the outer surface of the test piece is avoided.
- 4. The C/SiC material multilayer thermal protection structure force thermal coupling analysis test system of claim 1, wherein: in the data acquisition module, data are acquired in a non-contact measurement mode.
- 5. The C/SiC material multilayer thermal protection structure force thermal coupling analysis test system of claim 4, wherein: the temperature born by the inner surface and the outer surface of the test piece and the temperature of the outer surface of the test piece under the force-thermal load coupling condition are obtained through a thermal infrared imager temperature test system; and the deformation data test of the test piece is obtained by a lamb optical digital image strain test system.
- The force thermal coupling analysis test method of the C/SiC material multilayer thermal protection structure is characterized by comprising the following steps of: the method comprises the following steps:1) Obtaining a test piece;2) Building a test system, wherein the test system comprises a test piece, a thermal load simulation module, a pressure load simulation module and a data acquisition module;3) And testing the test piece through the test system to obtain temperature distribution and deformation data of the outer surface of the test piece under the force-thermal load coupling condition.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310319670.9A CN116448442A (en) | 2023-03-29 | 2023-03-29 | Force thermal coupling analysis test system and method for C/SiC material multilayer thermal protection structure |
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| CN202310319670.9A CN116448442A (en) | 2023-03-29 | 2023-03-29 | Force thermal coupling analysis test system and method for C/SiC material multilayer thermal protection structure |
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| CN116448442A true CN116448442A (en) | 2023-07-18 |
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