173 results about "Thermal test" patented technology

The invention discloses a medium-deep buried pipe heat pump system capacity configuration design method, which comprises the following steps of: acquiring short-term heat exchange test data and heat exchange theoretical data of a medium-deep buried pipe, and performing data inversion to obtain comprehensive thermophysical parameters of a rock-soil body; building a building heat load prediction model according to the historical heat load, the historical state data and the building information to obtain a predicted heat load, determining a heat supply mode according to the predicted heat load, and performing dynamic heat supply simulation by adopting a long-term heat exchange model of the medium-deep buried pipe heat pump system to obtain configuration operation data, and optimizing the medium-deep layer buried pipe heat pump system long-term heat exchange model according to the configuration operation data, and outputting project system capacity configuration by the optimized medium-deep layer buried pipe heat pump system long-term heat exchange model. According to the method, the precision and efficiency of capacity configuration of the medium-deep buried pipe heat pump system can be improved, meanwhile, good interpretability is achieved, and the method has great significance in reducing the construction cost, saving energy and reducing emission.

The invention discloses an external thermal insulation and heat transfer testing device for a thermal insulation and decoration integrated plate, and relates to the technical field of thermal insulation and decoration integrated plate heat transfer testing. By arranging the longitudinal position adjusting assembly and the transverse position adjusting assembly, the positions of the first temperature measuring unit and the second temperature measuring unit are adjusted at the same time, that is, when the transverse position adjusting assembly adjusts the transverse positions of the first temperature measuring assembly and the second temperature measuring assembly, the first temperature measuring unit and the second temperature measuring unit are adjusted; the longitudinal position adjusting assembly longitudinally adjusts the positions of the first temperature measuring unit and the second temperature measuring unit at the corresponding positions at the same time, so that the first temperature measuring unit and the second temperature measuring unit are located at a plurality of temperature measuring points in the testing time period, and then temperature values in different areas of the outer wall of the heat preservation and decoration integrated plate are obtained. According to the multiple measured temperature values, the overall heat transfer performance of the heat preservation and decoration integrated plate can be analyzed, the local heat transfer performance of the heat preservation and decoration integrated plate can be known, and comprehensive analysis of the heat transfer performance condition of the heat preservation and decoration integrated plate is facilitated.

The invention belongs to the technical field of satellite thermal test, and provides a batch satellite thermal test dynamic allocation automatic test system and an application method in order to reduce the cost of a thermal test system and improve the test efficiency, the automatic test system comprises a load test equipment group, a measurement and control test equipment group, a test interface equipment group and an energy equipment group, a switch matrix board card module is connected with an interface flange plate on a vacuum thermal test tank, and is connected with the switch matrix board card module, an application / data server and a test terminal through a network switch. According to the number of satellites to be tested in the configuration parameters, the number of equipment resources, the mapping matrix of the connection relation of all the components and the test working condition, dynamic resource allocation is achieved, and the automatic testing efficiency of batch satellite thermal tests is improved.

The invention relates to the technical field of radiator monitoring, and particularly discloses a radiator heat dissipation performance dynamic test system, which is characterized in that a heat source simulation body is arranged on a heat transfer interface of a radiator, and a high-fidelity dynamic electric power load is applied to the heat source simulation body to simulate an actual working condition; radiating a microwave detection signal to a space where the heat source simulator is located and receiving a multi-path scattering response signal; the three-dimensional dielectric constant dynamic distribution of the heat source simulation body is reconstructed by solving the inverse scattering problem fused with the space-time constraint; according to the material dielectric constant-temperature relation mapping, three-dimensional temperature field dynamic distribution is generated; and finally, intelligently identifying and extracting a migration track and a temperature change curve of the highest temperature point in the space from the continuous time sequence temperature field data, and taking the migration track and the temperature change curve as a direct evaluation basis for the dynamic heat dissipation performance of the radiator. According to the method, lossless, full-field, real-time visualization and quantitative analysis of the migration process of the dynamic hot spots in the hidden heat source are realized, and the authenticity of the dynamic heat test is improved.

The invention discloses a wafer structure, a packaging module and a thermal testing chip, and relates to the technical field of chip thermal testing, and the wafer structure comprises a plurality of wafers arranged at intervals and cutting channels connecting two adjacent wafers. Each wafer comprises a surface wiring layer, a temperature measuring unit and a heating unit, the temperature measuring unit and the heating unit are stacked below the surface wiring layer, the surface wiring layer is provided with a temperature measuring pin and a heating pin which are independent from each other, and the temperature measuring unit is electrically connected with the temperature measuring pin through a temperature measuring metal via hole. The heating unit is electrically connected with the heating pins through the heating metal via holes; the heating pins in the plurality of wafers are arranged independently from each other, and the temperature measuring pins in the plurality of wafers are arranged independently from each other. According to the technical scheme, the universality of the hot test chip is improved, and the development cost is reduced.

The invention relates to the technical field of spacecraft vacuum thermal tests, in particular to a spacecraft vacuum thermal test motion simulation device, which comprises a base, a pitching mechanism, a rotating mechanism and a transmission monitoring assembly, and is characterized in that the pitching mechanism is arranged on the base; the rotating mechanism is arranged on the pitching mechanism and connected with the pitching mechanism, and the rotating mechanism can drive the load to rotate around the first axis; the pitching mechanism drives the rotating mechanism to swing around a second axis, so that the load can swing around the second axis; the transmission monitoring assembly is connected with the rotating mechanism and used for detecting whether the power input end of the rotating mechanism and the power output end of the rotating mechanism conduct synchronous transmission or not. According to the application, the power input end of the rotating mechanism and the power output end of the rotating mechanism can be ensured to keep synchronous transmission in the test process, so that when the rotating mechanism rotates at a certain speed, the load can be effectively ensured to complete the operation at a set angle within a set time, thereby restoring the trueness of the vacuum thermal test of the spacecraft, and improving the test efficiency. And the accuracy of test data is improved.

The invention provides a spacecraft thermal test thermal response automatic test method and system. The method comprises the steps that S1, preset configuration information is acquired, and a resistance interpretation test is carried out on a current power output loop; s2, initial test current is applied to the power output loop passing the test, and the temperatures of all test points are obtained regularly; and S3, judging whether the temperature change of the measuring point meets the response condition or not, if so, judging that the power output loop is matched with the measuring point meeting the response condition, and testing the next power output loop, and if not, returning to the step S2 and increasing the test current step by step until the measuring point meeting the matching condition exists. The testing process is high in safety, it is initially determined that the configuration of the power output loop is not abnormal, then the matching performance of the temperature measuring point and the power output loop is determined step by step in a stepped power-up mode, and the problems that due to the fact that the current applied to the power output loop is too large for a long time, a heating piece is burnt or the temperature of a product is abnormal are completely eradicated.

The utility model provides a heat resistance testing device for automotive upholstery, which relates to the technical field of heat resistance testing for automotive upholstery and comprises a fixed frame, a movable frame is arranged above the fixed frame, the inner wall of the movable frame is rotatably connected with a rotating rod, two symmetrical clamping mechanisms are arranged in the movable frame, and the clamping mechanisms are connected with the rotating rod. And the clamping mechanism comprises a supporting seat, the bottom surface of the supporting seat is fixedly connected with a connecting plate, and the inner wall of the connecting plate is rotationally connected with a rotating pipe. According to the heat resistance testing device for the automotive upholstery, through the arrangement of the fixing frame, the clamping mechanism, the moving frame and the rotating rod, the automotive upholstery can be slowly rotated after being fixed, so that it is ensured that the heating plate uniformly heats all parts of the surface of the automotive upholstery, and the situation that the temperature of the side, facing the heating plate, of the upholstery is different from that of the side, back to the heating plate, of the upholstery is avoided; the surface temperature of the interior trim part is relatively uniform during the heat resistance test, so that the test accuracy is improved.

The invention relates to a real-time measurement method for an enthalpy value in an ablation process of a thermal protection material in an electric arc wind tunnel test, is used for a ground test of an electric arc wind tunnel thermal protection system, and belongs to the research field of ground aerodynamic thermal tests of aircrafts. The non-equilibrium temperature (rotation, rotation and electron) and the concentration of atomic nitrogen and atomic oxygen of a stagnation point area of a stagnation point model of the heat-proof material are obtained, online measurement of the local center stagnation point enthalpy value of the heat-proof material is achieved, the whole-process real-time monitoring of the material ablation process is achieved, the enthalpy value simulation range of various types of arc wind tunnels such as tubular, segmented and laminated arc wind tunnels can be covered, and the performance of the heat-proof material is improved. The method has very wide applicability; and rapid and long-time measurement of the whole ablation process of the heat-proof material can be realized, the response frequency can be up to 100Hz, and the measurement period is greater than or equal to 1h.

The present application relates to the technical field of condition monitoring, and in particular to a method for monitoring the operating condition of an engine thermal test device, the method comprising: clustering the operating modes of historical operating data to obtain multiple operating types; using the historical operating data of the operating type to which the real-time operating data belongs as a test sample, and in the test sample, using the LOF algorithm to obtain the degree of abnormality of the real-time operating data under multiple candidate K values; using the median of the candidate K value as the starting point, calculating the objective function of each step length, and using the step length when the objective function takes the minimum value as the target step length; obtaining multiple target K values ​​based on the target step length, comparing the average degree of abnormality and degree threshold of the real-time operating data under each target K value, and obtaining the condition monitoring result. Through the technical solution of the present application, the accuracy of the operating condition monitoring result of the engine thermal test device can be improved.

Systems and methods for thermal testing in a firmware framework. In some embodiments, an Information Handling System (IHS) may include a controller, where the controller comprises firmware that, upon execution by a processing core, causes the processing core to instantiate an orchestrator; and a plurality of devices coupled to the controller, where each device comprises firmware that, upon execution by a corresponding processing core, causes the corresponding processing core to instantiate a node as part of a firmware framework, and where the orchestrator is configured to trigger thermal data collection by one or more selected nodes prior to the booting of any Operating System (OS) of the IHS.

Systems and methods for testing in a datacenter are disclosed. In at least one embodiment, a thermocouple arrangement within a heat spreader of a thermal test vehicle (TTV) is provided to represent a lidless computing device to be commissioned based in part on heat flux feedback received from a thermocouple arrangement that includes at least two thermocouples at angles from different edges of a heat spreader toward a center of a heat spreader and includes a third thermocouple is perpendicular to at least one of different edges of a heat spreader.

The invention discloses a test method for a high-load heating tube for a mold, and belongs to the technical field of single-head electric heating tube detection. The method specifically comprises the following steps: S1, historical data acquisition: acquiring cold-state electrical performance data of single-head electric heating tubes with different specifications and under different working conditions; s2, historical data preprocessing: performing preprocessing including data cleaning, data normalization and data standardization on historical data to obtain a standardized data set; the test process design covers a full-period closed loop of cold state detection, hot state leakage current test, reliability test, secondary hot state leakage current test and secondary cold state detection, the electrical safety (leakage current control) under a high-load working condition is verified through the hot state test, and the reliability of an actual use scene is simulated through a rapid on-off test. Meanwhile, the appearance, temperature, gas release and other states of the heating pipe are monitored in real time, abnormal testing is terminated in time, safety risks are avoided, and it is ensured that the detection result can comprehensively reflect the actual use performance of the heating pipe.

The invention relates to the technical field of power cycle tests, in particular to a test method for automatically interspersing static characteristic tests in a power cycle test, which comprises the following steps of: 1, performing a power cycle test on a tested sample, and judging the aging degree; counting the cycle number of the power cycle test; 2, judging whether the cycle number of the power cycle test reaches a preset value N or not, if yes, pausing the power cycle test, waiting for state recovery, and executing the step 3; if not, continuing to execute the step 1; 3, stopping the power cycle test, and entering a static parameter test; 4, all interspersed static parameter tests are finished, a power cycle test is recovered, and an interspersed transient thermal test is carried out; 5, judging whether a stop condition is triggered or not, and if yes, executing the step 6; if not, executing the step 1; and step 6, ending the loop test. Static parameter testing can be interspersed in power cycle testing, and the overall reliability of the tested sample is improved.

The invention discloses a thermotechnical test method and device for a high-temperature heat pipe. The thermotechnical test method comprises the following steps: determining an installation angle of a to-be-tested heat pipe and the lengths of an evaporation section, a heat insulation section and a condensation section of the to-be-tested heat pipe; the to-be-tested heat pipe is heated to enter a starting stage; after the to-be-tested heat pipe enters the stable heat carrying stage, increasing the heating power to control the temperature of the heat insulation section of the to-be-tested heat pipe to continuously rise; and when the to-be-tested heat pipe reaches the preset working temperature, determining the maximum load-out power of the to-be-tested heat pipe according to the temperature data of the preset temperature point location. The invention belongs to the field of high-temperature heat pipe performance testing. The performance parameters of the high-temperature heat pipe can be accurately reflected.

The invention provides a large heat flow test control method for model prediction compensation, which takes a graphite heating finite element model as a prediction model for large heat flow test system control, and comprises the following steps of: firstly, expressing a radiation heating process of a test piece by using a graphite heating element according to a virtual work principle; establishing a transfer function between input electric power and output radiation heat of a controlled object, and substituting a temperature field, which is obtained by calculation of the prediction model and changes along with time, of graphite heating into closed-loop control of a test system; and finally, establishing a time sequence prediction model, comparing a test heating target temperature field, predicting an error generated by a test system, applying the error as an input to a controller of the system, and carrying out pre-adjustment compensation on controller parameters. According to the large heat flow test control method for model prediction compensation provided by the invention, the problems of large inertia, nonlinearity and time-varying control of a thermal test system formed by graphite heating elements are solved, and the construction accuracy of a ground aerodynamic thermal simulation test environment is ensured.

The application discloses a kind of vertical shaft shaft wall rock-lining thermal interaction test device and use method, it is related to mine construction engineering field.The thermal evolution characteristics of deep vertical shaft wall rock unloading cooling process, the thermal interaction between wall rock-lining can be tested and analyzed in laboratory.According to the following method: step one: test device assembly;Step two: wall rock initial state simulation;Step three: wall rock pressure relief cooling process;Step four: concrete shaft lining pouring;Step five: thermal test analysis.Application of the device for testing and analysis, the thermal response characteristics of wall rock unloading in high-temperature environment, the thermal interaction law between wall rock-lining, for accurately evaluating the stress condition of shaft lining under thermal coupling conditions of deep vertical shaft, lay a foundation.

The invention discloses a thermal test tool which comprises a back plate, a base, a heating assembly and a first sealing piece, the back plate is arranged on the base, the base is provided with an inner surface facing the back plate, the inner surface of the back plate is provided with a first containing groove and a second containing groove, and the second containing groove is located on the periphery of the first containing groove; the heating assembly comprises a heating piece, and at least part of the heating piece is located in the first containing groove. The first sealing piece is arranged in the second containing groove and located on the periphery of at least part of the heating piece. When the back plate is arranged on the base, the back plate and the base exert pressure on the first sealing piece, so that the first sealing piece is tightly attached to the second containing groove.

The present application relates to the technical field of aircraft active thermal protection test technology and thermal test equipment technology, in particular to a device and method for extreme surface load test of aircraft sCO2 thermal protection components, comprising a vacuum system, an electric induction heating system located inside the vacuum system, a supercritical carbon dioxide circulation system arranged outside the vacuum system, a supercritical carbon dioxide circulation pipeline extending into the vacuum system and located above the electric induction heating system and in communication with a test piece, and a medium supply system in communication with the supercritical carbon dioxide circulation system. The present application constructs a comprehensive test simulation device integrating a vacuum environment, electromagnetic induction heating, a supercritical cooling loop, high-precision measurement, data processing and a control system, and the overall structure of the device is compact, small in footprint and strong in expandability, and the device is suitable for thermal performance research of microstructure cooling units and components under high heat flow density and multi-physical field coupling conditions.

The present application relates to the technical field of building thermal test, and provides an experimental device for coupling sky cold and hot radiation effects and a control method thereof.The device comprises a first radiation cooling component, a solar radiation component and an air cooling component, the first radiation cooling component is obliquely arranged on both sides and connected at the top to form a detection space, the air outlet of the air duct of the air cooling component is located at the bottom of the components on both sides, the air return port is opposite to the top, and the solar radiation component is fixed in the air duct away from the detection space on one side.The present application cooperatively arranges the obliquely combined first radiation cooling component, the air cooling component with air supply at the bottom and air return at the top, and the solar radiation component arranged in the air duct in isolation, constructs a detection environment balanced in cold and hot radiation, realizes coupling simulation of solar radiation heat effect and sky radiation cold effect, can more accurately test the performance of energy production type building envelope components, and solves the technical problem that the existing building thermal test device has low test precision and cannot meet the performance evaluation of energy production type building envelope components.

The invention provides an ultra-large array plane radar satellite decoupling vacuum thermal test method, which comprises the following steps of: arranging a satellite and radar antennas in a vacuum tank, detaching the radar antennas from the satellite, arranging the radar antennas on one side of the satellite side by side, and respectively arranging infrared simulation devices around the satellite to simulate external thermal flow; a wave absorbing device is arranged on an antenna array plane to absorb microwaves and simulate external heat flow, the power level of an infrared simulation device is adjusted according to the heat radiation level of the satellite surface, the power level of the wave absorbing device is adjusted according to the microwave emission power and the heat radiation level of the antenna array plane, and a vacuum thermal test is performed on the satellite and the antenna. According to the invention, vacuum thermal tests on a satellite and a radar antenna due to an overlarge antenna array plane can be avoided, a whole-satellite microwave wireless emission state test can be carried out, extremely high-risk operation caused by hanging and unfolding in an antenna tank is avoided after the antenna and the satellite are decoupled, the tank occupation period of links such as test state establishment and withdrawal is greatly shortened, and the test efficiency is improved. And the model development efficiency is improved.

The application discloses an online identification method for pyrolysis and ablation interface evolution of carbonized ablation material based on X-ray image fusion enhancement. In the ground thermal test of the carbonized ablation material, a plurality of groups of images of the carbonized ablation material at different moments are obtained through X-ray imaging, an image fusion enhancement algorithm is adopted to improve the image quality, the local features of the pyrolysis and ablation interface are enhanced, the image noise is reduced through local sliding window averaging, and the pyrolysis and ablation interface is identified in real time based on a gradient algorithm. The application can realize real-time automatic measurement of the ablation amount, the interface between the pyrolysis layer and the carbonization layer, and the interface between the pyrolysis layer and the original layer in the ground thermal test of the carbonized ablation material, overcome the problems that the traditional measurement method is difficult to identify the interface between the pyrolysis layer and has low accuracy, and improve the measurement technical level of the ground thermal test of the thermal protection material, thereby providing support for the design of the ablation thermal protection system.

The embodiment of the application provides a kind of to be placed in cooling water tank high temperature high pressure steam-water passive residual heat exchanger thermal test device and method, the test device includes: passive residual heat exchanger, steam boiler, multifunctional test auxiliary water tank, water tank cooling pump, cooling water tank cooler, first electric stop valve, first electric regulating valve, check valve, second electric regulating valve, third electric stop valve, first flowmeter, second flowmeter, first temperature sensor, second temperature sensor, third temperature sensor, fourth temperature sensor, fifth temperature sensor, second electric stop valve and cooling water tank.The technical scheme can conveniently simulate the actual operating condition of passive residual heat exchanger, realize the adjustment of hot side steam flow, and realize the control of cold side steady-state temperature condition.

The present invention discloses a device for testing the drag reduction and heat exchange characteristics of a water-soluble drag-reducing solution. The device comprises: a liquid storage tank, an agitator, a variable frequency water pump, a preheating section, a heat exchange test section, a differential pressure test section, a cooler, a heating controller, a cooling tower, a temperature sensor, a pressure sensor, a differential pressure sensor, a data acquisition instrument, and a computer. The device of the present invention overcomes the problem that existing devices can only test the drag reduction characteristics but cannot test the heat exchange characteristics at the same time, and can only perform tests at room temperature. In addition, the experimental section of the device adopts a snap-on connection, which is easy to replace, and the heating method adopts efficient, uniform, and energy-saving electromagnetic induction heating. The device can realize the drag reduction and heat exchange characteristic tests of different flow rates, different temperatures, different pipe structures, and different types of drag reducing solutions. It is easy to operate and has excellent experimental test results.

The invention relates to a thermodynamic component combined test, and provides a thermodynamic component combined test system and a test method in order to solve the problems that an afterburning cycle engine gas generator is large in propellant mass flow deviation, large in combustion product pollution, high in hot test run cost and the like. The test system comprises a fuel gas generator, a gas venturi tube and a thrust chamber which are coaxially connected; a first component access port is formed in the top of the fuel gas generator, a second component access port is formed in the side face of the fuel gas generator, the first component access port and the second component access port are used for accessing a first component propellant and a second component propellant respectively, and a plurality of fuel gas performance monitoring ports are formed in the side face of the gas venturi tube; a second component regeneration cooling access port is formed in the side surface of the outlet end of the thrust chamber and is used for regenerating and cooling a second component propellant and then accessing the second component propellant into the thrust chamber; the test method based on the test system can effectively improve the efficient, reliable and environment-friendly hot test run test between the fuel gas generator and the thrust chamber.

The present application belongs to the technical field of satellite thermal test, in order to reduce the cost of thermal test system and improve the test efficiency, a kind of "batch satellite thermal test dynamic allocation automatic test system and application method" is provided, the automatic test system includes load test equipment group, measurement and control test equipment group, test interface equipment group, energy equipment group, through switch matrix board module and the interface flange plate on vacuum thermal test tank connection, and switch matrix board module, application / data server and test terminal are connected through network switch, under the arrangement of automatic test software task in application / data server, according to the mapping matrix of the number of satellites to be tested, the number of equipment resources, the connection relationship of each component and the test condition in configuration parameter, resource dynamic allocation is realized, and the efficiency of batch satellite thermal test automation test is improved.

The invention discloses a thermal sensitive element jump judgment device for a dynamic thermal test of a fire-fighting sprinkler head, relates to the technical field of fire-fighting part detection equipment, and is used for testing the response performance of the fire-fighting sprinkler head. The device comprises a shell, a test piece mounting seat, a jump judgment mechanism and a plunger, the jump judgment mechanism comprises an elastic pressure applying assembly and a conductive detection assembly, a ceramic insulation ejector rod is sleeved with a stainless steel compression spring, after a test element is mounted, the spring is compressed to apply a preset load, and meanwhile high-temperature electric leakage is avoided; the conductive detection assembly forms a loop through the wire lug, the switch nut and the conductive material part, and the spring resets to trigger the loop to be conducted after the element jumps. The test piece mounting base is detachable and adapts to fire sprinkler heads of different specifications, the device is compact in structure, jumping judgment is accurate and free of lag, the problems that manual observation lags and recording errors are large in a traditional device are effectively solved, and the device is suitable for static action temperature testing of the fire sprinkler heads.

The application discloses a kind of combustion chamber component residual strain measurement method and device, it is related to gas turbine technical field.The method includes: preparing speckle pattern on the surface of combustion chamber component test piece;Reference image is collected before test, and the space pose of image collection module and ambient light parameter are recorded;The thermal test is carried out to test piece;After test, the recorded parameters are strictly reproduced, and deformation image is collected;Based on digital image correlation algorithm, reference image and deformation image are compared and analyzed, and surface residual strain distribution is obtained.The application solves the technical problems that residual strain is difficult to separate and full-field quantitative measurement after thermal test, realizes non-contact, high-precision, repeatable residual strain measurement, and provides key data support for evaluating combustion chamber component life and reliability.

The embodiment of the application discloses a kind of thermal test device and test method, thermal test device includes metal body, metal body includes two metal plates distributed in working medium passage two sides. A plurality of electrically conductive ends are arranged at each metal plate, and the plurality of electrically conductive ends include at least two electrically conductive initial ends and electrically conductive terminal, in at least two electrically conductive initial ends, select any one electrically conductive initial end as test initial end, and test initial end and electrically conductive terminal are respectively connected to the two poles of power supply. The thermal test device disclosed in the application, by selecting any one of at least two electrically conductive initial ends as test initial end, the heating length of the metal plate located on both sides of the working medium passage can be controlled, thereby the heating conditions of symmetrical heating and asymmetrical heating can be simulated, so that the flow and heat exchange law inside the working medium passage under non-uniform thermal load can be tested, and the thermal hydraulic parameters of the working medium passage under a specific electric power distribution can also be obtained, and the test efficiency of the heat exchange equipment can also be improved.

The invention discloses a concrete specific heat capacity measuring device and method based on a gradient temperature control circulation method. The system adopts an innovative double-layer heat insulation structure water tank design. The test method comprises three stages: firstly, carrying out an empty box heating test to determine the background heat capacity of the system; then a pre-balanced standard curing test block is put in for a main heating stage; and finally, accurately measuring the heat capacity of the test block through a dynamic balance stage. According to the method, the double-layer heat insulation design and the dynamic equilibrium criterion are creatively combined, the real effective specific heat capacity of the MPCM concrete can be obtained in a complete test block state, the effective specific heat capacity of the MPCM concrete can be directly and accurately quantified on the premise that the real engineering structure form (standard curing test block) of the MPCM concrete is kept, the test precision is improved compared with that of a traditional method, and the method is suitable for popularization and application. The single test time is short, a reliable and efficient test means is provided for thermal performance research and engineering application of the phase change concrete, and the method has universality for testing the specific heat capacity of the concrete material.