10 results about "Nuclear test" patented technology

The invention relates to the technical field of aircraft ground assessment tests, in particular to a high-enthalpy plasma wind tunnel radiation heat flux measuring device which comprises a shell, an inner sleeve and a thermocouple. A through hole is formed in the center of the shell along the axis, the lower end of the inner sleeve is inserted into the through hole, and the top and the inner wall of the shell are fixedly connected with the inner sleeve; a cooling water channel is arranged between the shell and the inner sleeve, the center of the inner sleeve is provided with a channel along the axis, the top of the channel is provided with an inner step, optical glass and a heat insulation sleeve are embedded in the channel from top to bottom, the top of the heat insulation sleeve is open, the bottom of the heat insulation sleeve is provided with a guide hole, and a probe core is embedded in the heat insulation sleeve; the thermocouple penetrates through the guide hole to be connected with the probe core and is used for measuring the temperature of the probe core. The device is easy to manufacture and convenient to install, the diameter and thickness of the probe core can be optimized according to the size of heat flow and the shape of a test model, and the device has high flexibility; and parts are convenient to replace, and repeated use is achieved.

The application discloses a kind of aerospace engine nozzle regulating piece repeated life examination test methods.The described method is respectively to test sample medium-tail gas-load-temperature environment examination test and tail gas-load-temperature environment examination test: the cycle of above-mentioned two tests obtains a big cycle, after each big cycle ends, the performance of test sample is detected according to failure criterion and fitting curve, when the life index of test sample drops below failure criterion, the number of cycle test is obtained according to the fitting curve, the repeated life under different failure criterion is calculated according to the number of cycle test, select the shortest one as repeated life.The application realizes the repeated life evaluation of military aircraft nozzle regulating piece by medium-tail gas-load-temperature environment examination test and tail gas-load-temperature environment examination test, guarantees the service safety of aerospace equipment and makes the life of regulating piece to be fully played.

The invention discloses a testing device for a ceramic matrix composite sharp front edge thermal examination test piece, belongs to the technical field of ceramic matrix composite front edge thermal tests, and solves the problem that the existing front edge structure is high in high-temperature ablation test cost. The device specifically comprises a sharp front edge thermal examination test piece and a water-cooling test tool. The water-cooling test tool comprises a connecting part, a tool transition section and a cooling liquid interface; one end of the tool transition section is provided with a connecting part connected with a sharp front edge thermal examination test piece; a cooling liquid circulation channel in the tool transition section is communicated with the cooling liquid connector. According to the invention, the temperature of the thermal assessment area of the front-edge thermal assessment test piece is high, and the tool transition section is arranged to prevent the heat of the front-edge thermal assessment area from being transferred to the tool installation interface area to influence the connection reliability; circulating cooling liquid is introduced into the cooling liquid circulating channel through the cooling liquid connector, heat on the testing tool is transferred out through cooling liquid circulation, and the temperature of the testing tool is reduced.

Devices and systems for testing nuclear components are disclosed. An outer shell and inner shell containing a nuclear test component are fed with a test gas which is heated by nuclear reactions. A second gas is fed into the gas outlet to cool the test gas.

The present application belongs to the field of engine test technology, and relates to a method and device for controlling the temperature of the low-pressure turbine outlet gas during a sustained test. The method comprises: step S1, determining a plurality of sustained test intake temperatures according to the engine flight mission profile given by the demander; step S2, determining the engine large-state operating time corresponding to each sustained test intake temperature; step S3, for each sustained test intake temperature, determining by simulation the time proportion of different low-pressure turbine outlet gas temperature ranges within the engine large-state operating time; step S4, allocating the duration of the large-state sustained test time at given different intake temperatures according to the time proportion; step S5, controlling the engine operating speed and nozzle area so that the engine continues to operate for the allocated time within the specified low-pressure turbine outlet gas temperature range. The present application solves the problem of mismatch between the assessment test and the actual thermal load during the sustained test.

The invention provides a bushing monitoring sensor arc endurance capability assessment test method and device. The method comprises the following steps: arranging an arc electrode and an arc striking wire in a bushing sample; installing a to-be-assessed monitoring sensor to a bushing end screen and an oil taking port; according to the arc test circuit diagram, test wiring of the arc test complete equipment is completed; carrying out a partial discharge test, and determining the effectiveness of the bushing monitoring sensor to be assessed according to the obtained first test data; and performing a bushing arc test to obtain second test data, calculating arc energy to determine the effectiveness of the arc test, and determining the arc resistance level of the to-be-assessed monitoring sensor when the arc test is effective. The method and the system can effectively evaluate the arc tolerance capability of the bushing monitoring sensor, and provide guidance for model selection and test assessment of the bushing monitoring sensor.

The invention discloses an aircraft interstage structure function and force and heat bearing capacity testing method, and relates to the technical field of aerospace aircraft ground tests. A test piece, a force and heat assessment test device and a pushing and punching test device are applied, and the test piece comprises an interstage support frame, an interstage pushing and punching module and an upper stage cabin section; the force and heat assessment test device is used for simulating a complex force and heat comprehensive environment borne by an aircraft interstage section and measuring the structural response condition of a test piece; the pushing and punching test device is used for verifying the feasibility of parameter design of the inter-stage pushing and punching module and observing the coordination of separation motion; according to the invention, in a ground laboratory environment, simulated flight force and thermal load are simultaneously or continuously applied to an interstage structure, and after a preset load environment is assessed, a real dynamic movement process of working of a pushing and punching separation mechanism and an upper stage is immediately triggered and tested; the key blank of the two-stage injection stage section from component static strength assessment to system dynamic function verification is filled.

The invention relates to the field of thermal protection material ablation assessment tests, in particular to a method for determining a cold wall catalytic coefficient of a thermal protection material, and the method comprises the steps: S100, calibrating a flow field; s200, preparing a heat-proof material: arranging a coaxial calorimeter at a stationary point of a coating probe, and mounting the coating probe subjected to pre-coating by adopting the heat-proof material on a feeding mechanism; s300, collecting a stationary point response temperature; s400, the cold wall stagnation point heat flux density is calculated; s500, obtaining the mole fractions of the components: obtaining the mole fractions of the components corresponding to the three flow fields by utilizing the calibrated incoming flow total enthalpy and incoming flow total pressure according to an NASA high-temperature air component library; s600, obtaining a stagnation point heat flow; s700, obtaining a stationary point heat flow curved surface diagram; s800, obtaining a matching curve; and S900, obtaining the cold wall catalytic coefficient.

The invention provides an ablative gas-phase product sampling device for a heat-proof material flat plate model, and relates to the technical field of aircraft ground assessment tests. The flat plate model is installed in the tool, upstream airflow is used for heating the flat plate model, the flat plate model is heated to be ablated, and an ablated gas phase product is released; a cooling water channel is formed in the tool, so that the tool can work for a long time in a pneumatic thermal environment; the stop block is connected to the downstream side of the tool and used for limiting displacement of the flat plate model in the airflow direction. The sampler is installed in the check block and used for collecting ablated gas phase products released after the flat plate model is heated. The device can adapt to a severe test environment brought by high-temperature supersonic airflow, in-situ sampling of ablated gas phase products under the vacuum condition is achieved, and meanwhile the sampling process and the ablating process do not interfere with each other.

This invention relates to a method for measuring the enthalpy of ultra-high enthalpy non-equilibrium airflow stagnation points, used for ground tests of arc wind tunnel thermal protection systems. Specifically, it pertains to the field of aircraft ground aerodynamic thermal testing research. Based on a developed dual-band laser absorption spectroscopy method, it measures the non-equilibrium temperature of the airflow on the surface of a water-cooled stagnation point model and the component concentrations of atomic nitrogen and oxygen, obtaining the internal energy enthalpy and chemical enthalpy of the stagnation point model, thereby achieving the measurement of the enthalpy of ultra-high enthalpy non-equilibrium airflow stagnation points. This method complements existing methods and fills the gap in enthalpy measurement in the 50-100 MJ / kg range for aerodynamic thermal testing. Furthermore, this method is not limited to measuring airflow parameters during the testing and commissioning phase; it can also achieve full-process flow field parameter monitoring for aerodynamic thermal evaluation tests of aircraft thermal protection materials.