393 results about "Measurement test" patented technology

The invention relates to a multifunctional deformation measurement device and a measurement method, and belongs to the technical field of thermal deformation measurement. Manufacturing a multifunctional deformation measuring device; marking the test piece to be tested; calibrating the precision of the measurement system by using a reference standard substance; a temperature sensor is installed on the test platform; vacuumizing treatment is conducted through a vacuum system; temperature control is carried out through a temperature precise regulation and control module; forming a heat radiation boundary; adjusting the visual angle and focal length of the measuring camera; adjusting a monochromatic illumination light source to realize light coverage on the tested piece; spraying speckles on the test piece to be tested; measuring the initial state of the tested piece; temperature control is carried out through a temperature precise regulation and control module; testing and recording the deformation condition of the tested piece at each temperature point in the whole test process; the method can solve the problems that a measurement test piece is only limited to a material-grade sample, the measurement environment simulation application range is small, the measurement error is large and the like in a traditional method, and is used for guaranteeing high-precision measurement of thermal deformation of a large-size composite material structure of a spacecraft.

The invention relates to the field of pipeline welding, in particular to a prediction model construction method, system and equipment of a heat affected zone and a prediction method. The method comprises the steps that phase change parameters of a metal microstructure phase change model are corrected based on a thermal simulation test; building a heat affected zone microstructure finite element prediction model according to the circumferential weld simulation calculation finite element model; and correction is carried out based on a heat affected zone hardness test and a small punch test correlation parameter correction method, and the heat affected zone strength prediction model is trained by using the expansion database to obtain the pipeline welding joint heat affected zone strength prediction model. Based on a material performance determination test, a finite element model construction method and a finite element model expansion database mode, the accuracy of the heat affected zone strength prediction model is greatly improved, the research cost is reduced, the prediction from a microstructure to macroscopic performance is realized, and the method is suitable for popularization and application. And the defect that the softening mechanism of the hot area material cannot be clarified by traditional macroscopic mechanical property test analysis is overcome.

The invention discloses a rod type six-component high-precision trace rolling moment wind tunnel balance and a measurement method, and belongs to the technical field of aerospace force measurement test power measurement. According to the invention, the problems of large processing difficulty, long processing period and incapability of meeting aviation tests in research and development of micro rolling moment balances at present are solved. A longitudinal column beam, a transverse column beam and a roll-on *-shaped beam are connected between a front cone and a combined element and between a rear cone and the combined element respectively, a resistance beam is arranged on the combined element, the thickness range of sheet beams of a multi-sheet structure of the longitudinal column beam is 0.5 mm-0. 8mm, the gap range of the sheet beams is 0.5 mm-1mm, the thickness range of sheet beams of a multi-sheet structure of the transverse column beam is 0.5 mm-0. 8mm, and the gap range of the sheet beams is 0.5 mm-1mm. According to the rod type six-component high-precision trace rolling moment wind tunnel balance and the measurement method, rolling output is effectively increased, and matching output of small rolling moment and loads in other directions is achieved.

The invention belongs to the technical field of wind tunnel tests, and discloses a test device and a test method for measuring aerodynamic characteristics of an aircraft by simulating air inlet flow. A ventilation model of the test device is installed on the upper portion of a tail boom support through a balance corrugated pipe and a ventilation supporting rod, a variable sideslip angle device is installed between the rear section of the tail boom support and an installation platform, a flowmeter, an ejector and other measuring devices are fixed to the installation platform, and the rear end of the installation platform is fixedly connected with a bent knife mechanism of a wind tunnel. The sideslip angle changing device changes the sideslip angle of the ventilation model. The test method comprises the steps of wind tunnel test preparation; performing a wind tunnel test; and processing test data. According to the invention, a supporting mode of'tail boom + lifting 'is adopted, so that perfect combination of a test system and a supporting system is realized; the hollow telescopic sleeve with the spherical hinges at the two ends is adopted, compensation of airflow pipeline length and angle changes caused by sideslip angle deflection is achieved, a solution is provided for accurate simulation of large continuous high-speed wind tunnel air inlet flow, and engineering practical value is achieved.

The invention discloses a continuous wind tunnel force measurement test balance zero point monitoring and correction method, and belongs to the technical field of aircraft wind tunnel tests. The problem that in the prior art, in order to guarantee the accuracy of test data, a compressor needs to be shut down frequently to collect windless test data, and the continuous wind tunnel test efficiency is greatly affected is solved. The problem that zero change correction cannot be carried out on collected balance strain in the prior art is solved. According to the invention, through the installation of the wind tunnel experiment support system and the wind tunnel test model, the collection of windless and windy test data and the calculation of the balance zero point correction value based on time change, the accurate correction of the balance zero point of the force measurement test is realized, and then the six-element force and torque of the aerodynamic load borne by the test model are calculated. The method can significantly improve the efficiency of the continuous wind tunnel test, reduces the time for collecting the zero point and the dead weight of the balance, can significantly improve the precision and the reliability of the continuous wind tunnel force measurement test data, and can be applied to the wind tunnel force measurement test.

The invention relates to a fault diagnosis method of a photovoltaic inverter, a computer program product and equipment. The fault diagnosis method comprises the following steps: applying a test input signal to a photovoltaic inverter to be diagnosed, and collecting an actual measurement test signal of the photovoltaic inverter in response to the test input signal; performing analog simulation on the test input signal by using a photovoltaic inverter model pre-generated by the photovoltaic inverter to obtain an analog test signal; and comparing the actual measurement test signal with the simulation test signal to obtain the operation state of the photovoltaic inverter. According to the invention, whether the photovoltaic inverter is in an abnormal operation state or not can be known conveniently and quickly by comparing the actual measurement test signal with the simulation test signal. Furthermore, when the photovoltaic inverter is in an abnormal operation state, possible fault reasons of the photovoltaic inverter can be quickly positioned by analyzing the difference value between the actual measurement test signal and the simulation test signal, and a control scheme or a design scheme of the photovoltaic inverter can be adjusted.

The invention belongs to the technical field of hypersonic wind tunnel tests, and discloses a test evaluation device and method for a slender body appearance attitude control jet flow aerodynamic interference effect. The test evaluation device comprises a spray pipe bracket, a sieve-shaped core pipe and a balance which are sequentially connected from front to back; the balance adopts an annular structure, a semiconductor strain gauge is pasted on a sensitive element of the balance, the rear end of the balance is connected with a jet-flow supporting rod, and the jet-flow supporting rod is provided with a jet-flow air inlet; a spray pipe is fixed on the spray pipe bracket; a spray pipe outlet penetrates out of the aircraft model; a jet flow pipeline which sequentially penetrates through the jet pipe support, the sieve-shaped core pipe, the aerodynamic force measuring balance and the jet flow supporting rod is arranged on the central axis of the aircraft model. The test evaluation method comprises the steps of conventional force measurement test, jet flow force measurement test, determination of influence quantity of jet flow interference, jet flow supplementary force measurement test, determination of jet flow medium parameters, and establishment of a jet flow state table of the attitude control jet flow engine of the slender aircraft. And technical support is provided for design and installation of the attitude control jet engine of the slender aircraft.

The invention discloses a balance centering measurement and correction method for a wind tunnel force measurement test, and belongs to the technical field of wind tunnel force measurement. The problem that in the prior art, a traditional balance centering measurement and correction method is large in test result error due to the fact that the actual centering position and the theoretical centering position of a balance are inconsistent is solved. According to the invention, a wind tunnel test model is designed and processed, the positions of loading points are determined, each loading point is loaded, the angle of attack of a balance is adjusted through a support system, and then a normal force and a pitching moment are measured through the balance; according to the normal force and the pitching moment, force arms of the loading points at the fixed angle of attack are obtained, and the actual distance between each loading point and the balance calibration center in the flow direction is obtained through fitting; and obtaining the actual position of the balance center according to the difference between the actual distance and the theoretical distance from each loading point to the balance center along the flow direction. The method effectively improves the precision of the obtained balance center calibration position, and can be applied to a wind tunnel force measurement test.

The embodiment of the invention relates to the field of foundation pile reverse design, in particular to a foundation pile reverse design method and equipment based on multi-objective optimization and machine learning. One specific implementation mode of the method comprises the steps that a foundation pile actual measurement data set is collected; updating processing is conducted, and a foundation pile actual measurement updating data set is obtained; dividing the foundation pile actual measurement update data set to obtain a foundation pile actual measurement sample data set and a foundation pile actual measurement test data set; based on the foundation pile actual measurement sample data set and the foundation pile actual measurement test data set, constructing a machine learning model for predicting the bearing capacity of the foundation pile; generating an initial foundation pile design data set; based on a machine learning model for predicting the bearing capacity of the foundation pile, optimizing the initial foundation pile design data set to obtain target foundation pile design data; and sending the target foundation pile design data to a foundation pile construction control terminal to construct a foundation pile. According to the implementation mode, the foundation pile design efficiency and accuracy are improved.

The invention discloses a Gaussian process modeling method for a controlled separation steerage of an assembly aircraft, and belongs to the technical field of aerodynamics. In order to achieve the steering aerodynamic force obtaining precision of the combined aircraft, the method comprises the steps that a steering aerodynamic force database of a secondary aircraft in a disturbing flow field in the separation process of the combined aircraft is obtained through a wind tunnel grid force measurement test; the obtained first-stage aircraft attack angle, second-stage aircraft attack angle, two-stage aircraft gap and second-stage aircraft rudder deflection angle are combined into an input feature matrix, and the obtained pitching rudder deflection moment of the second-stage aircraft in the interference flow field of the first-stage aircraft serves as an output vector to obtain a training set, a verification set and a test set; and importing the training set into a Gaussian process regression model, training the Gaussian process regression model, verifying the trained Gaussian process regression model by using the verification set, and then testing by using the test set to obtain the Gaussian process regression model of the controlled separation steerage of the combined aircraft to predict the steerage aerodynamic torque.

The invention discloses a gas-liquid low-temperature two-phase flow precise monitoring and metering test system, which comprises a segmented sensing acquisition module, a high-speed signal analysis module, a pulsation resonance identification module, an active damping control module, a phase change intelligent identification module and a monitoring metering output module, a plurality of groups of separated fluid dynamic response sensors are arranged in a low-temperature two-phase flow pipeline and are respectively positioned at a two-phase mixing inlet section, a middle stable section and an outlet section, so that segmented data acquisition is realized. The method has the advantages that the resonance risk caused by gas-liquid phase change can be accurately identified, a damping structure is regulated and controlled in real time, and system resonance and sensor damage are effectively avoided; meanwhile, through multi-point flow velocity fusion and gas phase molar fraction dynamic correction, high-precision measurement of the two-phase fluid volume flow is achieved, the measurement stability and the system safety are improved, and the device is widely suitable for low-temperature gas-liquid mixed transportation scenes.

The invention discloses a deck type arch bridge static wind load separation measurement test device, and belongs to the technical field of bridge detection, the deck type arch bridge static wind load separation measurement test device comprises a support plate, a support frame, an arch rib force measurement mechanism, a stand column force measurement mechanism and a bridge floor force measurement mechanism, and the support plate is supported on the ground through a support block; the arch rib force measuring mechanism is supported on the supporting plate, and the stand column force measuring mechanism is supported on the supporting frame and located on one side of the convex face of the arch rib section. The bridge deck force measuring mechanism is supported on the supporting frame and located on the side, away from the arch rib section, of the stand column force measuring mechanism. The device is simple in structure, convenient to use and high in universality, and all measuring parts are not connected with one another, so that adverse factors such as turbulent flow and eddy current in the testing process can be reduced on the premise that the complete aerodynamic configuration of the arch bridge is guaranteed. And independent force measurement is carried out on the arch rib sections, the arch bridge stand columns and the bridge deck slab, so that the influence of pneumatic interference among components on a measurement result is thoroughly eliminated, and the accuracy and reliability of data are greatly improved.

The invention belongs to the technical field of shock tunnel tests, and discloses a test device for measuring multiple parameters in a high-enthalpy shock tunnel tube. The multi-parameter measurement test device is installed on a driven section of the shock tube and comprises a front high-pressure transition section, a high-pressure visible section and a rear high-pressure transition section which are sequentially connected from front to back through flanges. The multi-parameter measurement test device adopts built-in circular tube thick-wall optical glass to perform non-contact optical measurement, so that the pressure bearing safety is ensured, and the influence of the change of an inner flow channel on a flow field is avoided; the correction lens is arranged on the outer side of the optical glass, so that the problem of imaging distortion of the circular tube is avoided, and more effective test data is further obtained; meanwhile, the device is combined with a reserved surface laser incidence window, a line laser incidence and receiving interface, a pressure sensor interface and a heat flow sensor interface, is used for measuring multiple parameters such as a wave system structure, components, pressure and heat flow flowing in the shock tube, and has engineering practical value.

The invention provides a GIS circuit breaker switching-on strategy method considering contact ablation, relates to the field of high-voltage electric appliance control, and solves the problem that the sending time of a switching-on action signal is not accurate due to the fact that the influence of contact ablation is not fully considered in an existing method. The method comprises the following steps: carrying out a dynamic resistance measurement test on GIS circuit breakers of the same model, determining dynamic resistance change data, fitting the dynamic resistance change data into a change relation curve related to contact resistance and stroke of the GIS circuit breakers and the number of times of breaking, and representing the ablation condition of the contact; the method comprises the following steps: acquiring historical operation data of a GIS circuit breaker in online operation, obtaining dynamic resistance during current opening, comparing the dynamic resistance with a change relation curve obtained in a dynamic resistance measurement test, determining a current contact ablation condition, and performing compensation adjustment on closing command sending time of the GIS circuit breaker next time according to the change relation curve; according to the invention, the excitation inrush current of different degrees generated during the no-load switching-on operation of the transformer can be effectively suppressed.

The invention relates to a high-temperature-resistant temperature and vibration composite sensor applied to the field of measurement and testing, which comprises a composite sensor body and a composite circuit board arranged in the composite sensor body, and adopts the cooperation of a thermal insulation sleeve, a magnetic induction ring, a thermal insulation protection feedback unit and a ventilation regulation and control unit. According to the composite sensor, the adaptability of the composite sensor body to the environment is effectively promoted, the composite sensor body can be effectively isolated and protected under the high-temperature condition, and the situation that components in the composite sensor body are damaged due to continuous heat transfer is prevented, so that the durability of the composite sensor body is remarkably improved; meanwhile, heat exchange protection can be effectively carried out on the internal environment of the composite sensor body, the influence of heat on all components in the composite sensor body is further reduced, and the heat resistance of the composite sensor body is enhanced.

The invention discloses a wind tunnel continuous force measurement test method, and belongs to the technical field of wind tunnel force measurement tests. In order to solve the problem that the precision of a wind tunnel continuous force measurement test is not high when the Mach number is large, the method comprises the steps that a wind tunnel test supporting system, a force measurement test balance and a test model are installed in a wind tunnel, and a windless test is carried out to obtain windless test data; performing a wind test, and collecting wind tunnel test data of different train tests; processing to obtain the load of the test model under the action of the wind tunnel test section airflow; converting a force vector and a torque vector under a balance coordinate system into a force vector and a torque vector under a test model body shafting and a force vector and a torque vector under a wind tunnel airflow shafting through conversion of a coordinate axis system; obtaining a force coefficient vector and a torque coefficient vector under a shaft system of the test model body and a force coefficient vector and a torque coefficient vector under a shaft system of wind tunnel airflow; a curve of aerodynamic force changing along with the angle of attack and a curve of torque coefficient changing along with the angle of attack of the test model are obtained through fitting with a local weighted linear regression method.

The utility model relates to the technical field of grating performance testing, and particularly discloses a high-speed grating performance testing device, which comprises a testing motor, an output shaft of the testing motor is provided with a grating disc to be tested; a reference encoder which is installed on the test motor and is used for measuring the actual rotation amount of the test motor; the shading part is used for carrying a light-emitting element and a light-sensitive element to be detected; the moving assembly is used for carrying the shading cloth part and can drive the shading part to do linear translational motion along the X axis, the Y axis and the Z axis in the three-dimensional space; the temperature control part is used for wrapping the shading part and changing the temperature in the shading part; the test host is electrically connected with the reference encoder and the photosensitive element; according to the utility model, measurement errors at different installation distances can be obtained, the measurement precision of the high-speed grating encoder applied to the high-speed environment measurement work in the later period is ensured, and the production quality of the high-speed grating encoder is ensured.

The utility model relates to the technical field of air tightness detection, and discloses a flywheel housing gear chamber air tightness detection device comprising a detection box, the top of the detection box is fixedly connected with a vacuum pump, the output end of the vacuum pump is fixedly connected with a connecting pipe, and the outside of the connecting pipe is fixedly connected with a vacuum valve. The outer portion of the connecting pipe is fixedly connected with a vacuum meter, the bottom end of the connecting pipe is fixedly connected with a connecting hose, the bottom end of the connecting hose is arranged outside a quick-change connector, the quick-change connector is fixedly connected to the top of a gear chamber sealing cover plate, and a gear chamber sealing gasket is arranged at the bottom of the gear chamber sealing cover plate. And the gear chamber sealing gasket is arranged at the top of the gear chamber. According to the utility model, through the arrangement of the vacuum pump, a measurement test of the vacuum sealing performance of the gear chamber can be carried out conveniently, and through the arrangement of the water tank, the sealing performance of the gear chamber can be judged more accurately.

The invention belongs to the technical field of aerospace force measurement test power measurement, and discloses a three-component micro-load balance calibration device and a three-component micro-load balance calibration method. The three-component micro-load balance calibration device comprises a pulley, an air bearing, a vibration exciter, a loading head, a calibration support rod, a six-degree-of-freedom adjusting mechanism, a laser positioning source, a nylon rope, a spherical loading point and the like. The six-degree-of-freedom adjusting mechanism is connected with the balance, the balance is fixedly connected with the calibration supporting rod, one end of the calibration supporting rod is fixedly connected with the balance, the other end of the calibration supporting rod is connected with the loading head, the loading head is connected with the pulley through the nylon rope, the air bearing is arranged in the pulley, the vibration exciter is arranged on the pulley base, and the laser positioning source is installed on the support. And the light source of the laser displacement meter can be projected to the loading head. According to the invention, the balance calibration of the micro-load balance with the measuring range within 10mN can be realized, and the defects that the loading cannot be realized due to the too small measuring range of the micro-load balance, the calibration result of the micro-load balance is influenced due to the too large uncertainty of the calibration system and the like are overcome.

The invention discloses a drop hammer device for an impact performance test of an unmanned aerial vehicle body structure and a test method.The device comprises an impact force measurement test platform, an impact loading test platform and a multi-stage electric hydraulic telescopic rod, and the impact force measurement test platform is located above the impact loading test platform; the multi-stage electric hydraulic telescopic rod is mounted between the impact force measurement test platform and the impact loading test platform; the method comprises the following steps: S1, installing a drop hammer device and adjusting an impact loading test platform; s2, mounting and testing a tested object of the unmanned aerial vehicle; and S3, test recording. According to the drop hammer device for the impact performance test of the unmanned aerial vehicle body structure and the test method disclosed by the invention, the device can adjust the test positions of unmanned aerial vehicle tested objects with different shapes and specifications at high precision, solves the problem that centers of the three objects are coaxial, and can meet different drop hammer test conditions; the method is used for evaluating the collision safety of the civil light and small unmanned aerial vehicle with the maximum takeoff weight of about 0.25 kg-25 kg.

The invention discloses a vehicle frame type undercarriage in-situ turning moment measurement test verification device which comprises a bottom plate, a vertical module, a torsion module, an undercarriage and a measurement module. The vertical module comprises two triangular supports, a fixed beam, two sliding rails, two sliding blocks, a vertical hydraulic actuator, a loading seat and two connecting pieces; the torsion module comprises a bearing seat, a bearing, a rotating shaft, a torque sensor, two connecting rods and two torsion units, and each torsion unit comprises a fixing frame and a heading hydraulic actuator; the measuring module comprises two mounting plates and 2M measuring units. Each measuring unit comprises a force bearing seat, a six-dimensional force sensor and two flanges. The device can accurately measure the tire load and the torsional moment when the undercarriage turns in situ, is modularized, is easy to maintain and upgrade, can provide stable and reliable measurement data, and reduces the influence of external environmental factors.

The utility model discloses a microcomputer-controlled high-precision disc spring pressure testing machine which comprises a workbench, a lower pressure plate, an upper pressure plate, a displacement measuring scale and a microcomputer. Four vertically-arranged guide columns are fixed to the workbench, the two guide columns are oppositely arranged, an upper cross beam is fixedly installed between the two guide columns, ball screws are installed on the inner sides of the guide columns, a movable cross beam is installed between the two ball screws, and the ball screws can rotate to drive the movable cross beam to move in the vertical direction. The bottom of the lower pressing disc is installed on the table top of the workbench through load sensors, and the number of the load sensors is at least two. The upper pressing disc is fixedly installed on the movable cross beam and located over the lower pressing disc. The displacement measuring scale is vertically installed on the upper pressure plate and the lower pressure plate, and the displacement measuring scale can measure the distance between the upper pressure plate and the lower pressure plate. The load sensor and the displacement measuring scale are both in data connection with the microcomputer so as to realize high-precision measurement test of the disc spring.

The invention discloses a bearing lubricating grease film thickness measurement test device and method, and relates to the technical field of mechanical device tests.The bearing lubricating grease film thickness measurement test device comprises a test box and a supporting table, a disc driving mechanism is arranged in the test box, and a ball driving mechanism is arranged on the supporting table; the ball driving mechanism comprises a ball rotation driving mechanism and a ball movement driving mechanism, the ball movement driving mechanism is further provided with a longitudinal load loading mechanism and a supporting mechanism used for placing balls, the supporting table is provided with an optical measurement system, and the test box is further provided with an environment simulation system. The balls and the glass disc are extruded through the longitudinal load loading mechanism, lubricating grease is smeared on the lower portion of the glass disc, the loaded condition and the working condition of the lubricating grease in the main shaft bearing are truly reduced as much as possible, and the film thickness parameter of the lubricating grease is obtained under the action of the optical measurement system. Therefore, real-time monitoring and recording of the film thickness of the test lubricating grease are realized.

The invention discloses a method for judging abnormal abrasion of an end face seal and a computer program product, and belongs to the field of abnormal sealing monitoring. A plurality of monitoring values such as the end face sealing compression amount, a temperature monitoring point, a leakage amount monitoring point and a pressure monitoring point in the end face sealing test system are used as characteristic values, the collected temperature parameter rising rate is used as a basis, and the fluctuation conditions of signals of the end face sealing compression amount, the leakage amount monitoring point and the pressure monitoring point are considered; according to the method, the current temperature rising condition is corrected, finally the current temperature rising condition is compared with a preset temperature rising speed threshold value for judgment, multiple analysis and judgment are conducted, the accuracy of temperature anomaly judgment is improved, and meanwhile the method is based on an infrared end face sealing measurement test device, and the accuracy of sealing face temperature rise measurement is improved.

The invention discloses a spectrum analysis method and device based on an X-ray fluorescence spectrometer and a medium, belongs to the technical field of electronic measurement and testing, and aims to solve the technical problems that in existing spectrum analysis, background deduction is carried out through a peak stripping method, effective background deduction needs a large number of iteration processes, and the time complexity of an algorithm is large. The method comprises the following steps: acquiring an actually measured spectrogram of a sample to be detected and a pure element spectrum corresponding to a target element through an X-ray fluorescence spectrometer; respectively deducting the background in the actually measured spectrogram and the background in the pure element spectrum by combining a straight line method and a peak stripping method; and determining the specific gravity of the pure element spectrum of the target element in the target spectrogram, and determining the content of the target element in the to-be-detected sample based on the specific gravity. By means of the method, the number of iterations needed by the peak stripping method can be remarkably reduced, then the efficiency of the peak stripping method in the spectrogram background deduction process is improved, and the spectral line background is deducted efficiently.

The invention provides a continuous variable thrust jet flow interference wind tunnel test method and system. The method comprises the following steps: determining incoming flow conditions and test jet flow parameters; constructing a continuous variable thrust test system; performing a low-pressure environment spray pipe thrust calibration test on the continuous variable thrust test system; establishing a variable thrust jet flow force measurement test model; and carrying out a continuous variable thrust jet flow interference wind tunnel test to obtain a jet flow interference wind tunnel test result of the variable thrust jet flow force measurement test model under the continuous variable thrust condition. According to the invention, through the design and construction of the continuous variable thrust jet flow generation device and the jet flow control system, the correlation between the thrust of the nozzle and the jet flow obtained through calibration is combined, so that the continuous change of the thrust can be realized in the test process; data acquisition and test result acquisition of the jet flow interference wind tunnel test of the variable thrust jet flow force measurement test model under the continuous variable thrust condition are completed, and force measurement test research is carried out on the reverse jet flow interference effect of a main engine of a recoverable rocket and other continuous variable thrust aircrafts.

The invention relates to the field of multifunctional mechanical measurement test stands, and discloses a multifunctional mechanical measurement test stand which comprises a motor fixing support and a test adjusting assembly which are connected to form a test stand base. The motor fixing assembly and the motor testing assembly are installed above the motor fixing support and the testing adjusting assembly respectively, the motor fixing assembly is used for fixing a motor, and the motor testing assembly is used for installing motor testing equipment. Compared with the prior art, the method has the advantages that multiple testing devices are installed in a unified mode, testing is conducted according to the optimal sequence, and a series of problems that the testing cost is high, the efficiency is low, and the testing result is inaccurate due to the testing sequence are solved.

This invention relates to the field of research on the operational characteristics of overpressure relief devices, and particularly to an experimental device for measuring the operational characteristics of overpressure relief devices under water hammer conditions. The device includes: a high-pressure air compressor, a frame, a piston accumulator, a quick-opening device, a high-pressure test assembly, and a high-frequency dynamic pressure sensor. This invention enables the measurement of operational characteristics under different pressure rise rate loads caused by water hammer phenomena on a test bench, providing an experimental platform for the research on the operational characteristics of overpressure relief devices under high pressure rise rates. The overall device is simple, quick, and stable. It effectively solves the problem of applying high pressure rise rate loads in current overpressure relief device operational characteristic measurement tests, overcomes the danger of using combustible gas explosions as pressure sources in existing operational characteristic measurement tests, and overcomes the shortcomings of existing test methods, such as long testing times, the need to calculate gas explosion pressure, and the difficulty in accurately controlling the pressure rise rate.

The invention discloses a multifunctional granular material repose angle calibration test device, and belongs to the technical field of granular material repose angle measurement. The device comprises a long cylinder lifting device, a parameter measuring platform, a particle pushing device, a particle filling and recycling device and a long cylinder, through ingenious cooperation of all the components, automatic cylinder changing, long cylinder clamping and lifting, parameter measurement and particle pushing and recycling are achieved; the automation level of a granular material repose angle measurement test is improved, and a large amount of manpower, material resources and time are saved; the granular material repose angle measuring device improves the test process of granular material repose angle measurement, reduces the test measurement error, improves the working efficiency, achieves the effect of centralized three-dimensional operation, saves the test space and cost, and makes a prominent contribution to the measurement of the granular material repose angle.

To provide a substrate for a high frequency device, which satisfies requirements of low dielectric loss tangent, adhesion and transparency.A substrate for a high frequency device comprising a transparent glass substrate 16 and a transparent resin base material 20 bonded to the glass substrate 16 via an optical clear adhesive 18, wherein the dielectric loss tangent of the resin base material 20 in dielectric loss tangent measurement test is 0.01 or less, the peel strength in peel test is 3.0 Worn or more, and the amount of out gas in out gas test is 5.0 μg / g or less.