255 results about "Measurement test" patented technology

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 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 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 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 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 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 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.

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.

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.

The present invention discloses a single-point reconstruction method for the initial reading of a balance in a wind tunnel model rudder efficiency test. The method uses the current rudder deflection angle state as a reference to correct the initial reading before adjustment, thereby solving the initial reading zero-point drift caused by temperature changes in the balance strain gauge and data acquisition equipment, thereby quickly obtaining the initial reading applicable to the current rudder deflection angle state. Within the angle variation range, only one sample point needs to be collected to calculate the initial reading at the required angle, and the entire collection and processing process takes no more than 3 seconds. Compared with the traditional initial reading collection method, the single-point reconstruction method shortens the time by 360 seconds and improves the efficiency by 99%. The test result error introduced by the method is less than 0.00005, which meets the advanced index requirements of the low-speed wind tunnel force measurement test. At the same time, the evaluation criteria for the applicable scenarios of the method are designed to provide a guiding basis.

The invention belongs to the technical field of steady-state scanning wind tunnel tests of terminal-sensitive projectiles, and particularly relates to a backlight profile-based steady-state scanning parameter measurement system for a terminal-sensitive projectile, which comprises a backlight measurement system for steady-state scanning parameters of the terminal-sensitive projectile and a steady-state scanning parameter resolving system, wherein the terminal sensitive projectile steady-state scanning parameter backlight measurement system comprises an active light source, a high-speed camera and a vertical wind tunnel; the steady-state scanning parameter resolving system comprises an edge line segment acquisition module, a steady-state scanning angle acquisition module and a steady-state scanning rotating speed acquisition module; the obtained steady-state scanning angle and the steady-state scanning rotating speed of the terminal-sensitive projectile are important test data of a vertical wind tunnel terminal-sensitive projectile steady-state scanning parameter measurement test, and a data basis can be provided for design optimization and performance identification of the terminal-sensitive projectile.

The invention discloses a high-temperature and high-pressure acoustic-electric combined measurement test device, the test device comprises an experiment cabin, a piston rod, an ultrasonic assembly and a resistor assembly, the experiment cabin comprises a pressure cavity surrounding shell and a base, a pressure cavity body is formed in the pressure cavity surrounding shell, and a piston opening is formed in the other end of the pressure cavity surrounding shell; one end of the piston rod penetrates through the piston opening and is positioned in the cavity body of the pressure cavity; the ultrasonic assembly comprises an ultrasonic transmitting probe and an ultrasonic receiving probe, the ultrasonic transmitting probe is located in one end of the piston rod, and the ultrasonic receiving probe is located in the base; the resistor assembly is located between the piston rod and the base. The invention further provides a use method of the high-temperature and high-pressure acoustic-electric combined measurement test device. Compared with the prior art, the high-temperature and high-pressure acoustic-electric combined measurement test device has the advantage that rock resistivity and ultrasonic wave velocity characteristics can be measured at the same time in a high-temperature and high-pressure environment.

The application provides a kind of bar type magnetic core effective permeability low frequency distribution measurement method and device, it is related to low frequency fluctuation detection and application technical field.The method comprises: winding test coil on coil framework, the winding length of test coil is measured and the number of turns is recorded;Test magnetic core is inserted into different positions of test coil, and the inductance of test coil is measured when test magnetic core is in different positions;According to the relationship between permeability and inductance, the area average effective permeability of test magnetic core in different positions is calculated;Based on the preset algorithm, the effective permeability distribution function of test magnetic core is fitted;According to the effective permeability distribution function of test magnetic core, the effective permeability distribution function of the bar type iron-based nanocrystalline alloy magnetic core to be measured is obtained.The application can reduce the measurement error of magnetic core effective permeability, improve the modeling reliability, and obtain the effective permeability distribution function, so as to reduce repeated experiments and improve the modeling efficiency.

The invention discloses an experimental measurement test bed for interaction force between a retainer and a guide surface. The test bed comprises a base, a displacement loading device, an acting force measuring device, a tested unit, an inner ring loading device and a driving device, the tested unit comprises a tested retainer, a tested bearing inner ring, a tested bearing outer ring and a bearing seat; the acting force measuring device is used for measuring the force / torque borne by the measured retainer; the displacement loading device is used for adjusting the spatial position of the measured retainer through the acting force measuring device and positioning the measured retainer; the inner ring loading device is used for applying a static radial load to the inner ring of the tested bearing; the driving device is used for driving the tested bearing inner ring to rotate. The test bed can directly and accurately measure the interaction force between the retainer and the guide surface in the rolling bearing.

The invention discloses a novel power system false data injection attack detection method based on CPO-CNN-SE. The method comprises the following steps: preprocessing a measurement test of a novel power system; performing hyper-parameter optimization by using a crown porcupine optimization algorithm (CPO) to improve the precision of the CNN detection model; meanwhile, in consideration of synchronous increase of the FDIA detection speed, a compression excitation (SE) attention mechanism is introduced, a CNN-SE mixed learning model is formed, and the characterization efficiency of the CNN on FDIA spatial features is enhanced; and finally, carrying out binary classification on the FDIA feature data through a full connection layer, a sigmoid classifier and a binary cross entropy loss function. According to the invention, the FDIA detection precision is improved, and the synchronous improvement of the detection speed is realized.

In some implementations, a test device may initiate a set of measurements by a set of sensors of the test device and of a device under test (DUT), wherein the DUT is a memory device. The test device may obtain the set of measurements of the DUT from the set of sensors based on initiating the set of measurements. The test device may analyze the set of measurements of the DUT, using a first model, to identify one or more defects present with the DUT. The test device may determine, using a second model, that the one or more defects present with the DUT satisfy a failure threshold. The test device may provide, based on the failure threshold being satisfied for the DUT, an output indicating that the failure threshold is satisfied for the DUT.

The present invention provides a binder powder for nonaqueous secondary battery electrodes, which contains a particulate polymer, and which, when a measurement test for obtaining a sheet sample by hot-pressing the binder powder and measuring the surface free energy of the sheet sample is carried out, can increase the surface free energy of the sheet sample. The dispersion component [gamma] Sd and the polar component [gamma] Sp of the surface free energy satisfy the following formula (1): O < = [gamma] sp / [gamma] sd < = 2 (1).

Disclosed example video extensometers include: a load string configured to secure a test specimen; an imaging device configured to capture images of a surface of the test specimen when secured in the load string; a storage device configured to store a plurality of first calibration parameters corresponding to intrinsic properties of the imaging device; and control circuitry configured to: perform a verification process using the first calibration parameters to verify that a plurality of second calibration parameters correspond to an arrangement of the test specimen with respect to the imaging device; and perform an optical strain measurement process to measure displacement of the test specimen based on the first calibration parameters and the second calibration parameters.

The invention discloses a PIV flow field measurement test support frame for a cooling fan, an upper connecting frame is provided with a plurality of upper fixing holes, the upper connecting frame is provided with a support plane used for being attached to and supported on an end face position outside or inside a fan hole area of the cooling fan, one end of each of the plurality of fixing holes penetrates through the support plane, and the other end of each of the plurality of fixing holes penetrates through the support plane. Hot melt adhesive is dripped into the multiple upper fixing holes to fix the cooling fan and the upper connecting frame; the lower connecting frame is used for being detachably supported and fixed on a test platform or a base; the upper end of the vertical cylinder frame is fixed with the upper connecting frame, and the lower end of the vertical cylinder frame is fixed with the lower connecting frame; when the fanning hole area of the cooling fan is located on the inner side of the vertical cylinder frame on the vertical projection plane, through holes are formed in the peripheral wall of the vertical cylinder frame. The cooling fan model can be conveniently and stably supported to complete a PIV test, it is guaranteed that hot melt adhesive cannot enter the fan to damage the model, it is guaranteed that the cooling fan model can be rapidly disassembled and assembled, and meanwhile, the flow field of the cooling fan cannot be affected.

A continuous wind tunnel force measurement test method belongs to the technical field of wind tunnel force measurement tests. To solve the problem of low accuracy in continuous wind tunnel force measurement tests at relatively high Mach numbers, the present invention includes installing a wind tunnel test support system, a force measurement test balance, and a test model in the wind tunnel, conducting a no-wind test to obtain no-wind test data; conducting a windy test and collecting wind tunnel test data for different train runs; processing to obtain the loads on the test model under the action of the airflow in the wind tunnel test section; through coordinate system transformation, converting the force vector and moment vector in the balance coordinate system into the force vector and moment vector in the test model body axis system and the force vector and moment vector in the wind tunnel airflow axis system; obtaining the force coefficient vector and moment coefficient vector in the test model body axis system and the force coefficient vector and moment coefficient vector in the wind tunnel airflow axis system; respectively using the method of locally weighted linear regression to fit the curves of the aerodynamic force of the test model varying with the angle of attack and the curve of the moment coefficient varying with the angle of attack.

An intelligent perception system measurement test method based on image color calibration, the method is used for color defect parameter acquisition of the camera, and is used for intelligent perception test data set calibration, and the intelligent model is tested by using the calibrated data set. The method can apply the color parameters of the camera to the data through a quadratic function, obtain a test data set containing related hardware parameters, make the test of the intelligent model more close to the actual performance of the future algorithm, effectively improve the accuracy of the test result, and by comparing the test results before and after calibration, whether the current camera meets the task requirements can be effectively determined.

The present application provides a gas rudder force measurement test installation bracket and an operation method, including: a frame body fixed to the top of the test bench by bolts; a mounting plate with a keyway and bolt holes for installing a gas rudder force measurement device on one side, the keyway being symmetrically arranged along the center of the mounting plate, and the bolt holes being symmetrically arranged on both sides of the keyway; a vertical adjustment device installed on the frame body for adjusting the position of the mounting plate in the vertical direction; a horizontal adjustment device installed on the frame body for adjusting the position of the mounting plate in the horizontal direction. By independently setting the frame body and the mounting plate, and simultaneously using the horizontal adjustment device and the vertical adjustment device on the frame body to adjust the position of the mounting plate, and then installing the gas rudder force measurement device after fixing the adjusted position, compared with the related art, the present application has higher versatility and saves the installation labor cost at the same time.

The utility model discloses a while-drilling earthquake source energy and wave field measurement test device, which relates to the technical field of well drilling data experiment equipment and comprises a support component, the support component comprises a shaft upper cover, a wellhead four-way joint and a shaft which are sequentially connected through flanges, and a well inner cavity is formed. The detection assembly comprises a rock sample box connected with the shaft and an impact force detector located below the rock sample box, a rock sample capable of sliding relative to the rock sample box is arranged in the rock sample box, a cushion block making contact with the rock sample is arranged at the bottom of the rock sample box, and the rock sample acts on the impact force detector through the cushion block. The rock sample box is internally provided with a plurality of ground wave detectors in contact with the rock sample, the ground drilling assembly comprises a drill bit, the drill bit is used for impacting the rock sample, the problems that a lot of time needs to be spent on finding a proper well position and the cost is high when a field experiment is carried out in reality are solved, and by applying the device, the non-timeliness of the field experiment and the experiment cost are greatly saved.

The invention discloses an electromagnetic disturbance simulation test method, system, equipment and medium in an extreme multi-physical environment, and belongs to the technical field of electric power engineering and measurement testing, and the method comprises the steps: electrifying a test device, obtaining extreme multi-physical environment data, generating multiple groups of test conditions, and setting test points; setting the voltage of a high-voltage source, setting an acquisition mode and a trigger value of an oscilloscope, controlling the switching frequency of a pulse transmission line to be adjusted and applied to a to-be-detected electronic transformer, drawing an I-V curve of the electronic transformer according to an acquisition result, and combining the I-V curves of the electronic transformer under multiple groups of temperature and humidity conditions, and analyzing to obtain the failure voltage and the failure current of the electronic transformer. According to the method, the performance data of the electronic mutual inductor under different temperature and humidity conditions and electromagnetic disturbance environments are comprehensively and accurately collected, the data can be deeply analyzed through a scientific and reasonable data processing method and a strict failure judgment criterion, and the performance and reliability of electronic equipment are accurately evaluated.

The invention provides an automatic calibration method and device for a detector tester, electronic equipment and a medium, and relates to the field of calibration measurement test.The initial moment T0 of a detector for obtaining a damped oscillation signal is obtained through the detector tester, and the method comprises the steps that i-M, i-M + 1 and i-M + 2 are obtained, and sample point signals x [i-M], x [i-M + 1], x [i-M + 2]... x [i] corresponding to the moment i are obtained, and calculating a filtered signal y [i-1] through a formula, when x [i] is greater than G * y [i-1] and G is a multiple of a threshold coefficient, determining a starting moment T0 of a damped oscillation signal, obtaining a damping coefficient, a natural frequency and sensitivity based on T0, and automatically calibrating a detector tester based on the damping coefficient, the natural frequency and the sensitivity. According to the method, the detector tester is automatically calibrated, complicated operation of calibration personnel is avoided, and the calibration precision and the calibration efficiency are improved.

The present disclosure relates to systems and methods related to test and measurement systems, and in particular to millimeter wave material testing systems including a test and measurement instrument for testing the radar transmittance and reflectivity of a material. The test and measurement equipment measures the insertion loss of the material under test. The test and measurement equipment includes a reference device in contact with a first surface of the material under test, the reference device including a reflective component and an absorptive component. The test device is in contact with a second surface of the material under test that is opposite to the first surface. The test device includes: a first transmitter for outputting a first signal of a predetermined frequency to the reflective component of the reference device through the material under test; a first receiver for receiving the first reflected signal from the reflective component; a second transmitter for outputting a second signal of a predetermined frequency to the absorptive component of the reference device through the material under test; and a second receiver for receiving the second reflected signal from the material under test.

The present application discloses a data optimization method, device, equipment and medium based on cubic spline interpolation, which relates to the field of data processing technology, including obtaining original pressure data of the surface of a wing model after a wind tunnel pressure test is completed, generating a pressure data matrix based on the original pressure data; calculating the pressure coefficient of each pressure measuring point in the pressure data matrix, obtaining the pressure coefficient matrix of all pressure measuring points, and setting a corresponding angle of attack sequence to be interpolated for each of the pressure measuring points; using the cubic spline interpolation method to interpolate the pressure coefficient determinant of the pressure measuring point in the pressure coefficient matrix to the corresponding angle of attack sequence to be interpolated, so as to obtain the pressure coefficient interpolation results of all the pressure measuring points of the wing model; using the pressure coefficient interpolation results to optimize the wind tunnel pressure test data, which can avoid the Runge phenomenon caused by the Lagrange high-order interpolation polynomial, solve the data oscillation problem at the edge of the interpolation interval, improve the data rounding accuracy, and provide technical support for the optimization of the wind tunnel pressure test.

1. The name of the design product: the universal measuring test adapter for the aviation special equipment with pull rod. 2. The use of the design product: for the aviation special equipment measuring test. 3. The design points of the design product: the combination of shape and pattern. 4. The picture or photo that best shows the design points: perspective view 1.