69 results about "Surface pressure" patented technology

The invention provides an active and passive combined microwave remote sensing detection method for earth surface air pressure and air pressure profile, which comprises the following steps: by combining a satellite-borne / airborne millimeter wave differential absorption radar and a satellite-borne / airborne microwave radiometer and utilizing oxygen differential absorption measurement, obtaining accurate land / ocean surface air pressure data; and the air pressure profile is further obtained by combining temperature and humidity profile data measured by a satellite-borne / airborne microwave radiometer. Compared with the prior art, the method has the advantages that active and passive microwaves are adopted for combined detection, detection information obtained by a microwave radiometer is complemented, calculation of the surface pressure is enhanced, and the surface pressure inversion precision is improved; according to the method, the surface pressure value can be obtained, and the atmospheric pressure profile can also be obtained. According to the method, accurate surface pressure detection can be realized, and the atmospheric pressure profile can be further deduced by combining the temperature profile and the humidity profile observed by the microwave radiometer.

The invention relates to the technical field of fluid mechanics modeling and aerodynamic acoustic analysis, in particular to a spectral orthogonal decomposition-based separated flow wall surface pressure pulsation dominant structure modeling method, which comprises the following steps of: acquiring a whole flow field and / or wall surface unsteady pressure data of a separated flow under a preset working condition; performing spectral orthogonal decomposition on the unsteady pressure data, performing frequency domain decoupling on multi-scale features, and extracting feature values and spatial dominant feature modes under each feature frequency; constructing a complex wave packet physical parameterized model, fitting the spatial dominant feature modals, and compressing the spatial dominant feature modals into sparse physical parameter vectors after nonlinear regression solution; and reconstructing a wall surface pressure pulsation dominant component based on the sparse physical parameter vector and the characteristic value, and carrying out at least one of flow mechanism analysis and pneumatic order reduction modeling according to the dominant component. Therefore, the problems of low reconstruction precision and the like caused by the fact that asymmetric evolution and variable acceleration convection of a large-scale structure in separation flow wall surface pressure pulsation cannot be accurately represented in a frequency domain in related technologies are solved.

This application discloses a method for establishing a pressure distribution data prediction model, relating to the field of aircraft aerodynamic design technology. The method includes: dividing a reference pressure distribution dataset and operating conditions under various conditions into a training set, a validation set, and a test set; dividing the training set into training subsets corresponding one-to-one with grid regions; setting a reference neural network model for each grid region; adaptively expanding the training subsets based on a preset expansion region to obtain an expanded training subset; using the expanded training subsets within each grid region to obtain a reference neural network model with a mapping relationship between operating conditions and pressure distribution data; updating the preset expansion region using the validation set and jumping to the step based on the preset expansion region until a pressure distribution data prediction model for each grid region is obtained; testing the pressure distribution data prediction model using the test set, and if a first preset condition is met, it is the final prediction model. This method constructs a model to quickly and accurately predict surface pressure distribution data.

The utility model relates to oil seal detection frock technical field especially relates to a kind of floating oil seal surface pressure and torque on-line detection device, including pedestal, through-hole is provided in the pedestal, through-hole is provided with force transmission shaft, linear bearing is provided with the outer sleeve of force transmission shaft, the floating oil seal of being detected is set in the one end of force transmission shaft, sensor is set in the other end, and the sensor is used to measure the surface pressure and torque transferred by the force transmission shaft. By increasing linear bearing in pedestal, and change main shaft to linear optical axis, reduce the friction between shaft and support base, optimize the transmission accuracy of surface pressure value;By canceling the use of traditional torque sensor and pressure sensor, change to two-dimensional force sensor, torque value and surface pressure value can be detected simultaneously, and the sensor is set at one end of linear optical axis, all weight of frock is supported by support base, so that the sensor is not affected by other force values, further improve the detection accuracy.

The invention provides a testing device for balls, which comprises a support member and a panel, and is characterized in that the support member is of a spherical structure; the panel is detachably attached to the outer surface of the support member such that the panels having different surface patterns can be attached to the outer surface of the support member according to test requirements. According to the ball testing device provided by the invention, the influence of panels with various surface styles on the overall aerodynamic performance of a ball is researched in a controllable and accurate manner. The ball testing device can further comprise a pressure scanning device arranged in the supporting component and a through pressure measuring pipe formed on the panel, one end of the pressure measuring pipe is arranged at the static pressure hole, and the other end of the pressure measuring pipe is connected to the pressure scanning device, so that the surface pressure change of the ball can be directly measured; and more comprehensive and more accurate measurement data can be provided. The invention further provides a ball testing system.

The application discloses a high angle of attack nonlinear separated flow aerodynamic force correction method, which comprises the following steps: obtaining aircraft surface pressure distribution data at zero reduced frequency by using a DES method; dividing surface elements on the surface area of the aircraft, and generating an AIC matrix AIC by using a dipole grid method based on the geometric information of each surface element; obtaining the aerodynamic force and moment of each surface element according to the AIC, and generating an aerodynamic force matrix A DLM,k＝0 of all surface elements at zero reduced frequency by using the aerodynamic force and moment of each surface element; interpolating the aircraft surface pressure distribution data obtained by using the DES method to each surface element to obtain the aerodynamic force matrix A DES of all surface elements; obtaining a force correction matrix W according to A DLM,k＝0 and A DES ; correcting the AIC matrix AIC by using the force correction matrix W to obtain a corrected aerodynamic force influence coefficient matrix AIC * ; and performing aerodynamic force correction and aeroelastic calculation by using the corrected aerodynamic force influence coefficient matrix AIC * , so as to complete the high angle of attack nonlinear separated flow aerodynamic force correction. The application can have both the calculation precision of CFD and the calculation efficiency of an engineering method.

Provided is a rotary electric machine that suppresses local increases in surface pressure generated on a stator by using a housing with improved circularity, and that improves reliability. The rotary electric machine of the present invention has a rotor, a stator, and a cylindrical housing that fixes the stator from the outer periphery side, the housing having a flange that extends in the outer peripheral direction on the axial end portion of the outer peripheral surface, the flange having a recess that extends in the circumferential direction.

The utility model relates to the technical field of environmental test equipment, and particularly discloses a window sealing device of a high-low temperature damp-heat low-pressure test box, which comprises a window frame, and a multi-sealing component, an elastic component and a buffer layer are arranged on the inner wall of the window frame; the multi-sealing assembly is composed of an outer-layer sealing ring, an inner-layer sealing ring and a middle supporting ring, the elastic assembly comprises a plurality of annular spring sets which are arranged on the outer wall of the extension plate and are annularly distributed, and the outer-layer sealing ring resists high temperature, chemical corrosion and friction loss and bears external environment pressure; low-temperature elastic compensation and deformation self-adaption capacity are provided through the inner-layer sealing ring, stress is dispersed in the middle of the supporting ring, the situation that single-layer sealing loses efficacy due to local overload is avoided, and therefore multi-layer sealing protection is achieved. The pre-tightening force of the annular spring set is transmitted to the supporting ring through the inner-layer sealing ring, overall supporting of the sealing structure is formed, and the annular array design of the annular spring set ensures that the pressure of the sealing face is evenly distributed.

The invention provides a dynamic response method adopting automobile intelligent windshield wiper direct current control, which comprises the following steps: generating initial curved surface feature distribution information by analyzing curved surface area friction force and key point resistance distribution, and analyzing a swing angle change rate and contact surface pressure distribution in combination with a real-time position calibration value; obtaining detailed resistance distribution data of each key point; calculating a swing force balance value and a regional resistance compensation value, and determining a forward trajectory correction value and a reverse trajectory adjustment value; a dynamic motion track parameter is generated by combining the speed optimization weight ratio, the track parameter updating rate is updated, and adjusted windshield wiper arm motion control data is obtained; the windshield wiper arm is driven to execute the dynamic track, and if the pressure distribution deviates from a preset threshold value, the swing force balance value is finely adjusted; and analyzing the action of the friction force of the curved surface region on the long-term operation stability, and judging whether the track parameter update rate meets the adaptive requirement or not by combining the region resistance compensation value to obtain a final long-term parameter adjustment range.

The application provides a combined prediction method and system for a wind resistance coefficient and a surface pressure field, and relates to the technical field of automobile aerodynamics. The combined prediction method predicts the pressure field and the wind resistance coefficient in parallel in the same network, and calibrates the wind resistance coefficient derived from the pressure field obtained by pressure field integration and the wind resistance coefficient directly regressed by the network with physical consistency constraints, so that the model has physical credibility and interpretability while ensuring numerical accuracy, thereby being capable of locating a key stress area and serving an automobile modeling iteration process.

The utility model relates to an optical MEMS pressure sensing device for measuring the surface pressure of a water tank, and the device comprises a pressure obtaining mechanism which is constructed to be of a disc structure with an inner cavity, a first plane of the pressure obtaining mechanism is provided with a pressure obtaining diaphragm, and a second plane of the pressure obtaining mechanism is provided with a second pressure obtaining diaphragm; a second plane of the pressure acquisition mechanism is provided with a filling hole communicated with an inner cavity of the disc structure, and the filling hole is arranged to be sealed and covered by a sealing cover; the pressure sensing mechanism is arranged in an inner cavity of the connecting rod connected with the pressure acquisition mechanism; the pressure transmission mechanism is arranged to be of a pipeline structure communicating with an inner cavity of the pressure obtaining mechanism and an inner cavity of the connecting rod, and the pipeline structure is arranged to be filled with pressure conduction liquid. In addition, the utility model further provides the water tank. The optical MEMS pressure sensing device provided by the embodiment of the utility model is convenient to install and arrange, good in anti-vibration effect, high in measurement accuracy, convenient to use and high in adaptability.

The application provides a high-speed train surface flow field rapid prediction method based on extremely sparse measurement data, which comprises the following steps: (1) constructing a high-precision surface pressure distribution database; (2) extracting a dominant space mode of a training set pressure distribution matrix; (3) compressive sensing reconstruction; (4) adopting an improved particle swarm optimization algorithm to obtain an optimal sensor layout scheme; and (5) establishing a rapid prediction model. The application has reasonable conception, can accurately reconstruct the surface pressure field of the high-speed train under multiple working conditions, and can rapidly and effectively predict the surface pressure distribution of the high-speed train under different working conditions through the construction of the high-precision surface pressure distribution database.

A method for estimating well surface pressure includes measuring pressure in a well during pumping a fracture treatment. For each of at least two changes in flow rate of the pumping, a well pipe friction pressure loss, a perforation friction pressure loss and near wellbore pressure loss are determined using events in the measured pressure induced by the at least one change in flow rate. Fracture pressure is determined at times of each of the at least two changes in flow rate from the measured pressure using the determined well pipe friction pressure loss, determined perforation friction pressure loss and near wellbore pressure loss. Fracture pressure is interpolated between the determined fracture pressures to estimate the surface pressure at times intermediate the determined fracture pressures.

The application discloses a pressure measuring hole layout method and system, an embedded atmospheric data sensing system and a flying wing layout aircraft. The pressure measuring hole layout method comprises the following steps: S100, a full-machine computational fluid dynamics model of the flying wing layout aircraft is constructed, surface pressure data of the aircraft under different flight conditions is obtained through CFD calculation, and different flight conditions and corresponding surface pressure data of each flight condition form a surface pressure database; and S200, a mixed integer linear programming model is constructed, and a pressure measuring hole layout scheme is solved based on a pressure measuring hole candidate point set and the corresponding surface pressure database. The application is particularly suitable for the pressure measuring hole layout of the flying wing layout aircraft, and can improve the measurement accuracy and robustness of the embedded atmospheric data sensing system carried by the flying wing layout aircraft.

The invention provides a wingtip vortex active control method and system based on surface pressure feedback and synthetic jet and a medium, and the method comprises the steps: collecting pressure data in real time based on a pressure sensor array arranged on the surface of a wing; performing time-frequency analysis on the pressure data, and extracting the shedding frequency and pressure pulsation characteristics of the current wingtip vortex; retrieving flow field characteristics based on the wingtip vortex optimal disturbance modal database of the pre-solution analysis to obtain dimensionless information; converting the dimensionless information into driving frequency, driving voltage and a phase instruction of a synthetic jet actuator to generate periodic jet; continuously monitoring the power spectrum density and suction peak change of a pressure sensor at a specific position of a wing, and judging whether a flow field meets a rapid instability condition or not; and if the rapid instability condition is not met, the frequency or phase difference of the synthetic jet is adjusted, rapid capture and closed-loop control from flow field data to optimal disturbance application can be achieved, and instability and rapid attenuation of the wingtip vortex are effectively promoted.

This invention provides a method and system for measuring atmospheric data using integrated optical sensing, comprising: real-time acquisition of surface pressure distribution and surface recovery temperature using a FADS subsystem, and inversion of Mach number, static pressure, and attack angle parameters; periodic laser emission using a MOADS subsystem, and analysis of atmospheric parameters such as air velocity, attack angle, and density through backscattering spectroscopy; independent Kalman filters running on the FADS and MOADS subsystems, performing local optimal estimations using aerodynamic equations and observation equations; employing a federated Kalman filtering algorithm, dynamically adjusting the weights based on the residual covariance matrix of the two subsystems, and jointly solving the pressure, temperature data, and optical signals based on the adjusted weights, outputting Mach number, attack angle, total / static pressure, total / static temperature, and atmospheric density. The technical solution of this invention addresses the technical problems of high cost and limited environmental adaptability associated with using FADS or MOADS systems alone in existing technologies.

This surface pressure display device comprises: a reception unit that receives detection data from a surface pressure measurement tool passed through a conveyance path for conveying a substrate; and an arithmetic unit that calculates the surface pressure applied to the substrate, on the basis of the detection data. The arithmetic unit: identifies, on the basis of the conveyance speed calculated on the basis of time variation in the detection data received by the reception unit, the position in the conveyance direction with respect to rows of a plurality of pressure detection units aligned in the width direction of the conveyance path, at respectively different times; rearranges detection signals of the respective rows identified at the respective times in the order of conveyance direction position; and generates a surface pressure image on the basis of the detection signals of the rows in correspondence with the conveyance direction position.

The invention relates to the technical field of fluid mechanics, and discloses a nozzle surface pressure field distribution prediction method, system and device and a storage medium, and the method comprises the steps: obtaining a three-dimensional structure of a sample nozzle under different values of a geometric model critical dimension parameter, and combining with a fixed value of a boundary condition parameter of the sample nozzle, simulating each three-dimensional structure to obtain a surface pressure field distribution simulation result; based on the geometric feature data of each three-dimensional structure and the surface pressure field distribution simulation result, training the deep learning model to obtain a nozzle surface pressure field distribution prediction model; and determining a three-dimensional to-be-measured structure of the to-be-measured nozzle according to the actual values of the key dimension parameters of the geometric model of the to-be-measured nozzle, and obtaining a surface pressure field distribution prediction result by using the prediction model based on geometric feature to-be-measured data obtained by sampling the three-dimensional to-be-measured structure. The nozzle surface pressure field distribution can be quickly and accurately predicted, and the nozzle design efficiency and the performance optimization level are improved.

The application discloses a kind of based on ambient temperature helium's lateral thermal jet interference simulation method, this method includes: according to the research of inflow condition and gas engine jet condition obtains jet and inflow momentum ratio, mass flow ratio;Model and nozzle meet geometric similarity condition, using ambient temperature helium jet simulates real gas jet, according to ground wind tunnel inflow momentum condition and simulation momentum ratio condition, determine the momentum of helium jet, total pressure and mass flow;Using ground wind tunnel test method obtains jet interference wall surface pressure distribution, interference force / torque.The application can be used for ground simulation hot jet interference wind tunnel test.

The invention relates to the technical field of electrolysis, and discloses an intelligent electrolytic bath shell surface hardness judgment method based on pressure self-adaption, which comprises the following steps: acquiring cylinder impact shell surface pressure data in real time through a pressure sensor, calculating the pressure change rate at adjacent sampling moments, and calculating a hardness index by using a pressure-hardness mapping model in combination with the change rate and the impact frequency. The index is compared with a threshold value, the shell surface hardness is judged, a high-low pressure mode is selected, an electromagnetic valve is controlled to switch an air source, the air cylinder pressure is stabilized through a self-adaptive algorithm, the crust breaking pressure is rapidly and stably adjusted, it is ensured that the system efficiently operates under different shell surface hardness, compared with a traditional system, the daily air consumption is reduced by 54.9%, and energy conservation and emission reduction are achieved; the crust breaking success rate is increased to 97% from 85%, and production interruption and material waste are reduced; the replacement period of the hammer head is prolonged from 15 days to 35 days, the maintenance cost is reduced, and the production efficiency is improved.

The utility model belongs to the technical field of pressure test, and discloses a wing surface pressure distribution experiment teaching demonstration platform, which comprises a wind tunnel, a module plug, a test model, a hose I, a multi-tube pressure gauge and a water tank, the test model comprises a test point concentration head, a mounting chuck and an airfoil model; the mounting chuck comprises a circular plate I and a circular plate II which are connected; the measuring point concentration head is of a cubic structure and is fixedly connected with the circular plate I; the test model is provided with a plurality of pressure measuring holes and a plurality of channels, and the pressure measuring holes and the channels are the same in number. The wind tunnel is used for providing airflow for the airfoil model; the module plug comprises a cubic block and a pipe I; a plurality of through holes A are formed in the cubic block, and the through holes A are arranged into an array B; the multi-tube pressure gauge is used for measuring the pressure intensity of the pressure measuring hole; the water tank is connected with the multi-tube pressure gauge and used for supplying water to the multi-tube pressure gauge and adjusting the liquid level height in the multi-tube pressure gauge. When the hose I and the channel are disassembled and assembled, the operation is simpler and more convenient.

An object of the present disclosure is to provide an adsorbent body that can be adsorbed on any curved surface.SOLUTION: An adsorbent according to one aspect of the present disclosure is an adsorbent that adsorbs to a surface of an object by vacuum adsorption, the adsorbent including an adsorbent main body having a concave portion, a vacuum generator that depressurizes the concave portion, and a plurality of adsorption portions arranged inside the concave portion, wherein the plurality of adsorption portions each have an arc-shaped bottom surface and are arranged so as to surround a central portion of the concave portion as a whole and so as to be in contact with a wall surface constituting the concave portion, and the plurality of adsorption portions are configured so that ground contact surface pressures of the respective adsorption portions are balanced when adsorbing to the object.SELECTED DRAWING: Figure 2

The application discloses a kind of marine hydrographic detecting instrument launching device and its launching method, it is related to detecting instrument launching technical field, including throw frame and mounting bracket.The application disclosed has when submarine meets special situation, needs to throw load, one-way electromagnetic valve opens, seawater is filled into throw frame, adjusting hydraulic cylinder one drives sealing extrusion plate to extrude water body, water body is guided to the inside wall of throw frame under the action of conical guide column, the reaction force of extrusion of water body cooperates compression spring rod to push the abutment plate, when the pressure received by abutment plate reaches certain value, curved pull-off rod is pulled off, then curved surface pressure plate is passively deflected towards outside, L-shaped butt block loses the limitation of curved surface pressure plate, in this moment, abutment plate is passively pushed out from throw frame, and the impact energy carried by abutment plate is relatively large, so that the submarine has an upward impact kinetic energy after one throw, accelerating the rising effect of submarine.

An object of the present disclosure is to provide a method for predicting a change in surface pressure over time in consideration of the progress of transformation for a coil after winding.SOLUTION: A prediction method according to an aspect of the present disclosure is a method for predicting a change in surface pressure of a coil obtained by coiling a hot-rolled sheet, the method including a first calculation step of calculating an initial stress state of the coil immediately after coiling using operation conditions including a shape of the hot-rolled sheet, a cooling condition, and a coiling condition, a second calculation step of calculating a change in a coil internal stress state based on a change in volume of the coil using a temperature distribution over time and a transformation rate of the coil after coiling, and a step of predicting a change in surface pressure of the coil over time using the initial stress state calculated in the first calculation step and the change in the coil internal stress state calculated in the second calculation step.SELECTED DRAWING: Figure 1

According to the nonlinear strength criterion of the rock-soil body, the stress condition when the strength of the rock-soil body is damaged meets the formula: q / 2 = a (p / 2) 2 + b (p / 2) + C0, the principal stress sigma1 when the rock-soil body is damaged under different surrounding rocks sigma3 is obtained through a conventional triaxial shear test of the rock-soil body, and the specific numerical values of parameters a, b and C0 are solved through quadratic regression analysis between q / 2 and P / 2. C0 can also be measured through a tensile strength test, so that a rock-soil body strength criterion formula is obtained; the strength criterion is derived on the basis that the rock-soil body begins to crack from the maximum shear stress surface, the influence of the initial cohesion and the maximum shear surface pressure stress on the cohesion is considered, the uncertainty of determining parameters by drawing a Mohr circle tangent in the traditional Mohr-Coulomb criterion is avoided, the fitting precision of test data is improved, and the test efficiency is improved. And meanwhile, the calculation accuracy in practical application is improved, and the solved tangent slope is less than or equal to 1.0, which accords with the definition of physics on the friction coefficient.

The application relates to the technical field of atmospheric data and belongs to the technical field, and provides an embedded atmospheric data system parameter solving method based on triangulation. The method comprises the following steps: performing aerodynamic simulation on an airplane in a full envelope range, and selecting a suitable surface pressure hole layout; constructing a parameter solving coefficient sum for the pressure hole layout; constructing a numerical table of the parameter solving coefficient sum under a series of Mach numbers, attack angles and sideslip angles, forming three-dimensional data with the sum as a coordinate axis; performing spatial division on scattered data points (x, y, z) through a Delaunay triangulation method, forming a tetrahedral mesh in a three-dimensional space; positioning the position of (x, y, z) obtained by the pressure hole measurement value through a DT.pointLocation method in Matlab, determining the tetrahedral mesh where the (x, y, z) is located; and solving corresponding atmospheric data parameters through interpolation. The algorithm performance is reliable, and atmospheric parameters can be accurately solved according to the pressure measurement value of the embedded pressure sensor.

The invention relates to an adapter (100) for connecting a radiator thermostat (300) to a radiator valve (200) comprising a base body (10), a preloading element (30), and a union nut (20), wherein the base body (10) has a receptacle (12) for the radiator valve (200) and at least one contact surface (11a) for forming surface contact with an axial contact surface (213) of the radiator valve (200), and wherein the union nut (20) is screw-connectable or screw-connected to a threaded ring (11) of the base body (10), and wherein the preloading element (30) can be arranged between the union nut (20) and the base body (10) such that the preloading element (30) is forced radially inwards at least partially by screwing the union nut (20) onto the threaded ring (11), and an axial surface pressure is exerted between the contact surface (11a) and the axial contact surface (213).

The application provides an ECMWF mode element bias correction method based on AttUnet, and belongs to the meteorological prediction field. The method uses a deep convolutional neural network in 4 elements of ECMWF mode output surface, 2m temperature, surface pressure, 2m specific humidity and 10m wind, and performs bias correction on the 0.125 degree resolution ECMWF mode output result. The method first constructs a feature library according to the ECMWF mode output elements, and then uses the XgBoost tool to analyze the sample library and sort the importance, and further screens the factors combined with artificial experience and considers the terrain information. Then, the deep convolutional neural network is used for prediction and bias correction to obtain more accurate 0.125 degree grid products. At the same time, in the model debugging stage, by optimizing the learning rate and the loss function, the model has good prediction performance for extreme disastrous weather.

The invention discloses a large-scale cabin section structure model ultimate strength test device and test method under a complex load, and relates to the technical field of ship structure test, and the device comprises a large-scale structure test platform, a large-scale cabin section structure model, a boundary constraint device, a support constraint device and a complex load loading device. The bottom of the model is positioned and supported through four sets of supporting constraint devices, one end simulates end boundary conditions through two sets of boundary constraint devices, and the other end applies a composite load of bending moment, torque and surface pressure through a complex load loading device. According to the method, the multi-load coupling effect borne by a ship under the real sea condition can be accurately simulated, the problems that an existing test load working condition is single, boundary constraint is inaccurate and the like are solved, accurate evaluation of the ultimate strength and the failure mechanism of a large-scale cabin section structure model under the multi-load combined effect is achieved, and the test efficiency is improved. And the spanning of a ship structure strength test technology from single-load evaluation to multi-load coupling accurate evaluation is promoted.