15 results about "Surface pressure" patented technology

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 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.

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.

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 present application relates to wide area aircraft technical field, disclose a kind of wide area aircraft atmospheric data pressure measuring layout method and device of waverider configuration, comprising: the aerodynamic simulation of each flight state of target waverider configuration wide area aircraft is carried out, obtains the surface pressure distribution of target waverider configuration wide area aircraft under each flight state;According to the surface pressure distribution of target waverider configuration wide area aircraft under each flight state determines the alternative pressure measuring point set for carrying out atmospheric data pressure measurement;From alternative pressure measuring point set, select the pressure variation with the change of angle of attack or sideslip angle meets the preset rule as the target pressure measuring point set of target waverider configuration wide area aircraft.The problem that sensor cannot be arranged in special position such as waverider configuration wide area aircraft stagnation point is fully considered, realizes with less sensor quantity to complete flight parameter acquisition and calculation, provides effective solution for the flight parameter measurement of waverider configuration wide area aircraft full flight process.

The present application belongs to the technical field of flow field intelligent prediction based on numerical simulation, and particularly relates to a ship surface fluid pressure field intelligent prediction method, program, device and storage medium based on a combination of a reduced-order model and a neural network. The present application maps the unstructured grid data obtained by numerical simulation into structured grid data by using a surrogate model, ensuring the uniformity of the subsequent data processing format. On this basis, the main modal of the surface pressure field and the corresponding grid node normal vector is extracted by the reduced-order model. Then, the full-link neural network is used to realize the rapid prediction of the new ship type basis coefficient, so that for the new ship type, only the design parameters need to be input without inputting the ship grid, the rapid prediction of the ship surface load distribution, the external normal vector distribution and the pressure resistance can be realized, and reliable technical support can be provided for the ship structure strength design and safe navigation at sea.

This invention discloses a parametric simulation method for ocean forecasting based on cross-density vertical mixing processes, comprising: Step 1, acquiring a three-dimensional multivariate marine environmental field, water depth data, vortex trajectory dataset, vortex kinetic energy data, and atmospheric driving field. The environmental field includes sea surface height, ocean temperature, ocean salinity, and meridional and zonal current velocities; the atmospheric driving field includes wind speed, sea surface pressure, 2-meter temperature, sea surface temperature, shortwave radiation, cloud component, precipitation, and relative humidity; Step 2, introducing vortex horizontal asymmetry, constructing a parametric ocean model based on cross-density vertical mixing processes, and calculating the vertical mixing coefficient; Step 3, constructing a regional ocean model based on the regional ocean numerical model ROMS, and verifying the vertical mixing coefficient; Step 4, performing ocean forecasting using the parametric ocean model based on cross-density vertical mixing processes. This invention links vertical mixing with the influence of vortex horizontal asymmetry, improving the accuracy of multi-element ocean simulation.

The application discloses a bulge design method of presetting arbitrary three-dimensional pressure distribution, comprising the following steps: inputting a preset three-dimensional pressure distribution and a leading edge line, generating a corresponding initial shock wave surface, discretizing the leading edge line into a plurality of discrete points and constructing a corresponding initial flow surface; solving the curvature radius and the flow surface pressure distribution of each initial flow surface point; based on the curvature radius and the pressure distribution, twisting the initial flow surface point to a virtual meridian plane, solving the flow parameters thereof; constructing a shock wave preset line of the initial shock wave surface and a corresponding local tangent surface; mapping the flow parameters to a three-dimensional Cartesian space, reconstructing an iterative flow surface, generating a three-dimensional flow field containing an iterative shock wave surface and an iterative bulge surface; judging the three-dimensional flow field coordinate error, if the three-dimensional flow field coordinate error is less than a preset threshold value, outputting the iterative bulge surface, otherwise, replacing the initial value with the current iterative flow surface and the shock wave surface and repeating the above steps until convergence. The application realizes the reverse design of the bulge with the arbitrary three-dimensional pressure distribution, and expands the flexibility of the bulge design.

The application discloses a kind of hypersonic wind tunnel nozzle cooling structure design method, belongs to aerodynamics wind tunnel design technical field.The application solves the problem that the temperature limit of currently commonly used material is lower than the temperature of wind tunnel operation during the operation of hypersonic equipment, and it is difficult to simultaneously consider support-thermal protection performance.The application determines the inner wall surface pressure according to the design Mach number of nozzle by designing the thickness of nozzle inner shell, calculates the thickness of nozzle inner shell according to the national standard of pressure vessel, determines the position and size range of nozzle cooling structure, carries out CFD simulation calculation on nozzle cooling structure, carries out multi-objective optimization on nozzle cooling structure, selects materials and processing technology.The application solves the problem that hypersonic wind tunnel can normally operate under existing material system by reasonable cooling structure design when the operating temperature of hypersonic wind tunnel exceeds the temperature limit of existing materials.

Providing a technology to suppress uneven surface pressure in the electrode body. [Solution] The energy storage device disclosed herein comprises an electrode body in which positive electrodes and negative electrodes are alternately stacked with a separator in between, a case for housing the electrode body, and a spacer disposed between the case and the electrode body. The outer surface of the electrode body has a first surface at one end in the stacking direction of the positive and negative electrodes, a second surface at the other end in the stacking direction, and a third surface between the first and second surfaces. The first surface, the second surface, and the third surface are composed of a separator. The first end of the separator in the longitudinal direction is located on the third surface. The separator has a first region that includes the first end and is located on the third surface. The first region covers a part of the spacer and has a joint with the spacer.

The application provides a simulation method and system for deep water explosion impact resistance of a large-depth underwater vehicle, and the method comprises the following steps: obtaining underwater vehicle external geometric data and target structure region, and obtaining structure material parameters; calculating a deep diving static water pressure, an equivalent static pressure distribution of the target structure region, and establishing a prototype simulation model and a scale-down test model; performing a test to obtain simulated structure surface pressure, simulated structure strain time curve, simulated bubble motion trajectory and scale-down strain data; based on the above data, constructing a static water pressure term, an impact wave and a bubble pulsation pressure time term, and superimposing and constructing a joint load simulation model, and then obtaining an error, and if the condition is met, the simulation is completed. The simulation method for deep water explosion impact resistance of the large-depth underwater vehicle can dynamically couple high static water pressure, underwater explosion shock wave and bubble pulsation, so as to realize precise simulation of the deep water explosion impact load resistance of the large-depth underwater vehicle structure.

The present disclosure relates to a method for controlling slugging that eliminates the need for subsurface measurements, using exclusively data obtained from the topside. The present disclosure is intended to increase the efficiency and scope of slug mitigation strategies, contributing to the optimization of production and reduction of associated losses. Specifically, the proposed method uses measurements of pressure, flow rate, and other variables collected at the top, being integrated with advanced control algorithms and predictive models, promoting the optimization of multiphase flow, mitigating the impacts of slugging, and reducing operational losses.