24 results about "Full scale test" patented technology

The invention discloses an aerospace equipment performance evaluation method based on digital test data fusion, and belongs to the field of electronic engineering and computer science, and the method comprises the steps: designing a physical test and a digital test, selecting related indexes of aerospace equipment, and carrying out corresponding physical and digital tests around the related indexes of the aerospace equipment; performing preprocessing and multi-source data integration on the physical test data; performing data quality evaluation and virtual data division on the digital test data; and performing double fusion on the result through an adaptive fusion algorithm to obtain a performance evaluation result. The advantages of the digital test and the physical test can be fully exerted, and comprehensive and accurate evaluation of the aerospace equipment performance is realized through deep fusion of the digital test data and the physical test data.

The invention discloses a method and a device for matching and mapping data of a digital-real test of aerospace equipment, belongs to the field of electronic engineering and computer science, and is suitable for the aerospace equipment capable of simultaneously carrying out a digital test and a real object test. Comprising the steps of reading a data file of a digital-real test, matching space coordinates of the data of the digital-real test, matching time sequences of the data of the digital-real test, matching magnitude of the data of the digital-real test and mapping the data of the digital-real test. According to the method, the differences of the aerospace equipment data real-time test data in the data magnitude, the time dimension and the space dimension are considered, the corresponding relation of the data real-time test data is established through the mapping and matching method, and full fusion and utilization of the data real-time test data are facilitated.

The invention discloses a high-precision digital penetration simulation method. The method comprises the following steps: constructing a penetration body finite element model and a target finite element model; obtaining penetration conditions of the penetration body, wherein the penetration conditions comprise an attack angle, a penetration rate and a penetration angle; obtaining a contact relation and a boundary condition of the penetration body and the target; on the basis of the conditions, simulation of the penetration process is carried out; comparing a simulation result of the penetration process with an actual test result; and if the deviation between the simulation result of the penetration process and the actual test result is within the threshold value, outputting a penetration body overload curve, and if the deviation is not within the threshold value, correcting the penetration body finite element model and the target finite element model, and repeating the steps. The invention further discloses high-precision digital penetration simulation equipment and a storage medium. According to the high-precision digital penetration simulation method provided by the invention, a digital penetration simulation result can be ensured to be consistent with a real object test result, and the precision of the digital penetration simulation method is improved.

The invention provides a rocket launching safety analysis method based on a mobile rocket launching device, and the method comprises the steps: assembling a first finite element model of the rocket launching device and a second finite element model of a rocket body according to each typical working condition demand before rocket launching, and generating an analysis model corresponding to each working condition; corresponding preset conditions are applied to all the analysis models, simulation testing is carried out, and testing data corresponding to all the analysis models are obtained; and comparing each test data with a corresponding preset safety threshold, and outputting a safety evaluation result of rocket launching. In the design stage, the problems of insufficient structural strength, installation interference and the like are found in advance by simulating and covering the full-process working conditions of erecting, docking, to-be-launched and the like, and the subversive risk in a physical test is avoided. According to the scheme, through multi-aspect evaluation, the comprehensiveness of safety analysis is improved, the dependence on a physical test is reduced, and the research and development cost and period are reduced.

The invention discloses a method for judging leakage of a series sealing system of aircraft reciprocating motion parts. The method comprises the following steps: S1, constructing a two-dimensional axis model; s2, setting material attribute parameters; s3, defining an analysis step; s4, setting a friction coefficient; s5, defining boundary conditions and loads; s6, carrying out grid division; s7, calculating contact pressure distribution data; s8, oil film thickness distribution is obtained through calculation; S9, the contact pressure of each sealing face is calculated; s10, the flow in the two combined seals is calculated; and S11, obtaining a leakage conclusion of the series sealing system. Reliable sealing performance can be directly obtained through a simulation calculation technology, the problems of long test period, high cost and the like in a real object test are avoided, and the sealing performance test universal for different types of airplane reciprocating motion part sealing systems is realized. Through finite element simulation and multi-object-field fluid-solid coupling numerical simulation, interaction between the series sealing systems is analyzed, and whether the series sealing systems leak or not can be accurately determined.

The invention discloses a method for improving the tank body strength of a metal packaging tank. The method comprises the steps that a three-dimensional tank body model is established; dividing the intervals of the rolling ribs into M groups, and adjusting the intervals of the rolling ribs in each group one by one in the adjusting range of the intervals of the rolling ribs so as to obtain A tank body models; carrying out analogue simulation of a negative pressure test on the A tank body models to output A negative pressure simulation intensities; b tank body models with the negative pressure simulation strength corresponding to the rolling rib spacing of each dimension being larger than or equal to the preset negative pressure strength are screened out; real object tanks of the B tank body models are manufactured, and a real object test is conducted on the real object tanks; and M rolling rib spacing ranges corresponding to the real object tank bodies with the real object negative pressure strength larger than or equal to the preset negative pressure strength are selected, and the final rolling rib position is determined in the ranges. Software simulation and physical tests are combined to determine the position of the rolling rib for improving the strength of the tank body, so that the time cost and the economic cost are effectively reduced.

The application belongs to the field of control system design, and discloses a thrust estimation method based on a time domain convolution network, and proposes a thrust estimator based on a multilayer residual time domain convolution network. On the one hand, a Gaussian error linear unit activation function is used to replace the correction linear unit in the residual block to solve the neuron death problem. On the other hand, the overall structure of the multilayer convolution network is adjusted by using residual connection, so that the network training speed and the thrust estimation effect are further improved. The comparison results with the traditional seven methods show that the method has significant advantages in convergence speed and estimation accuracy. In addition, the application also applies the method to an actual control system of an aero-engine, and further verifies the real-time performance and feasibility of the control scheme through a micro turbojet engine test bed test.

The invention provides a system early-stage scheme refined design and verification method based on a total element digital model and a prototype, and relates to the technical field of system modeling simulation. The system early-stage scheme refined design and verification method based on the total-factor digital model and the prototype comprises the following steps: step 1, establishing an equipment demand model; 2, designing a demand model and system simulation model interface; step 3, constructing a system simulation model; step 4, expanding the scheme space; 5, space expansion is designed in detail; and step 6, performing optimization verification. According to the method, based on a total-element digital prototype and scheme design and verification, the original work with verification conditions in a detailed design stage is realized, the work is advanced to the scheme design stage, design defects are found in advance, the original work needs to be carried out through a large number of physical tests in an integrated test stage, and the work needs to be carried out through multiple iterations in digital prototype test verification. And the test reliability and the test efficiency of the physical test are improved.

A reliability design optimization method suitable for separating impact components of a shedding connector belongs to the technical field of engineering optimization. In order to solve the problems that traditional reliability optimization design is highly dependent on physical test, and the test cycle is long and the cost is high, the present application proposes a spatial self-adaptive sampling strategy for Kriging surrogate model, which combines model prediction uncertainty and gradient information, dynamically identifies active constraints, thereby effectively reducing misclassification and redundant sampling; in view of the different response characteristics of the objective function and the constraint function, an anisotropic sampling space is constructed for each function, guiding the sample to focus on the area with higher optimization potential; based on the maximum chord deviation criterion, the sampling points are placed in the nonlinear significant area, so as to improve the accuracy of the local surrogate model and accelerate the convergence speed, thereby realizing reliability design optimization.

The present application relates to a kind of MMC valve electric stress equivalent calculation method, device and storage medium, wherein method includes: step S1: based on electromagnetic transient simulation obtains the time-domain waveform of each working condition under flexible converter valve bridge arm current;Step S2: select the time-domain waveform of any phase bridge arm current is obtained by windowed Fourier transform in preset time window, and further extract direct current component and fundamental frequency alternating current component;Step S3: draw electric stress curve;Step S4: based on the electric stress curve under each working condition respectively statistics first eigenvalue of the first characteristic value of the electric stress level of direct current component and the second eigenvalue of the electric stress level of fundamental frequency alternating current component;Step S5: obtain test direct current value and test alternating current value after combining safety factor.Compared with prior art, the present application accurately quantifies the electric stress requirement of flexible converter valve from system operating condition without relying on large-scale physical test.

The utility model belongs to the technical field of airplane structure design and verification, and discloses an airplane aileron full-size test supporting device which comprises a loading mechanism and a bearing mechanism. Wherein a plurality of groups of loading mechanisms are arranged at intervals, each group comprises two loading mechanisms which are arranged at an angle, the two loading mechanisms respectively correspond to one aileron joint of the aileron, and the loading mechanisms are configured to apply tension or pressure to the aileron joints; the bearing mechanism is provided with a supporting structure, and the supporting structure is hinged to the aileron. The loading mechanisms are configured to apply tension or pressure to aileron joints of the ailerons so as to simulate the influence on the ailerons when an aircraft wing deforms, each loading mechanism corresponds to one aileron joint of the aileron so as to ensure that the ailerons can be uniformly stressed, and the bearing mechanism can fully limit the ailerons and prevent the ailerons from overturning in the operation process of the loading mechanisms; the structure of the test equipment is greatly simplified, the aileron angle can be changed, and subsequent aileron loading tests at different angles can be met.

The invention provides a data fusion aviation flight control actuator reliability quantitative comprehensive evaluation method, and relates to the field of mechanical and electrical product reliability, and the method comprises the steps: S1, collecting the design data of a flight control actuator; s2, developing a development test and an identification test; s3, converting the fault time of the reliability strengthening / HALT test into fault occurrence time under a conventional stress condition; s4, converting the fault time of the reliability acceleration test into fault occurrence time under a conventional stress condition; s5, performing MTBF evaluation in a development test stage based on results of the step S3 and the step S4; and S6, performing multi-stage MTBF comprehensive evaluation based on the Bayesian theory. According to the method, the advantages of low cost, high efficiency and repeatability of a simulation test and high confidence of a physical test are utilized, the one-sidedness and limitation of a single data source are made up, a potential fault mode is more comprehensively exposed, and the confidence level is improved; reliability verification of the flight control actuator which is long in service life and high in reliability can be achieved under the limited test time and sample size.

The invention discloses an anti-shaking storage bottle structure design method and an anti-shaking storage bottle structure.The anti-shaking storage bottle structure design method specifically comprises the following steps that a storage bottle three-dimensional model is established; performing structural simulation analysis on the three-dimensional model of the storage bottle to obtain structural stress distribution; performing fluid simulation analysis on the three-dimensional model of the storage bottle to obtain fluid motion parameters; and determining the storage bottle structure according to the structural stress distribution and the fluid motion parameters. According to the method, rapid optimization design of the storage bottle structure can be achieved, and high-cost physical tests in a traditional design method can be avoided.

The invention relates to an MMC valve electrical stress equivalent calculation method and device and a storage medium. The method comprises the steps that S1, time domain waveforms of bridge arm currents of a flexible DC converter valve under all working conditions are obtained based on electromagnetic transient simulation; s2, selecting the time domain waveform of any phase of bridge arm current, performing windowing Fourier transform in a preset time window to obtain a frequency spectrum component, and further extracting a direct current component and a fundamental frequency alternating current component; s3, drawing an electrical stress curve; s4, respectively carrying out statistics on a first characteristic value representing the electrical stress level of the direct-current component and a second characteristic value representing the electrical stress level of the fundamental-frequency alternating-current component based on the electrical stress curve under each working condition; and S5, obtaining a test direct current value and a test alternating current value in combination with the safety coefficient. Compared with the prior art, the electrical stress requirement of the flexible direct current converter valve is accurately quantified from the operating condition of the system under the condition of not depending on a large-scale physical test.

The present application relates to a safety valve pilot valve debugging system based on a semi-physical real-time simulation system, a main valve virtual test system, which collects and obtains the pressure boundary conditions of the main valve inlet and back pressure cavity simulated by a physical test system to simulate the parameter state of the main valve virtual test system, a motor controller, which receives the calculated main valve opening and movement speed and drives a linear motor to drive a pneumatic cylinder to follow the simulation main valve opening in real time, and feedback the influence of the main valve opening on the back pressure cavity pressure, so as to realize the state coupling between the pilot valve physical test system and the main valve virtual test system, and achieve the purpose of testing the pilot valve debugging state based on the semi-physical real-time simulation system. The present application uses the main valve virtual test system to replace the traditional physical test system to test the pilot valve debugging state, which can greatly reduce the difficulty and cost of building a large flow gas supply system caused by using the main valve physical test system, and also improve the pilot valve debugging efficiency and batch quality stability and consistency.

The present application relates to the technical field of tunnel construction, and provides an experimental method and system for studying the synergistic effect of surrounding rock and concrete support. The method includes: making a physical test model of tunnel surrounding rock and shotcrete support to obtain measured data; according to the physical test model of tunnel surrounding rock and shotcrete support, establishing a corresponding finite element simulation model to obtain finite element simulation data; arranging cohesive units between the surrounding rock units and the concrete support units in the finite element simulation model, and constructing its cohesive constitutive model considering Coulomb friction, and the cohesive constitutive model is used to characterize the contact characteristics between the surrounding rock and the concrete support; based on the measured data and the finite element simulation data, using the gradient optimization algorithm to iteratively determine the optimal parameters of the cohesive model; importing the optimal parameters of the cohesive constitutive model into the finite element simulation model, and conducting tunnel surrounding rock and shotcrete support synergistic bearing mechanism analysis based on the finite element simulation model.

The invention discloses a ship power system virtual debugging method, which relates to the technical field of ship power system debugging test, and comprises the steps of test procedure compiling, test instruction table generation, test system model construction, model-based virtual debugging implementation, test result analysis and scheme optimization, virtual debugging to physical test and the like. Through virtual debugging, test operators and test regulations can be drilled in advance, blindness of a physical test is avoided, and test safety is improved. And meanwhile, through virtual debugging, safe and reliable test regulations are formed, physical test development is guided, the test efficiency is effectively improved, and the test period is shortened.

The invention belongs to the technical field of plasma sources, and discloses a remote plasma source variable cross-section quartz tube structure optimization design method and related equipment, and a microwave remote plasma source is subjected to two-dimensional modeling, grid division, material parameter and physical field setting, analogue simulation and optimization solution. Accurate optimization design of the shape of the inner surface of the quartz tube is achieved, the problem that a traditional cylindrical quartz tube cannot finely regulate and control plasma flow and distribution is solved, and the advantages that electron density distribution uniformity is improved, plasma outlet flux is improved, and the power utilization rate is improved are achieved. And the optimization design is carried out through simulation analysis, so that the design period is shorter and the design cost is lower compared with a physical test mode.

The application provides a kind of automobile collision seat cushion system simulation model quality promotion method and system, method includes: obtaining cushion foam material model by seat three-dimensional model, first impact tooling model is constructed to carry out impact simulation test to cushion foam material model, and obtain cushion material simulation test data;Cushion material simulation test data and cushion material physical test data are made to benchmark analysis, and the material parameters of cushion foam material model are updated according to the analysis result;Obtain cushion system model through seat three-dimensional model, the second impact tooling model is constructed to carry out impact simulation test to the preset area of cushion system model, and obtain cushion system simulation test data;Cushion system simulation test data and cushion system physical test data are made to benchmark analysis, and the skeleton material parameters and structure parameters of seat three-dimensional model are updated according to the analysis result.The application can save the cost of automobile development by verifying, benchmarking and optimizing the automobile seat cushion model.

The present invention discloses a method for the mechanical environment test of a reusable spacecraft, which includes conducting virtual mechanical tests, building a mechanical environment test system, conducting high-level mechanical environment tests on the reusable spacecraft, determining the structural damage conditions, and predicting the remaining life of the spacecraft. The present invention predicts the dynamic response of the spacecraft structure through virtual mechanical tests, estimates the working life of the structure, and proposes high-level mechanical environment test conditions to simulate the reuse conditions. It can conduct physical tests on the spacecraft and extract the natural frequency values, and use the proportion of the decrease in the structural natural frequency as the judgment basis to determine the damage conditions of the spacecraft under the action of the mechanical environment in the working state, determine whether it can meet the requirements of reuse, and predict the remaining life. This method combines virtual tests with physical tests to effectively determine the life of the structure of the reusable spacecraft. The high-level physical tests also improve the test efficiency and provide an important basis for the reliability analysis of the spacecraft.

The application discloses a kind of hydraulic drive foot type robot joint control experiment table, belong to foot type robot field.The application transforms self-destructive full physical test into predictive research under laboratory conditions, accurately simulates complex and changeable force or torque load spectrum.In the research, the force loading test under fixed position and the force loading test under position change are carried out using the joint control experiment table, it is proved that after the position parameter of joint control cylinder valve is added in feedforward link, the load simulation cylinder can output the expected force curve;Then step position, sinusoidal position and high-low pressure energy-saving experiment are carried out on joint control system based on servo proportional valve and based on cartridge valve respectively, it is proved that compared with single high-pressure oil source control, using high-low pressure oil source can save 25%-38% energy.

The invention relates to the field of electronic components, and particularly discloses a finite element-based multilayer ceramic capacitor board bending mechanical failure analysis method, which comprises the following steps of: establishing an MLCC board bending simulation geometric model according to geometric parameters of an MLCC, a PCB (Printed Circuit Board) and a pressure head in combination with a board bending test standard; the ceramic body is partitioned according to the distribution characteristics of the inner electrodes, and equivalent mechanical parameters of the ceramic body are calculated; establishing an equivalent plate bending finite element model of the MLCC in finite element software ANSYS; determining a stress index reference point, and eliminating adverse effects of singular points; obtaining failure strain of the plate bending test and an MLCC failure mode; and verifying the finite element model and carrying out failure mode analysis. Compared with a traditional physical test failure analysis method, the method has the advantages that the requirements for cost, time, equipment and the like are greatly reduced, and development of MLCC failure analysis and structural design is promoted.

This invention relates to the field of hardware-in-the-loop (HIL) simulation testing, and discloses a HIL simulation system, method, electronic device, and medium for magnetic levitation bearings. The system includes: a magnetic levitation bearing, a simulation development computer, and a real-time simulation target machine. The simulation development computer constructs a drive circuit model based on the drive circuit of the magnetic levitation bearing and sends the completed drive circuit model to the real-time simulation target machine. The real-time simulation target machine collects the operating data of the magnetic levitation bearing in real time, inputs the operating data into the drive circuit model to obtain the first operating state of the magnetic levitation bearing, and determines the first control parameters based on the first operating state to drive the magnetic levitation bearing to move. The real-time simulation target machine pre-stores various correspondences between the operating states of the magnetic levitation bearing and the control parameters. This addresses the problems existing when studying magnetic levitation bearing systems using full physical testing or full digital simulation methods.

The invention relates to the technical field of space flight and aviation, in particular to a comprehensive test platform and test method for an air refueling reel electric drive system. The test platform is composed of an electric dynamometer, an electric dynamometer loader, a test cabinet and an intermediate frequency power supply. The electric dynamometer simulates the load of a reel in the air refueling process, and the main body is a permanent magnet synchronous motor. The electric dynamometer loader is used for controlling a load motor so as to simulate a load change process under different working conditions of aerial refueling; the test cabinet simulates and sends out various working condition control instructions in the air refueling process through a human-computer interaction interface; the medium-frequency power supply simulates a power supply provided by the airplane for the electric driving device. According to the invention, the huge cost for building a full-physical test environment in each test process is reduced, the automation degree of the test is improved, the economic benefit is prominent, and meanwhile, reference is provided for the design of other electric drive device test platforms with complex working conditions.