5 results about "Critical location" patented technology

This invention belongs to the field of power technology and relates to a method for verifying and optimizing the external insulation design of ultra-high voltage bushings under complex environments. The method includes: acquiring parameters; constructing a finite element model; simulating the electric field under normal operating conditions; determining key locations; extracting the peak electric field intensity at key locations under three complex operating conditions; and judgment and optimization. This invention accurately simulates real operating environments such as high humidity and contamination by constructing simulation models for three typical complex operating conditions: discontinuous water film, a wet contamination layer containing a dry strip, and a locally wet contamination layer. It effectively characterizes the abrupt changes in the dielectric properties of the dielectric material under complex environments and the resulting solid-liquid-gas three-phase interface effect. Simultaneously, by comparing the peak electric field intensity under complex operating conditions with the preset critical discharge electric field intensity, it scientifically assesses the deterioration impact of complex environments on high-risk areas, accurately determines whether the original design meets the insulation safety requirements under complex operating conditions, and optimizes designs with potential safety hazards.

The present disclosure relates to a welding deformation control method and device, a box body, a washing and sweeping vehicle and a storage medium. The welding deformation control method comprises: establishing a finite element model of a box body component; based on the finite element model, performing welding deformation prediction and extracting deformation data of a key position of the box body component; in the case that the deformation data does not meet the design requirements of the box body component, obtaining influencing factors of the welding deformation; determining the sensitivity of each influencing factor to the deformation of the key position, wherein the sensitivity is used to quantify the deformation control effect of each influencing factor; and determining a target deformation control scheme according to the sensitivity of each influencing factor, wherein the target deformation control scheme comprises at least one influencing factor. The present disclosure can combine advanced finite element simulation technology and multi-objective decision-making method to realize comprehensive quantitative evaluation and priority ranking of various influencing factors in the welding process.

This invention belongs to the field of aero-engine design technology, and provides an in-situ sampling simulation component for fatigue life of multiple critical locations under the same stress on an aero-engine rotor disk, along with its design method. The simulation component is cut in situ from the rotor disk component, centered on the fatigue-critical location. Stress control structures are fabricated in non-critical locations, including two radial stress gradient adjustment grooves and two thickness-direction principal stress gradient adjustment grooves. These are used to adjust the first principal stress gradient in the crack depth and length directions, respectively, to ensure consistency with the actual service condition of the rotor disk and to guarantee that the crack initiation location matches the failure mode. The fatigue-critical location retains its original material state without secondary processing. Loading structures are located on both sides of the loading section, supporting hole loading or clamping loading. This simulation component can be used for high-fidelity low-cycle fatigue testing, enabling accurate assessment of the fatigue life dispersion of multiple fatigue-critical locations with the same or similar peak stress levels on an aero-engine rotor disk.

The application discloses an aircraft key part damage prediction method, system, device, medium and product, relates to the field of aircraft life prediction, and the method comprises the steps of: generating a plurality of sample double-channel stress histories randomly for an aircraft key part; calculating a sample damage value history corresponding to each sample double-channel stress history by adopting a multi-axial fatigue calculation method based on a critical plane method according to material performance parameters; training a deep learning network model based on a time domain convolution network by taking the sample double-channel stress history as input and taking the sample damage value history as a label to obtain a fatigue damage prediction model; obtaining a measured double-channel stress history of the aircraft key part in a service process; inputting the measured double-channel stress history into the fatigue damage prediction model to obtain a corresponding damage value history, and realizing damage prediction of the aircraft key part. The application can improve damage value calculation efficiency, thereby improving aircraft residual life prediction efficiency.

The invention provides a concrete shrinkage deformation reverse modeling compensation method, and belongs to the technical field of wind tunnel construction, and the method comprises the steps: building a pouring unit adjacent relation topological graph, optimizing a pouring time sequence through a graph coloring algorithm, and building a heat-humidity-force multi-physics field coupling finite element model; kriging interpolation is adopted to reconstruct complete temperature field distribution and extract a temperature deviation field, Kalman filtering inversion is used to correct hydration heat source parameters, a moving boundary identification algorithm is used to update dynamic boundary conditions, an incremental iteration algorithm is used to solve coupling response, and a Green function stress response matrix is used to quickly calculate stress field distribution. When the stress value of the key position exceeds the threshold value, reverse compensation calculation is started to generate a template adjustment instruction, actually measured data is fed back to the model to form closed-loop iteration, and the technical problem of wind tunnel structure construction deformation control failure caused by insufficient concrete shrinkage deformation prediction precision is solved.