12 results about "Structural failure" patented technology

This invention discloses a method for assessing the vulnerability of bridge piers under ship impact, comprising: obtaining the tensile stress threshold at the pier base for different failure states of the bridge pier under ship impact; extracting multiple parameter combinations from the core parameter space affecting the tensile stress at the pier base using the optimal Latin hypercube sampling method; calculating the tensile stress at the pier base corresponding to each parameter combination using a finite element model of the bridge pier under ship impact, and fitting an initial surrogate model for the tensile stress at the pier base; based on the prediction accuracy of the initial surrogate model, supplementing the extraction of multiple parameter combinations in the parameter space region where the prediction error or the degree of nonlinearity of the function is greater than the corresponding threshold; and using the supplemented extracted parameter combinations to return to the operation of calculating using the finite element model to obtain a new surrogate model; repeating this process until the prediction accuracy of the final surrogate model meets the requirements; and fitting the pier vulnerability curve for each failure state. This embodiment is more consistent with the damage mechanism of concrete cracking and structural failure.

The invention discloses a power tower environment state intelligent detection system and method, and relates to the technical field of power detection. The method comprises the following steps: acquiring the attitude, vibration and micrometeorological data of a tower in real time through a multi-dimensional sensing module; performing Kalman filtering and fast Fourier transform by using an edge processing module, and performing de-noising, interpolation completion and space-time alignment on the original data; extracting a structural feature vector representing the stability of the tower and an environmental load vector representing the external pressure, and carrying out feature fusion; constructing a comprehensive risk index model containing an environmental sensitivity coupling factor, and quantitatively evaluating the nonlinear influence of wind load and icing on the structure failure probability; and automatically triggering the unmanned aerial vehicle to inspect or send a power-off suggestion according to the risk index level. Through deep fusion of edge calculation and multi-source data, the problems that traditional monitoring data is large in noise and lacks environment coupling analysis are effectively solved, and accurate hierarchical dynamic early warning is achieved.

A data processing system and method for generating structural engineering documents using artificial intelligence (AI) is disclosed. The system comprises a memory storing a dataset of engineered structures, including instances of structural failures, and a machine learning model trained on the dataset to perform structural analysis and generate optimized design documents. The AI system receives input data specifying design requirements, simulates the structure's behaviours under various conditions, and generates structural engineering documents, including 3D CAD models, based on an optimal combination of materials. The system may include a feedback integration module for continuous refinement of the machine learning model, an analytics engine for performance monitoring, and an electronic filing integration for streamlining the design approval process. The AI system learns from past projects to rapidly generate code-compliant, cost-optimized, and resilient structural designs.

The invention belongs to the technical field of aviation experiment data acquisition, and relates to a helicopter external load data acquisition device, system and method. The device is characterized in that tension and pressure sensors are mounted at a sling of an external load, a hanging point and a joint of the external load and an external load data acquisition barrel, and are used for measuring dynamic tension change in hoisting operation, transmitting the dynamic tension change to a multi-channel data acquisition case and feeding back actual acting force of the external load on a helicopter; the mechanical state provides a direct basis for evaluating a flight safety threshold value and preventing overload or structural failure; the motion sensor is a sensing unit and is used for capturing three-dimensional motion states of the helicopter and the external load in real time and transmitting the three-dimensional motion states to the multi-channel data acquisition case; the flight parameter collector is used for providing GPS height, longitude, latitude and course data and transmitting the data to the multi-channel data acquisition case; the multichannel data acquisition case is internally provided with an acquisition loading modular board card, supports multichannel signal synchronous acquisition and processing, and communicates with a measurement and control computer in a helicopter cabin through a data transmission module.

The invention provides a structure fault detection method and device for a storage stacker, and the method comprises the steps: collecting original vibration data through arranging vibration sensors at a walking unit, a lifting unit, a rotation unit and a telescoping unit of the stacker, calculating a vibration acceleration effective value after band-pass filtering and mean value removal processing, and calculating a fault detection result of the stacker; judging the running state of the component according to a preset threshold condition; only carrying out sliding window calculation, average processing and centralized dimension reduction on the running state data, and extracting maximum values of a walking unit and a lifting unit and effective values of a rotation unit and a telescopic unit as features; inputting a neural network model, and outputting a fault probability in real time; therefore, main mechanical parts of the stacking machine can be covered, real-time early warning of faults is achieved, detection is more timely, the omission ratio is lower, the requirement for maintenance according to conditions is met, and the operation and maintenance cost is reduced.

The present application relates to offshore wind power safety monitoring technology, and specifically discloses a wind turbine tower and blade adaptive protection system and method based on visual monitoring. The present application dynamically constructs a horizontal reference resistant to wave interference through an onboard high-definition camera capturing sea surface flare, and fuses tower edge recognition to calculate the inclination in real time. When the inclination continuously exceeds the limit, the blade is segmented to contract to reduce wind load, and the inclination change rate after contraction is used to distinguish between elastic deformation and structural failure. For the case where the inclination does not change, a coaxial laser scanning device is started to excite local vibration of the tower, and the loosening point is located by analyzing the time delay of vibration wave conduction. The present application can realize millimeter-level precision monitoring of tower inclination; the active protection mechanism of the blade reduces the risk of accidents; improves the precision of non-contact fault location, and reduces the diving maintenance operation. It is mainly suitable for structural health monitoring and safety protection of large offshore wind turbine generators.

The present application belongs to the technical field of aviation experiment data collection, and relates to a helicopter external load data collection device, system and method. The device comprises: a tension and compression force sensor installed at a sling, a hanging point and a connection position of the external load data collection barrel of the external load, used for measuring dynamic tension changes in hoisting operation and transmitting the changes to a multi-channel data collection machine case, feeding back actual force of the external load on the helicopter, providing a direct basis of mechanical state for evaluating flight safety threshold, preventing overload or structural failure; a motion sensor is a sensing unit, used for capturing three-dimensional motion state of the helicopter and the external load in real time and transmitting the state to the multi-channel data collection machine case; a flight parameter collector is used for providing GPS height, longitude, latitude and heading data and transmitting the data to the multi-channel data collection machine case; a collection and loading modularized board card is arranged in the multi-channel data collection machine case, supporting multi-channel signal synchronous collection and processing, and communicating with a measurement and control computer in the helicopter cabin through a data transmission module.

The application relates to the field of marine engineering and structural safety, and discloses a quantitative analysis method for the minimum tide level of barge loading and unloading operation on a bucket foundation, which comprises the following steps: constructing a digital twin model considering multi-physical field coupling; collecting dynamic data of the operation site in real time through a sensor network; performing real-time self-correction on key physical parameters of the model by using an extended Kalman filtering algorithm; performing prospective simulation on the operation process under different tide conditions based on the corrected model, obtaining the probability distribution of load effect; performing reliability analysis in combination with a structural resistance model, calculating the structural failure probability under each tide level, and comparing the structural failure probability with a preset acceptable risk threshold, so that the minimum operable tide level is determined. Through digital twin and real-time data fusion, the application realizes dynamic and prospective quantitative evaluation of the barge loading and unloading operation risk, gets rid of the dependence on subjective experience, and significantly improves the scientificity, safety and economic benefit of operation decision.

The invention relates to a deformation monitoring type self-elevating tower, and relates to the technical field of tower structures and monitoring, the deformation monitoring type self-elevating tower comprises a platform, height adjusting mechanisms and a deformation monitoring mechanism, the bottom of the platform is symmetrically provided with a plurality of groups of height adjusting mechanisms, and the height adjusting mechanisms are provided with the deformation monitoring mechanism. The height adjusting mechanisms at the bottom of the platform are used for adjusting the height of the platform to adapt to different terrains or load conditions, the deformation monitoring mechanisms are integrated on the height adjusting mechanisms to monitor deformation (such as bending and inclination) of the tower structure in real time and feed back data to the control system, and when it is monitored that deformation exceeds a safety threshold value, the control system controls the control system to operate. The system can automatically trigger height adjustment or give an alarm, self-adaptive adjustment of the height of the tower and deformation real-time monitoring are achieved, the height adjusting mechanism is allowed to flexibly adapt to the uneven ground, the deformation monitoring mechanism can give an early warning of structural failure in advance, and the accident risk is reduced.

The application provides an adapter suitable for aircraft ejection process, which is composed of multiple fixing members, compared with the traditional single adapter, the weight of the single fixing member is obviously reduced, and the impact caused by the collision with the object during the scattering process is small; the adapters of the fixing members have the same shape, and are combined by using the unified shape, the adaptability is strong, the aerodynamic shape is consistent, the scattering trajectory and the expected landing point can be predicted by the program; the separation mechanism of the adapter is designed by using the pre-compression spring structure, which can provide a buffer for the material deformation, when the material deforms, the separation mechanism of the adapter can quickly compensate a certain amount, keep the attitude of the aircraft stable and unchanged, and avoid the structural failure of the adapter caused by the material deformation.

This invention relates to the field of damage prediction technology, specifically to a P-I equivalent damage prediction method based on accumulated energy. The purpose of this invention is to construct an equivalent damage relationship for quantifying impact parameters and structural failure, namely, a P-I equivalent damage prediction method based on accumulated energy. Addressing the damage problem of devices under test under different peak values ​​and pulse widths of impact, starting from the dynamic response of the structure under high overload impact, this invention constructs a P-I equivalent damage relationship characterizing the critical damage of the structure by comparing the peak accumulated energy and critical accumulated energy under different peak values ​​and pulse widths of load. This can guide the impact-resistant optimization design of measurement devices under high overload environments, theoretically providing support for the impact-resistant optimization design of devices under high overload environments, and promoting the engineering process of equivalent damage methods for measurement devices.

The invention discloses an aircraft panel assembly stress distribution balance regional characterization method and system, and the method comprises the steps: dividing different regional assembly stress distribution modes and stress region types, and building a stress region division criterion which is dynamically adjusted along with errors and gaps; obtaining stress data through combination of finite element simulation and multi-sensor collaborative test measurement, and preprocessing the stress data; constructing an assembly stress balance mathematical statistical model, and defining a stress balance index integrated with an error penalty term; establishing a multi-dimensional comprehensive evaluation index system, and carrying out quantitative evaluation by adopting combined weighting and a mixed evaluation function; and assembly stress balance distribution control and process optimization are realized. According to the method, the stress gradient-stress area-error / gap three-dimensional coupling model is constructed, a complete technical chain of distribution mode division-data acquisition-preprocessing-statistical modeling-distribution comprehensive evaluation-optimization is formed, the assembly stress balance can be accurately quantified, the assembly process is scientifically optimized, and the structure failure risk is reduced.