Aerospace Science and Technology最新文献

{"title":"Vibration-attitude integrated control of a large two-dimensional planar phased array antenna","authors":"Li Pei ,&nbsp;Liu Xiang ,&nbsp;Cai Guoping ,&nbsp;Sun Jun ,&nbsp;Zhu Dongfang","doi":"10.1016/j.ast.2025.110030","DOIUrl":"10.1016/j.ast.2025.110030","url":null,"abstract":"<div><div>Phased array antennas are pivotal for observing, identifying, and tracking targets, serving both military and civilian needs. They are growing larger and more complex to meet the demand for high-resolution Earth observation. However, their intricate design, low-frequency density, and significant coupling make dynamic analysis and control design challenging. This paper introduces a novel large-scale, space-deployable, two-dimensional planar phased array antenna and investigates its dynamic modeling and active control. Unlike traditional one-dimensional phased array antenna, this antenna can scan in two directions, providing a larger scanning area. To suppress antenna vibration, the paper proposes a control strategy using ropes as actuators. Firstly, the paper details the structure of the phased array antenna, including its attitude and vibration actuators. Then, using the hybrid coordinate method and the velocity variation principle, it derives the antenna's rigid-flexible coupled dynamic model. Subsequently, the paper designs an attitude-vibration controller for the antenna, integrating the computed torque control method, Linear Quadratic Regulator (LQR), and Bang-Bang control theory. This includes considering the unidirectionality and saturation of the rope control forces and optimizing the placement of rope actuators using Particle Swarm Optimization (PSO). Finally, numerical simulations validate the effectiveness and accuracy of the theoretical investigation. The results indicate that the antenna model possesses characteristics of low-frequency density and robust rigidity-flexibility coupling, with optimization of actuator quantity and placement enhancing control efficiency. Furthermore, the dynamic model accurately describes the antenna's behavior, achieving results consistent with ADAMS software. The attitude-vibration coupled controller maintains precise directional accuracy, effectively suppressing vibrations.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110030"},"PeriodicalIF":5.0,"publicationDate":"2025-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143402511","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Research on integrated design method of wide-range hypersonic vehicle/engine based on dynamic multi-objective optimization","authors":"Zeyang Zhao ,&nbsp;Yue Ma ,&nbsp;Ye Tian ,&nbsp;Zhijian Ding ,&nbsp;Hua Zhang ,&nbsp;Shuhong Tong","doi":"10.1016/j.ast.2025.110031","DOIUrl":"10.1016/j.ast.2025.110031","url":null,"abstract":"<div><div>A hypersonic vehicle powered by an air-breathing engine enables efficient long-range delivery and high-speed flexible access to space. The key to achieving high-performance operation of hypersonic vehicles lies in high-efficiency and well-matched hypersonic vehicle/engine integration configuration design. While machine learning-assisted intelligent optimization has shown initial success in hypersonic vehicle/engine integration design, over-reliance on basic and simplistic intelligent methods has led to a significant dependency on sample size and a tendency to easily converge to local optima. This study addresses the need for wide-speed-range, small-sample, and multi-criteria hypersonic vehicle/engine integration design by developing a parametric model for the hypersonic vehicle/engine configuration. Leveraging computational fluid dynamics (CFD) technology, the study uses the Deep Active Subspace (DAS) model along with the Improved Multi-Objective Coati Optimization Algorithm (IMOCOA). This approach is applied to small-sample dynamic multi-point and multi-objective optimization design with the objective of achieving an optimal hypersonic vehicle/engine configuration design characterized by low drag, a high lift-drag ratio, and a high total pressure recovery coefficient across various operating conditions. The results indicate that the Mean Absolute Percentage Error (MAPE) for predicting hypersonic vehicle/engine integration performance using the DAS model is &lt;2 %. Validation of the Pareto solution set from multi-objective optimization shows that dynamic multi-objective optimization enhances performance by &gt;3 % compared to static multi-objective optimization. In comparison to the pre-optimization configuration, the optimized configuration demonstrates a 12.97 % reduction in total drag, with a 9.77 % improvement in lift-drag ratio and a 10.27 % enhancement in total pressure recovery coefficient, highlighting rapid and efficient hypersonic vehicle/engine integration configuration design and performance improvement.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"159 ","pages":"Article 110031"},"PeriodicalIF":5.0,"publicationDate":"2025-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143379050","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"In-flight measurements of lightning locations using an aircraft-mounted lightning mapper","authors":"Zachary Milani ,&nbsp;Leonid Nichman ,&nbsp;Edgar Matida ,&nbsp;Liam Fleury ,&nbsp;Mengistu Wolde ,&nbsp;Eric Bruning ,&nbsp;Greg M. McFarquhar ,&nbsp;Pavlos Kollias","doi":"10.1016/j.ast.2025.110038","DOIUrl":"10.1016/j.ast.2025.110038","url":null,"abstract":"<div><div>Real-time measurements of lightning locations can improve flight safety by providing aircraft operators with valuable information about nearby weather conditions. Lightning warnings can be especially valuable when piloting aircraft that are more susceptible to a direct strike such as electric aircraft, hydrogen-powered aircraft, and even UAVs with composite skins. At best, weather updates are broadcast from weather services every 2.5 to 5 mins, but it's not uncommon for an intermittent connection to cause service stability issues. Therefore, an aircraft-mounted lightning mapper might be the most practical source of real-time lightning information for pilots. This work investigates the in-flight performance of the aircraft-mounted Stormscope Weather Mapping System (WX-500 Series 2) through comparisons to the Houston Lightning Mapping Array, National Lightning Detection Network, and the GOES - Geostationary Lightning Mapper. Measurements from two thunderstorms near Houston, TX, yielded WX-500 detection efficiencies of 33 % and 42 % for intracloud flashes, 75 % and 64 % for cloud to ground flashes, and 53 % and 79 % for total flashes. The WX-500 bearing measurement was accurate to within ±14° (σ), which improved to ±4° when integration time was increased from 2 to 30 s and clear outliers were ignored. The WX-500 range measurement was overestimated by an average of +74 km (±50 km) when the average true flash distance was 94 km. The WX-500 accurately depicted the boundary of lightning activity at an integration time of 1 min which is sufficient for the circumnavigation of thunderstorms.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110038"},"PeriodicalIF":5.0,"publicationDate":"2025-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143445579","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"On the vibration of hybrid turbine blades with an interaction between surface discontinuities and twist angle variation","authors":"Krzysztof Kamil Żur ,&nbsp;Jinjin Yuan ,&nbsp;Hulun Guo ,&nbsp;Zhenyu Cheng ,&nbsp;Błażej Bartoszewicz","doi":"10.1016/j.ast.2025.110035","DOIUrl":"10.1016/j.ast.2025.110035","url":null,"abstract":"<div><div>Damage related to surface fracture and changes in the twist angle of the blades are some of the most common in turbines. Modern structural health monitoring systems (SHM) are designed mainly based on vibrational signals of structures. Advanced models are necessary to create effective SHM and control systems and perform complex experiments for nonlinear dynamics of rotating structures.</div><div>For the first time, the present paper comprehensively theoretically investigates and explains the effect of the angle and depth of crack surface with blades' twist angle variation on their vibration during rotation and stationary conditions. The first-order shear deformation theory and the improved Novozhilov nonlinear shell theories are combined to consider nonlinear effects and the possibility of considering thin and thick blades with different twist angles. In addition, the blade model obtained also considers the centrifugal force effect and hybrid carbon-based composite material properties such as graphene platelets-reinforced external layers and variously oriented and dispersed carbon nanotubes-reinforced internal layers. Nonlinear coupled Euler-Largange equations of motion are discretised by the effective meshless IMLS-Ritz method. Comprehensive numerical experiments are performed to show the effects of surface crack angle and depth, variations of twist and preset angles, aspect ratio, hub radius ratio, and rotation speed on linear and nonlinear frequencies and vibrational modes of the hybrid twisted blades. In addition, results can show the resistance of the carbon-based composite material on changes in blade dynamics for surface crack presence.</div><div>The results show that the backbone curve shifts to the right as the crack length increases. In addition, it is interesting that the pre-twisted angles significantly impact the blades' mode. With increased pre-twist angles of the cracked blade, vibrational mode switching occurs. Finally, it can be seen that with an increase in rotation speed, natural frequencies are increased for the first eight modes of vibration. Taking into account modes of vibration, we can see that for higher modes, higher rotation speed introduces mode switching, which may related to crack presence. Moreover, among the four CNT patterns, the pre-twisted composite blade with FG-X distribution pattern has the highest linear and nonlinear frequencies and stiffness, followed by UD, FG-V and FG-O patterns. The presented results, new findings, and conclusions may significantly improve the planning of experimental works and the interpretation of results from SHM-designed systems for rotating blades.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110035"},"PeriodicalIF":5.0,"publicationDate":"2025-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143387892","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Nonlinear dynamic inversion control with unknown control effectiveness and actuator dynamic","authors":"Rui Cao ,&nbsp;Yanbin Liu","doi":"10.1016/j.ast.2025.110036","DOIUrl":"10.1016/j.ast.2025.110036","url":null,"abstract":"<div><div>The incremental nonlinear dynamic inversion (INDI) method has been widely applied across various fields and is theoretically capable of achieving precise control of complex nonlinear systems. However, its performance is affected when control effectiveness is uncertain or actuator bandwidth is constrained. In this paper, we propose an adaptive nonlinear dynamic inversion algorithm with actuator dynamics (ANDIa) that incorporates a virtual control matrix and a nonlinear system estimator to address these limitations. Comparative analyses with the INDI controller demonstrate that ANDIa significantly improves control performance under conditions of uncertain control effectiveness and limited actuator bandwidth.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110036"},"PeriodicalIF":5.0,"publicationDate":"2025-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143395481","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Efficient machine learning method for supercritical combustion: Predicting real-fluid properties and chemical ODEs","authors":"Yuqing Cai ,&nbsp;Ruixin Yang ,&nbsp;Han Li ,&nbsp;Jiayang Xu ,&nbsp;Ke Xiao ,&nbsp;Zhi X. Chen ,&nbsp;Hu Wang","doi":"10.1016/j.ast.2025.110034","DOIUrl":"10.1016/j.ast.2025.110034","url":null,"abstract":"<div><div>In the context of supercritical reactive flow simulations, the real-time direct integration of chemical ordinary differential equations (ODE) and multi-component real fluid thermal-physical properties (Therm) are the primary demands on computational resources. As the number of components requiring a solution increases, the computational load also rises, particularly for combustion models involving turbulence-chemistry interactions, such as Eulerian stochastic fields (ESF). In this study, we improve the hybrid flamelet/random dataset (HFRD) <span><span>[1]</span></span> by incorporating a set of equilibrium-based random samples, thereby developing a hybrid flamelet-equilibrium/random data (HFERD) method and training a multi-layer perceptron surrogate model (MLP) for the Therm and ODE modules. The investigation of supercritical <span><math><mi>C</mi><msub><mrow><mi>H</mi></mrow><mrow><mn>4</mn></mrow></msub></math></span> premixed combustion with homogeneous isotropic turbulence and <span><math><msub><mrow><mi>H</mi></mrow><mrow><mn>2</mn></mrow></msub></math></span> coaxial jet combustion provides robust verification. This demonstrates the accuracy and generalization ability of the proposed HFERD and Therm/ODE-MLP approaches. Additionally, the integration of MLP modules has achieved a 10 and 20 acceleration effect. However, due to the limitation of flow calculations, the total acceleration effect can reach up to 5 times on the same CPU platform.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"159 ","pages":"Article 110034"},"PeriodicalIF":5.0,"publicationDate":"2025-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143350733","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Ballistic protection and damage mechanism of ceramic composite armor under two-dimensional pre-stressed constraints by molten metal casting","authors":"Fangfang Qi ,&nbsp;Cheng Wang ,&nbsp;Wenlong Xu","doi":"10.1016/j.ast.2025.110021","DOIUrl":"10.1016/j.ast.2025.110021","url":null,"abstract":"<div><div>To meet the requirements for lightweight and high-performance protection in ceramic composite armor, two-dimensional prestressing of brittle ceramics is achieved based on the principle of molten metal cooling shrinkage. The protective performance of two-dimensional prestressed (2DP) and non-prestressed (2DN) ceramic composite armors is evaluated through ballistic impact tests. High-speed cameras and 3D digital image correlation (3D-DIC) techniques are employed to dynamically capture the penetration and damage processes of the ceramic composite armor targets. The Rosin-Rammler distribution model is used to analyze and compare the fragmentation degrees of ceramic targets after penetration. Additionally, full process coupled simulation, encompassing the preparation and the ballistic impact of ceramic composite target, is achieved through the finite element software ProCast and Ls-Dyna. Based on the depth of penetration (DOP) test, the residual depth of witness after penetration is measured, and the protection coefficients of two type of target at different velocities are quantitatively obtained. The experimental and simulation results indicate that, 2DP ceramic composite armor demonstrates better ballistic protection capability compared to 2DN ceramic composite armor. The presence of prestress prolongs the dwell time of the projectile on the projectile-facing surface, which hinders the forward movement of the projectile, resulting in significant velocity attenuation and radial deformation of projectile's nose. Additionally, the fragment size of 2DP ceramic composite armor is smaller, and the ceramic fragmentation energy absorption continuously dissipates the kinetic energy of projectile. Within a velocity range of 600 m/s∼1400 m/s, the protection coefficient of 2DP is 8.11 % to 48.64 % higher than that of 2DN.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"159 ","pages":"Article 110021"},"PeriodicalIF":5.0,"publicationDate":"2025-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143379047","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Unsteady aerodynamic performance of tandem configurations of three flapping and fixed airfoils","authors":"Gang Li ,&nbsp;Jianghao Wu ,&nbsp;Yanlai Zhang ,&nbsp;Long Chen","doi":"10.1016/j.ast.2025.110032","DOIUrl":"10.1016/j.ast.2025.110032","url":null,"abstract":"<div><div>Flow interaction in a tandem double-airfoil (flapping-fixed) configuration can simultaneously enhance the aerodynamic performance of both the flapping and the fixed airfoil. However, it is unclear whether further enhancement occurs in configurations with more flapping and fixed airfoils. In this paper, we numerically simulated the aerodynamic performance and flow structure of three self-propelled types of triple-airfoil configurations using the lattice Boltzmann method. These configurations include flapping-fixed-fixed, flapping-fixed-flapping, and flapping-flapping-fixed configuration, and were compared with single-airfoil and double-airfoil configurations. Results show that compared with the double-airfoil configuration, the flapping-fixed-fixed airfoil configuration can improve the total lift and lift efficiency without additional input power, although propulsion velocity may decrease. The trailing edge vortex shed from the frontmost flapping airfoil induces a low-pressure region (suction) on the upper surface of the rearmost fixed airfoil, enhancing lift performance. The flapping-fixed-flapping and flapping-flapping-fixed airfoil configurations can simultaneously increase total lift and propulsion velocity, but they require more input power, resulting in reduced lift efficiency. These two configurations can generate strong jets. Overall, the total lift coefficient of the triple-airfoil configuration is generally between that of single-airfoil and double-airfoil configurations, with the total lift increment primarily due to the increase in the lifting surface. In addition, by redistributing the aerodynamic force of each airfoil, the triple-airfoil configuration manipulates the total pitching moment while maintaining the total lift almost constant. This is significantly different from the control mechanism of conventional aircrafts, and the pitching moment can be manipulated widely using multiple control parameters (including the angles of attack of the middle and rearmost airfoil). Our findings reveal the mechanism of lift enhancement and pitch control in triple-airfoil interaction, guiding the design of micro air vehicles using these configurations.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110032"},"PeriodicalIF":5.0,"publicationDate":"2025-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143378774","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Enhancing the combustion performance of solid propellants by external magnetic field","authors":"Songchen Yue ,&nbsp;Geng Xu ,&nbsp;Linchen Dai ,&nbsp;Wei Liu ,&nbsp;Meng Cui ,&nbsp;Shiyao Shao ,&nbsp;Peijin Liu ,&nbsp;Wen Ao","doi":"10.1016/j.ast.2025.110013","DOIUrl":"10.1016/j.ast.2025.110013","url":null,"abstract":"<div><div>Propellant combustion under a magnetic field demonstrates significant potential for advancement. This study explores the potential of using magnetic fields to improve combustion performance of solid composite propellants. The experimental setup involved a custom-made apparatus that could adjust the intensity and direction of the magnetic field and laser ignition device. The research demonstrated that applying a magnetic field shortened the ignition delay time, accelerated the burning rate, and improved the propellant's combustion efficiency. Specifically, applying a 196 mT magnetic field reduces ignition delay time from 493.08 ms to 483.68 ms, increased the burning rate from 2.41 mm/s to 2.86 mm/s, and raised combustion efficiency from 82.65 % to 90.15 %. Specific impulse also improved from 2315 N·s/kg to 2347 N·s/kg. The magnetic field's effect was more pronounced in propellants with higher oxidizer content. However, when combustion was perpendicular to the magnetic field direction, the influence slightly diminished. We further investigated the combustion physical mechanism of the propellant under the influence of a magnetic field. The results demonstrate that the magnetic field enhances propellant combustion by reducing the ignition delay time of aluminum particles and lowering the flame height. This discovery offers promising insights for enhancing propellant performance.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"159 ","pages":"Article 110013"},"PeriodicalIF":5.0,"publicationDate":"2025-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143377177","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"On flight instabilities of capsule-rigid parachute system during supersonic planetary descent","authors":"Luca Placco ,&nbsp;Giulio Soldati ,&nbsp;Matteo Bernardini ,&nbsp;Francesco Picano","doi":"10.1016/j.ast.2025.110026","DOIUrl":"10.1016/j.ast.2025.110026","url":null,"abstract":"<div><div>High-fidelity time-evolving simulations of a rigid parachute trailing behind a descent module in a supersonic flight regime have been performed, employing Large-Eddy Simulation (LES) and Immersed-Boundary Method (IBM) techniques. The study aims to establish the fluid dynamic nature of the ‘breathing’ instability present also in a rigid decelerator, and thus its independence from structural flexibility. The turbulent wake of the descent capsule interacts with the bow shock generated by the parachute acting as the primary triggering factor. Energetic turbulent structures, accurately resolved by Large-Eddy Simulation, induce local fluctuations in the parachute shock, destabilizing its equilibrium with the upstream flow and leading to continuous cyclic motion of the shock wave. This motion correlates with periodic variations in flow pressure inside the canopy control volume, impacting parachute performance. Based on simulation results, a zero-dimensional model is developed to predict the unsteady dynamics of the shock motion and the decelerator performance. The model is driven by input fluctuations from the capsule wake, reproducing the main frequencies of shock position oscillations and drag variations as observed in simulations. It is apparent that unsteadiness is eventually triggered by low-frequency wake perturbations. Thus, the study provides insights into factors contributing to unsteady parachute responses in supersonic regimes.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110026"},"PeriodicalIF":5.0,"publicationDate":"2025-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143387894","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}