Aerospace Science and Technology最新文献_第6页

Interaction between vortex shedding and flap oscillation in separation control of a stalled aerofoil 失速翼型分离控制中旋涡脱落与襟翼振荡的相互作用

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-05-09 DOI: 10.1016/j.ast.2025.110300

Yannian Yang , Pengyu Li , Yongsheng Zhou , Tao Zhou , Yu Liu , Stefan Pröbsting

{"title":"Interaction between vortex shedding and flap oscillation in separation control of a stalled aerofoil","authors":"Yannian Yang , Pengyu Li , Yongsheng Zhou , Tao Zhou , Yu Liu , Stefan Pröbsting","doi":"10.1016/j.ast.2025.110300","DOIUrl":"10.1016/j.ast.2025.110300","url":null,"abstract":"<div><div>Flow control for lifting surfaces at high angle of attack is essential to increase the lift coefficient. Inspired by covert feathers of birds, a passive rotatable flap is added to the suction surface of an aerofoil to analyze its effectiveness and flow control mechanism from the perspective of fluid structure interaction. The lift coefficients of the aerofoil are measured by a balance, increasing near the stall angle and reaching maximum augmentation of 25% with the flap. Particle image velocimetry measurements show that the transition of trailing edge shear layer to vortex shedding occurs later due to the flap, and the separation zone becomes smaller, which work together to enhance the lift-to-drag ratio. Flap movement is influenced by unsteady trailing edge vortex shedding, with the flap pop-up angle increasing together with the aerofoil angle of attack and reaching a maximum value around <span><math><msup><mrow><mn>84</mn></mrow><mrow><mo>∘</mo></mrow></msup></math></span>, beyond which it decreases again. Moreover, the experimental data observes the low frequency flow pulsation and flap oscillation in addition to the high frequency trailing edge vortex shedding, which has a modulation effect on the flow fluctuation and flap oscillation magnitude.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110300"},"PeriodicalIF":5.0,"publicationDate":"2025-05-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143936471","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}

引用次数: 0

Multi-fidelity transonic aerodynamic loads estimation using Bayesian neural networks with transfer learning 基于迁移学习贝叶斯神经网络的多保真度跨声速气动载荷估计

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-05-09 DOI: 10.1016/j.ast.2025.110301

Andrea Vaiuso , Gabriele Immordino , Marcello Righi , Andrea Da Ronch

{"title":"Multi-fidelity transonic aerodynamic loads estimation using Bayesian neural networks with transfer learning","authors":"Andrea Vaiuso , Gabriele Immordino , Marcello Righi , Andrea Da Ronch","doi":"10.1016/j.ast.2025.110301","DOIUrl":"10.1016/j.ast.2025.110301","url":null,"abstract":"<div><div>Multi-fidelity surrogate models are of particular interest in aerospace applications, as they combine the computational efficiency of low-fidelity simulations with the accuracy of high-fidelity models. This methodology, often implemented via data fusion, aims to reduce the cost of data generation while preserving predictive accuracy. Despite the widespread use of traditional machine learning techniques to improve surrogates and perform data fusion tasks, there remains a need for novel approaches that further improve predictive reliability—particularly in terms of uncertainty quantification—without substantially increasing the computational cost of generating high-fidelity training samples. In this study, we propose a Bayesian neural network framework designed for multi-fidelity prediction of transonic aerodynamic data, employing transfer learning to integrate computational fluid dynamics data of varying fidelities. The probabilistic nature of the model allows also quantification of the uncertainty in the input space, making it well suited for analyzing the inherently complex and nonlinear behavior of the transonic aerodynamic responses under investigation. Our results demonstrate that the proposed multi-fidelity Bayesian model outperforms classical data fusion Co-Kriging method, both in accuracy and generalization capabilities on unseen data.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110301"},"PeriodicalIF":5.0,"publicationDate":"2025-05-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143936470","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}

引用次数: 0

Developing 3D risk-informed no-fly zones for urban UAS operations 开发城市无人机操作的三维风险禁飞区

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-05-09 DOI: 10.1016/j.ast.2025.110297

Zhenyu Gao , John-Paul Clarke , Javid Mardanov , Karen Marais

{"title":"Developing 3D risk-informed no-fly zones for urban UAS operations","authors":"Zhenyu Gao , John-Paul Clarke , Javid Mardanov , Karen Marais","doi":"10.1016/j.ast.2025.110297","DOIUrl":"10.1016/j.ast.2025.110297","url":null,"abstract":"<div><div>Unmanned aerial systems (UAS), an integral part of the advanced air mobility (AAM) vision, are capable of performing a wide spectrum of tasks in urban environments. The societal integration of UAS is a pivotal challenge, as these systems must operate harmoniously within the constraints imposed by regulations and societal concerns. In complex urban space, safety has been a perennial obstacle to the large-scale deployment of UAS. To facilitate risk-aware UAS operations planning, we convert public risk constraints in an urban environment into 3D no-fly zones that UAS operations should avoid to adequately reduce risk to entities of value. We utilize a conditional probability framework that comprehensively integrates most existing basic models for UAS ground risk. To demonstrate the concept, we build prototype no-fly zones for a Chicago downtown model and investigate their characteristics under different conditions. We believe that the 3D no-fly zone has the potential to become a new routine tool for UAS operations planning, urban airspace management, and policy making. This idea can also be extended to address other societal impacts, such as noise and privacy, thereby paving the way for a unified, society-aware urban airspace management scheme.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110297"},"PeriodicalIF":5.0,"publicationDate":"2025-05-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143936469","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}

引用次数: 0

A systematic investigation of interior point methods for aerodynamic shape optimization 气动外形优化的内点法系统研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-05-09 DOI: 10.1016/j.ast.2025.110302

Prateek Ranjan , Wanzheng Zheng , Kai James

{"title":"A systematic investigation of interior point methods for aerodynamic shape optimization","authors":"Prateek Ranjan , Wanzheng Zheng , Kai James","doi":"10.1016/j.ast.2025.110302","DOIUrl":"10.1016/j.ast.2025.110302","url":null,"abstract":"<div><div>We present an Interior-Point optimization framework for aerodynamic shape optimization, integrating the high-fidelity SU2 suite with IPOPT to handle high-dimensional, nonlinear design problems. The framework is evaluated using two standardized test cases from the AIAA Aerodynamic Design Optimization Discussion Group. The study systematically examines barrier parameter update strategies, including Mehrotra probing, the LOQO update rule, and quality function minimization, assessing their effectiveness in achieving convergence within non-convex design spaces. A KKT-error-based globalization approach is implemented to ensure stability and convergence to stationary points across different optimization scenarios. Results indicate that both heuristic and quality function-based update methods outperform the Fiacco-McCormick barrier parameter update strategy. However, the choice of update method is highly dependent on problem dimensionality: the quality function minimization approach performs favorably in low-dimensional design spaces, whereas heuristic methods exhibit superior convergence characteristics for higher-dimensional shape optimization problems. To further investigate the behavior of these strategies, gradient-based scaling methods—combined with heuristic and non-heuristic update techniques—are applied to a family of perturbed RAE 2822 airfoils and NASA Common Research Model wings. The results reveal the presence of multiple local optima within the design space, demonstrated by primal and dual residuals that confirm stationarity and feasibility at the converged solutions. While multiple local minima exist, we argue that the design space for both problems is relatively flat.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110302"},"PeriodicalIF":5.0,"publicationDate":"2025-05-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144068602","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}

引用次数: 0

Adaptive safety attitude control of a hybrid VTOL UAV under transition flight subject to multiple faults and uncertainties 多故障和不确定性下过渡飞行混合垂直起降无人机的自适应安全姿态控制

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-05-09 DOI: 10.1016/j.ast.2025.110284

Yifang Fu , Ban Wang , Huimin Zhao , Mengqi Zhou , Ni Li , Zhenghong Gao

{"title":"Adaptive safety attitude control of a hybrid VTOL UAV under transition flight subject to multiple faults and uncertainties","authors":"Yifang Fu , Ban Wang , Huimin Zhao , Mengqi Zhou , Ni Li , Zhenghong Gao","doi":"10.1016/j.ast.2025.110284","DOIUrl":"10.1016/j.ast.2025.110284","url":null,"abstract":"<div><div>Hybrid VTOL UAVs combine the configuration advantages of fixed-wing UAVs and rotary-wing UAVs, offering great environmental adaptability and improved forward flight efficiency, but they also impose more stringent demands on UAVs' safety attitude control, particularly during the transition mode. To address this issue, this paper proposes an adaptive safety attitude control strategy for a hybrid VTOL UAV to compensate for multiple faults and uncertainties under transition flight. Firstly, dynamic modeling and control allocation scheme design of the studied UAV are performed. Then, a novel reaching law-based sliding mode control strategy is developed, ensuring robust tracking performance under model uncertainties while mitigating control chattering. Following this, an adaptive fault-tolerant control strategy is formulated for the VTOL UAV, which is capable to simultaneously address model uncertainties and actuator faults in both rotors and control surfaces, while effectively preventing the overestimation of adaptive control parameters and avoiding control chattering. Finally, simulation tests of the UAV's transition flight under multiple faults and uncertainties are conducted. The quantitative comparison results demonstrate the effectiveness of the proposed strategy for enhancing attitude control safety.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110284"},"PeriodicalIF":5.0,"publicationDate":"2025-05-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143936486","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}

引用次数: 0

Deep learning based dynamics identification and linearization of orbital problems using Koopman theory 基于库普曼理论的深度学习动力学辨识与轨道问题线性化

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-05-09 DOI: 10.1016/j.ast.2025.110295

George Nehma, Madhur Tiwari, Manasvi Lingam

{"title":"Deep learning based dynamics identification and linearization of orbital problems using Koopman theory","authors":"George Nehma, Madhur Tiwari, Manasvi Lingam","doi":"10.1016/j.ast.2025.110295","DOIUrl":"10.1016/j.ast.2025.110295","url":null,"abstract":"<div><div>The study of the Two-Body and Circular Restricted Three-Body Problems in the field of aerospace engineering and sciences is deeply important because they help describe the motion of both celestial and artificial satellites. With the growing demand for satellites and satellite formation flying, fast and efficient control of these systems is becoming ever more important. Global linearization of these systems allows engineers to employ methods of control in order to achieve these desired results. We propose a data-driven framework for simultaneous system identification and global linearization of the Circular, Elliptical and Perturbed Two-Body Problem as well as the Circular Restricted Three-Body Problem around the L1 Lagrange point via deep learning-based Koopman Theory, i.e., a framework that can identify the underlying dynamics and globally linearize it into a linear time-invariant (LTI) system. The linear Koopman operator is discovered through purely data-driven training of a Deep Neural Network with a custom architecture. This paper displays the ability of the Koopman operator to generalize to various other Two-Body systems without the need for retraining. We also demonstrate the capability of the same architecture to be utilized to accurately learn a Koopman operator that approximates the Circular Restricted Three-Body Problem.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110295"},"PeriodicalIF":5.0,"publicationDate":"2025-05-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144068601","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}

引用次数: 0

Experimental and numerical study on stability enhancement casing treatment in a counter-rotating axial compressor 对转轴流压气机机匣增稳处理的实验与数值研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-05-08 DOI: 10.1016/j.ast.2025.110290

Yanchao Guo , Yawei Liu , Lei Wang , Limin Gao , Xiaochen Mao , Ruiyu Li

{"title":"Experimental and numerical study on stability enhancement casing treatment in a counter-rotating axial compressor","authors":"Yanchao Guo , Yawei Liu , Lei Wang , Limin Gao , Xiaochen Mao , Ruiyu Li","doi":"10.1016/j.ast.2025.110290","DOIUrl":"10.1016/j.ast.2025.110290","url":null,"abstract":"<div><div>To fill the gap in experimental research on adaptive stability enhancement casing treatment in stabilization of the counter-rotating axial compressor (CRAC), this paper takes a two-stage CRAC as the research object, and conducts a discrete distributed self-recirculating casing treatment (SRCT) stability augmentation experiment. The stabilization improvement approach previously proposed, cross-stage front-jet SRCT (F_SRCT) scheme, is verified by dynamic measurement experimentation. The results show that F_SRCT can increase the stall margin by 7.21 % at the design speed condition. At the range of 50 % ∼ 100 % speed conditions, F_SRCT improves the stall margin by 5.80 % ∼ 8.12 % without reducing the peak efficiency. Besides, F_SRCT also increases the total pressure ratio by 0.30 % ∼ 1.16 %, which indicates that F_SRCT promotes the power capacity of the rotors. F_SRCT changes the propagation form and velocity of stall cells, diminishes the circumferential propagation of stall cells and mitigates the flow instability between stages, thereby suppressing the stall onset and altering the mode of stall development. Additionally, the beneficial effect of F_SRCT on the tip flow field accelerates the instability recovery rate, which enhances the safety of mechanical operation. The aforementioned surprised results highlight the potential for achieving adaptive stabilization of CRACs, thereby laying a solid foundation and confidence for future research work.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110290"},"PeriodicalIF":5.0,"publicationDate":"2025-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143947075","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}

引用次数: 0

Prediction method for mechanical properties of inflatable wing and its buckling failure mechanism 充气翼力学性能预测方法及屈曲破坏机理

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-05-07 DOI: 10.1016/j.ast.2025.110304

Zebei Mao , Ziping Li , Boyang Chen , Hang Ge , Yonghui Xu , Junqi Wang , Xinmin Chen

{"title":"Prediction method for mechanical properties of inflatable wing and its buckling failure mechanism","authors":"Zebei Mao , Ziping Li , Boyang Chen , Hang Ge , Yonghui Xu , Junqi Wang , Xinmin Chen","doi":"10.1016/j.ast.2025.110304","DOIUrl":"10.1016/j.ast.2025.110304","url":null,"abstract":"<div><div>With the advancement of aerospace technology, inflatable wings (renowned for their lightweight design and rapid deployment capabilities) have emerged as a promising solution for unmanned aerial vehicle rapid-response missions and extreme lightweight requirements. However, their reliability and safety under extreme conditions or sudden loads remain significant challenges, particularly due to limited research on buckling failure mechanisms. This study systematically investigates the load-bearing characteristics and failure evolution patterns of inflatable wings under internal pressure regulation through combined experimental and simulation approaches. Utilizing a self-developed lever-type loading platform, full-scale static loading experiments were conducted on inflatable wings under 10–35 kPa internal pressures, quantitatively revealing a linear correlation between internal pressure and structural stability. Experimental results demonstrate that wing bending stiffness and critical buckling loads increase linearly with inflation pressure. An explicit dynamic model based on membrane elements was proposed, achieving precise predictions of buckling loads (3.0 % error) and bending stiffness (6.89 % error). Analysis indicates that compressive stress on the upper surface skin induces wrinkling waves, while shear strain in the ribs exacerbates stress redistribution, leading to cascading failure from localized to global instability through progressive collapse. The established quantitative relationship model among internal pressure, stiffness, and failure loads provides theoretical support for structural design optimization and dynamic pressure regulation strategies for inflatable wings.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110304"},"PeriodicalIF":5.0,"publicationDate":"2025-05-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143927415","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}

引用次数: 0

Effect of ammonium perchlorate content on the combustion and injection efficiency of Al-H2O gelled propellant 高氯酸铵含量对Al-H2O凝胶推进剂燃烧和喷射效率的影响

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-05-07 DOI: 10.1016/j.ast.2025.110306

Songchen Yue , Gangchui Zhang , Youbiao Chu , Yao Shu , Jian Jiang , Peijin Liu , Wen Ao

{"title":"Effect of ammonium perchlorate content on the combustion and injection efficiency of Al-H2O gelled propellant","authors":"Songchen Yue , Gangchui Zhang , Youbiao Chu , Yao Shu , Jian Jiang , Peijin Liu , Wen Ao","doi":"10.1016/j.ast.2025.110306","DOIUrl":"10.1016/j.ast.2025.110306","url":null,"abstract":"<div><div>Aluminum-water (Al-H<sub>2</sub>O) propellant is a solid propulsion that offers the advantages of cost-effectiveness and minimal signal feature. Nonetheless, prevailing formulations of Al-H<sub>2</sub>O propellants result in 70–80 % combustion residue, presenting a potential hazard in terms of nozzle blockage and specific impulse. In this study, oxidants were introduced into an Al–H₂O propellant to establish a methodology for enhancing combustion efficiency and injection efficiency. Thermal gravimetric analysis, laser ignition experiments, and ignition tests using a laboratory-scale solid rocket motor (SRM) were conducted to systematically investigate the influence of varying ammonium perchlorate (AP) content on the combustion behavior and thrust characteristics of Al-H₂O propellants. The investigation identified a notable improvement in the combustion characteristics of Al-H<sub>2</sub>O propellants upon the introduction of AP. Following the inclusion of AP at a mass fraction of 12 %, the propellant exhibited a 36 % reduction in ignition delay time and a 54 % increase in burning rate. After the addition of an appropriate amount of AP, the combustion efficiency of the Al-H<sub>2</sub>O propellants increased from 88.4 % to 93.4 %. SRM firing experiments corroborated heightened combustion chamber pressure and thrust for Al-H<sub>2</sub>O propellants enriched with AP. Notably, the introduction of 12 % AP resulted in a substantial decrease in propellant residue rate from 66 % to 27 %. This finding demonstrated that the introduction of AP offers a viable means to mitigate the formation of combustion residue, holding promise for guiding the developmental trajectory of Al-H<sub>2</sub>O propellants in propulsion systems.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110306"},"PeriodicalIF":5.0,"publicationDate":"2025-05-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143931899","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}

引用次数: 0

Prioritized experience replay-based adaptive hybrid method for aerospace structural reliability analysis 基于优先经验重播的航空结构可靠性分析自适应混合方法

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-05-07 DOI: 10.1016/j.ast.2025.110257

Jiongran Wen, Baiyang Zheng, Chengwei Fei

{"title":"Prioritized experience replay-based adaptive hybrid method for aerospace structural reliability analysis","authors":"Jiongran Wen, Baiyang Zheng, Chengwei Fei","doi":"10.1016/j.ast.2025.110257","DOIUrl":"10.1016/j.ast.2025.110257","url":null,"abstract":"<div><div>Reliability assessment of aerospace structures is crucial for ensuring operational safety and preventing catastrophic failures. However, conventional reliability methods face significant challenges in adapting to diverse scenarios and capturing complex failure mechanisms under extreme conditions. To address the dual challenges of single-model dependency and modeling inaccuracy in such scenarios, the Prioritized Experience Replay-based Adaptive Hybrid Method (PER-AHM) is proposed by integrating PER-based hybrid optimization framework (PER-HOF) and adaptive modeling method (AMM). Specifically, PER-HOF is developed to efficiently obtain optimal parameters of surrogate models, by combining prioritized experience pool, dynamic update mechanism and trial switching strategy; AMM is designed to select the most suitable model for specific problems, via considering multiple metrics. The significance of the PER-AHM lies in its ability to select models in a modular manner, share solving experience and enhance the accuracy and efficiency of aerospace structural reliability analysis. To illustrate the efficiency of the developed method, two examples are used, including reliability analysis of two-dimensional nonlinear system and aeroengine high-pressure turbine radial deformation, which demonstrate that PER-AHM outperforms traditional methods in prediction accuracy and reliability assessment precision. This research provides an accuracy and efficient solution for aerospace structural reliability analysis.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110257"},"PeriodicalIF":5.0,"publicationDate":"2025-05-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143936468","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}

引用次数: 0