Aerospace Science and Technology最新文献

{"title":"The influence of axial slot casing treatment on non-synchronous blade vibration of axial compressor","authors":"Shijie Mu ,&nbsp;Weimin Wang ,&nbsp;Wei Wang ,&nbsp;Zhibo Zhang ,&nbsp;Yanzhen Liu","doi":"10.1016/j.ast.2025.110686","DOIUrl":"10.1016/j.ast.2025.110686","url":null,"abstract":"<div><div>Non-synchronous vibration generally occurs near stall in axial-flow fans and compressors, markedly reducing overall efficiency and shortening blade fatigue life. To fix this problem, we designed four axial slot configurations for a 1.5-stage axial compressor and numerically explored their influence on non-synchronous vibration and the associated lock-in phenomenon. An in-depth investigation of the flow field reveals that the axial slot functions by dynamically modifying the pressure and velocity distribution in the low-momentum area to optimize the momentum chain over the whole flow passage. The presence of axial slots attenuates the propagation speed of disturbances, shifts the primary excitation source from the dominant tornado vortex to the tip leakage vortex, and alters the fluid–structure interaction during non-synchronous vibration. This work proposes a harmonic-balance-based approach that links nonlinear dynamics to vortex-shedding frequency and aerodynamic conditions, thereby quantifying lock-in intensity and providing an early-warning indicator for non-synchronous vibration. By using this method, it is found that the axial slot can suppress the flow-induced vibration of the blade to a great extent by reducing the frequency range corresponding to the lock-in phenomenon. This work provides a new perspective for understanding the formation and development of non-synchronous vibration.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"167 ","pages":"Article 110686"},"PeriodicalIF":5.8,"publicationDate":"2025-07-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144772301","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":"Dynamic coverage path planning method for UAV formations in multi-region aerial tasks","authors":"Quancheng Pu ,&nbsp;Lu Yang,&nbsp;Tieshan Li","doi":"10.1016/j.ast.2025.110683","DOIUrl":"10.1016/j.ast.2025.110683","url":null,"abstract":"<div><div>Planning coverage paths for multiple discrete regions is a prerequisite for Unmanned Aerial Vehicle (UAV) formations to perform continuous coverage tasks. However, precisely solving for the globally optimal path is computationally challenging, and maintaining formation shape under the interference of static and dynamic obstacles is difficult. Traditional path planning methods often perform poorly in large-scale, multi-region coverage tasks due to getting trapped in local optima or low computational efficiency, making it challenging to maintain formation shape while achieving swarm obstacle avoidance. This study proposes a novel dynamic multi-region coverage path planning method to enhance the task efficiency and safety of UAV formations in complex environments. First, a heuristic optimization algorithm, PGS2, was developed, incorporating three optimized mechanisms to significantly enhance global search capabilities. In nine scenarios with varying numbers of access points and discrete regions, PGS2 reduced average path costs by 56.7% and 1.35% compared to six baseline algorithms, demonstrating superior optimization performance and stability. Second, the Orthogonal Artificial Potential Field (Orthogonal APF) path planning algorithm and a gradient-mapping-based swarm self-avoidance method were proposed, achieving dynamic path planning while maintaining formation shape through virtual target point design. Orthogonal APF achieved a 100% target arrival rate in nine multi-obstacle scenarios, with path deviation reduced by an average of 31.93% compared to four other algorithms, validating its effectiveness and unique path recovery capability. In a simulation environment with three regions and multiple obstacles, the UAV formation could avoid static obstacles in approximately 5 seconds and dynamic obstacles in about 2 seconds, while the virtual target point mechanism ensured formation recovery within approximately 3 seconds post-avoidance and supported formation reconfiguration for varying UAV counts. This study provides an innovative path planning method for efficient and safe UAV formation operations in multi-region, complex environments, with comparisons to traditional methods demonstrating its significant advantages in path optimization, obstacle avoidance, and task continuity.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"167 ","pages":"Article 110683"},"PeriodicalIF":5.8,"publicationDate":"2025-07-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144750608","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":"Algebraic local correlation-based transition model for wide-speed-range flows considering crossflow effects","authors":"Haijun Jiang ,&nbsp;Zaijie Liu ,&nbsp;Chao Yan","doi":"10.1016/j.ast.2025.110692","DOIUrl":"10.1016/j.ast.2025.110692","url":null,"abstract":"<div><div>In this study, we present an algebraic transition model designed for three-dimensional flows across a wide range of speeds. Building on the foundational principles of a one-equation local correlation-based model, we introduce two key enhancements. First, we extend the model to account for crossflow-induced transitions by developing a novel crossflow transition onset function. Second, we simplify the model to a zero-equation formulation through the introduction of an algebraic intermittency factor. Initial validation of our algebraic model was conducted using a series of flat plates and straight cones, demonstrating performance comparable to the one-equation model in two-dimensional and axisymmetric flows. Further assessments were carried out on an inclined prolate spheroid in subsonic flows, as well as the hypersonic international flight research and experimentation (HIFiRE) -5 elliptic cone and hypersonic transition research vehicle (HyTRV) in hypersonic flows, to evaluate the model's efficacy in three-dimensional configurations. Comparisons with experimental data indicate that our algebraic model accurately predicts crossflow-induced transitions with reasonable precision.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"167 ","pages":"Article 110692"},"PeriodicalIF":5.8,"publicationDate":"2025-07-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144772280","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":"Numerical study on the aerodynamic performance of ducted fans under free windmilling conditions","authors":"Yibo Zhao,&nbsp;Zhiqiang Chang,&nbsp;Xiaocheng Zhu,&nbsp;Zhaohui Du","doi":"10.1016/j.ast.2025.110700","DOIUrl":"10.1016/j.ast.2025.110700","url":null,"abstract":"<div><div>With the rapid development of electric aviation propulsion, ducted fans have gained widespread application as a novel propulsion device due to their high efficiency, safety, and low noise characteristics. Motor power off during flight can lead to a rapid decrease in rotor speed, resulting in a windmilling condition, with a sharp decline in thrust, and significant threats to the safety and stability of the aircraft. In this study, steady and unsteady Reynolds Averaged Navier-Stokes methods are employed to numerically simulate the windmilling conditions of ducted fans. The Kriging surrogate model is used to efficiently determine the windmilling rotational speed. The flow characteristics of ducted fans under windmilling conditions exhibit significant similarity, with a strictly linear relationship between windmilling rotational speed and forward velocity. With a suitable deviation angle model, a predictive model for windmilling rotational speed is provided, demonstrating an estimation error of approximately 1 %. Additionally, the windmilling characteristics of ducted fans under various crosswind conditions are analyzed.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"167 ","pages":"Article 110700"},"PeriodicalIF":5.8,"publicationDate":"2025-07-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144772298","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":"New compact water cycle algorithm-based trajectory planning and control frameworks for indoor assistant UAVs","authors":"Nesrine Tenniche ,&nbsp;Boubekeur Mendil","doi":"10.1016/j.ast.2025.110684","DOIUrl":"10.1016/j.ast.2025.110684","url":null,"abstract":"<div><div>Elderly and disabled individuals, particularly those who are blind or visually impaired, often face challenges navigating their homes due to cluttered spaces and limited spatial awareness. To support their independence, an indoor assistant unmanned aerial vehicle (UAV) system is proposed to perform assistive tasks such as navigation guidance, object delivery, and environmental monitoring, where safe and adaptive UAV operation can significantly enhance quality of life. However, indoor environments impose strict limitations on energy, memory, and onboard computation. To address these limitations, a new compact Water Cycle Algorithm (cWCA) is proposed as the first compact variant of the original WCA. While classical WCA achieves strong performance in constrained environments, it requires large populations and is computationally demanding. In contrast, cWCA introduces a compact probabilistic solution model with only two candidate solutions per iteration, drastically reducing memory usage and computation time. Its novelty lies in preserving WCA's natural flow mechanisms within a lightweight, compressed framework suitable for real-time execution. The proposed cWCA is applied to both trajectory planning and control in a simulated home-like environment containing 40 obstacles. It generates smooth, collision-free paths and automatically tunes 18 control gains for accurate tracking. Across 15 simulation trials, cWCA outperforms the original WCA and the compact versions of Firefly Algorithm (cFA), Differential Evolution (cDE), Genetic Algorithm (cGA), Particle Swarm Optimization (cPSO), Artificial Bee Colony (cABC), and Teaching-Learning-Based Optimization (cTLBO) in path efficiency, energy consumption, and control accuracy. These results highlight cWCA's potential as a lightweight solution for real-time, embedded assistive UAV applications.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"167 ","pages":"Article 110684"},"PeriodicalIF":5.8,"publicationDate":"2025-07-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144723591","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":"Multi-objective trajectory planning for flexible spacecraft via physics-informed neural network","authors":"Xilin Zhong,&nbsp;Shujie Liu,&nbsp;Ti Chen,&nbsp;Haiyan Hu","doi":"10.1016/j.ast.2025.110710","DOIUrl":"10.1016/j.ast.2025.110710","url":null,"abstract":"<div><div>This study addresses the autonomous collision-free motion planning of a spacecraft with flexible appendages using a neural network embedded with the rigid-flexible dynamics. The study presents the trajectory diffusion network and input transition method for local motion planning with rigid-flexible dynamics taken into account. Furthermore, the study deals with the coupling among three Euler angles via the inter-Euler-angle embedding method, and a reconstruction loss function designed to incorporate the coupling dynamics into the network. The proposed neural network integrates with the rapidly-exploring random tree star framework for the overall collision-free motion planning, and a precise algorithm designed for collision detection with the consideration of the deformation of the appendages. Both simulation and experimental studies validate the effectiveness of the motion planning method.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"167 ","pages":"Article 110710"},"PeriodicalIF":5.8,"publicationDate":"2025-07-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144772300","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":"The influence of chemical models on hypersonic nonequilibrium flow field characteristics in numerical simulations","authors":"Yiyang Du ,&nbsp;Lihui Liu ,&nbsp;Chenggeng Wu ,&nbsp;Junya Yuan ,&nbsp;Guobiao Cai ,&nbsp;Bijiao He","doi":"10.1016/j.ast.2025.110680","DOIUrl":"10.1016/j.ast.2025.110680","url":null,"abstract":"<div><div>Hypersonic vehicles generate significant thermochemical nonequilibrium phenomena during reentry into the Earth's atmosphere, accompanied by complex physical processes, which pose challenges for accurate numerical prediction. Several chemical models have been developed to predict nonequilibrium flow fields, but research on the discrepancies among models at extremely high Mach is currently limited and it is essential to conduct further research, as the nonequilibrium phenomena intensify and these discrepancies become more significant under such conditions. To investigate the computational differences among the Park (1993) <span><span>[9]</span></span>, Dunn and Kang (1973) <span><span>[5]</span></span>, and Gupta et al. (1990) <span><span>[10]</span></span> chemical models, numerical simulations of hypersonic reentry nonequilibrium flow fields were conducted at an altitude of 60 km and within a Mach range from 15 to 30. The findings reveal that those three chemical models primarily alter the distribution difference of the NO component. The Park model has a significantly higher NO dissociation rate, resulting in a notably lower NO mass fraction. In terms of heat flux distribution, as the shock distance exceeds the thermochemical relaxation distance, allowing the nonequilibrium state behind the shock to transition to an equilibrium state, the aerodynamic heat flux calculated by the Park model is the maximum, while the minimum for the Dunn-Kang model. Finally, by comparing to the experimental data from Mars Pathfinder and Radio Attenuation Measurement (RAM-C II), the Park model shows better performance in predicting aerodynamic heating, with the calculation error maintained within 16.2%.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"167 ","pages":"Article 110680"},"PeriodicalIF":5.8,"publicationDate":"2025-07-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144723590","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":"Experimental study on effusion cooling characteristics under a swirl premixed methane-air flame in gas turbine combustor","authors":"Xiang Lu,&nbsp;Yuansen Li,&nbsp;Yunlai Xiao,&nbsp;Bing Ge","doi":"10.1016/j.ast.2025.110698","DOIUrl":"10.1016/j.ast.2025.110698","url":null,"abstract":"<div><div>This study investigates the impact of equivalence ratio and mainstream velocity on the effusion cooling effectiveness under a swirl-premixed methane-air flame, revealing novel insights into the cooling performance under varying combustion conditions. Three distinct cooling effectiveness distribution modes are identified, each governed by the interplay between equivalence ratio and mainstream velocity. Mode A (Mixture Impingement Mode), observed at low equivalence ratios, is characterized by a unique chemical reaction-driven cooling mechanism, where unburned mixture impingement on the wall results in locally enhanced cooling effectiveness. Notably, this mode exhibits a stable low-cooling zone in the corner recirculation region, a phenomenon that remains consistent across test conditions. As the equivalence ratio increases, the system transitions to Mode B (Transitional Mode), where the lowest cooling effectiveness shifts toward the swirl impingement zone. At high equivalence ratios, Mode C (Swirl Impingement Mode) emerges, dominated by swirl-induced impingement effects that significantly reduce cooling effectiveness, while the location of the lowest cooling point remains unchanged. The study further demonstrates that increasing mainstream velocity, coupled with a reduction in equivalence ratio, not only enhances cooling effectiveness but also improves its spatial uniformity under constant heat load conditions. These findings provide critical design guidelines for optimizing effusion cooling in gas turbine combustors, offering a significant advancement in understanding the complex interactions between combustion dynamics and cooling performance.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"167 ","pages":"Article 110698"},"PeriodicalIF":5.8,"publicationDate":"2025-07-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144750657","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":"Tonal noise of a fan with porous-wavy leading edge","authors":"Ruibiao Gao ,&nbsp;Hui Lei ,&nbsp;Hang Tong ,&nbsp;Liangfeng Wang ,&nbsp;Kangshen Xiang ,&nbsp;Weijie Chen","doi":"10.1016/j.ast.2025.110711","DOIUrl":"10.1016/j.ast.2025.110711","url":null,"abstract":"<div><div>This work presents numerical studies of rotor-stator interaction tonal noise reduction using porous materials and wavy leading edge. The rotor-stator interaction flow field is solved using the Unsteady Reynolds-Averaged Navier-Stokes (URANS) equation, while the noise is predicted by Goldstein’s acoustic analogy method. Firstly, three bionic configurations are designed. The results show that configurations incorporating porous materials underperform the wavy leading edge in noise reduction at the first blade passing frequency (BPF). This is primarily because the use of porous materials amplifies pressure fluctuations at the porous-solid junction and weakens the effectiveness of suppressing pressure fluctuation correlations. Secondly, a wavy configuration design is applied to the porous-solid junction, creating the Wavy-Porous Wavy Leading Edge (WPWLE) blade. The noise reduction capability of WPWLE is significantly improved, achieving a noise reduction level of 9.5 dB at 1BPF. The WPWLE suppresses pressure fluctuations at the leading edge, and effectively mitigates pressure fluctuations at the porous-solid junction. Furthermore, the WPWLE retains the capability to reduce pressure fluctuations correlations.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"167 ","pages":"Article 110711"},"PeriodicalIF":5.8,"publicationDate":"2025-07-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144750656","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":"Optimal design and aerodynamic performance analysis of a radial inflow turbine in the helium‒xenon mixture Brayton cycle","authors":"Yinke Qi ,&nbsp;Xiaofeng Ma ,&nbsp;Peixue Jiang ,&nbsp;Yinhai Zhu","doi":"10.1016/j.ast.2025.110699","DOIUrl":"10.1016/j.ast.2025.110699","url":null,"abstract":"<div><div>The helium‒xenon mixture Brayton cycle has a moderate operating pressure; therefore, is potential to serve as a heat-to-power conversion technology for future hypersonic vehicles using ceramic matrix composite (CMC) materials. In this study, a viable methodology for one-dimensional optimal design and three-dimensional simulation of a radial inflow turbine in the helium‒xenon mixture Brayton cycle was established based on real gas properties. First, the optimal cycle operating point corresponding to the minimum system weight under a given cycle output power was obtained using the interior-point method. Then, coupling the particle swarm optimization algorithm, a single-stage radial inflow turbine with an expansion ratio of 2.12 and a flow rate of 3.5 kg/s was designed. Finally, a numerical simulation was conducted to investigate the turbine characteristics under design and off-design conditions. The turbine exhibits a favorable aerodynamic performance with an efficiency of 83.64 % and output power of 433.12 kW, and has a relatively broad high-efficiency area. Even when the expansion ratio increases above 4.0 and the turbine operates under choked conditions, the minimum efficiency remains at above 79 %, satisfying the requirements of varying conditions in practical operation. This study provides a foundation for research on heat-to-power conversion technology for next-generation CMC hypersonic vehicles.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"167 ","pages":"Article 110699"},"PeriodicalIF":5.8,"publicationDate":"2025-07-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144723586","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}