Aerospace Science and Technology最新文献

{"title":"Analysis of Discharge Characteristics in Large-Scale ICP Generator Featuring Swirling Intake","authors":"Yue Niu ,&nbsp;Weimin Bao ,&nbsp;Donglin Liu ,&nbsp;Xiaoping Li ,&nbsp;Yanming Liu","doi":"10.1016/j.ast.2025.110706","DOIUrl":"10.1016/j.ast.2025.110706","url":null,"abstract":"<div><div>This study is based on the Experimental Research Apparatus for Electromagnetic Science of Hypersonic Vehicle Plasma in Near Space, focusing on a large-scale inductively coupled plasma (ICP) generator capable of producing high-enthalpy, high-density plasma. This study investigates the impact of a porous swirling inlet structure, a specialized inlet method, on the discharge characteristics of the ICP generator. A three-dimensional multi-physics coupled model was developed for the ICP generator, which has a diameter of 180 mm and a length of 815 mm, to simulate discharge behavior at inlet swirl angles of 0°, 45°, and 60°. Under identical operating conditions, spectroscopic diagnostics combined with electron collision cross-section methods and the Saha equation were employed to determine the radial distributions of electron temperature and electron density for different inlet angles. The results indicate that increasing the inlet swirl angle significantly enhances the peak plasma temperature and electron density, while diminishing the spatial uniformity of discharge parameters. Based on these findings, engineering design recommendations are proposed: a 0° inlet angle ensures superior discharge uniformity and stability; a 45° inlet angle provides an optimal balance among temperature, electron density, and uniformity, making it a recommended practical design; while a 60° inlet angle achieves higher electron temperature and density but requires careful consideration of its pronounced radial decay and spatial nonuniformity in practical applications.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"167 ","pages":"Article 110706"},"PeriodicalIF":5.8,"publicationDate":"2025-07-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144739725","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":"Command governor for impact-angle guidance to fast targets under field-of-view constraint","authors":"Seokwon Lee ,&nbsp;Namhoon Cho ,&nbsp;Youdan Kim","doi":"10.1016/j.ast.2025.110695","DOIUrl":"10.1016/j.ast.2025.110695","url":null,"abstract":"<div><div>This paper introduces a command governor for two-phase impact-angle control guidance schemes applicable to air-to-air engagements. Although two-phase guidance is effective in surface-to-surface interception, it shows limitations for aerial targets with speeds similar to or greater than those of the interceptor. To improve the switching guidance scheme for anti-air missiles while complying with the seeker field-of-view constraint and terminal impact-angle requirements, we introduce a command governor that generates a look-angle command to track during the first guidance phase. The proposed command governor integrates a correction policy based on the solution characteristics in the first phase and prediction-based correction in the second phase. Hence, interception of fast aerial targets with a specified impact angle is achieved by incorporating the proposed command governor into the two-phase guidance scheme. An analysis of the region of feasible initial conditions ensures the capturability of the guidance law, and numerical simulations illustrate its effectiveness for interception at specified impact angles.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"167 ","pages":"Article 110695"},"PeriodicalIF":5.8,"publicationDate":"2025-07-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144739724","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 investigation of engine position effects on contrail formation and evolution in the near-field of a realistic aircraft configuration","authors":"Annunziata Rémy ,&nbsp;Bonne Nicolas ,&nbsp;Garnier François","doi":"10.1016/j.ast.2025.110703","DOIUrl":"10.1016/j.ast.2025.110703","url":null,"abstract":"<div><div>The present study investigates the impact of engine position on contrail formation and near-field evolution in a realistic three-dimensional aircraft configuration. Detailed numerical simulations are conducted using a Reynolds-Averaged Navier-Stokes (RANS) approach coupled with mesh adaptation techniques. A Eulerian microphysical model is used to characterize contrail ice crystal properties and their evolution under varying dilution conditions. The setup is based on a Boeing 777-like geometry, including fuselage, wings, engines, and tailplane. Two microphysical activation scenarios are considered: one incorporating adsorption-based ice nucleation and the other assuming fully activated soot particles. The latter for two soot number emission indices. The dilution process and wake structure exhibit a strong dependence on engine placement, which significantly influences plume saturation. In highly diluted configurations, enhanced early-stage mixing reduces plume temperature and increases relative humidity, favoring the growth of larger ice crystals. Depending on the soot number concentration, vapor depletion effects may outweigh dilution-driven changes in water vapor availability. In adsorption-limited activation scenarios, increased dilution reduces the concentration of sulfur species, leading to a lower activation fraction and the formation of smaller ice crystals. Additionally, across the scenarios, the modified jet-vortex interaction alters particle distribution and their access to water vapor, further shaping their growth. These effects ultimately impact the contrail's optical properties, particularly its optical thickness.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"167 ","pages":"Article 110703"},"PeriodicalIF":5.8,"publicationDate":"2025-07-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144750655","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":"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":"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}

{"title":"Compressibility modifications of FPV model for supersonic combustion in Scramjet engine based on OpenFOAM","authors":"Rui Xue,&nbsp;Xin He,&nbsp;Jing Yang","doi":"10.1016/j.ast.2025.110705","DOIUrl":"10.1016/j.ast.2025.110705","url":null,"abstract":"<div><div>Accurate simulation of supersonic combustion in scramjet engines remains challenging due to compressibility effects like shock-induced pressure fluctuations and thermo-kinetic coupling, which are inadequately captured by conventional Flamelet/Progress Variable (FPV) models. This work introduces compressibility modifications to the FPV framework, implemented within OpenFOAM as the novel CFPVFoam solver. In this solver, the species mass fractions are retrieved from flamelet libraries while temperature is solved implicitly via the energy equation to resolve thermo-kinetic coupling. An exponential scaling law was employed for pressure correction to dynamically adjust progress-variable source terms for shock/expansion wave effects. After that, validation against two scramjet configurations, which are DLR’s strut-based scramjet engine and UVA’s ramp-injected scramjet engine, demonstrates high fidelity in capturing shock trains, recirculation zones, and supersonic combustion induced flow structures. Comparisons of velocity, pressure, and temperature distributions show good agreement with experimental data, with errors primarily due to the RANS limitations in shear-layer resolution. The established CFPVFoam solver provides an effective tool for scramjet engine simulation with considering the compressibility physics into turbulent combustion modeling.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"167 ","pages":"Article 110705"},"PeriodicalIF":5.8,"publicationDate":"2025-07-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144721691","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}