Aerospace Science and Technology最新文献

{"title":"Polydisperse microparticles distribution in supersonic crossflow: An experimental study of the influence of momentum flux and mass loading","authors":"Pengnian Yang,&nbsp;Likun Ma,&nbsp;Zhixun Xia,&nbsp;Yunchao Feng,&nbsp;Binbin Chen,&nbsp;Libei Zhao,&nbsp;Xingyuan Chen","doi":"10.1016/j.ast.2025.110975","DOIUrl":"10.1016/j.ast.2025.110975","url":null,"abstract":"<div><div>Particle-laden jet in supersonic crossflow (PJSC) have significant applications in high-speed propulsion systems, yet experimental studies on particle distribution are scarce. This study employed a direct-connected test system that generated a supersonic crossflow (∼1394 m·s⁻¹) and a sonic particle-laden jet. High-speed planar laser scattering was used to visualize polydisperse microparticles (0.1–150 µm) within the flow field. We systematically examined the effects of the momentum flux ratio (<em>J</em>) and the particle mass loading (<em>S</em>) on the particle distribution. Instantaneous particle distributions exhibited three distinct spatial patterns, namely, small-scale fluctuating distribution near the jet exit, large-scale roller-type distribution in near-wall regions, and trailing distribution in high-penetration zones. Their strong bilateral fluctuation characteristics were revealed through statistical analysis. Streamwise intersecting and longitudinal stratification induced by differences in gas-particle penetration depths drive distribution pattern transitions. Shear vortex dynamics govern fluctuating and roller-type formations for low-inertia particles. Meanwhile, particle size dispersion causes trajectory divergence for high-inertia particles, which form trailing patterns. Strong fluctuation mechanisms diverge fundamentally: windward fluctuations arise from the spatial persistence of fluctuating and trailing distributions, while leeward fluctuations correlate with the rapid dispersion of roller-type particles. Quantitative analysis confirms that <em>J</em> dominates particle penetration depth. Notably, the advantages of near-field penetration undergo nonlinear amplification downstream, which highlights the decisive role of near-injector conditions. A semi-empirical mode is established that correlates <em>J</em> with particle penetration depth. This work provides theoretical guidance for designing high-speed propulsion systems and offers foundational insights into supersonic multiphase flow.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110975"},"PeriodicalIF":5.8,"publicationDate":"2025-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145158185","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":"Effect of stage-impingement on the composite cooling performance of turbine vane leading edge utilizing in-wall channel","authors":"Xinnan Chen,&nbsp;Bo Bai,&nbsp;Yongbo Xia,&nbsp;Zhigang Li,&nbsp;Jun Li","doi":"10.1016/j.ast.2025.110967","DOIUrl":"10.1016/j.ast.2025.110967","url":null,"abstract":"<div><div>The present study proposes a novel stage impingement structure to enhance the composite cooling performance of the turbine vane leading edge. Numerical methods are employed, with multiple verifications conducted to ensure accuracy and reliability. Comprehensive comparative analyses of flow and heat transfer characteristics are performed under both adiabatic and conjugate heat transfer conditions, and the influence of the coolant flowrate is also analyzed. The findings indicate that the additional impingement increases the flow resistance of the coolant while simultaneously promoting a more balanced distribution of film coolant across each row of showerhead holes. Although the convective heat transfer on the target surface remains largely unaffected by the stage impingement, the total heat flux on the internal walls is significantly enhanced by over 70 %, thereby maximizing the heat absorption potential of the coolant. Despite a deterioration in adiabatic film coverage caused by recirculation vortex, the optimized internal cooling mechanisms effectively enhance the composite cooling performance. Compared to the conventional design, the stage impingement structure achieves an approximately 6.46 % increase in area-averaged overall cooling effectiveness on the leading edge under the design condition, corresponding to a temperature reduction of about 58 K. Further, standard deviation analysis reveals that excessive coolant flowrate compromises cooling uniformity, despite a continuous increase in area-averaged effectiveness.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110967"},"PeriodicalIF":5.8,"publicationDate":"2025-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145158199","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":"Assembly preload adjustment for mesh antennas considering coupling effects of dimensional errors and thermal deformation","authors":"Aodong Qiao ,&nbsp;Jinhua Zhang ,&nbsp;Yuqing Feng ,&nbsp;Qiangqiang Zhao ,&nbsp;Bin Fang ,&nbsp;Jun Hong","doi":"10.1016/j.ast.2025.110920","DOIUrl":"10.1016/j.ast.2025.110920","url":null,"abstract":"<div><div>The mesh antenna is an extensively utilized antenna structure for its large deployed-to-stowed ratio. Since its surface shape, which determines the electromagnetic performance, is formed by the assembly preload acting on cables, it is of vital importance to properly adjust the preload distribution in the assembly stage. However, the existing methods usually neglect either the thermal deformation or the dimensional errors of components. To improve the surface accuracy of front net, a thermal-structural model of mesh antennas considering the coupling effects of thermal deformation and dimensional errors is established, and an assembly preload adjustment method is proposed in this paper. Different from previous studies, the dimensional errors and thermal deformation of the antenna are coupled in the thermal-structural model, and the dimensional errors are split into multiple differential steps to simulate the practical deformation process of the structure. After the assembly preload adjustment, the maximum RMS errors in case 1 ∼ case 3 given in this paper are reduced by 30.6%, 28.7% and 30.8% respectively. Compared with methods proposed in previous work, the proposed method can more effectively adjust the preload of antenna while considering the coupling effects of thermal deformation and dimensional errors, and significantly enhance the in-orbit surface accuracy of antenna.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110920"},"PeriodicalIF":5.8,"publicationDate":"2025-09-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145118561","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 and numerical investigation on stability enhancement mechanisms of self-recirculating casing treatment","authors":"Hao Wang ,&nbsp;Haoguang Zhang ,&nbsp;Wuli Chu ,&nbsp;Fengyu Jing","doi":"10.1016/j.ast.2025.110951","DOIUrl":"10.1016/j.ast.2025.110951","url":null,"abstract":"<div><div>The stall induced by tip leakage flow (TLF) seriously restricts the stable operating range of the compressor. This study investigates the stability enhancement mechanism of the radially inclined self-circulating casing treatment (SCT) through experiments and unsteady numerical simulations, with a focus on analyzing the influences of the number and bleed position of the SCT structures on the stall margin. The results indicate that the negative pre-swirl provided by the radially inclined SCT increases the rotor tip loading and the total pressure ratio. Compared with the non-radially inclined SCT, a higher stall margin improvement (SMI) is obtained. The N20B70 scheme with 20 SCT structures and the bleed position at 70% Ca (Ca represents the rotor tip axial chord length) has the strongest stability enhancement capability, achieving an SMI of 15.5%. The more SCT structures there are, the stronger the compressor stability. The reason is that the increase in the number of SCT structures raises the frequency of the bleed effect, and the time is shorter than the time it takes for the TLF to recover to a low-speed state, keeping the TLF at a relatively high speed all the time. The upstream TLF is blocked by the downstream TLF with fully circumferential development, which is the fundamental cause of the low-speed region. For the SCT schemes with different bleed positions, precisely controlling the TLF with fully circumferential development is the key factor affecting the stability enhancement capability.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110951"},"PeriodicalIF":5.8,"publicationDate":"2025-09-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145158201","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":"Locally optimal aerodynamic shape design for stratospheric airships: A GA-driven MDO framework with CAD/CFD validation","authors":"Yuxiang Tian","doi":"10.1016/j.ast.2025.110965","DOIUrl":"10.1016/j.ast.2025.110965","url":null,"abstract":"<div><div>In recent years, powered airships have been considered promising alternatives for high-altitude, long-endurance missions. To address the issues of high computational costs, insufficient consideration of engineering constraints, and disconnect from manufacturing validation in existing global optimisation methods, a local optimal multidisciplinary design optimisation (MDO) framework based on genetic algorithms (GAs) is proposed in this study. In this framework, an industry-friendly lightweight parametric model (seven-segment Bézier) is innovatively used for parametric modelling of the airship fuselage, which enables precise control over critical geometric features. By establishing a multiobjective fitness function with adjustable weights and incorporating nonlinear constraints, the multi-objective genetic algorithm (MOGA) is used to efficiently search for locally Pareto optimal solutions within the feasible engineering domain. The optimised results are reconstructed into a three-dimensional model in SolidWorks and validated rigorously through a high-fidelity virtual flight test platform. Compared with the baseline design, the optimised scheme achieves a significant increase in volume of 29.8 % and 9.5 %, a reduction in the drag coefficient of 7.2 % and 4.3 %, and an improvement in energy efficiency of 26.4 % and 4.8 % while maintaining the structural stress threshold. Sensitivity analysis and Monte Carlo simulations further confirm the robustness of the solution to manufacturing tolerances. The integrated framework established in this study, which combines parametric modelling with GA local optimisation and CAD/CFD validation, provides a computationally efficient, reliable, and manufacturable solution for the engineering design of stratospheric airships, thereby significantly advancing the transition from theoretical optimisation to practical application.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110965"},"PeriodicalIF":5.8,"publicationDate":"2025-09-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145105242","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":"GCN-HF: A graph convolutional network approach for efficient aerodynamic heating prediction","authors":"Wanshu Li ,&nbsp;Wenwen Zhao ,&nbsp;Gang Dai ,&nbsp;Zhiyu Duan ,&nbsp;Yuxin Yang ,&nbsp;Weifang Chen","doi":"10.1016/j.ast.2025.110962","DOIUrl":"10.1016/j.ast.2025.110962","url":null,"abstract":"<div><div>Accurate and efficient prediction of aerodynamic heating remains a pivotal challenge in hypersonic vehicle design, where conventional computational fluid dynamics (CFD) methods face inherent trade-offs between numerical accuracy and computational efficiency. This investigation introduces GCN-HF, an innovative graph-based deep learning framework designed explicitly for predicting three-dimensional hypersonic heat flux. The proposed methodology systematically converts structured grid systems into graph-structured representations, establishing a unified architecture that synergistically integrates local geometric characteristics with global inflow conditions through multi-scale feature fusion. Departing from conventional data-driven paradigms, our framework inherently processes non-Euclidean spatial data while maintaining computational efficiency across arbitrarily structured grids, thereby demonstrating superior generalization capabilities for geometrically complex configurations. The novel integration strategy, which couples global inflow conditions with local geometric features, enables a comprehensive characterization of aerodynamic heating mechanisms, significantly enhancing model adaptability to diverse inflow conditions and geometric variations. Validation studies reveal remarkable performance metrics: For interpolation cases under known inflow conditions, the method attains area-averaged mean relative errors (<em>MRE</em>) of &lt;10.5% across blunt cones, blunt bicones, and sharp cones, with localized maximum <em>MRE</em> (<em>MRE</em>_max) limited to 3%. In geometric extrapolation scenarios, the framework achieves domain-averaged <em>MRE</em> of &lt;17% for blunt configurations while maintaining <em>MRE</em>_max at 7.9%. Notably, comparative analysis demonstrates the computational acceleration of 109-230 × compared to conventional CFD techniques for configuration extrapolation tasks, preserving engineering-level accuracy throughout. This paradigm establishes an optimal equilibrium between predictive fidelity and computational efficiency for real-time aerodynamic analysis while exhibiting robust extensibility and substantial application potential in aerospace engineering design optimization.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110962"},"PeriodicalIF":5.8,"publicationDate":"2025-09-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145118563","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":"A high-accuracy shape sensing method for deformation digital twin monitoring of thin-walled aircraft structures","authors":"Qihang Chen ,&nbsp;Yang Zhang ,&nbsp;Xin Dong ,&nbsp;Jiacheng Cui ,&nbsp;Yongkang Lu ,&nbsp;Pai Zheng ,&nbsp;Wei Liu","doi":"10.1016/j.ast.2025.110960","DOIUrl":"10.1016/j.ast.2025.110960","url":null,"abstract":"<div><div>High-accuracy deformation monitoring of thin-walled aircraft structures, referring to panels of primary load-bearing components such as wings and fuselage sections, is a critical link in surface-shape feedback during flexible manufacturing, as it is a key prerequisite for ensuring compliant assembly. Shape sensing technology provides essential support to achieve this goal. However, traditional methods are often sensitive to strain noise and heavily dependent on material parameters. This paper presents a shape sensing method for deformation digital twin monitoring (DDTM) of thin-walled aircraft structures that combines the inverse finite element method (iFEM) with Bayesian inference and Gaussian process modeling. The method corrects displacement estimation errors online and does not rely on prior material parameters. A bilinear interpolation scheme is used to extend the correction across the full structure under sparse sensing conditions. The approach is tested on reduced-scale wing panels made of aerospace-grade aluminum alloy and CFRP during robot-assisted shape compensation assembly. Experimental results show that the method achieves a maximum relative error of 12.80% and an average relative error of 4.66%. Compared with conventional iFEM, the average error is reduced by 64.42% on average. The proposed method improves sensing accuracy and robustness, providing a reliable and efficient tool for high-precision DDTM during aircraft manufacturing.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110960"},"PeriodicalIF":5.8,"publicationDate":"2025-09-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145265577","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":"Mechanism of effects of adjustable stator clearances axial location on a high-load axial flow compressor performance","authors":"Haoguang Zhang (张皓光) ,&nbsp;Yue Li (李玥) ,&nbsp;Hao Wang (王浩) ,&nbsp;Ruizheng Yang (杨睿正) ,&nbsp;Wuli Chu (楚武利)","doi":"10.1016/j.ast.2025.110934","DOIUrl":"10.1016/j.ast.2025.110934","url":null,"abstract":"<div><div>To investigate the influence of the partial clearance position of adjustable stator blades on the performance and flow field of an axial compressor, a numerical simulation was first conducted on an inlet-stage compressor with a loading coefficient of 0.5. The results indicate that the instability mechanism of the prototype compressor is attributed to the accumulation of low-energy fluid generated by tip leakage flow in the stator blade passage near-stall conditions. This fluid blocks the blade tip passage, subsequently triggering flow instability within the compressor. Then, based on the instability mechanism analysis of the prototype compressor, five different research schemes with varying partial clearance axial positions were designed by simultaneously shifting at both the blade root and tip. Results show that: Using the original platform positions (25 %∼60 % Ca at the root, 23 %∼48 % Ca at the tip) as the datum, forward-shifting the axial position of the platforms improves the compressor's total pressure ratio and efficiency across the entire operating range. Among these configurations, the scheme with platforms positioned closest to the leading edge (0 %∼35 % Ca at the root, 0 %∼25 % Ca at the tip) improved the compressor's pressure ratio and efficiency at peak efficiency condition by 0.64 % and 0.85 %, respectively. Additionally, the stall inception location shifted to the rotor tip region. When the platform axial position is shifted rearward, the compressor performance initially improved but subsequently deteriorated.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110934"},"PeriodicalIF":5.8,"publicationDate":"2025-09-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145105169","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":"Delaying the buzz onset in a supersonic inlet by multi-row disk concept","authors":"Sohrab Panahandeh Taghi-Abad,&nbsp;Mohammad Hossein Moghimi Esfand-Abadi,&nbsp;Javad Sepahi-Younsi","doi":"10.1016/j.ast.2025.110963","DOIUrl":"10.1016/j.ast.2025.110963","url":null,"abstract":"<div><div>At subcritical operating conditions of the supersonic air inlets, if the mass flow rate drops below a certain threshold for any reason, the shock waves begin to oscillate back and forth through the inlet, causing the inlet to become unstable. This event is known as the buzz phenomenon. A literature review reveals that one of the proposed methods for improving the inlet stability is using the Multi-Row Disk (MRD) arrangement concept. In this method, part of the inlet compression body is replaced with a series of disks, and between these disks, a series of cavities are created that can prevent flow separation. The use of this method is novel and very limited studies have been conducted on it so far. Most of the studies have focused on the effects of the size and number of cavities that are created between the disks on the inlet performance parameters, and no research has been done about the inlet stability and buzz phenomenon. Therefore, the main goal of the present study is to investigate the effects of MRD method on preventing and postponing the buzz phenomenon. In this research, an axisymmetric supersonic inlet is computationally studied at a free stream Mach number of 2. The Reynolds-Averaged Navier-Stokes (RANS) equations are solved in an unsteady state and the k-ω turbulence model is used to account for the turbulence effects. The results showed that MRD method can delay the buzz onset and increase the subcritical stability margin of the inlet significantly. In addition, this method, relying on simple geometric principles, not requiring complex control systems, and not adversely affecting the inlet performance parameters, can improve the inlet stability by decreasing the amplitude and frequency of the buzz oscillations.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110963"},"PeriodicalIF":5.8,"publicationDate":"2025-09-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145105166","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":"ResMLP-informed analytical model of asymmetric Mach reflection on V-shaped blunt leading edges under sideslip conditions and its application to pressure/heating loads","authors":"Luoyu Rao,&nbsp;Tao Zhang,&nbsp;Fan Lei,&nbsp;Chongguang Shi,&nbsp;Chengxiang Zhu,&nbsp;Yancheng You","doi":"10.1016/j.ast.2025.110928","DOIUrl":"10.1016/j.ast.2025.110928","url":null,"abstract":"<div><div>This paper describes a residual multilayer perceptron-informed analytical model for predicting the asymmetric Mach reflection (MR) configuration on V-shaped blunt leading edges under nonzero sideslip angles. A physics-guided neural network framework is leveraged alongside a simplified continuity equation to predict the detachment distance of the detached shock at the triple point. By embedding this hybrid model into the three-dimensional simplified continuity equation, an additional predictive framework is developed to characterize the asymmetric MR structure at the crotch region under sideslip conditions. Comparative analysis reveals that the model effectively captures variations in the Mach stem height and the displacement of triple points on both the windward and leeward sides as the sideslip angle varies. Moreover, by forecasting the behavior of the curved shock at the crotch, the model successfully identifies the primary shock interaction structure under sideslip conditions. In scenarios where the model predicts primary MR, both theoretical analyses and simulation results reveal a strong positive correlation between the intensity of the secondary transmitted shock and the peak pressure and heating loads at various sideslip angles.Conversely, when the model predicts a same-family regular reflection, the dimensionless local pressure/heating peaks significantly decrease relative to the MR case.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110928"},"PeriodicalIF":5.8,"publicationDate":"2025-09-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145158200","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}