Aerospace Science and Technology最新文献

{"title":"Maintaining long-term stability of aeroengines under extreme environments: insights from a stochastic blisk model subjected to Lévy colored noise","authors":"X.F. Chen ,&nbsp;W. Zhang ,&nbsp;Y.F. Zhang","doi":"10.1016/j.ast.2026.111867","DOIUrl":"10.1016/j.ast.2026.111867","url":null,"abstract":"<div><div>This study is the first to investigate the complex nonlinear dynamics of the blisk structure under both parametric, external and extreme random excitations. The extreme load is modeled by Lévy colored noise with heavy-tailed characteristics and temporal correlation. The amplitude-frequency response equations are derived using the averaging method. The amplitude-frequency response curves reveal the hardening nonlinearity and bistable characteristics of the blisk system under primary parametric resonance and 1:1 internal resonance. Notably, a low-frequency side peak in the response of the disk signifies energy transfer from the blade to the disk. Within the bistable region, Lévy colored noise induces the occurrence of stochastic switching between low- and high-amplitude oscillation states, as well as stochastic resonance. Importantly, larger noise intensities or shorter correlation times lead to persistent high-amplitude oscillations, which are observable through the time history and wavelet transform. This phenomenon may result in fatigue damage to the blisk structure and even exert a catastrophic impact on aircraft safety. Therefore, we introduce the mean first passage time and define a transition probability to quantify this state transition. The results demonstrate that greater noise intensity, shorter correlation time, or a smaller stability index markedly increase the likelihood of the catastrophic transition. The above findings can provide new theoretical support for the long-term stable operation, structural health monitoring, and fault diagnosis of aeroengines in extreme environments.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111867"},"PeriodicalIF":5.8,"publicationDate":"2026-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146135213","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 model of Mach reflection in axisymmetric steady overexpanded jets: Development and applications","authors":"V. Rolland ,&nbsp;B. Shoesmith ,&nbsp;E. Timofeev","doi":"10.1016/j.ast.2026.111858","DOIUrl":"10.1016/j.ast.2026.111858","url":null,"abstract":"<div><div>This paper modifies the semi-analytical model (the MOCMR model) of Mach reflection in axisymmetric wedge-generated supersonic flow by Shoesmith and Timofeev (Shock Waves 31, 945-957 (2021)) to predict Mach reflection configurations at the axis of symmetry in an overexpanded jet just downstream from the exit of a nozzle. The jet flow is considered to be a steady, inviscid flow of an ideal gas with constant specific heats. Similar to the original MOCMR model, the MOCMR model for jet flow is based on a number of flowfields solved using the method of characteristics, a Mach stream flowfield solved by quasi-one-dimensional relations, and the three-shock theory at the triple point. The modifications include the incorporation of the jet boundary instead of a wedge surface, the addition of the Prandtl-Meyer expansion fan resulting from the interaction of the reflected shock with the jet boundary, and the method to efficiently and accurately resolve very small Mach disks. The results for flowfield structure and Mach disk radius and location are extensively compared with the experimental and numerical ones available in the literature as well as with the inviscid numerical simulations using an in-house adaptive unstructured finite-volume flow solver. The influence of various model assumptions on accuracy is examined. The proposed model is demonstrated to produce results of similar accuracy using considerably less computational resources as compared to time-marching CFD simulations, at the same time directly providing quantities which are difficult to extract from CFD flowfields. The application of the developed model lends additional support to the conjecture that seemingly regular reflections observed at the axis of symmetry in some physical experiments are due to insufficient optical resolution to discern a very small Mach disk. Furthermore, parametric studies are conducted for a range of exit Mach numbers and nozzle pressure ratios and the influence of these parameters on Mach disk radius and the slip line is examined.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111858"},"PeriodicalIF":5.8,"publicationDate":"2026-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146135212","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":"Eco-design vision for reusable vertical launch vehicles supported by multi-disciplinary design methodology and framework","authors":"Antonio Gregorio, Fabrizio Borgna, Roberta Fusaro, Giuseppe Narducci, Nicole Viola","doi":"10.1016/j.ast.2026.111871","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111871","url":null,"abstract":"","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"92 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146135214","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":"3D droplet spacing and clustering characteristics in low-temperature kerosene swirl spray via holographic imaging","authors":"Yue Zhao, Hang Zhang, Yu Wang, Yingwei Sheng, Yun Zhao, Sukai Pan, Yingchun Wu, Ge Song, Tao Liu, Xuecheng Wu","doi":"10.1016/j.ast.2026.111839","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111839","url":null,"abstract":"","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"92 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146138314","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":"Exploring the feasibility of parachute recovery systems for catastrophic failures in passenger aircraft","authors":"Samandar Khan Afridi ,&nbsp;Shakoor Akhtar ,&nbsp;Talha Zafar Khan ,&nbsp;Mohsin Ali Koondhar ,&nbsp;Ibrahim Mahariq ,&nbsp;Ezzeddine Touti","doi":"10.1016/j.ast.2026.111866","DOIUrl":"10.1016/j.ast.2026.111866","url":null,"abstract":"<div><div>This paper investigates the feasibility and effectiveness of a Parachute Recovery System (PRS) as an advanced airframe safety enhancement for commercial aircraft, focusing on the Boeing 777. A mixed-methods approach integrates analytical, order-of-magnitude aerodynamic modeling, expert qualitative assessments, and real-world case studies. Simulation results indicate a generated drag force of approximately 26.4 kN, demonstrating the PRS capability to achieve limited drag contribution under idealized descent assumptions during in-flight emergencies. Evidence from Cirrus SR20 and SR22 aircraft further validates PRS performance, achieving safe, low-impact landings with high survivability rates. However, large-scale implementation poses considerable engineering, financial, and regulatory challenges, including structural reinforcement, deployment reliability, and certification complexity. The cost-benefit analysis suggests that although initial and maintenance costs are significant, they may be offset by long-term safety improvements and reduced insurance liabilities. The study recommends the integration of lightweight composite materials, multi-stage deployment systems, comprehensive testing, and specialized pilot training, alongside collaboration among manufacturers, airlines, and regulatory authorities to streamline certification and operational adoption. The findings highlight the potential of PRS to advance next-generation aviation safety, enhance passenger survivability, and establish new benchmarks in commercial aircraft design and emergency recovery systems.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"173 ","pages":"Article 111866"},"PeriodicalIF":5.8,"publicationDate":"2026-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146134792","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":"Distributed defending strategies in target-attacker-defender game with applications to cooperative guidance","authors":"Jiliang Xie,&nbsp;Kemao Ma","doi":"10.1016/j.ast.2026.111852","DOIUrl":"10.1016/j.ast.2026.111852","url":null,"abstract":"<div><div>A nonzero-sum Target-Attacker-Defender game is investigated, where the target attempts to evade the attacker, the attacker aims to capture the target while evading the defenders, and the multiple defenders strive to capture the attacker while achieving the cooperation among them. A new class of cost functions segmented by the game times are developed to reflect the objectives of the respective agents. By optimizing these cost functions, the optimal strategies of the agents are derived, forming an equilibrium solution of the differential game. Furthermore, considering the communication interactions between the defenders, distributed defending strategies are derived for the defenders, where each defender’s strategy depends only on its own information and that of its connected neighbors. It is proved that the distributed strategies of the defenders, together with the optimal strategies of the target and the attacker, form an ϵ equilibrium solution of the differential game. The designed strategies are applied to a terminal guidance scenario, where a tactical missile intercepts an actively-defended target. Simulations are conducted to verify the effectiveness of the design.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"173 ","pages":"Article 111852"},"PeriodicalIF":5.8,"publicationDate":"2026-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146134793","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":"Inverse airfoil shape identification using POD-ANN ROMs: A coarse Mesh approach for computational efficiency","authors":"Kapil Aryal ,&nbsp;Vivek Nair ,&nbsp;Nishith K R Gorla ,&nbsp;Sandeep Patil ,&nbsp;Brian H. Dennis","doi":"10.1016/j.ast.2026.111773","DOIUrl":"10.1016/j.ast.2026.111773","url":null,"abstract":"<div><div>This paper compares two non-intrusive reduced-order models for predicting surface-pressure fields in inverse airfoil shape identification with deforming meshes. Proper Orthogonal Decomposition (POD) and feed-forward neural networks map geometric and flow parameters to POD coefficients for rapid field reconstruction. The models are trained on 200 CFD snapshots of steady two-dimensional laminar separated flow (<span><math><mrow><mi>R</mi><mi>e</mi><mo>=</mo><mn>1000</mn></mrow></math></span>) using either coarse or fine meshes to quantify accuracy-cost trade-offs. Results show that the coarse-mesh model achieves accuracy similar to the fine-mesh model while reducing offline training cost by nearly sixfold. Both models exhibit similar robustness in inverse design under noisy targets, and the reduced-order formulation smooths discretization-induced noise in the objective function, improving optimizer convergence.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111773"},"PeriodicalIF":5.8,"publicationDate":"2026-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146134790","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":"Aerodynamic optimization strategy and experimental study on short inlet in crosswind conditions using decoupled intuitive class shape transformation curves","authors":"Xintao Zhang ,&nbsp;Gang Sun ,&nbsp;Lijuan Feng ,&nbsp;Yongfeng Jin ,&nbsp;Anran Ju","doi":"10.1016/j.ast.2026.111857","DOIUrl":"10.1016/j.ast.2026.111857","url":null,"abstract":"<div><div>With the increasing diameter of high-bypass-ratio turbofan nacelles, reducing nacelle weight has become a critical design objective. Shortening the inlet length is an effective approach to achieve this goal but poses challenges under crosswind conditions due to flow separation and distortion risks. This study investigates the aerodynamic characteristics and optimization of short inlets subjected to crosswind. A distortion mechanism is revealed, showing that the coupling between the unsteady ground vortex and the diffuser flow is the key cause of flow instability and pressure distortion. Based on steady-state computational fluid dynamics analysis, a wall-velocity-based criterion is proposed for rapid engineering assessment of separation. A decoupled intuitive class shape transformation (DiCST) parameterization method is developed to independently control the fore-body and aft-body of the inlet, enhancing local shaping flexibility. Furthermore, a multi-objective optimization framework combining support vector machines with a genetic algorithm is established, transforming distortion evaluation into a flow-separation classification problem. The optimized short inlet achieves a length reduction of approximately 0.05 times the engine diameter in average while maintaining distortion within acceptable limits. Wind tunnel tests confirm that the optimized configuration suppresses flow separation effectively under crosswind conditions, validating the proposed design methodology.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111857"},"PeriodicalIF":5.8,"publicationDate":"2026-02-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146134794","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":"Design and implementation of real-time dihedral angle control for enhanced flight stability of quadrotor UAV","authors":"Nihat Çabuk","doi":"10.1016/j.ast.2026.111844","DOIUrl":"10.1016/j.ast.2026.111844","url":null,"abstract":"<div><div>This study presents a real-time geometry-aware control strategy and its experimental validation for quadrotor UAVs equipped with actively adjustable dihedral angles. By integrating a cascaded PID control architecture with dynamic dihedral modulation, the system adapts its aerodynamic configuration during flight to enhance stability and responsiveness. Unlike conventional fixed-geometry multirotors, this platform enables geometric tuning in flight via a centralized actuation mechanism. Nonlinear simulations and autonomous flight tests were conducted for five different dihedral configurations (<span><math><mrow><mi>γ</mi><mo>=</mo><mo>−</mo><msup><mn>7</mn><mo>∘</mo></msup><mo>,</mo><mo>−</mo><mn>3</mn><mo>.</mo><msup><mn>5</mn><mo>∘</mo></msup><mo>,</mo><msup><mn>0</mn><mo>∘</mo></msup><mo>,</mo><mo>+</mo><mn>3</mn><mo>.</mo><msup><mn>5</mn><mo>∘</mo></msup><mo>,</mo><mo>+</mo><msup><mn>7</mn><mo>∘</mo></msup></mrow></math></span>) under identical flight scenarios, including takeoff, hover and landing. Performance metrics such as altitude accuracy, attitude stability (roll, pitch, yaw), and structural vibration levels were analyzed. The findings validate the feasibility and effectiveness of geometry-aware control for multirotor systems. In addition, this work introduces a novel class of UAVs capable of real-time structural reconfiguration, enabling adaptation to changing flight conditions, payload variations, or mission profiles.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"173 ","pages":"Article 111844"},"PeriodicalIF":5.8,"publicationDate":"2026-02-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146134808","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":"Correlation between aerodynamic forces and vortex dynamics of a NACA0012 wing section in compressible dynamic stall via IDDES","authors":"Dechuan Ma,&nbsp;Gaohua Li,&nbsp;Jiahao Liu,&nbsp;Can Liu,&nbsp;Fuxin Wang","doi":"10.1016/j.ast.2026.111843","DOIUrl":"10.1016/j.ast.2026.111843","url":null,"abstract":"<div><div>Dynamic stall on helicopter retreating blades involves complex flow phenomena, particularly with the emergence of local supersonic regions and shock waves. This study investigates the force generation mechanisms of a pitching NACA0012 wing section in dynamic stall using improved delayed detached eddy simulations (IDDES). At a moderate Reynolds number of <span><math><mrow><mi>R</mi><msub><mi>e</mi><mi>c</mi></msub><mo>=</mo><mn>500</mn><mo>,</mo><mn>000</mn></mrow></math></span> and reduced frequencies <span><math><mrow><mi>k</mi><mo>=</mo><mn>0.15</mn></mrow></math></span> and 0.25, the compressibility effects are examined by varying the freestream Mach number (<span><math><mrow><msub><mi>M</mi><mi>∞</mi></msub><mo>=</mo><mn>0.1</mn></mrow></math></span>, 0.3, and 0.5). An extended force partitioning method (E-FPM) is proposed to establish a direct linkage between flow fields and aerodynamic forces in compressible flows. In all cases, the majority of force production is attributed to the second Galilean invariant of the velocity gradient tensor, while the remainder arises from nonzero velocity divergence and density fluctuations due to compressibility. Prior to stall onset, leading-edge suction dominates lift and drag production, and turbulent separation vortices (TSVs) also have a positive contribution. As <em>M</em>_∞ increases, the leading-edge stagnation point moves upstream. The insufficient flow acceleration reduces fluid stretching and strain around the high-curvature leading edge, causing a loss in lift when <em>M</em>_∞ reaches 0.5. Upon stall onset, the dynamic stall vortex (DSV) becomes the main force contributor. At higher <em>M</em>_∞, the DSV forms earlier due to advanced stall onset, which leads to earlier drag divergence and increased drag. However, the DSV also sheds earlier and weakens with enhanced compressibility. The reduced vorticity and increased density fluctuations within the vortex core region of the DSV result in lower peak lift and drag. With the DSV shedding, its positive contribution from the vortex core region diminishes without vorticity feed. The negative contribution from the vortex-induced stretching and strain becomes dominant and leads to lift stall. This work provides new insights into compressible dynamic stall physics and demonstrates the E-FPM’s effectiveness in identifying the physical origins of aerodynamic forces in such compressible, vortex-dominated flows.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"173 ","pages":"Article 111843"},"PeriodicalIF":5.8,"publicationDate":"2026-02-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146134810","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}