Aerospace Science and Technology最新文献

{"title":"Mixed-auxiliary systems based switching adaptive tracking control for conversion mode of tilt-rotor aircraft","authors":"Wen Li,&nbsp;Shuang Shi,&nbsp;Mou Chen,&nbsp;Qingxian Wu","doi":"10.1016/j.ast.2025.110921","DOIUrl":"10.1016/j.ast.2025.110921","url":null,"abstract":"<div><div>An adaptive tracking control scheme for the conversion mode of twin tilt-rotor aircraft is proposed under input saturation and fixed-time prescribed performance requirements. First, due to the tilting features, a longitudinal switched nonlinear model is constructed in view of aerodynamic analysis to facilitate controller design. Second, considering the input saturation, the distribution-based multi-auxiliary systems are designed to match the requirements of time-related flexible prescribed performance. Third, a novel adaptive switching controller is designed to reduce the influences caused by modeling uncertainty. Finally, an XV-15-based simulation result verifies the effectiveness of the proposed method.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110921"},"PeriodicalIF":5.8,"publicationDate":"2025-09-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145219743","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":"Input matrix compensated strong tracking filter for maneuvering spacecraft tracking","authors":"Peng Zhang ,&nbsp;Nan Zhang ,&nbsp;Hexi Baoyin ,&nbsp;Zhaokui Wang","doi":"10.1016/j.ast.2025.110995","DOIUrl":"10.1016/j.ast.2025.110995","url":null,"abstract":"<div><div>Accurate tracking of maneuvering space targets is crucial, as their unpredictable movements pose significant challenges in increasingly congested space environments. A widely used method for tracking impulsive maneuvering targets is the Strong Tracking Filter (STF). While effective, this method has two primary limitations in practical applications. First, it causes significant transient tracking errors following a maneuver. Second, because the method relies on measurement residuals to detect maneuvers, it is unable to distinguish between actual maneuvers and measurement outliers, leading to misinterpretations that degrade tracking accuracy. This paper proposes two key improvements to overcome these issues. First, an input matrix compensation framework is introduced based on a residual orthogonalization criterion, which updates the covariance in a way that better reflects the physical impact of unknown maneuvers through the system’s input matrix. This modification effectively eliminates transient tracking error overshoots while maintaining tracking accuracy. Second, an auxiliary filter is introduced to handle measurement outliers, allowing for precise differentiation between outliers and maneuvers, thereby enhancing the algorithm’s robustness in the presence of outliers. Simulation results demonstrate that the proposed method outperforms the STF in terms of convergence, accuracy, and robustness, particularly in scenarios with measurement outliers.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110995"},"PeriodicalIF":5.8,"publicationDate":"2025-09-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145195528","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 of dynamic characteristics of Rotor 37 induced by back pressure and rotation speed variation","authors":"Fan Liu ,&nbsp;Hong-Kai Ren ,&nbsp;Fu-Zhen Chen ,&nbsp;Hong Yan","doi":"10.1016/j.ast.2025.110987","DOIUrl":"10.1016/j.ast.2025.110987","url":null,"abstract":"<div><div>The dynamic characteristics of fan component have an important impact on the transient performance and stable working margin during aero-engine acceleration and deceleration processes. The effects of the amplitude and frequency of back pressure variation on the dynamic characteristics of Rotor 37 are investigated in the designed rotation speed and during acceleration and deceleration processes. The shock wave evolution in cascade flow field is analyzed based on the three dimensional unsteady simulations of a single passage model. The results show that the dynamic operating points do not move along the constant rotation speed line when the outlet boundary is specified with a variable back pressure. The dynamic characteristics exhibit a hysteresis loop, and the corresponding position of shock wave in the cascade flow also shows a hysteresis variation. This hysteresis loop expands with the increase of back pressure amplitude, and deforms with the back pressure frequency. Based on the back pressure pulsation frequency and the characteristic time of disturbance propagation, a dimensionless pulsation frequency (<span><math><msub><mi>S</mi><mi>f</mi></msub></math></span>) is defined to reveal the influence of frequency on the rotor flow and the phase of variations. The dynamic characteristics of the rotor are closer to the steady results with <span><math><mrow><msub><mi>S</mi><mi>f</mi></msub><mo>≈</mo><mn>0</mn></mrow></math></span>. The hysteresis of the dynamic characteristics becomes significant with the range of <span><math><mrow><mn>0</mn><mo>&lt;</mo><msub><mi>S</mi><mi>f</mi></msub><mo>&lt;</mo><mn>1</mn></mrow></math></span>. As for <span><math><mrow><msub><mi>S</mi><mi>f</mi></msub><mo>&gt;</mo><mn>1</mn></mrow></math></span>, the influence range of back pressure variation on the rotor flow is decreased significantly and eventually limited to the region near the outlet. Moreover, the effects of constant and variable back pressure on the transient performance of Rotor 37 are compared during acceleration and deceleration processes between 90 % to 100 % designed rotation speed. The rotor efficiency hysteresis and fluctuation are elucidated to be associated with the leakage vortex breakage based on the total pressure loss distribution of the tip flow.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110987"},"PeriodicalIF":5.8,"publicationDate":"2025-09-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145265742","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":"Development and characterisation of a turbulent boundary layer facility at the Delft University of Technology","authors":"Max W. Knoop,&nbsp;Abdelrahman Hassanein,&nbsp;Woutijn J. Baars","doi":"10.1016/j.ast.2025.110972","DOIUrl":"10.1016/j.ast.2025.110972","url":null,"abstract":"<div><div>A new facility for studying turbulent boundary layer flows has been developed at the Delft University of Technology and is referred to as the DU-BLF: Delft University Boundary Layer Facility. Its design and boundary layer data characteristics are presented in the current work. The DU-BLF can be employed for a range of studies revolving around boundary layer flows, <em>e.g.</em>, covering fundamentals of boundary layer development, flow control with passive surface modifications, and control efforts with active technologies. A modular setup of the test section allows for a relatively long development length, with both physical and optical access over its complete extent. For the present characterisation, a turbulent boundary layer was developed under a zero (streamwise) pressure gradient, with the aid of a flexible ceiling. We establish the general flow characteristics, including freestream turbulence intensity levels, acoustic noise characteristics, boundary layer-integral parameters, and wall-normal profiles of the first and second-order turbulence statistics. Results are validated by employing multiple measurement techniques, namely, hot wire anemometry, particle image and tracking velocimetry, and wall-pressure measurements. Results are shown for friction Reynolds numbers up to <span><math><mrow><mi>R</mi><msub><mi>e</mi><mi>τ</mi></msub><mo>≈</mo><mn>5</mn><mspace></mspace><mn>100</mn></mrow></math></span>, and reveal that the boundary layer flow adheres to the expected behaviour of canonical wall-bounded turbulence. Data of the current turbulent boundary layer measurements are made available <span><span>online</span><svg><path></path></svg></span>.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110972"},"PeriodicalIF":5.8,"publicationDate":"2025-09-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145266475","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":"Investigation of aero-optical effects and passive control in subsonic cavity flows","authors":"Kunpeng Long ,&nbsp;Qiang Zhang ,&nbsp;Rongrong Xue ,&nbsp;Jinying Li ,&nbsp;Haotong Ma","doi":"10.1016/j.ast.2025.111000","DOIUrl":"10.1016/j.ast.2025.111000","url":null,"abstract":"<div><div>This study investigates aero-optical wavefront distortions induced by open cavity flows at subsonic to transonic speeds (Mach 0.5-0.8) through combined high-frequency wind tunnel experiments and fluid-optical coupled simulations as complementary. A rectangular cavity configuration is examined under fully developed turbulent boundary layers, with and without leading-edge passive flow control devices. Time-resolved optical path difference (OPD) fields are measured at 20 kHz using a wavefront sensor, and decomposed into tilt and high-order aberrations via Zernike modal analysis. Results reveal that large-scale shear-layer oscillations dominate at lower Mach numbers, contributing primarily to tilt aberrations, while higher Mach numbers introduce compressibility-driven high-order distortions. Passive control devices, such as transverse rods and flat-top spoilers, effectively suppress coherent vortex structures, leading to significant reductions in low-order aberrations with minimal penalties in high-order modes. Spectral analysis shows strong alignment between dominant OPD frequencies and Rossiter resonance modes. Among all tested geometries, the flat-top spoiler achieves the most consistent control across Mach regimes. These findings provide insights into the flow-optics coupling mechanisms in cavity environments and inform the aerodynamic design of integrated optical systems in high-speed flight.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111000"},"PeriodicalIF":5.8,"publicationDate":"2025-09-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145266476","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":"Tuning and miniaturization of active vibration controllers of a fixed-wing composite aircraft drone using the experiment-on-the-loop system","authors":"Tarcisio M.P. Silva ,&nbsp;Giulio Franchini ,&nbsp;Prabakaran Balasubramanian ,&nbsp;Abdulaziz Buabdulla ,&nbsp;Sudhir Kumar Singh ,&nbsp;Mohammed AlNuaimi ,&nbsp;Rashed AlHammadi ,&nbsp;Marco Amabili","doi":"10.1016/j.ast.2025.111004","DOIUrl":"10.1016/j.ast.2025.111004","url":null,"abstract":"<div><div>Active vibration control (AVC) in Unmanned Air Vehicles (UAV) enhances flight stability, enables lighter and more efficient designs, and improves fuel efficiency and payload capacity. However, AVC systems require careful design, and this study demonstrates how they can be efficiently tuned on a fixed-wing, composite aircraft drone using a purely experimental approach, leveraging the newly developed Experiment-in-the-Loop (EITL) method. The EITL is a real-time optimizer, capable of autonomously running hundreds or thousands of experimental tests on a target structure. In each test, the EITL iteratively refines the control parameters, progressively improving their performance. The EITL offers the advantage of being fast, tuning the controllers within hours, and not relying on numerical models. In this paper, 9 AVC systems are tuned, including four Positive Position Feedback (PPFs) controllers and five higher-order controllers. Experimental results show that these controllers reduce vibrations on the composite aircraft drone by an average of 55 % over 7 resonant modes in the frequency range from 0 to 250 Hz. In addition, results show how AVC systems can be practically implemented using lightweight hardware. The developed scaled-down AVC system weighs 183.8 g and occupies 273.5 cm³, making it a promising solution for onboard UAV applications.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111004"},"PeriodicalIF":5.8,"publicationDate":"2025-09-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145266516","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":"Adaptive mask physics-driven neural network for complex flow field prediction using self-supervised learning","authors":"Zekai Lu ,&nbsp;Bingfeng Qian ,&nbsp;Mingming Guo ,&nbsp;Ming Yang ,&nbsp;Lei Zhang","doi":"10.1016/j.ast.2025.110966","DOIUrl":"10.1016/j.ast.2025.110966","url":null,"abstract":"<div><div>High-precision complex flow field prediction faces challenges in balancing accuracy, efficiency, and physical consistency. This study proposes an Adaptive coding Multi-airfoil Physics-Driven Neural Network (AMPD-NN) employing variable wall condition processing technology for unified prediction across airfoil families with thickness ratios of 6%-15% and camber variations of 0%-4%. The model uses self-supervised training based on physics conservation equation residual minimization, requiring only boundary conditions and geometric parameters while reducing labeled data dependence. Under subsonic conditions, flow field prediction errors remain within 4% with SSIM of 0.965–0.973. Lift and drag coefficient prediction errors are 2.22%-2.70% and below 5%, respectively. Transonic extrapolation validation shows increased errors of 15–16% but within acceptable ranges. Compared with ANSYS Fluent, the model achieves 78–109 × speedup for single predictions and 2.5–2.7 × improvement for batch processing while eliminating mesh generation, enabling efficient parametric analysis.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110966"},"PeriodicalIF":5.8,"publicationDate":"2025-09-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145219728","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":"An extensive search strategy of UAV swarm based on hybrid ant colony optimization approach under unpredictable environment","authors":"Minghui Yao ,&nbsp;Cong Shi ,&nbsp;Yan Niu ,&nbsp;Qiliang Wu ,&nbsp;Cong Wang","doi":"10.1016/j.ast.2025.110996","DOIUrl":"10.1016/j.ast.2025.110996","url":null,"abstract":"<div><div>Large-scale collaborative searching and attacking targets with unknown attributes is an important military application scenario for multiple Unmanned Aerial Vehicles (UAV) swarms. This paper mainly focuses on the mission allocation problem of UAV formations in an uncertain search environment. In this paper, a hybrid swarm intelligence approach, called improved ant colony optimization and semi-artificial potential field (IACO-SAPF), is introduced. The IACO-SAPF algorithm enhances the pheromone update method and state transition mechanism based on the ACO method. Then, local pheromone update mechanism is improved by introducing the concept of the SAPF method to maintain the UAV flying at a safe distance from the obstacle under uncertain environment. In addition, in order to successfully destroy the target with dynamic characteristics or defensive attributes, we introduce an encirclement attack (EA) algorithm into the IACO-SAPF approach to encircle and attack the target in specific formations. Finally, as compared to the other four methods, simulation results show that the IACO-SAPF algorithm demonstrates superior robustness against wind and communication interference. Furthermore, the UAV swarm could successfully encircle and attack the target with dynamic or defensive features in complicated battlefield environment.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110996"},"PeriodicalIF":5.8,"publicationDate":"2025-09-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145219814","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":"Spray characteristics of a liquid jet of kerosene in a parallel back-facing step cavity in high-temperature supersonic crossflow","authors":"Jiang Chuanjin ,&nbsp;Yuan Jiazhou ,&nbsp;Wang Peng ,&nbsp;Bao Heng ,&nbsp;Tian Liang ,&nbsp;Zhong Zhan ,&nbsp;Nie Wansheng ,&nbsp;Tong Yiheng","doi":"10.1016/j.ast.2025.110989","DOIUrl":"10.1016/j.ast.2025.110989","url":null,"abstract":"<div><div>The atomization characteristics of kerosene fuel in a parallel back-facing step cavity combustor under high-enthalpy supersonic crossflow were experimentally investigated in this work. High-speed photography and schlieren methods were employed to study the effects of the combustor configuration on the penetration depth, spray survival distance, and cavity spray factor. The study reveals that the streamwise pressure gradient formed by the expansion fan significantly suppresses the oscillation of the upper boundary of the jet. Compression waves and reflected shocks significantly increase the penetration depth of the jet, with the maximum increase reaching 80 %. Additionally, these waves can reduce the survival distance of the liquid jet by up to 30 %. When the shock wave impinges on the bow shock wave generated by the jet, the jet becomes unstable, and large-amplitude oscillations occur. Additionally, a separation zone exists upstream of the jet, where a significant number of droplets accumulate. Jet oscillation results from three types of shock/shock interactions in front of the jet. The oscillation of the spray factor is caused by the cavity’s self-pulsation and is related to the shear layer’s impact on the cavity’s trailing edge. The fuel distribution in the mainstream region is not strongly correlated with that inside the cavity.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110989"},"PeriodicalIF":5.8,"publicationDate":"2025-09-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145265918","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 Locally enhanced physics-informed neural network surrogate model for rapid aerothermal assessment of aero-engine nozzles","authors":"Tiange Ma,&nbsp;Xi Xi,&nbsp;Chuanqi Zhao,&nbsp;Yang Xu,&nbsp;Huiying Zhang,&nbsp;Hong Liu","doi":"10.1016/j.ast.2025.111002","DOIUrl":"10.1016/j.ast.2025.111002","url":null,"abstract":"<div><div>A novel deep learning surrogate model based on a Locally Enhanced Physics-Informed Neural Network (LE-PINNs) is proposed to address the challenge of rapid and accurate prediction of aerothermal and aerodynamic performance for aero-engine exhaust nozzles under varying operating conditions. The model takes geometric information and inflow boundary conditions as inputs, outputting flow field variables (density, pressure, temperature, etc.). The core innovation lies in its unique dual-network collaborative prediction framework: the global network, constrained by the Reynolds-Averaged Navier-Stokes (RANS) equations, captures primary flow field characteristics, while the boundary network specializes in high-precision modeling of pressure and temperature distributions near the nozzle walls. The model was trained and validated using a high-fidelity dataset generated by high-precision CFD simulations, covering a range of nozzle pressure ratios (NPR) from 4.0 to 14.5 and corresponding variations in the expansion area ratio (AR).</div><div>Test results demonstrate that, LE-PINNs exhibits superior prediction accuracy across the entire flow field, particularly near the walls, achieving an average relative error in wall temperature predictions below 1 %, significantly outperforming than Fully Connected Neural Networks (FCNN) and standard Physics-Informed Neural Networks (PINNs) models. In predicting key parameters at the nozzle outlet (temperature, velocity, thrust, etc.), LE-PINNs maintains deviations below 1 % compared to CFD results, accurately capturing shock wave structures and their intensities. Furthermore, its prediction efficiency is approximately 360 times faster than traditional CFD methods for single-case inference within the trained parameter range (NPR from 4.0 to 14.5 and AR from 1.22 to 2.39).</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111002"},"PeriodicalIF":5.8,"publicationDate":"2025-09-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145219963","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}