Aerospace Science and Technology最新文献

{"title":"Deep reconstruction of schlieren images for scramjet combustion flow field analysis using FCSD-net with feature completion strategy","authors":"Linjing Li ,&nbsp;Ye Tian ,&nbsp;Xue Deng ,&nbsp;Hua Zhang ,&nbsp;Maotao Yang ,&nbsp;Mengqi Xu ,&nbsp;Jingrun Wu","doi":"10.1016/j.ast.2025.110371","DOIUrl":"10.1016/j.ast.2025.110371","url":null,"abstract":"<div><div>Reconstructing schlieren images of flow fields using wall pressure measurements is widely regarded as an effective technique for monitoring the state of flow fields in scramjet engines. However, this reconstruction process can be significantly affected by wave system changes resulting from flow field oscillations and boundary layer interference. To tackle this issue, we introduce a dual-branch network structure based on a feature completion strategy, known as FCSD-Net. FCSD-Net integrates a transformer-based primary branch with a convolutional neural network-based auxiliary branch to capture multi-dimensional semantic features. Additionally, a fourth-order feature fusion module is designed to effectively combine global features. Experimental results indicate that FCSD-Net can efficiently reconstruct schlieren images. This method achieves improvements of 5.54 % in SSIM, 3.02 dB in PSNR, and 2.4 % in P-corr compared to leading neural network models. The proposed approach accurately reconstructs wave system structures and turbulence in supersonic flow fields, providing a solid data foundation for analyzing flow field stability in combustion.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"164 ","pages":"Article 110371"},"PeriodicalIF":5.0,"publicationDate":"2025-05-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144168138","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 boundary integral formulation for predicting acoustic waves generated by large deformations of bodies","authors":"Massimo Gennaretti,&nbsp;Beatrice De Rubeis","doi":"10.1016/j.ast.2025.110354","DOIUrl":"10.1016/j.ast.2025.110354","url":null,"abstract":"<div><div>This paper presents the application and assessment of a recently introduced boundary integral formulation for solving wave equations in domains bounded by porous or solid surfaces undergoing large deformations. Specifically, it is applied to predict acoustic waves generated by large-amplitude pulsations of a sphere immersed in an unbounded, quiescent, inviscid perfect gas. Fluid perturbations are expressed in terms of the velocity potential. The focus is on the assessment of the capability of the integral formulation to capture the effects induced by significant boundary deformations. To isolate these effects, fluid nonlinearities are neglected, as their contributions are given by field volume terms and fall outside the scope of this study. The numerical application of the boundary integral formulation is accomplished by a zero-th order boundary element method, complemented by a novel harmonic-balance approach for time integration. This innovative approach provides an efficient and robust solution method for handling periodic perturbation propagation phenomena. For a wide range of amplitudes and frequencies of sphere oscillation, the deformable-boundary integral formulation solving the linear wave equation for the velocity potential is validated against analytical linear solutions. In the case of large-amplitude, high-frequency pulsations the analytical solution, not available in the literature, is derived in this work under subsonic surface speed conditions. Numerical results highlight the multi-harmonic nature of the radiated acoustic field and provide an analysis of the boundary contributions associated with surface dynamic deformation. Successful applications to porous deforming spherical and wing-like shaped boundaries are also presented for the sake of completeness.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"164 ","pages":"Article 110354"},"PeriodicalIF":5.0,"publicationDate":"2025-05-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144168139","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 vortex dynamics control in the delta wing using dual synthetic jets","authors":"Hao Wang,&nbsp;Zhenbing Luo,&nbsp;Xiong Deng,&nbsp;Yi Deng","doi":"10.1016/j.ast.2025.110369","DOIUrl":"10.1016/j.ast.2025.110369","url":null,"abstract":"<div><div>By implementing dual synthetic jets (DSJ) control on a slender delta wing, the leading-edge vortex (LEV) is effectively managed, resulting in substantial modifications to the flow field structure on the upper surface. The co-rotating acceleration generated by the DSJ significantly retracts the LEV and reduces its rotational radius. This process also leads to a significant optimization of the flow topology in the breakdown region of the baseline flow, effectively eliminating unstable spiral points. Furthermore, the axial velocity of the vortex is modified, delaying the breakdown point and extending the high-speed flow path by 22 % of the chord length. Despite the high-frequency, periodic nature of the DSJ, the vortex axis position remains stable, with minimal fluctuations, ensuring overall vortex stability. Additionally, the frequency characteristics of the vortex core are improved, exhibiting a shift toward higher frequencies.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"164 ","pages":"Article 110369"},"PeriodicalIF":5.0,"publicationDate":"2025-05-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144168137","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":"Replicated clock on an unmanned aerial vehicle with picosecond-level precision","authors":"Xueyi Tang ,&nbsp;Haiyuan Sun ,&nbsp;Chenhao Yan ,&nbsp;Lijiaoyue Meng ,&nbsp;Yibin He ,&nbsp;Rui Liu ,&nbsp;Shiguang Wang ,&nbsp;Lijun Wang","doi":"10.1016/j.ast.2025.110362","DOIUrl":"10.1016/j.ast.2025.110362","url":null,"abstract":"<div><div>Unmanned aerial vehicles (UAVs) are increasingly employed in various fields owing to their mobility and cost-effectiveness. High-precision applications, such as communications, remote sensing, formation flight, and cooperative localization, require accurate onboard frequency standards and reliable time–frequency synchronization. Conventional approaches utilizing temperature-compensated or oven-controlled crystal oscillators (TCXO or OCXO) and chip-scale atomic clocks (CSAC) are limited by insufficient precision and stability. While optical frequency synchronization achieves femtosecond-level precision, its complexity, high power requirements, and environmental constraints make it unsuitable for UAVs. Similarly, global navigation satellite system (GNSS)-based synchronization is vulnerable to interference, further limiting its effectiveness. This study proposes a novel method for replicating ground-based atomic frequency standards on UAVs using transponders and active carrier-phase compensation. The proposed approach equips UAVs with simple radio frequency (RF) transponder structures to achieve picosecond-level precision in onboard clocks. Experimental validation on a tethered UAV demonstrated frequency stability of 2.68E-12 at 1 s, 6.78E-15 at 1000 s, and a clock phase stability of 6.66 ps at 2000 s, indicating that the proposed method significantly outperforms conventional crystal oscillators by several orders of magnitude. The findings highlight the efficacy of this method in achieving high-precision frequency synchronization for UAVs, enhancing communication reliability and supporting advanced scientific and technological applications. This approach also paves the way for integrated time–frequency synchronization networks spanning air, space, and ground domains.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"164 ","pages":"Article 110362"},"PeriodicalIF":5.0,"publicationDate":"2025-05-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144168136","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":"Scale effect on the hypersonic inlet under fluid-thermal-structure interaction","authors":"Binhao Li,&nbsp;Chenglong Wang,&nbsp;Mingbo Sun,&nbsp;Yu Yuan,&nbsp;Zhenguo Wang","doi":"10.1016/j.ast.2025.110361","DOIUrl":"10.1016/j.ast.2025.110361","url":null,"abstract":"<div><div>Hypersonic inlet is exposed to severe aerodynamic force/heat loads, the impacts caused by the Fluid-Thermal-Structure Interaction (FTSI) are crucial. This paper proposes a three-dimensional FTSI framework and studies the FTSI effects of inlet. Subsequently, the mechanism of FTSI is elaborated, and the scale effect on hypersonic inlet is analyzed. Research shows that the traditional design of thermal-protection materials on the forebody and the lip cannot meet the long-endurance flight requirements. FTSI will cause a sharp increase in the temperature at the inlet shoulder and the position of the first reflected shock wave in the isolator, which is prone to lead structural failure. Lift of forebody, pressing down of lip and inlet shoulder lead to the increasing of mass flow coefficient by approximately 10 % and the decreasing of total pressure recovery coefficient by about 7 %. Scale effect on inlet under FTSI is revealed. Small-scale inlet is likely to be unstart state under FTSI. Absolute thickness of structure and the boundary layer of the small-scale inlet is thinner, resulting in a more uniform and faster temperature rise of the structure, which leads to smaller y direction deformation of the small-scale inlet. Although the effect of the increasing wall temperature and the decrease in y direction deformation are opposite on the forward movement of the shock wave, FTSI makes the forward movement rate of the shock wave slightly larger in the small-scale isolator.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110361"},"PeriodicalIF":5.0,"publicationDate":"2025-05-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169218","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 of the buzz phenomenon in a supersonic inlet with and without the bleed","authors":"Javad Sepahi-Younsi","doi":"10.1016/j.ast.2025.110346","DOIUrl":"10.1016/j.ast.2025.110346","url":null,"abstract":"<div><div>The primary aim of this study is to investigate the buzz phenomenon and its onset mechanism in a supersonic air inlet by analyzing wind tunnel test data. The inlet under examination is an axisymmetric and mixed-compression inlet designed for a Mach number of 2. To examine the effects of boundary layer suction on changing the mechanism and characteristics of the buzz phenomenon, applying the slot and porous suctions has also been investigated. The results show that the inlet without the bleed has no little buzz, and the buzz starts as the big buzz according to Dailey's criterion. With the application of the boundary layer suction method, the buzz oscillations are not only significantly delayed, but the buzz type also changes to the little buzz according to the Ferri criterion. A comparison of slot and porous bleeds shows that the slot bleed performs better in both delaying the buzz phenomenon and reducing the amplitude of oscillations.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110346"},"PeriodicalIF":5.0,"publicationDate":"2025-05-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144124967","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 hybrid algorithm of TCN-iTransformer for aircraft aerodynamic parameter estimation based on dual attention mechanism","authors":"Tongyue Li,&nbsp;Haiqing Si,&nbsp;Jingxuan Qiu,&nbsp;Jiayi Li,&nbsp;Yiqian Gong","doi":"10.1016/j.ast.2025.110350","DOIUrl":"10.1016/j.ast.2025.110350","url":null,"abstract":"<div><div>Based on the dual attention mechanism, the paper proposes a new hybrid algorithm of TCN-iTransformer for aircraft aerodynamic parameter estimation. This algorithm adopts a new iTransformer architecture, which applies Self-Attention and Feed-Forward Neural Network (FFNN) in inverted dimensions, and enhances the feature extraction by the prepositive placing an improved Temporal Convolutional Network (TCN) based on the Frequency-Enhanced Channel Attention Mechanism (FECAM). To effectively suppress the noise in flight data, the result of Variational Mode Decomposition (VMD) based on the rime optimization algorithm (RIME) is used as the supplementary input for TCN-iTransformer. To verify the effectiveness of this algorithm, the paper applies the flight test data of a typical propeller aircraft to train and validate the model. It conducts a comparative analysis of its estimation effect with that of Transformer and Long Short-Term Memory (LSTM) under the same circumstances. Results show that the proposed new hybrid algorithm is practical and effective, which performs well in terms of both efficiency and accuracy. To further demonstrate its superiority and necessity, comparisons with the SOTA and ablation studies were conducted, which validated its optimal performance and the necessity of its proposal.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"164 ","pages":"Article 110350"},"PeriodicalIF":5.0,"publicationDate":"2025-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144168135","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":"High-fidelity simulation of angled liquid jet breakup in supersonic crossflow","authors":"Dong-Gyu Yun ,&nbsp;Young-Lin Yoo ,&nbsp;Hong-Gye Sung","doi":"10.1016/j.ast.2025.110328","DOIUrl":"10.1016/j.ast.2025.110328","url":null,"abstract":"<div><div>The liquid break-up in supersonic crossflow is primarily encountered in scramjet engines. An angled liquid jet injector can be considered an effective way to enhance liquid breakup and atomization, which is particularly convenient to implement and requires no additional work. The process of liquid fuel breakup, atomization and mixing of fuel involves multiple complex phenomena that are closely interconnected. This study aims to provide a comprehensive analysis of the processes of ligament and droplet breakup and atomization in an angled jet in supersonic crossflow using the homogeneous mixture model and large eddy simulation. Without assuming an ad hoc initial droplet distribution from the injector, the entire breakup process from the primary liquid column breakup to the secondary breakup is thoroughly investigated throughout the entire flow field. The complex structures, such as shockwaves, horseshoe vortex, counter-rotating vortex pair and liquid column surface instabilities such as KH and RT unstable waves, around the liquid column are observed. Key physical and engineering information, such as surface wavelength, breakup length, spray spread angle, droplet size distribution, and pressure loss, is characterized for different injection angles, including acute, perpendicular, and obtuse angles relative to the crossflow. After comparing the numerical results with experimental data, a formula for the angled liquid jet is proposed. The spray distribution in the shape of a <span><math><mstyle><mi>Ω</mi></mstyle></math></span> is confirmed through secondary breakup, and Sauter mean diameter distribution at specific locations is compared. Additionally, the droplet distribution is analyzed using both a histogram and a Rossin-Rammler distribution.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110328"},"PeriodicalIF":5.0,"publicationDate":"2025-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144117113","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 flow field prediction for a subsonic three-stage compressor under a design condition based on dissipation weighting analysis","authors":"Haodong Lei,&nbsp;Xiaoxu Kan,&nbsp;Minghao Yuan,&nbsp;Wanyang Wu,&nbsp;Jingjun Zhong","doi":"10.1016/j.ast.2025.110341","DOIUrl":"10.1016/j.ast.2025.110341","url":null,"abstract":"<div><div>The flow field in a multistage compressor is complex and the loss evolution mechanism of each stage requires further study. A subsonic three-stage compressor designed by the authors’ team was used as the research object. The applicability of the total pressure loss weighting analysis method based on a vortex structure in a stage environment was discussed, and then, the operability of a dissipation weighting processing method based on <em>Ω–V</em>_db extraction was discussed. This method has wider applicability and provides more accurate extraction data. The evolution law of the flow loss of the rotor and stator blades at all stages of the compressor under the design conditions was studied. Further, the complete three-stage dissipation weighting was extracted using this method, and the dissipation of the rotor in the first and second stages, from the shroud dissipation property as the dominant factor, to the profile dissipation property as the dominant factor (27.3 %, 32.57 %), was analyzed. The results indicate that dissipation migration (32.11 %, 49.13 %) of the suction side of the first- and second-stage stator blades is the main development law of the design condition. Finally, the flow field of the compressor from the design point to the near-stall condition is accurately predicted, and a flow-field optimization strategy for the design point is provided.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110341"},"PeriodicalIF":5.0,"publicationDate":"2025-05-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144139717","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Numerical study on the control of flow in the rudder-body junction region using High-energy jet array","authors":"Yi Zhou,&nbsp;Zhenbing Luo,&nbsp;Qiang Liu,&nbsp;Yan Zhou,&nbsp;Wei Xie","doi":"10.1016/j.ast.2025.110335","DOIUrl":"10.1016/j.ast.2025.110335","url":null,"abstract":"<div><div>The maneuverability of high-speed aircrafts in flight needs to be improved. However, conventional control methods for rudder deflection have disadvantages such as poor control effect and low control efficiency. In this paper, the ability of using high energy jet arrays to change the structure of the rudder plate flow field and enhance the control efficiency of the rudder is numerically simulated and analyzed. The high-energy jet arrays are arranged along the flow direction on the windward side of the rudder, which are the upstream high-energy jet array, the midstream high-energy jet array, and the downstream high-energy jet array. The control effects of three position high energy jet arrays were compared and analyzed. The results show that the vortex pair behind the upstream high-energy jet array is fully developed due to its proximity to the leading edge of the rudder, resulting in an increase in the area of the low-pressure region behind the exit of the jet, and that the pressure on the rudder varies significantly with time. The high energy jet arrays in the midstream and downstream do not cause significant periodic changes in the pressure on the windward side of the rudder, while the position close to the downstream allows the two controls to raise the area of the high-pressure region on the windward side of the rudder more and reduce the area of the low-pressure region caused by the vortex pair behind the jet. But with high-energy jet array control, jets close to the area of the plate create additional side forces on the surface of the plate. In this study, numerical simulations were used to analyze the effect of applying high-energy jet arrays in different flow direction positions to improve the effectiveness of high-speed aircraft rudders. In this paper, a new concept of using active flow control method to improve the control efficiency of high-speed aircrafts is proposed. These findings can provide a reference for future research on rudder efficiency of high-speed aircraft.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110335"},"PeriodicalIF":5.0,"publicationDate":"2025-05-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144125294","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}