Aerospace Science and Technology最新文献

{"title":"Three-dimensional internal flow characteristics of bypass shock-induced thrust vector control","authors":"Xin Chen ,&nbsp;Wenjie Fang ,&nbsp;Zhao Liu ,&nbsp;Kexin Wu ,&nbsp;Hang Li ,&nbsp;Vignesh Ram Petha Sethuraman ,&nbsp;Ajith Kumar. S ,&nbsp;Kunhang Li","doi":"10.1016/j.ast.2025.111015","DOIUrl":"10.1016/j.ast.2025.111015","url":null,"abstract":"<div><div>In the current article, the computational fluid dynamics methodology by solving Reynolds-averaged Navier-Stokes equations is used to investigate the controllability and accuracy of a three-dimensional bypass shock-induced thrust vector control system, featuring an arc-shaped mass flow bypass with an active control function. Several blockage area ratios on the bypass channel have been analyzed to illustrate the control performance of the bypass shock-induced thrust vector nozzle, where they are 0, 0.05, 0.06, 0.3, 0.6, and 0.9, respectively. The computational results indicate that the flow choking in the arc-shaped bypass occurs at both its outlet and bypass throat for various blockage area ratios; furthermore, with an increasing blockage area ratio, the vectoring angle and the bypass mass flow ratio decrease continuously. While the blockage area ratio is constant, both the thrust ratio and specific impulse coefficient rise with the increasing nozzle pressure ratio; however, the deflection angle and thrust efficiency constantly decrease. A smaller nozzle pressure ratio corresponds to a larger vectoring angle. Significant Mach disc forms, as the convergent-divergent nozzle is under severe over-expanded conditions. Both the blockage area ratio and nozzle pressure ratio are fixed, and the bypass mass flow ratio increases linearly with the increase of the bypass width ratio, resulting in a gradual increase in the vectoring angle; meanwhile, the thrust efficiency, thrust ratio, and specific impulse coefficient gradually decrease.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111015"},"PeriodicalIF":5.8,"publicationDate":"2025-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145266477","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":"Vibration control and well-posedness analysis for a flexible spacecraft with pinned-end boundary input","authors":"Xuyang Lou ,&nbsp;Pinren Wang ,&nbsp;Xin Huang ,&nbsp;Yifei Ma","doi":"10.1016/j.ast.2025.110923","DOIUrl":"10.1016/j.ast.2025.110923","url":null,"abstract":"<div><div>This paper addresses the vibration control problem for a spacecraft with flexible appendages and boundary disturbance. The flexible spacecraft is modeled by a partial differential equation combined with boundary conditions. The control objective is to steer the flexible spacecraft to the desired angular position and simultaneously suppress vibrations by only applying control forces at the hub of the flexible spacecraft. To achieve the above objective, this paper proposes a novel boundary controller that acts at the pinned end and utilizes only the signals from the pinned end. With a disturbance observer, the boundary disturbance estimation is achieved. Then, based on operator semigroup, Lyapunov method, and LaSalle’s invariance principle, the well-posedness and asymptotic stability of the closed-loop system are guaranteed. Finally, the effectiveness and superiority of the designed boundary controller are verified through simulations.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110923"},"PeriodicalIF":5.8,"publicationDate":"2025-09-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145265919","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":"Structural damage diagnosis and prognosis with fleet digital twin considering similarity of individual structural features","authors":"Jiaqi Xu ,&nbsp;Dingqiang Dai ,&nbsp;Xuan Zhou ,&nbsp;Marco Giglio ,&nbsp;Claudio Sbarufatti ,&nbsp;Leiting Dong","doi":"10.1016/j.ast.2025.110983","DOIUrl":"10.1016/j.ast.2025.110983","url":null,"abstract":"<div><div>Diagnosis and prognosis of the structural health state based on online monitoring data is crucial for enabling condition-based maintenance and ensuring the safety of aeronautical structures. However, most existing studies focus on structural damage diagnosis and prognosis at the individual level, often overlooking the potential of utilizing fleet-wide data, which requires accurately measuring the similarity between structures and the correlation of damage states across individuals in the fleet. To address this, we propose a novel method for fleet-level structural damage diagnosis and prognosis that leverages the similarity of individual structural features. The method introduces a Physics-Decoded Variational Neural Network, enabling accurate extraction of structural features as well as quantifying damage. Additionally, a copula function is used to model the joint probability distribution of damage states across different structures, based on structural feature similarity metrics. This approach allows for collaborative updating of damage states across the fleet using observations from individual structures during the diagnosis process. Validation on a typical damaged aeronautical panel demonstrates that the proposed method achieves more accurate diagnosis and prognosis of individual structural damage states within a fleet, while reducing uncertainties during service compared to conventional individual-based approaches. This method shows promise for integration into a fleet-level airframe digital twin framework, advancing the implementation of condition-based maintenance across fleets.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110983"},"PeriodicalIF":5.8,"publicationDate":"2025-09-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145266488","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":"Large eddy simulation on the interaction effect of shock waves induced by wall ramps on strut flame","authors":"Zi-jian Zhao,&nbsp;Chao-yang Liu,&nbsp;Wei Huang","doi":"10.1016/j.ast.2025.111008","DOIUrl":"10.1016/j.ast.2025.111008","url":null,"abstract":"<div><div>Struts are a commonly used structure in scramjet engines. Their advantage lies in their ability to serve as both fuel injectors and flame stabilizers under high-speed conditions. In a strut-based combustor, there exist complex shock-wave structures and shock-wave-flame interactions. In this work, wall ramps were placed on the walls of the strut-based combustor to study the impact of oblique shock waves on the strut-jet flame. Three ramp-installation schemes were designed, and three-dimensional transient numerical studies were carried out using large-eddy simulation based on the OpenFOAM platform. The large-scale vortex structures were captured, and the interaction between the oblique shock waves induced by the ramps and the strut-jet flame was analyzed from the perspective of shock wave and vortex interactions. The dimensions of the struts and ramps were customized. The numerical results indicate that the shock waves induced by the ramps can significantly affect the strut-jet flame. Under strong compression, large-scale vortex structures are formed, and the flame mixing layer expands, promoting the mixing of the fuel jet and air, thus enhancing combustion. The stabilization mechanism of the strut-jet flame under the influence of the ramp-induced shock waves was analyzed. Additionally, a mechanism analysis of the flow-blockage phenomenon occurring in the simulation study was conducted. This research contributes to a better understanding of the flow-combustion phenomena occurring within the strut-based combustor, providing a certain theoretical basis and guiding solutions for the design and research of strut-based combustors in scramjet engines.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111008"},"PeriodicalIF":5.8,"publicationDate":"2025-09-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145219810","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":"Parametric study of aeroelastic stability and response of flexible panel in Mach shock reflection","authors":"Yiwen He ,&nbsp;Dongyang Han ,&nbsp;Aiming Shi","doi":"10.1016/j.ast.2025.110968","DOIUrl":"10.1016/j.ast.2025.110968","url":null,"abstract":"<div><div>This paper presents a parametric study of aeroelastic stability and response of a two-dimensional panel in Mach shock reflection, revealing the effects of shock parameters, static pressure differential, and thermal stress. The analytical model of Mach reflection is established based on the three-shock theory, providing an accurate description of the flowfield with the quasi-one-dimensional flow assumption introduced, which enables the aeroelastic model to reflect the impacts of shock angles. The results indicate that the shock impingement location plays a crucial role in the panel aeroelastic performance, determining the instability form of the panel. The flow acceleration of quasi-one-dimensional flow aggravates the divergence instability but has a limited influence on the flutter instability. The increase in shock angle pushes the sonic throat downstream, limiting the acceleration of the flow above the panel, leading to a smaller post-divergence amplitude but a larger post-flutter amplitude. The exertion of static pressure differential aggravates the divergence instability, but suppresses the flutter instability. Similar to the situation in the supersonic flow without shock impingement, the thermal stress excites complicated nonlinear behaviors in the panel response, featured by the chaotic motions. Additionally, the Lyapunov indirect method is found to be inaccurate when evaluating the impacts of shock impingement location on the stability boundary of panel in Mach reflection.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110968"},"PeriodicalIF":5.8,"publicationDate":"2025-09-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145195527","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 on leakage and rotordynamic characteristics of labyrinth seal in rotor-stator disk cavity considering centrifugal and thermal effects","authors":"Xianci Xie ,&nbsp;Dan Sun ,&nbsp;Guozhe Ren ,&nbsp;Huan Zhao ,&nbsp;Zemin Yang ,&nbsp;Yizhen Zhao","doi":"10.1016/j.ast.2025.111009","DOIUrl":"10.1016/j.ast.2025.111009","url":null,"abstract":"<div><div>The leakage and rotordynamic characteristics of labyrinth seals in rotor-stator disk cavities are significantly influenced by their actual working clearance. In this study, the labyrinth seal of a certain aero-engine’s balance piston cavity was investigated. Firstly, a numerical model for fluid-structure-thermal coupling was established to calculate the realistic working clearance of the labyrinth seal under the combined effects of centrifugal and thermal deformations. Then, a multi-frequency elliptical whirl model was developed utilizing unsteady dynamic mesh technology to investigate the leakage and rotordynamic characteristics of the labyrinth seal. The impacts of operational parameters on centrifugal and thermal deformations of the labyrinth disk were analyzed. Furthermore, the influence of clearance variations in the labyrinth disk under actual working conditions on the leakage and rotordynamic characteristics of the seal was systematically investigated. The results show that compared with the design clearance, the sealing clearance is reduced by 34.9% when considering centrifugal and thermal deformations. Under the combined effects of centrifugal and thermal deformations, the leakage of the labyrinth seal decreases. Compared with cases where these factors are not considered, the leakage is reduced by 60.1%. The centrifugal and thermal deformations of the rotor influence the seal’s rotordynamic characteristics. The effective damping increases by 60.3% when considering centrifugal and thermal deformations, consequently improving the stability of the rotor system. The centrifugal and thermal deformations of the rotor augment the phase lag between the peak gas pressure and the maximum clearance within the seal, leading to a greater negative tangential force and enhancing the stability of the rotor system. The integrated fluid-thermal-structural coupling method demonstrates that realistic clearance effects can enhance the predictive accuracy of labyrinth seal rotordynamic characteristics by approximately 60.3%.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111009"},"PeriodicalIF":5.8,"publicationDate":"2025-09-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145265917","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":"Study on the method of avoiding resonance for double-walled single-crystal turbine blades based on crystallographic orientation design: A technique for solving macroscopic vibration problems from a microscopic scale","authors":"Y.C. Zhao ,&nbsp;H. Cheng ,&nbsp;H. Wang ,&nbsp;Y. Zhao ,&nbsp;Y.Z. Fan ,&nbsp;Z.X. Wen ,&nbsp;Z.F. Yue","doi":"10.1016/j.ast.2025.111013","DOIUrl":"10.1016/j.ast.2025.111013","url":null,"abstract":"<div><div>Third-order torsional vibration frequency dispersion and the corresponding resonance issues that occur in the new double-walled single crystal turbine blades present a challenging engineering design issue. Therefore, a breakthrough in the crystallographic orientation design technology is crucial to achieve frequency adjustment and resonance avoidance. In this study, based on the grain microstructure characteristics, the method of defining the crystal orientation deviation angle of single-crystal blades was proposed for the first time, and the decoupling model of the grain microstructure attitude angles was established accordingly. Subsequently, the experiments were conducted to validate the grain-attitude dependent vibration theory and the orientation research methodology. Then, numerical simulation tests of the orientation-dependent vibration characteristics were conducted to investigate the influence rule of the primary orientation deviation angle and quadrant angle, the secondary orientation rotation angle, and the coupled orientation deviation angle on vibration frequency. Finally, the design schemes were developed, and compared in terms of their effectiveness in achieving frequency adjustment and resonance avoidance. The results showed that Case 7 not only considerably reduced the frequency dispersion, but also achieved the safety-margin requirement for resonance. Therefore, the proposed orientation design method is effective in solving macroscale resonance issues from a microscale perspective in single-crystal blades, and is expected to provide support for the engineering design of turbine blades.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111013"},"PeriodicalIF":5.8,"publicationDate":"2025-09-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145219813","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 Validation of a Cross-Over Control Algorithm for Counter-Rotating Multi-Rotor Systems","authors":"Praveen Jawaharlal Ayyanathan ,&nbsp;Ehsan Taheri ,&nbsp;Aditya Vijayaraj ,&nbsp;Vrishank Raghav","doi":"10.1016/j.ast.2025.110997","DOIUrl":"10.1016/j.ast.2025.110997","url":null,"abstract":"<div><div>The region where two counter-rotating propellers cross over each other significantly influences the instantaneous aerodynamics, affecting the noise and vibrations. Implementing a blade cross-over angular position controller can aid in detailed aerodynamic and acoustic studies, enabling performance optimization. This work developed and validated a cross-over angular position control algorithm for mechanically decoupled multi-rotor systems. The algorithm is integrated with an angular speed controller, offering algorithmic simplicity and ease of implementation. The robustness of the proposed algorithm was evaluated by testing the algorithm in counter-rotating side-by-side and co-axial propeller configurations. The controller’s performance was further assessed at two different inter-rotor spacings and across varying speeds corresponding to different aerodynamic interaction regimes. To independently verify the controller’s performance, a post-validation technique was developed using a high-speed camera and image processing techniques to identify the cross-over angular position. Experimental results demonstrate successful cross-over angular position control within <span><math><mrow><mo>±</mo><msup><mn>2</mn><mo>∘</mo></msup></mrow></math></span> at low (600) to high (1875) RPM and <span><math><mrow><mo>±</mo><msup><mn>4</mn><mo>∘</mo></msup></mrow></math></span> at the highest 2000 RPM across all tested configurations and inter-rotor spacing values.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110997"},"PeriodicalIF":5.8,"publicationDate":"2025-09-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145266481","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":"Rotor tip assembly clearance overproof risk estimation method considering machining precision and assembly process uncertainties","authors":"Yingzhi Zhang ,&nbsp;Huibin Sun ,&nbsp;Wanxuan Liu ,&nbsp;Kai Chen ,&nbsp;Cheng Yan","doi":"10.1016/j.ast.2025.111011","DOIUrl":"10.1016/j.ast.2025.111011","url":null,"abstract":"<div><div>Rotor tip assembly clearance (RTAC) is a critical assembly precision index of aero-engines. Accurately evaluating the overproof risk of RTAC has great significance for precision and safety control. However, existing evaluation methods fail to consider the uncertainties inherent in machining precision and assembly process execution. To address this issue, this paper proposes an overproof probability estimation method considering machining precision and assembly process uncertainties. Uncertainties related to RTAC are classified into random variables and interval variables. The independence of overproof conditions is analyzed, and the significance of different overproof behaviors is illustrated. The correlation between overproof limit functions under different behaviors is revealed. According to the mutual exclusivity of overproof conditions, the overproof probability is defined. Then, the RTAC prediction model is divided into three sub-models, and the overproof probability estimation method strategy is proposed. The feasibility of the proposed method is verified through a case study. The results provide more reliable reference for engineers in overproof risk evaluation and decision-making.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111011"},"PeriodicalIF":5.8,"publicationDate":"2025-09-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145219812","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":"Unifying the computational modeling process of a radio-frequency gridded ion thruster","authors":"Woojin Joung ,&nbsp;Hyeondo Cho ,&nbsp;Guentae Doh ,&nbsp;Su-Kyum Kim ,&nbsp;Holak Kim ,&nbsp;Dongho Lee ,&nbsp;Sanghoo Park","doi":"10.1016/j.ast.2025.110994","DOIUrl":"10.1016/j.ast.2025.110994","url":null,"abstract":"<div><div>A gridded ion thruster powered by inductively coupled plasma (ICP), commonly known as a radio-frequency (RF) ion thruster (RIT), offers high specific impulse and efficiency suitable for deep space missions. However, experimental testing of RITs requires large vacuum facilities and costly instruments, leading many preliminary studies to rely on numerical simulations for design and optimization. Sophisticated numerical models can accurately predict ion thruster performances, including plasma characteristics and ion extraction. Nevertheless, prior studies typically treat gas dynamics, plasma discharges, and grid ion optics separately due to disparate spatial and temporal scales. In this study, we present a unified simulation methodology using COMSOL Multiphysics, which models the entire 10-s mN-class RIT system—from propellant injection to thruster performance—in a two-dimensional axisymmetric domain. Naturally, the realistic hole-type grid structure is simplified to a coaxial annular slit-type grid while maintaining key parameters, such as the cross-sectional geometry of each open grid region, the open screen grid area and the beam diameter. To reconcile the simplified geometry with a practical hole-type grid, three correction factors—gas flow correction, ion extraction probability correction, and ion beam divergence angle correction—are introduced. This method enables the investigation of plasma properties, including electron temperatures, densities, and plasma potentials, as well as thruster performance metrics, such as thrust, the mass utilization factor, electrical efficiency, and overall thruster efficiency. The simulation is completed within reasonable time and memory constraints. Simulated results are in good agreement with the previous experimental and numerical studies, demonstrating the validity of the unified simulation approach.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110994"},"PeriodicalIF":5.8,"publicationDate":"2025-09-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145265736","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}