Pub Date : 2026-07-01Epub Date: 2026-02-03DOI: 10.1016/j.ast.2026.111834
Shibin Luo, Shengxian Zheng, Jun Liu, Rui Liu, Daliang Yang
The double-swept waverider maintains excellent aerodynamic performance at high speeds while enhancing low-speed characteristics through vortex-lift effects, offering a promising approach for extending waverider applications across wide flight envelopes. However, existing research on this configuration has predominantly focused on basic aerodynamic features, with limited attention given to stability and controllability. To address this gap, a double-swept waverider with integrated control surfaces was designed using the projection method. And its lift-to-drag characteristics, static stability, and controllability across multiple speed regimes were systematically analyzed. Results indicate that the configuration consistently maintains static stability in both longitudinal and directional, whereas lateral static stability remains relatively weak. Longitudinal and directional control performance proves superior in subsonic conditions compared to supersonic and hypersonic regimes, while lateral controllability improves significantly under hypersonic conditions. Moreover, rudder deflection exerts minimal influence on pitch and roll channels, whereas differential elevon deflection induces significant pitch/yaw coupling effects.
{"title":"Static stability and control characteristics of the double-swept waveriders","authors":"Shibin Luo, Shengxian Zheng, Jun Liu, Rui Liu, Daliang Yang","doi":"10.1016/j.ast.2026.111834","DOIUrl":"10.1016/j.ast.2026.111834","url":null,"abstract":"<div><div>The double-swept waverider maintains excellent aerodynamic performance at high speeds while enhancing low-speed characteristics through vortex-lift effects, offering a promising approach for extending waverider applications across wide flight envelopes. However, existing research on this configuration has predominantly focused on basic aerodynamic features, with limited attention given to stability and controllability. To address this gap, a double-swept waverider with integrated control surfaces was designed using the projection method. And its lift-to-drag characteristics, static stability, and controllability across multiple speed regimes were systematically analyzed. Results indicate that the configuration consistently maintains static stability in both longitudinal and directional, whereas lateral static stability remains relatively weak. Longitudinal and directional control performance proves superior in subsonic conditions compared to supersonic and hypersonic regimes, while lateral controllability improves significantly under hypersonic conditions. Moreover, rudder deflection exerts minimal influence on pitch and roll channels, whereas differential elevon deflection induces significant pitch/yaw coupling effects.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111834"},"PeriodicalIF":5.8,"publicationDate":"2026-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146109796","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}
Pub Date : 2026-07-01Epub Date: 2026-02-10DOI: 10.1016/j.ast.2026.111889
Yongkang Zhao , Guangfeng An , Xianjun Yu , Baojie Liu , Dongbo Hao , Xi Nan
Next-generation variable-cycle engines impose stringent requirements on the operating range of compressor systems in terms of mass flow rate and pressure ratio. Variable stators provide an effective means to meet these requirements; however, rapidly and accurately determining the operating domain of multistage compressors with variable stators remains a major challenge. To address this issue, this paper proposes an efficient framework for extracting the operating domain of such compressors. First, an improved one-dimensional performance calculation strategy is developed, which preserves design-point accuracy while significantly enhancing prediction accuracy over a wide stator-angle adjustment range, reducing characteristic prediction errors by more than 50 %. Second, the determination of the operating domain is reformulated as the computation of an envelope surface enclosing performance scatter points across the full adjustment range, which simplifies data handling and facilitates the identification of operating-limit boundaries. Third, a rapid solution strategy for the operating domain is introduced, substantially reducing the computational cost. For a four-stage variable-stator compressor, the required computational effort is reduced to 6.8 % of the original cost, with the reduction becoming more pronounced as the number of adjustable stages increases. Throughout the entire operating domain, the efficiency prediction error remains below 10⁻⁶. The proposed method enables fast and accurate determination of the operating domain of multistage compressors with variable stators and provides an effective tool for operating-range analysis in variable-cycle engine applications.
{"title":"A fast method for determining the operating domain of multistage compressors with variable stators","authors":"Yongkang Zhao , Guangfeng An , Xianjun Yu , Baojie Liu , Dongbo Hao , Xi Nan","doi":"10.1016/j.ast.2026.111889","DOIUrl":"10.1016/j.ast.2026.111889","url":null,"abstract":"<div><div>Next-generation variable-cycle engines impose stringent requirements on the operating range of compressor systems in terms of mass flow rate and pressure ratio. Variable stators provide an effective means to meet these requirements; however, rapidly and accurately determining the operating domain of multistage compressors with variable stators remains a major challenge. To address this issue, this paper proposes an efficient framework for extracting the operating domain of such compressors. First, an improved one-dimensional performance calculation strategy is developed, which preserves design-point accuracy while significantly enhancing prediction accuracy over a wide stator-angle adjustment range, reducing characteristic prediction errors by more than 50 %. Second, the determination of the operating domain is reformulated as the computation of an envelope surface enclosing performance scatter points across the full adjustment range, which simplifies data handling and facilitates the identification of operating-limit boundaries. Third, a rapid solution strategy for the operating domain is introduced, substantially reducing the computational cost. For a four-stage variable-stator compressor, the required computational effort is reduced to 6.8 % of the original cost, with the reduction becoming more pronounced as the number of adjustable stages increases. Throughout the entire operating domain, the efficiency prediction error remains below 10⁻⁶. The proposed method enables fast and accurate determination of the operating domain of multistage compressors with variable stators and provides an effective tool for operating-range analysis in variable-cycle engine applications.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111889"},"PeriodicalIF":5.8,"publicationDate":"2026-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146153024","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}
Pub Date : 2026-07-01Epub Date: 2026-02-08DOI: 10.1016/j.ast.2026.111877
Yijing An , Huajie Xiong , Zengpei Liu , Yuxuan Gao , Zhihong Zhou
Timing control of electro-thermal anti-icing systems for aircraft and aero-engines often rely on empirical methods, leading to excessive energy consumption or insufficient heating that compromises flight safety. This study identifies stagnation point temperature as the key parameter for analysis and investigates the effects of environmental temperature, velocity, liquid water content (LWC), and medium volume diameter (MVD) on anti-icing performance. Quantitative relationships between these parameters and the timing control of anti-icing are derived. Additionally, the study explores the coupled effects of these parameters, introducing the icing influence factor , as a novel metric. A multiphysics-coupled simulation method was developed through secondary development in CFD, integrating airflow, droplet impingement, and transient heat conduction models. The accuracy of this numerical approach was validated by comparison with icing wind tunnel experiments. A mathematical model linking this factor to the timing control process is established, offering valuable insights that can inform design and optimization of electro-thermal anti-icing systems.
{"title":"Effects of icing and flight factors on surface temperature and heating time on composite electrothermal protection system","authors":"Yijing An , Huajie Xiong , Zengpei Liu , Yuxuan Gao , Zhihong Zhou","doi":"10.1016/j.ast.2026.111877","DOIUrl":"10.1016/j.ast.2026.111877","url":null,"abstract":"<div><div>Timing control of electro-thermal anti-icing systems for aircraft and aero-engines often rely on empirical methods, leading to excessive energy consumption or insufficient heating that compromises flight safety. This study identifies stagnation point temperature as the key parameter for analysis and investigates the effects of environmental temperature, velocity, liquid water content (LWC), and medium volume diameter (MVD) on anti-icing performance. Quantitative relationships between these parameters and the timing control of anti-icing are derived. Additionally, the study explores the coupled effects of these parameters, introducing the icing influence factor <span><math><msub><mi>α</mi><mi>E</mi></msub></math></span>, as a novel metric. A multiphysics-coupled simulation method was developed through secondary development in CFD, integrating airflow, droplet impingement, and transient heat conduction models. The accuracy of this numerical approach was validated by comparison with icing wind tunnel experiments. A mathematical model linking this factor to the timing control process is established, offering valuable insights that can inform design and optimization of electro-thermal anti-icing systems.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111877"},"PeriodicalIF":5.8,"publicationDate":"2026-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146138313","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}
Pub Date : 2026-07-01Epub Date: 2026-02-04DOI: 10.1016/j.ast.2026.111826
Ahmet Karaca, Ömer Onur
This study presents a methodology for reducing the number of critical load cases used in aircraft structural analysis through set theoretic optimization. The analysis begins with a high-dimensional dataset of millions of flight conditions with associated static six degrees of freedom (6-DOF) load responses across multiple monitoring stations. Critical load cases are first identified using traditional extrema selection methods. Each selected case is then expanded into a group by collecting nearby flight conditions according to a defined similarity threshold. To obtain the smallest set of representative load cases that collectively span all groups, the problem is formulated as a Set Cover optimization and solved using Integer Linear Programming (ILP), which guarantees the optimal solution. The proposed approach reduces the total number of load cases required for structural sizing, thereby decreasing the computational effort while ensuring full coverage of all critical scenarios through an exact and rigorous mathematical formulation.
{"title":"A Set Theoretic approach for reducing critical load cases in aircraft structural design","authors":"Ahmet Karaca, Ömer Onur","doi":"10.1016/j.ast.2026.111826","DOIUrl":"10.1016/j.ast.2026.111826","url":null,"abstract":"<div><div>This study presents a methodology for reducing the number of critical load cases used in aircraft structural analysis through set theoretic optimization. The analysis begins with a high-dimensional dataset of millions of flight conditions with associated static six degrees of freedom (6-DOF) load responses across multiple monitoring stations. Critical load cases are first identified using traditional extrema selection methods. Each selected case is then expanded into a group by collecting nearby flight conditions according to a defined similarity threshold. To obtain the smallest set of representative load cases that collectively span all groups, the problem is formulated as a Set Cover optimization and solved using Integer Linear Programming (ILP), which guarantees the optimal solution. The proposed approach reduces the total number of load cases required for structural sizing, thereby decreasing the computational effort while ensuring full coverage of all critical scenarios through an exact and rigorous mathematical formulation.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111826"},"PeriodicalIF":5.8,"publicationDate":"2026-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146175374","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}
Pub Date : 2026-07-01Epub Date: 2026-01-23DOI: 10.1016/j.ast.2026.111764
JinZe Wu , HongMeng Li , GuoXiu Li , Shuo Zhang , Dongxu Xue , ZhaoPu Yao , Tao Zhang
Investigating the coupling mechanisms among electric ignition parameters, bubble dynamics, and combustion reaction is of great significance for advancing both the theoretical understanding and engineering applications of electric ignition technology in ammonium dinitramide (ADN)-based liquid propellants. In this study, an integrated combustion diagnostics approach, including high-speed imaging, emission spectroscopy, tunable diode laser absorption spectroscopy, and gas chromatography-mass spectrometry, was employed to systematically explore the fundamental relationships among voltage parameters, multiphase physical processes, combustion characteristics, and the complex chemical reaction network of the propellant. The findings reveal that electric ignition combustion of propellant constitutes a complex process triggered by Joule heating and regulated by voltage, governed primarily by the dynamic competition between resistive heating and bubble suppression. In the low-voltage (< 80 V), energy input aligns with chemical kinetics rates, facilitating decomposition of methanol and ADN to generate highly reactive small molecules. This results in extended ignition delay but complete combustion, characterized by minimal formation of incomplete combustion products such as CO, HCN, and N₂O, as well as short combustion duration and high peak pressure. The optimal voltage window (∼ 80 V) achieves perfect balance between resistive heating and bubble suppression, delivering maximum heating efficiency and reaction stability, with the shortest ignition delay, lowest NH₃ residue, and maximum C₂ hydrocarbon production. In the high-voltage (> 80 V), excessive energy input intensifies bubble dynamics, disrupts heating stability, and promotes the accumulation of fuel and intermediate products. This leads to incomplete carbon oxidation and hindered nitrogen conversion, manifested by increased emissions of CO, N₂O, and CH₄, decreased yields of CO₂, NO, and N₂, and a notable reduction in peak combustion pressure. The findings of this study provide crucial scientific foundations for the customized design and precise control of next-generation green propulsion systems.
{"title":"Insights into combustion characteristics and mechanisms of green liquid propellant under electric ignition","authors":"JinZe Wu , HongMeng Li , GuoXiu Li , Shuo Zhang , Dongxu Xue , ZhaoPu Yao , Tao Zhang","doi":"10.1016/j.ast.2026.111764","DOIUrl":"10.1016/j.ast.2026.111764","url":null,"abstract":"<div><div>Investigating the coupling mechanisms among electric ignition parameters, bubble dynamics, and combustion reaction is of great significance for advancing both the theoretical understanding and engineering applications of electric ignition technology in ammonium dinitramide (ADN)-based liquid propellants. In this study, an integrated combustion diagnostics approach, including high-speed imaging, emission spectroscopy, tunable diode laser absorption spectroscopy, and gas chromatography-mass spectrometry, was employed to systematically explore the fundamental relationships among voltage parameters, multiphase physical processes, combustion characteristics, and the complex chemical reaction network of the propellant. The findings reveal that electric ignition combustion of propellant constitutes a complex process triggered by Joule heating and regulated by voltage, governed primarily by the dynamic competition between resistive heating and bubble suppression. In the low-voltage (< 80 V), energy input aligns with chemical kinetics rates, facilitating decomposition of methanol and ADN to generate highly reactive small molecules. This results in extended ignition delay but complete combustion, characterized by minimal formation of incomplete combustion products such as CO, HCN, and N₂O, as well as short combustion duration and high peak pressure. The optimal voltage window (∼ 80 V) achieves perfect balance between resistive heating and bubble suppression, delivering maximum heating efficiency and reaction stability, with the shortest ignition delay, lowest NH₃ residue, and maximum C₂ hydrocarbon production. In the high-voltage (> 80 V), excessive energy input intensifies bubble dynamics, disrupts heating stability, and promotes the accumulation of fuel and intermediate products. This leads to incomplete carbon oxidation and hindered nitrogen conversion, manifested by increased emissions of CO, N₂O, and CH₄, decreased yields of CO₂, NO, and N₂, and a notable reduction in peak combustion pressure. The findings of this study provide crucial scientific foundations for the customized design and precise control of next-generation green propulsion systems.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111764"},"PeriodicalIF":5.8,"publicationDate":"2026-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146033437","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}
Microwave electrothermal thrusters are a promising type of electric propulsion technology for small satellites, offering advantages in design simplicity, power efficiency, and fuel economy. A key factor determining thruster performance is the efficiency of heat transfer from the plasma to the propellant, which directly influences thrust efficiency and thermal management. While the previous studies have largely focused on experimental evaluations, the underlying physical mechanisms governing thermal behavior within the thruster remain poorly understood. This study addresses the gap by introducing a novel vortex generator technique and systematically investigating the influence of internal flow fields on thermal characteristics. A multi-objective design optimization has been conducted using an evolutionary algorithm coupled with a thermo-fluid model, with the injector geometry parameters treated as the design variables. The optimization has simultaneously minimized local heat losses to the top, side, and bottom walls as well as total heat loss. Additionally, a surrogate-assisted global sensitivity analysis has identified the key design parameters governing thermal behavior and flow structure formation. The results have revealed an optimal flow structure consisting of a cold downward outer flow and a heated upward inner flow, achieving approximately 15 % reduction in total thermal loads compared to conventional reverse vortex techniques. This improvement has been achieved even at low mass flow rates due to enhanced vertical propellant velocities. The analysis has identified the injector’s radial distance from the central axis and vertical injection angle as the most critical design factors directly affecting flow fields, thermal distributions, and overall system efficiency.
{"title":"Optimization of a novel reverse vortex generator for thermal management in microwave electrothermal thrusters via evolutionary algorithms","authors":"Tsubasa Ozawa , Suk Hyun Yeo , Keisuke Suenaga , Hideaki Ogawa","doi":"10.1016/j.ast.2026.111780","DOIUrl":"10.1016/j.ast.2026.111780","url":null,"abstract":"<div><div>Microwave electrothermal thrusters are a promising type of electric propulsion technology for small satellites, offering advantages in design simplicity, power efficiency, and fuel economy. A key factor determining thruster performance is the efficiency of heat transfer from the plasma to the propellant, which directly influences thrust efficiency and thermal management. While the previous studies have largely focused on experimental evaluations, the underlying physical mechanisms governing thermal behavior within the thruster remain poorly understood. This study addresses the gap by introducing a novel vortex generator technique and systematically investigating the influence of internal flow fields on thermal characteristics. A multi-objective design optimization has been conducted using an evolutionary algorithm coupled with a thermo-fluid model, with the injector geometry parameters treated as the design variables. The optimization has simultaneously minimized local heat losses to the top, side, and bottom walls as well as total heat loss. Additionally, a surrogate-assisted global sensitivity analysis has identified the key design parameters governing thermal behavior and flow structure formation. The results have revealed an optimal flow structure consisting of a cold downward outer flow and a heated upward inner flow, achieving approximately 15 % reduction in total thermal loads compared to conventional reverse vortex techniques. This improvement has been achieved even at low mass flow rates due to enhanced vertical propellant velocities. The analysis has identified the injector’s radial distance from the central axis and vertical injection angle as the most critical design factors directly affecting flow fields, thermal distributions, and overall system efficiency.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111780"},"PeriodicalIF":5.8,"publicationDate":"2026-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146095623","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}
Pub Date : 2026-07-01Epub Date: 2026-02-05DOI: 10.1016/j.ast.2026.111864
Zhengjie Liu, Wentao Huang, Yuhan Huang, Yu Zhang
As the core power system of aircraft, the fault prediction and health management of aircraft engines are of great significance in ensuring flight safety and optimizing maintenance strategies. Existing research faces the dual challenges of scarcity of real flight fault data and cross-domain feature differences. At present, most few-shot cross-domain fault diagnosis methods focus on efficient fault feature extraction and model structure optimization, while insufficiently leveraging diagnostic knowledge accumulated in the field over time. A key issue that remains unresolved in few-shot cross-domain fault diagnosis for aero-engine bearings is how to integrate valuable prior knowledge with effective cross-domain feature alignment methods into the diagnostic model. This study introduces a prior knowledge-informed multi-task collaborative learning (PKMTCL) approach. First, a cosine contrastive loss is introduced to implicitly embed prior diagnostic knowledge into the model, thereby reducing its dependence on large training datasets. Then, a novel information entropy-based prototype construction and cross-domain feature alignment strategy for the target domain is designed, effectively alleviating feature shift under varying working conditions. Finally, a multi-task collaborative learning framework is developed, where the inductive bias provided by auxiliary tasks guides the main task to learn more generalizable feature representations, thereby effectively improving the generalization performance of the main task. Experiments on two aero-engine bearing datasets demonstrate that, compared with state-of-the-art methods, the proposed method achieves higher fault identification accuracy and lower volatility in diagnostic results. The related code can be downloaded from https://github.com/LZJHIT/PKMTCL.
{"title":"Prior knowledge-informed multi-task collaborative learning for few-shot fault diagnosis of aero-engines","authors":"Zhengjie Liu, Wentao Huang, Yuhan Huang, Yu Zhang","doi":"10.1016/j.ast.2026.111864","DOIUrl":"10.1016/j.ast.2026.111864","url":null,"abstract":"<div><div>As the core power system of aircraft, the fault prediction and health management of aircraft engines are of great significance in ensuring flight safety and optimizing maintenance strategies. Existing research faces the dual challenges of scarcity of real flight fault data and cross-domain feature differences. At present, most few-shot cross-domain fault diagnosis methods focus on efficient fault feature extraction and model structure optimization, while insufficiently leveraging diagnostic knowledge accumulated in the field over time. A key issue that remains unresolved in few-shot cross-domain fault diagnosis for aero-engine bearings is how to integrate valuable prior knowledge with effective cross-domain feature alignment methods into the diagnostic model. This study introduces a prior knowledge-informed multi-task collaborative learning (PKMTCL) approach. First, a cosine contrastive loss is introduced to implicitly embed prior diagnostic knowledge into the model, thereby reducing its dependence on large training datasets. Then, a novel information entropy-based prototype construction and cross-domain feature alignment strategy for the target domain is designed, effectively alleviating feature shift under varying working conditions. Finally, a multi-task collaborative learning framework is developed, where the inductive bias provided by auxiliary tasks guides the main task to learn more generalizable feature representations, thereby effectively improving the generalization performance of the main task. Experiments on two aero-engine bearing datasets demonstrate that, compared with state-of-the-art methods, the proposed method achieves higher fault identification accuracy and lower volatility in diagnostic results. The related code can be downloaded from <span><span>https://github.com/LZJHIT/PKMTCL</span><svg><path></path></svg></span>.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111864"},"PeriodicalIF":5.8,"publicationDate":"2026-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146135557","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}
Pub Date : 2026-07-01Epub Date: 2026-02-05DOI: 10.1016/j.ast.2026.111859
Xin Liu, Song Ji, Mengmeng Sun, Dazhao Fan, Jiayang Lv, Mingze Suo, Rongrong Zhang, Zhen Yan, Yongjian Li
The exponential growth of remote sensing satellite deployments globally has exacerbated the imbalance between limited satellite-to-ground downlink capacity and the surging requirement for low-latency, mission-critical data transmission. This pressing issue is driving a transformative shift in remote sensing paradigms, transitioning from traditional “passive data collection with ground-based post-processing” to a novel model of “active sensing and real-time on-orbit processing” facilitated by intelligent satellites. However, there remains a significant deficiency in comprehensive surveys that systematically address on-orbit image processing technologies for intelligent remote sensing satellites, particularly those that provide integrative analyses of system architectures, cutting-edge advancements, and illustrative application scenarios. To address this shortfall, this paper systematically reviews research progress in on-orbit image data optimization and enhancement, as well as intelligent interpretation and thematic product generation technologies, from the perspective of the Layered Collaborative On-orbit Image Processing (LCOIP) framework. It elucidates the supporting role of these technologies in disaster response, national defense security, environmental protection, and agricultural remote sensing applications. Key technical challenges are identified. Furthermore, promising future development directions are explored, such as autonomous intelligent on-orbit processing by single satellites and collaborative on-orbit processing by functionally heterogeneous constellations. This aims to provide theoretical references and technical guidance for the development and application of next-generation intelligent remote sensing satellite systems.
{"title":"On-orbit image processing technology for intelligent remote sensing satellites: Progress, challenges, and opportunities","authors":"Xin Liu, Song Ji, Mengmeng Sun, Dazhao Fan, Jiayang Lv, Mingze Suo, Rongrong Zhang, Zhen Yan, Yongjian Li","doi":"10.1016/j.ast.2026.111859","DOIUrl":"10.1016/j.ast.2026.111859","url":null,"abstract":"<div><div>The exponential growth of remote sensing satellite deployments globally has exacerbated the imbalance between limited satellite-to-ground downlink capacity and the surging requirement for low-latency, mission-critical data transmission. This pressing issue is driving a transformative shift in remote sensing paradigms, transitioning from traditional “passive data collection with ground-based post-processing” to a novel model of “active sensing and real-time on-orbit processing” facilitated by intelligent satellites. However, there remains a significant deficiency in comprehensive surveys that systematically address on-orbit image processing technologies for intelligent remote sensing satellites, particularly those that provide integrative analyses of system architectures, cutting-edge advancements, and illustrative application scenarios. To address this shortfall, this paper systematically reviews research progress in on-orbit image data optimization and enhancement, as well as intelligent interpretation and thematic product generation technologies, from the perspective of the Layered Collaborative On-orbit Image Processing (LCOIP) framework. It elucidates the supporting role of these technologies in disaster response, national defense security, environmental protection, and agricultural remote sensing applications. Key technical challenges are identified. Furthermore, promising future development directions are explored, such as autonomous intelligent on-orbit processing by single satellites and collaborative on-orbit processing by functionally heterogeneous constellations. This aims to provide theoretical references and technical guidance for the development and application of next-generation intelligent remote sensing satellite systems.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111859"},"PeriodicalIF":5.8,"publicationDate":"2026-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146135562","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}
Pub Date : 2026-07-01Epub Date: 2026-02-08DOI: 10.1016/j.ast.2026.111878
Yaping Hu , Weiliang Zheng , Chen Wu , Yuxin Fan , Yaxin Du , Haoyu Yuan , Tianyi Zhang , Shuliang Jing
The impingement-film composite anti-icing provides higher heating efficiency and significant application potential for aircraft compared to conventional hot-air anti-icing. While prior studies have focused on stationary components, this study investigates the anti-icing performance of a full-scale rotating spinner via a combined experimental and numerical approach at high rotational speeds. Surface temperature was measured using a calibrated infrared thermal imager, while water film flow and ice evolution were captured with a high-speed camera. The numerical model couples external and internal airflow, heat transfer, surface water film dynamics with phase change, and solid conduction. Results indicate that the surface temperature initially rises slightly and then decreases, peaking near the fourth row of film holes. Predicted surface temperatures agree well with the experimental data within the uncertainty bands, yielding a mean absolute error of 1.5°C. The composite anti-icing mechanism is attributed to the combined effects of internal hot-air impingement heating and an external protective film formed by the ejected hot air, which simultaneously heats the surface and suppresses droplet impingement. Under the studied conditions, the rotating spinner remains fully protected at freestream temperatures slightly above −10°C. At −20°C, a continuous annular runback ice layer forms downstream of the film-hole region, with a maximum thickness of approximately 15 mm. In contrast, a stationary spinner under identical conditions exhibits an average surface temperature about 2.3°C lower, a larger ice accretion area, and a maximum ice thickness of 20 mm.
{"title":"Investigation of impingement-film composite anti-icing on a rotating spinner","authors":"Yaping Hu , Weiliang Zheng , Chen Wu , Yuxin Fan , Yaxin Du , Haoyu Yuan , Tianyi Zhang , Shuliang Jing","doi":"10.1016/j.ast.2026.111878","DOIUrl":"10.1016/j.ast.2026.111878","url":null,"abstract":"<div><div>The impingement-film composite anti-icing provides higher heating efficiency and significant application potential for aircraft compared to conventional hot-air anti-icing. While prior studies have focused on stationary components, this study investigates the anti-icing performance of a full-scale rotating spinner via a combined experimental and numerical approach at high rotational speeds. Surface temperature was measured using a calibrated infrared thermal imager, while water film flow and ice evolution were captured with a high-speed camera. The numerical model couples external and internal airflow, heat transfer, surface water film dynamics with phase change, and solid conduction. Results indicate that the surface temperature initially rises slightly and then decreases, peaking near the fourth row of film holes. Predicted surface temperatures agree well with the experimental data within the uncertainty bands, yielding a mean absolute error of 1.5°C. The composite anti-icing mechanism is attributed to the combined effects of internal hot-air impingement heating and an external protective film formed by the ejected hot air, which simultaneously heats the surface and suppresses droplet impingement. Under the studied conditions, the rotating spinner remains fully protected at freestream temperatures slightly above −10°C. At −20°C, a continuous annular runback ice layer forms downstream of the film-hole region, with a maximum thickness of approximately 15 mm. In contrast, a stationary spinner under identical conditions exhibits an average surface temperature about 2.3°C lower, a larger ice accretion area, and a maximum ice thickness of 20 mm.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111878"},"PeriodicalIF":5.8,"publicationDate":"2026-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146146830","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}
Pub Date : 2026-06-01Epub Date: 2026-02-02DOI: 10.1016/j.ast.2026.111812
Haiwang Li , Yiming Luo , Zhiyu Zhou , Gang Xie , Long Meng , Yuzhu Lou
This study experimentally optimized B-shaped and C-shaped holes on the flat plate and linear cascade models to maximize cooling effectiveness. Adiabatic cooling effectiveness was measured via Pressure-Sensitive Paint experiments, and Response Surface Methodology was used for cooling effectiveness prediction. Additionally, Particle Image Velocimetry experiments were conducted to analyze the flow field. Film holes were arranged on the flat plate and at four streamwise positions of the vane, with a 45° injection angle and no compound angle. Blowing ratios ranged from 0.5 to 2.5 at a density ratio of 1.5. The mainstream Reynolds number based on hole diameter was 10⁴ for flat plate experiments, and 10⁶ based on chord length for cascade experiments. Optimization results further demonstrate the cooling potential of both curved expansion holes. B-shaped holes achieved a maximum effectiveness improvement of 29.6%, while C-shaped holes reached 46.7%. Optimized B-shaped and C-shaped holes suppressed coolant lift-off and achieved full film coverage. The enhanced performance is primarily attributed to the increased spanwise outlet width, which induces jet bifurcation and significantly strengthens lateral coolant spreading via intensified anti-counter-rotating vortex pairs. Optimization effectiveness was highest on the suction side, followed by the flat plate, and lowest on the pressure side. The influence of structural parameters on cooling effectiveness is independent of wall curvature, enabling the application of flat plate optimization results to the vane.
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