Pub Date : 2026-02-10DOI: 10.1016/j.ast.2026.111847
Jiahui Qiu, Min Zhang, Juan Du, Mehdi Vahdati
{"title":"Effects of combined inlet pressure and temperature distortion on the internal flow of a transonic compressor","authors":"Jiahui Qiu, Min Zhang, Juan Du, Mehdi Vahdati","doi":"10.1016/j.ast.2026.111847","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111847","url":null,"abstract":"","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"7 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146153333","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 : 2026-02-10DOI: 10.1016/j.ast.2026.111892
Z.H. Fu, W. Zhang, Y.F. Zhang
{"title":"A Variable Curvature Deep Shell Model for Nonlinear Vibrations of Twisted Bilayer Graphene Reinforced Titanium Composites","authors":"Z.H. Fu, W. Zhang, Y.F. Zhang","doi":"10.1016/j.ast.2026.111892","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111892","url":null,"abstract":"","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"48 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146153021","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 : 2026-02-10DOI: 10.1016/j.ast.2026.111803
Sai Gowtham Somaroutu, Vijay Gopal
Designing contoured supersonic nozzles for high-speed wind tunnel facilities has traditionally relied on predefined expansion curves and Method of Characteristics (MoC) solutions patched across nozzle regions using curve-fitting techniques. These approaches require numerous sensitive inputs, including a predefined centerline flow distribution, where small inconsistencies can lead to nonphysical contours or poor exit-flow uniformity. This study presents a robust analytical method for designing a broad class of supersonic contoured nozzles using a constrained streamline-tracing approach. The method selects an appropriate streamline from a reference nozzle as the desired wall contour. The reference nozzle is a modified minimum-length configuration with a nonsingular acceleration profile, generated from a continuous MoC solution without patching or interpolation. Streamline selection criteria are formulated to avoid influences of gas centripetal acceleration, strong viscous interactions, sonic-line curvature effects near the throat, and excessive boundary-layer growth near the exit. After selecting the streamline as the inviscid contour, it is corrected for viscous effects using an integral compressible boundary-layer formulation. Numerical simulations were performed for contours designed using the proposed method and Sivells’ technique using the k–ω turbulence model. Test cases include high-Reynolds-number nozzles for Mach 1.8, 2.0, and 2.2, as well as a low-Reynolds-number case for Mach 4.0. An overall performance metric, ϕeff, is introduced to assess exit-flow quality by incorporating effective inviscid core area, flow distortion, and flow angularity. Results show that contours from the proposed method consistently outperform those from Sivells’ approach, with ϕeff values at the theoretical nozzle exit higher by a factor of 1.3–1.58, while retaining simplicity in implementation.
{"title":"A Robust Analytical Method for Designing Supersonic Contoured Nozzles Using Constrained Streamline-Tracing Approach","authors":"Sai Gowtham Somaroutu, Vijay Gopal","doi":"10.1016/j.ast.2026.111803","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111803","url":null,"abstract":"Designing contoured supersonic nozzles for high-speed wind tunnel facilities has traditionally relied on predefined expansion curves and Method of Characteristics (MoC) solutions patched across nozzle regions using curve-fitting techniques. These approaches require numerous sensitive inputs, including a predefined centerline flow distribution, where small inconsistencies can lead to nonphysical contours or poor exit-flow uniformity. This study presents a robust analytical method for designing a broad class of supersonic contoured nozzles using a constrained streamline-tracing approach. The method selects an appropriate streamline from a reference nozzle as the desired wall contour. The reference nozzle is a modified minimum-length configuration with a nonsingular acceleration profile, generated from a continuous MoC solution without patching or interpolation. Streamline selection criteria are formulated to avoid influences of gas centripetal acceleration, strong viscous interactions, sonic-line curvature effects near the throat, and excessive boundary-layer growth near the exit. After selecting the streamline as the inviscid contour, it is corrected for viscous effects using an integral compressible boundary-layer formulation. Numerical simulations were performed for contours designed using the proposed method and Sivells’ technique using the <ce:italic>k</ce:italic>–<ce:italic>ω</ce:italic> turbulence model. Test cases include high-Reynolds-number nozzles for Mach 1.8, 2.0, and 2.2, as well as a low-Reynolds-number case for Mach 4.0. An overall performance metric, <ce:italic>ϕ</ce:italic><ce:inf loc=\"post\">eff</ce:inf>, is introduced to assess exit-flow quality by incorporating effective inviscid core area, flow distortion, and flow angularity. Results show that contours from the proposed method consistently outperform those from Sivells’ approach, with <ce:italic>ϕ</ce:italic><ce:inf loc=\"post\">eff</ce:inf> values at the theoretical nozzle exit higher by a factor of 1.3–1.58, while retaining simplicity in implementation.","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"95 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146146714","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 : 2026-02-10DOI: 10.1016/j.ast.2026.111889
Yongkang Zhao, Guangfeng An, Xianjun Yu, Baojie Liu, Dongbo Hao, Xi Nan
{"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":"https://doi.org/10.1016/j.ast.2026.111889","url":null,"abstract":"","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"97 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-10","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}
Topology optimization is crucial for enhancing structural performance and reducing costs in fields such as aerospace, automotive, and civil engineering. However, traditional methods face exponentially growing computational costs as mesh resolution increases. Meanwhile, existing generative models often rely on image-based representations, which limits their adaptability to components at different resolutions. To overcome these limitations, we propose NG-TO (Neural Compression-based Generative Topology Optimization), an implicit generative method that integrates neural compression with diffusion models. Our framework first encodes topologies into a compact, resolution-invariant latent space. A diffusion model then operates within this space to generate new designs that comply with specified physical constraints. Evaluations in multi-resolution and out-of-distribution scenarios demonstrate the model’s capability for resolution-free encoding and constraint satisfaction, establishing a high-performance paradigm for spacecraft structural design.
{"title":"An Implicit Generative Topology Optimization Method Based on Neural Compression and Diffusion Models","authors":"Xinrui Zhou, Huirun Xie, Bokai Li, Jing Wang, Qineng Wang, Yonghe Zhang","doi":"10.1016/j.ast.2026.111850","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111850","url":null,"abstract":"Topology optimization is crucial for enhancing structural performance and reducing costs in fields such as aerospace, automotive, and civil engineering. However, traditional methods face exponentially growing computational costs as mesh resolution increases. Meanwhile, existing generative models often rely on image-based representations, which limits their adaptability to components at different resolutions. To overcome these limitations, we propose NG-TO (Neural Compression-based Generative Topology Optimization), an implicit generative method that integrates neural compression with diffusion models. Our framework first encodes topologies into a compact, resolution-invariant latent space. A diffusion model then operates within this space to generate new designs that comply with specified physical constraints. Evaluations in multi-resolution and out-of-distribution scenarios demonstrate the model’s capability for resolution-free encoding and constraint satisfaction, establishing a high-performance paradigm for spacecraft structural design.","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"95 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146146795","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 : 2026-02-09DOI: 10.1016/j.ast.2026.111785
Afsaneh Kheirani, Ilyass Tabiai, David St-Onge
Indoor inspection and mapping missions in tunnels, industrial facilities, and subterranean environments require aerial platforms capable of long-duration operation in cluttered, humid, and navigation-denied conditions. While multirotor drones provide high maneuverability, their endurance and payload capacity are fundamentally limited by battery-powered lift. Small indoor lighter-than-air vehicles alleviate this constraint through buoyancy; however, at meter-scale volumes, envelope materials become a critical limitation, as they largely determine system mass, gas retention, durability, and resistance to handling and collisions. Commonly used films present persistent trade-offs: metallized polyester offers low gas permeability but limited mechanical robustness, whereas polyurethane is more durable but heavier and more permeable.
{"title":"Vehicle Envelope with Lightweight Ultrafilm for Minimal Leakage (VELUM)","authors":"Afsaneh Kheirani, Ilyass Tabiai, David St-Onge","doi":"10.1016/j.ast.2026.111785","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111785","url":null,"abstract":"Indoor inspection and mapping missions in tunnels, industrial facilities, and subterranean environments require aerial platforms capable of long-duration operation in cluttered, humid, and navigation-denied conditions. While multirotor drones provide high maneuverability, their endurance and payload capacity are fundamentally limited by battery-powered lift. Small indoor lighter-than-air vehicles alleviate this constraint through buoyancy; however, at meter-scale volumes, envelope materials become a critical limitation, as they largely determine system mass, gas retention, durability, and resistance to handling and collisions. Commonly used films present persistent trade-offs: metallized polyester offers low gas permeability but limited mechanical robustness, whereas polyurethane is more durable but heavier and more permeable.","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"315 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146146797","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}
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