Variable-cycle engines (VCEs) require precise, wide-range turbine flow control while avoiding the complexity, weight, and durability issues of conventional geometric regulation. This study investigates suction-side slot injection as an aerodynamic regulation approach on the VKI-LS89 transonic nozzle guide vane profile. Steady 2D blade-to-blade RANS simulations are performed in a cascade configuration with spanwise periodic boundaries, and the baseline flow is validated against the MUR45 experimental condition. A parametric study is conducted to quantify how slot width, slot position, slot angle, and relative jet mass flow rate (<mml:math altimg="si19.svg"><mml:msub><mml:mover><mml:mi>m</mml:mi><mml:mi>˙</mml:mi></mml:mover><mml:mrow><mml:mi>i</mml:mi><mml:mi>n</mml:mi><mml:mi>j</mml:mi></mml:mrow></mml:msub></mml:math>) affect turbine flow capacity, total pressure loss, and internal flow features. Among the parameters tested, slot position exhibits the highest sensitivity, with the strongest regulation obtained when the slot is located at <mml:math altimg="si20.svg"><mml:mrow><mml:mi>x</mml:mi><mml:mo linebreak="goodbreak">/</mml:mo><mml:mi>C</mml:mi><mml:mo>≈</mml:mo><mml:mspace width="0.33em"></mml:mspace><mml:mn>25</mml:mn><mml:mo>%</mml:mo><mml:mo>−</mml:mo><mml:mn>35</mml:mn><mml:mo>%</mml:mo></mml:mrow></mml:math> (slightly upstream of the aerodynamic throat). Slot angle and jet mass flow show systematic trade-offs: counter-flow orientations and higher injection rates enhance blockage but increase mixing and wake loss. For a representative case with a perpendicular slot (<mml:math altimg="si21.svg"><mml:mrow><mml:msub><mml:mi>θ</mml:mi><mml:mrow><mml:mi>A</mml:mi><mml:mi>F</mml:mi><mml:mi>C</mml:mi></mml:mrow></mml:msub><mml:mspace width="0.33em"></mml:mspace><mml:mo linebreak="goodbreak">=</mml:mo><mml:mspace width="0.33em"></mml:mspace><mml:msup><mml:mn>0</mml:mn><mml:mo>∘</mml:mo></mml:msup></mml:mrow></mml:math>) and <mml:math altimg="si19.svg"><mml:msub><mml:mover><mml:mi>m</mml:mi><mml:mi>˙</mml:mi></mml:mover><mml:mrow><mml:mi>i</mml:mi><mml:mi>n</mml:mi><mml:mi>j</mml:mi></mml:mrow></mml:msub></mml:math> = 5%, the inlet mass flow is reduced by 10.41%. Mechanistically, slot position governs where blockage forms, slot angle controls the jet-mainflow interaction mode, and jet flow rate sets the intensity of momentum/energy exchange; together they regulate flow stability and loss growth. Balancing regulation effectiveness and loss penalty, for the present validated steady 2D blade-to-blade simulations on the VKI-LS89 profile and within the examined parameter space, a practical compromise is achieved with Δn/o ≈ 15%-26% (15.4%-25.8% in the tested cases), <mml:math altimg="si22.svg"><mml:mrow><mml:mi>x</mml:mi><mml:mo linebreak="goodbreak">/</mml:mo><mml:mi>C</mml:mi></mml:mrow></mml:math>≈ 0.25-0.35, θ ≈ 0°, and <mml:math altimg="si19.svg"><mml:msub><mml:mover><mml:mi>m</mml:mi><mml:mi>˙</mml:mi></mml:mover><mml:mrow><mml:mi>i</mml:mi><m
{"title":"Investigation on the Mechanism and Method of Wide Adaptability Turbine Aerodynamic Regulation","authors":"Lehan Lu, Hang Yuan, Xiao Qu, Meng Wu, Yongzhen Wang, Yanfeng Zhang","doi":"10.1016/j.ast.2026.111947","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111947","url":null,"abstract":"Variable-cycle engines (VCEs) require precise, wide-range turbine flow control while avoiding the complexity, weight, and durability issues of conventional geometric regulation. This study investigates suction-side slot injection as an aerodynamic regulation approach on the VKI-LS89 transonic nozzle guide vane profile. Steady 2D blade-to-blade RANS simulations are performed in a cascade configuration with spanwise periodic boundaries, and the baseline flow is validated against the MUR45 experimental condition. A parametric study is conducted to quantify how slot width, slot position, slot angle, and relative jet mass flow rate (<mml:math altimg=\"si19.svg\"><mml:msub><mml:mover><mml:mi>m</mml:mi><mml:mi>˙</mml:mi></mml:mover><mml:mrow><mml:mi>i</mml:mi><mml:mi>n</mml:mi><mml:mi>j</mml:mi></mml:mrow></mml:msub></mml:math>) affect turbine flow capacity, total pressure loss, and internal flow features. Among the parameters tested, slot position exhibits the highest sensitivity, with the strongest regulation obtained when the slot is located at <mml:math altimg=\"si20.svg\"><mml:mrow><mml:mi>x</mml:mi><mml:mo linebreak=\"goodbreak\">/</mml:mo><mml:mi>C</mml:mi><mml:mo>≈</mml:mo><mml:mspace width=\"0.33em\"></mml:mspace><mml:mn>25</mml:mn><mml:mo>%</mml:mo><mml:mo>−</mml:mo><mml:mn>35</mml:mn><mml:mo>%</mml:mo></mml:mrow></mml:math> (slightly upstream of the aerodynamic throat). Slot angle and jet mass flow show systematic trade-offs: counter-flow orientations and higher injection rates enhance blockage but increase mixing and wake loss. For a representative case with a perpendicular slot (<mml:math altimg=\"si21.svg\"><mml:mrow><mml:msub><mml:mi>θ</mml:mi><mml:mrow><mml:mi>A</mml:mi><mml:mi>F</mml:mi><mml:mi>C</mml:mi></mml:mrow></mml:msub><mml:mspace width=\"0.33em\"></mml:mspace><mml:mo linebreak=\"goodbreak\">=</mml:mo><mml:mspace width=\"0.33em\"></mml:mspace><mml:msup><mml:mn>0</mml:mn><mml:mo>∘</mml:mo></mml:msup></mml:mrow></mml:math>) and <mml:math altimg=\"si19.svg\"><mml:msub><mml:mover><mml:mi>m</mml:mi><mml:mi>˙</mml:mi></mml:mover><mml:mrow><mml:mi>i</mml:mi><mml:mi>n</mml:mi><mml:mi>j</mml:mi></mml:mrow></mml:msub></mml:math> = 5%, the inlet mass flow is reduced by 10.41%. Mechanistically, slot position governs where blockage forms, slot angle controls the jet-mainflow interaction mode, and jet flow rate sets the intensity of momentum/energy exchange; together they regulate flow stability and loss growth. Balancing regulation effectiveness and loss penalty, for the present validated steady 2D blade-to-blade simulations on the VKI-LS89 profile and within the examined parameter space, a practical compromise is achieved with Δn/o ≈ 15%-26% (15.4%-25.8% in the tested cases), <mml:math altimg=\"si22.svg\"><mml:mrow><mml:mi>x</mml:mi><mml:mo linebreak=\"goodbreak\">/</mml:mo><mml:mi>C</mml:mi></mml:mrow></mml:math>≈ 0.25-0.35, θ ≈ 0°, and <mml:math altimg=\"si19.svg\"><mml:msub><mml:mover><mml:mi>m</mml:mi><mml:mi>˙</mml:mi></mml:mover><mml:mrow><mml:mi>i</mml:mi><m","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"105 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146209927","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 : 2026-02-16DOI: 10.1016/j.ast.2026.111945
Zhibo Jia, Wei Fan, Ping Zhou, Hui Ren
The spinning circular solar sail is highly attractive in space-exploring missions due to its low areal density and compact fold strategy. Its accurate modeling and real-time simulations can help effectively predict the dynamic behavior, thus assisting its on-orbit operation and control. This work achieves efficient explicit simulations for the dynamics of spinning circular solar sails considering the orbit-attitude-vibration coupling effect. To achieve this, a dynamical circular solar sail model optimized for explicit integrators is established, where the Föppl-von Kármán (FvK) plate theory, without considering high-frequency in-plane vibrations, is adopted to describe the nonlinear deformations. Particularly, both the out-of-plane deflection and in-plane stresses for geometric stiffness are modeled, and their nonlinear coupling is taken into account. To address the time-varying coupling effect among the orbit, attitude, and vibration, a non-inertial floating frame is introduced to separate their degrees of freedom, thus that the multiscale challenge can be overcome. Furthermore, the local incremental rotation vector is then employed to get rid of singularities existing in large spatial rotations. Based on this, the explicit Lie group integrator is developed to efficiently solve the coupling dynamics of the solar sail. Numerical experiments are performed to verify the accuracy of the dynamic model and validate the high efficiency of the explicit simulations. This present work contributes to the explicit real-time simulation of spinning circular solar sails considering orbit-attitude-vibration coupling effects.
{"title":"Efficient explicit simulation for dynamics of spinning circular solar sails considering the orbit-attitude-vibration coupling effect","authors":"Zhibo Jia, Wei Fan, Ping Zhou, Hui Ren","doi":"10.1016/j.ast.2026.111945","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111945","url":null,"abstract":"The spinning circular solar sail is highly attractive in space-exploring missions due to its low areal density and compact fold strategy. Its accurate modeling and real-time simulations can help effectively predict the dynamic behavior, thus assisting its on-orbit operation and control. This work achieves efficient explicit simulations for the dynamics of spinning circular solar sails considering the orbit-attitude-vibration coupling effect. To achieve this, a dynamical circular solar sail model optimized for explicit integrators is established, where the Föppl-von Kármán (FvK) plate theory, without considering high-frequency in-plane vibrations, is adopted to describe the nonlinear deformations. Particularly, both the out-of-plane deflection and in-plane stresses for geometric stiffness are modeled, and their nonlinear coupling is taken into account. To address the time-varying coupling effect among the orbit, attitude, and vibration, a non-inertial floating frame is introduced to separate their degrees of freedom, thus that the multiscale challenge can be overcome. Furthermore, the local incremental rotation vector is then employed to get rid of singularities existing in large spatial rotations. Based on this, the explicit Lie group integrator is developed to efficiently solve the coupling dynamics of the solar sail. Numerical experiments are performed to verify the accuracy of the dynamic model and validate the high efficiency of the explicit simulations. This present work contributes to the explicit real-time simulation of spinning circular solar sails considering orbit-attitude-vibration coupling effects.","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"22 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146209736","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 : 2026-02-12DOI: 10.1016/j.ast.2026.111805
M. Mohsin Ali, , Amir Khan, M. Zain, Raja Amer Azim, Tariq Talha, Imran Akhtar
{"title":"Corrigendum to “A numerical investigation of aerodynamic and aeroacoustic performance of aerial screw propeller for small UAVs and VTOL” [AESCTE, Volume 172, May 2026, 111732]","authors":"M. Mohsin Ali, , Amir Khan, M. Zain, Raja Amer Azim, Tariq Talha, Imran Akhtar","doi":"10.1016/j.ast.2026.111805","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111805","url":null,"abstract":"","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"10 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146160987","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 : 2026-02-11DOI: 10.1016/j.ast.2026.111912
Lyu Leqi, Jin Xin, Zhang Huiqiang
{"title":"Numerical investigation on the atomization process in a hydrogen-oxygen gas-liquid coaxial injector","authors":"Lyu Leqi, Jin Xin, Zhang Huiqiang","doi":"10.1016/j.ast.2026.111912","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111912","url":null,"abstract":"","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"32 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146153056","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 : 2026-02-11DOI: 10.1016/j.ast.2026.111913
Yao-jia Han, Yi-pin Sun, Cheng-wei Fei
{"title":"CDM–Bayesian Framework for Multiscale Fatigue Life Prediction of Aircraft Mechanisms with Rigid–Flexible Coupling","authors":"Yao-jia Han, Yi-pin Sun, Cheng-wei Fei","doi":"10.1016/j.ast.2026.111913","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111913","url":null,"abstract":"","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"13 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146160997","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 investigation of acoustic resonance in aero-engine compressors based on fluid–structure–acoustic multi-physics measurements","authors":"Fei Wang, Baijie Qiao, Ming Zhong, Yanan Wang, Yuanshi Liu, Xuefeng Chen","doi":"10.1016/j.ast.2026.111915","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111915","url":null,"abstract":"","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"32 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146160570","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.2026.111886
Qianyang Sun , Wenxuan Liu , Jun Wu , Dahai Zhang , Fangzhou Lu , Peifei Xu , Qingguo Fei
The gas rudder is a thrust vectoring device and withstand the direct impingement of high-temperature gases emitted by the engine. Significant temperature gradients exist between the regions exposed to the gases and other areas, resulting in considerable thermal stress within the gas rudder structure. To address the issue of temperature gradients and thermal stress in the rudder, this paper introduces a design method that features a dredging thermal protection structure (DTPS) with embedded high thermal conductivity materials. Numerical simulations were conducted to evaluate the effect of parameters of the DTPS, including the thickness and thermal conductivity of the dredging layer and thickness of the insulation layer, on temperature gradients and thermal stress. The results confirm that DTPS effectively reduces the temperature gradients in the gas rudder structure. The maximum tensile stress in the fiber direction of the composite panel of the flow deflector using DTPS was reduced by 57.8%.
{"title":"Design and characteristics of dredging thermal protection structure under high temperature gradient","authors":"Qianyang Sun , Wenxuan Liu , Jun Wu , Dahai Zhang , Fangzhou Lu , Peifei Xu , Qingguo Fei","doi":"10.1016/j.ast.2026.111886","DOIUrl":"10.1016/j.ast.2026.111886","url":null,"abstract":"<div><div>The gas rudder is a thrust vectoring device and withstand the direct impingement of high-temperature gases emitted by the engine. Significant temperature gradients exist between the regions exposed to the gases and other areas, resulting in considerable thermal stress within the gas rudder structure. To address the issue of temperature gradients and thermal stress in the rudder, this paper introduces a design method that features a dredging thermal protection structure (DTPS) with embedded high thermal conductivity materials. Numerical simulations were conducted to evaluate the effect of parameters of the DTPS, including the thickness and thermal conductivity of the dredging layer and thickness of the insulation layer, on temperature gradients and thermal stress. The results confirm that DTPS effectively reduces the temperature gradients in the gas rudder structure. The maximum tensile stress in the fiber direction of the composite panel of the flow deflector using DTPS was reduced by 57.8%.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111886"},"PeriodicalIF":5.8,"publicationDate":"2026-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146153334","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}
Investigating nacelle intake under crosswind in whole-aircraft models is a frontier topic in modern aerospace propulsion research. However, investigations into the nonlinear flow characteristics of the leeward side nacelle intake influenced by fuselage interference remain scarce, and accurate modeling of this nonlinear flow continues to pose a significant challenge. Although data-driven approaches are cheap and efficient solutions, achieving high-fidelity reconstruction and prediction under small sample conditions remains a major obstacle. This paper investigates the causes of differences in the intake characteristics of windward and leeward side nacelles and evaluates the data-driven modeling performance of representative reduced-order models and deep learning methods, proposing a nonlinear hybrid prediction model framework. The model first extracts the dominant features of the unsteady nacelle intake flow through the proper orthogonal decomposition. The temporal evolution of the modal coefficients is subsequently modeled nonlinearly using neural networks. Finally, global error correction and uncertainty quantification are applied to the predicted flow field. The paper validates the approaches via a numerical example of a typical narrow-body commercial aircraft. The results show that the constructed hybrid prediction model exhibits excellent accuracy and stability across different training set proportions. Given that small sample conditions are a common limitation in aerospace engineering, this approach holds great potential for application in unsteady aerodynamic analysis and rapid evaluation of engine nacelles.
{"title":"Comparative Analysis of Nonlinear Data-Driven Modeling of Inlet Distortion for Nacelle Air-Intake System","authors":"Xiao Yuan, Chenxing Hu, Hao Liu, Fei Yang, Jiaao Gu, Zhichao Chai","doi":"10.1016/j.ast.2026.111890","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111890","url":null,"abstract":"Investigating nacelle intake under crosswind in whole-aircraft models is a frontier topic in modern aerospace propulsion research. However, investigations into the nonlinear flow characteristics of the leeward side nacelle intake influenced by fuselage interference remain scarce, and accurate modeling of this nonlinear flow continues to pose a significant challenge. Although data-driven approaches are cheap and efficient solutions, achieving high-fidelity reconstruction and prediction under small sample conditions remains a major obstacle. This paper investigates the causes of differences in the intake characteristics of windward and leeward side nacelles and evaluates the data-driven modeling performance of representative reduced-order models and deep learning methods, proposing a nonlinear hybrid prediction model framework. The model first extracts the dominant features of the unsteady nacelle intake flow through the proper orthogonal decomposition. The temporal evolution of the modal coefficients is subsequently modeled nonlinearly using neural networks. Finally, global error correction and uncertainty quantification are applied to the predicted flow field. The paper validates the approaches via a numerical example of a typical narrow-body commercial aircraft. The results show that the constructed hybrid prediction model exhibits excellent accuracy and stability across different training set proportions. Given that small sample conditions are a common limitation in aerospace engineering, this approach holds great potential for application in unsteady aerodynamic analysis and rapid evaluation of engine nacelles.","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"42 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146146828","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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