Aerospace Science and Technology最新文献_第5页

Aerodynamic design of fixed-wing VTOL aircraft powered by gas-driven fan propulsion system 气扇推进固定翼垂直起降飞机气动设计

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-10 DOI: 10.1016/j.ast.2025.110165

Yuanzhao Zhu, Guoping Huang, Chen Xia, Yang Wu

{"title":"Aerodynamic design of fixed-wing VTOL aircraft powered by gas-driven fan propulsion system","authors":"Yuanzhao Zhu, Guoping Huang, Chen Xia, Yang Wu","doi":"10.1016/j.ast.2025.110165","DOIUrl":"10.1016/j.ast.2025.110165","url":null,"abstract":"<div><div>This study introduces a novel gas-driven thrust fan (GDTF) propulsion concept for fixed-wing vertical takeoff and landing (VTOL) aircraft, aiming to combine high hovering efficiency with superior cruise performance. The design philosophy integrates a VTOL nacelle concept, encompassing a gas-driven fan along with intake and exhaust systems, into a conventional fixed-wing airframe. A key innovation is the introduction of an aerodynamic cowl, which passively modifies the effective capture area and mitigates spillage drag. Numerical simulations and low-speed wind tunnel experiments validated the proposed configuration, demonstrating that the GDTF-powered VTOL nacelle can achieve a thrust coefficient of 0.8, representing a significant improvement 66 % over the baseline design. The integrated aircraft attains a maximum lift-to-drag ratio of approximately 12.7 at the angle of attack of 4°, and the zero-lift drag coefficient (∼0.0228) falls within the typical range for subsonic aircraft. The results confirm that the proposed GDTF integration strategy yields both high hovering efficiency and favorable cruise characteristics. Additionally, these findings provide the foundation for developing an electric VTOL (eVTOL) variant capable of achieving flight speeds of 120 m/s, offering strong potential advantages for future urban air mobility (UAM) applications.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110165"},"PeriodicalIF":5.0,"publicationDate":"2025-04-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143869557","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}

引用次数: 0

Separation prediction and roughness effect simulation of iced airfoils based on a modified k–ω–γ transition model 基于修正的 k-ω-γ 过渡模型的结冰机翼分离预测和粗糙度效应模拟

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-09 DOI: 10.1016/j.ast.2025.110202

Jiawei Chen, Chong Yan, YuFei Zhang

{"title":"Separation prediction and roughness effect simulation of iced airfoils based on a modified k–ω–γ transition model","authors":"Jiawei Chen, Chong Yan, YuFei Zhang","doi":"10.1016/j.ast.2025.110202","DOIUrl":"10.1016/j.ast.2025.110202","url":null,"abstract":"<div><div>Ice accretion significantly complicates flow separation over airfoils, posing substantial challenges for turbulence models. In this work, a modified <span><math><mrow><mi>k</mi><mo>−</mo><mi>ω</mi><mo>−</mo><mi>γ</mi></mrow></math></span> transition model, which incorporates a separation correction and a roughness effect simulation, is developed for accurately predicting complex flows over iced airfoils. The model's ability to predict large separations is validated in several cases, including a periodic hill and airfoils with glaze ice and rime ice. The results indicate that the modified model can accurately predict the flow separation and aerodynamic force characteristics. At the stall angle of attack, the relative error between the modified <span><math><mrow><mi>k</mi><mo>−</mo><mi>ω</mi><mo>−</mo><mi>γ</mi></mrow></math></span> model and the experimental maximum lift coefficient is less than 5.0 %, in contrast, the error of the SST model results ranges from 22.0 % to 35.8 %. Additionally, a rough flat plate and several rough airfoils without or with ice are adopted to evaluate the model's ability to simulate roughness effects. The results show that the model can capture the early transition induced by different roughness heights. This approach also has advantages over the integral boundary-layer approach in calculating the heat transfer coefficient in the presence of separated flow.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110202"},"PeriodicalIF":5.0,"publicationDate":"2025-04-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143817454","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}

引用次数: 0

Numerical simulation study on aeroelastic stability mechanism of a transonic fan rotor 跨音速风机转子气动弹性稳定机理的数值模拟研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-09 DOI: 10.1016/j.ast.2025.110193

Yongbo Yu , Yanrong Wang , Le Han

{"title":"Numerical simulation study on aeroelastic stability mechanism of a transonic fan rotor","authors":"Yongbo Yu , Yanrong Wang , Le Han","doi":"10.1016/j.ast.2025.110193","DOIUrl":"10.1016/j.ast.2025.110193","url":null,"abstract":"<div><div>This study investigates the aeroelastic stability of fan rotor blades via the energy method. Research has identified shock waves, backflow, and radial flow as important factors causing aeroelastic instability in rotor blades. The variation in the aerodynamic damping of the rotor blade with the interblade phase angle is consistent with that on the suction surface. The larger the unsteady pressure amplitude is, the more difficult it is for the interblade phase angle to affect the phase of the unsteady pressure in the corresponding area. At a constant rotational speed, the radial flow on the suction surface gradually intensifies as the flow rate decreases. This strong radial flow causes aeroelastic instability near the stall point by altering the phase of the unsteady aerodynamic forces on the rotor blade surface. The aeroelastic instability boundary at different speeds is near the stall point. Regions with large unsteady aerodynamic pressure amplitudes on the rotor blade surface are located mainly near the leading edge of the suction surface, shock waves, and backflow areas. The phase of unsteady pressure in these regions undergoes a 180-degree shift due to the influence of shock waves and strong radial flow.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110193"},"PeriodicalIF":5.0,"publicationDate":"2025-04-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143844685","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}

引用次数: 0

Design optimization of axial slot casing treatment and blade in an axial compressor based on deep learning and reinforcement learning 基于深度学习和强化学习的轴流压缩机轴向槽套管处理和叶片设计优化

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-09 DOI: 10.1016/j.ast.2025.110209

Zhonggang Fan(范忠岗) , Yueteng Wu(吴跃腾) , Dun Ba(巴顿) , Min Zhang(张敏) , Yang Liu(刘洋) , Juan Du(杜娟)

{"title":"Design optimization of axial slot casing treatment and blade in an axial compressor based on deep learning and reinforcement learning","authors":"Zhonggang Fan(范忠岗) , Yueteng Wu(吴跃腾) , Dun Ba(巴顿) , Min Zhang(张敏) , Yang Liu(刘洋) , Juan Du(杜娟)","doi":"10.1016/j.ast.2025.110209","DOIUrl":"10.1016/j.ast.2025.110209","url":null,"abstract":"<div><div>Casing treatments have been identified as a promising approach to broaden the operational stability range of compressors by influencing the flow field and delaying the onset of rotating stall. In this study, an integrated optimization of axial slot casing treatment and blade is employed to improve the stall margin without peak efficiency penalty. The casing treatment is defined by 2 B-spline curves, and the blade is parameterized by free form deformation. A multi-objective optimization platform, leveraging machine learning techniques, is developed to facilitate this process. Stall margin improvements and efficiency are predicted using a transformer encoder model with an embedded multi-head self-attention mechanism. The optimization process, driven by reinforcement learning algorithms, aims to maximize stall margin improvement, with policy updates implemented using Proximal Policy Optimization (PPO) algorithms. The performance of the optimal design is further validated through numerical simulations, demonstrating a 13.1 % increase in stall margin without any penalty on peak efficiency. Detailed analysis of the flow field reveals a reduction in the intensity of the tip leakage flow, accompanied by an enhancement in the axial momentum of the main flow. As a result, the interface between the main flow and the tip leakage flow shifts toward the trailing edge. By reducing the influence of the vortex core, additional losses induced by the casing treatment are effectively counteracted, thereby preserving peak efficiency.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110209"},"PeriodicalIF":5.0,"publicationDate":"2025-04-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143830006","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}

引用次数: 0

Improved quadratic constitutive relation via turbulence anisotropy analysis and symbolic regression 通过湍流各向异性分析和符号回归改进二次构成关系

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-09 DOI: 10.1016/j.ast.2025.110166

XiangLin Shan , WeiWei Zhang

{"title":"Improved quadratic constitutive relation via turbulence anisotropy analysis and symbolic regression","authors":"XiangLin Shan , WeiWei Zhang","doi":"10.1016/j.ast.2025.110166","DOIUrl":"10.1016/j.ast.2025.110166","url":null,"abstract":"<div><div>Secondary flows widely appear in aerospace engineering, appearing in phenomena such as wing-body junction flows and corner flows in square ducts. These flows are driven by turbulence anisotropy and are characterized by motion perpendicular to the primary flow direction. Accurately capturing the anisotropy of Reynolds stresses is crucial for secondary flows, but existing turbulence models based on the linear constitutive relation perform poorly in this regard. This study investigates the quadratic constitutive relation (QCR) model, which provides a robust framework for Reynolds stress modeling. By integrating the QCR2024 model with anisotropy invariant maps, we propose a modeling approach for the model coefficients to better represent the Reynolds stress anisotropy in secondary flows. Through analytical derivation and feature selection, we obtain Reynolds stress expressions applicable to quasi-two-dimensional flows and use symbolic regression to construct the model. The new model is tested on developed turbulence in square duct and flow in rectangular diffuser, demonstrating higher predictive accuracy compared to existing QCR models (QCR2000 and QCR2024). This approach enables more accurate secondary flow prediction and holds significant promise for improving turbulence simulations in complex aerospace engineering applications.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110166"},"PeriodicalIF":5.0,"publicationDate":"2025-04-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143830007","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}

引用次数: 0

Sparse online Gaussian process regression-based robust nonlinear dynamic inversion for multirotor with forward flight ground effect 基于稀疏在线高斯过程回归的多旋翼前飞地面效应鲁棒非线性动态反演

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-09 DOI: 10.1016/j.ast.2025.110195

Jayden Dongwoo Lee, Youngjae Kim, Lamsu Kim, Natnael S. Zewge, Hyochoong Bang

{"title":"Sparse online Gaussian process regression-based robust nonlinear dynamic inversion for multirotor with forward flight ground effect","authors":"Jayden Dongwoo Lee, Youngjae Kim, Lamsu Kim, Natnael S. Zewge, Hyochoong Bang","doi":"10.1016/j.ast.2025.110195","DOIUrl":"10.1016/j.ast.2025.110195","url":null,"abstract":"<div><div>This paper proposes a sparse online Gaussian process-based robust nonlinear dynamic inversion (SOGPR-RNDI) to compensate for ground effect during forward flight. Ground effect is challenging to model as it varies with altitude, thrust, propeller radius, platform movement, and surface quality. Its characteristics change significantly during forward flight due to aerodynamic effects. To address this problem, sparse online Gaussian process regression (SOGPR), a non-parametric modeling method, is employed to estimate and compensate for ground effect in real-time. SOGPR updates the mean and variance through a recursive process and uses a kernel linear independence test to maintain a meaningful dataset while reducing a computational burden. The proposed controller integrates a baseline control input, a Gaussian process regression (GPR) control input, and a robust control input, which is designed using the time derivative of the uncertainty error to ensure tracking performance and mitigate chattering issues. In addition, finite-time asymptotic convergence of the closed-loop system is proved using Lyapunov stability. Simulation results demonstrate that the proposed method effectively compensates for ground effect during forward flight and achieves superior tracking performance compared to nonlinear disturbance observer (NDO), deep neural network (DNN), modified GPR (MGPR), and SOGPR-based nonlinear dynamic inversion (SOGPR-NDI). Notably, SOGPR-RNDI reduces altitude root mean square error (RMSE) by 18.7% and velocity RMSE by 12.4% compared to SOGPR-NDI. Moreover, the computational efficiency of SOGPR-RNDI is analyzed, demonstrating its real-time applicability through better training and execution times compared to other methods.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110195"},"PeriodicalIF":5.0,"publicationDate":"2025-04-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143888064","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}

引用次数: 0

Attention-based multi-modal learning for aircraft engine fan fault diagnosis 基于注意力的多模态学习在飞机发动机风扇故障诊断中的应用

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-08 DOI: 10.1016/j.ast.2025.110194

Jingjing Zhu , Sicong Liang , Zhaokai Ma , Xun Huang

{"title":"Attention-based multi-modal learning for aircraft engine fan fault diagnosis","authors":"Jingjing Zhu , Sicong Liang , Zhaokai Ma , Xun Huang","doi":"10.1016/j.ast.2025.110194","DOIUrl":"10.1016/j.ast.2025.110194","url":null,"abstract":"<div><div>This research proposes a methodology using the deep learning framework to investigate rotating fan fault diagnosis - an endeavor of both scientific significance and practical importance. The methodology includes two critical steps: (1) the generation of high-frequency coupled acoustic mode spectrogram features and (2) the application of the attention mechanism-based feature fusion technique to integrate vibration Mel spectrograms, acoustic Mel spectrograms, and coupled acoustic mode spectrograms. The coupled mode spectrogram feature is adopted in deep learning research on fan fault diagnosis for the first time. The theoretical derivation of the coupled acoustic source, based on nonlinear acoustics, is provided for a deepened physical understanding of the proposed feature. Our model is verified and validated by analyzing its predictive performance on the representative datasets from our rotating fan experiments. According to the results, adding the coupled mode spectrogram feature can increase the model accuracy by at least 19% on small datasets. Furthermore, the accuracy of the attention-based model can be, at most, 13% greater than that of the straightforward feature fusion-based model. It reveals that the proposed classification model holds the potential for advancing aircraft engine fault diagnosis techniques and enhancing aircraft operational safety.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110194"},"PeriodicalIF":5.0,"publicationDate":"2025-04-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143817379","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}

引用次数: 0

Relative navigation of circumlunar satellite formation in DSL mission: Real-time solution for incomplete observations DSL 任务中环月卫星编队的相对导航：不完整观测数据的实时解决方案

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-08 DOI: 10.1016/j.ast.2025.110196

Fan Wu , Rui Zou , Zichen Zhao , Xinlong Le , Ruichen Xi

{"title":"Relative navigation of circumlunar satellite formation in DSL mission: Real-time solution for incomplete observations","authors":"Fan Wu , Rui Zou , Zichen Zhao , Xinlong Le , Ruichen Xi","doi":"10.1016/j.ast.2025.110196","DOIUrl":"10.1016/j.ast.2025.110196","url":null,"abstract":"<div><div>DSL (Discovering the sky at the longest wavelengths) mission is crucial for probing the cosmic dawn and dark ages through ultra-long wavelength observations. However, it presents significant navigation challenges due to GNSS signal loss, difficulty in obtaining relative measurements and severe orbital ambiguity problem. Considering these factors, this paper proposes a cooperative relative navigation strategy for the DSL mission's incomplete inter-satellite observations, consisting of three main parts: unanchored positioning, anchor nodes positioning and coordinate registration. Firstly, we obtain unanchored positions using inter-satellite range information through a multi-satellite cooperative localization method, which can quickly resolve relative positions even with missing range measurements. Secondly, considering the incomplete angle measurements caused by field of view limitations and illumination conditions, we design a new information fusion and complementary method to determine positions of the ANS (Anchor Node Satellites). Thirdly, to achieve high-precision coordinate registration, we propose a covariance-weighted Procrustes analysis algorithm based on positioning accuracies of different anchor nodes to transform unanchored satellite positions into the desired coordinate system. These three proposed algorithms are combined as a fused navigation strategy. Numerical simulations of two practical cases, clustering and trailing formation in the DSL mission, validate the effectiveness of the proposed method, showing the efficiency dealing with incomplete measurement information. Specifically, even with only 30 % angle measurements and 70 % range measurements, the proposed method can still maintain 5-meter accuracy within a distance of 100 km under 50 μrad angle-measuring error and 0.1 m ranging error.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110196"},"PeriodicalIF":5.0,"publicationDate":"2025-04-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143830008","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}

引用次数: 0

Unwinding-free property of the dual-quaternion-based pose tracking controllers designed by fully actuated system approaches 采用全驱动系统方法设计的双四元数姿态跟踪控制器的无解卷特性

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-08 DOI: 10.1016/j.ast.2025.110197

Fu-Zheng Xiao, Li-Qun Chen

引用次数: 0

A unified dynamic modeling for FGM sandwich conical shell built-in reinforcing plate in airflow environment 气流环境下FGM夹层锥形壳内置加筋板的统一动力学建模

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-08 DOI: 10.1016/j.ast.2025.110204

Dong Shao , Mengqi Gao , Dongtao Wu , Ningze Sun

{"title":"A unified dynamic modeling for FGM sandwich conical shell built-in reinforcing plate in airflow environment","authors":"Dong Shao , Mengqi Gao , Dongtao Wu , Ningze Sun","doi":"10.1016/j.ast.2025.110204","DOIUrl":"10.1016/j.ast.2025.110204","url":null,"abstract":"<div><div>In this paper, a unified dynamic modeling for investigating the free and forced vibration of the functionally graded material (FGM) sandwich conical shell built-in reinforcing plate structures with arbitrary curve coupled boundaries is established. The structure is split into three structures by the intercept <em>b</em> and slope <em>k</em> of the relative position intersection curve which include hyperbola, parabola etc. The subshell is FGM sandwich shell and subjected to a temperature distribution field and airflow environment. Theoretical model of the substructure is expressed by using the Jacobian differential quadrature method (JDQM). Thereinto, the governing equations are derived from the Hamilton principle based on the first-order shear theory. To solve the coupling problem of curve boundaries in modeling process, a general penalty function is used to describe it. On this basis, a novel coupling method of spatial curve integral penalty function is developed by the coordinate transformation of the curve boundary displacement function. After comparing with the finite element method (FEM) results and verifying the effectiveness of the theoretical model, a series of numerical cases of the effects of geometry, material distribution, temperature field and incoming airflow velocity on the free and forced vibration characteristics are presented, which provides a reliable framework for studying the dynamic behavior of the FGM sandwich conical shell built-in reinforcing plate exposed in the airflow. In the parametric study, it was observed that increasing the intercept <em>b</em>, while keeping the slope <em>k</em> constant, can enhance the performance of the structure.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110204"},"PeriodicalIF":5.0,"publicationDate":"2025-04-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143844686","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}

引用次数: 0