Aerospace Science and Technology最新文献

英文中文

A divide-and-conquer machine learning transition model for airfoil flows: From steady linear-lift to unsteady stall stage 一个分而治之的机器学习过渡模型的翼型流动：从稳定的线性升力到非定常失速阶段

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-01 DOI: 10.1016/j.ast.2026.111778

Lei Wu , Tianyuan Liu , Zuoli Xiao

In this paper, a steady/unsteady integrated machine learning transition model is established via the divide-and-conquer (DaC) strategy, which covers a wide operating range of an airfoil from linear lift to deep stall. To consider the essential distinctions across different regions of the entire flow domain, a random forest binary classifier is adopted to detect the flow field as either intermittent spot or non-intermittent spot region. Two transitional intermittency factor regressors are crafted respectively within their own regions, thus facilitating the capture of crucial phenomenological details. Three airfoil geometries with different angles of attack, Mach numbers and Reynolds numbers are selected to fully validate the newly developed DaC model. The a posteriori results demonstrate that the DaC model aligns well with its benchmark counterpart across the full range of angles of attack, and can overcome the limitations of Non-DaC model in the stall stage of an airfoil frequently characterized by unsteady behavior. This divide-and-conquer-guided framework may advance the application of machine learning-based transition model to the airfoil design engineering, and potentially establish a generalizable strategy for modeling complex physics scenarios.

本文采用分而治之（DaC）策略建立了一个定/非定常集成机器学习过渡模型，该模型涵盖了翼型从线性升力到深度失速的广泛工作范围。为了考虑整个流域不同区域之间的本质区别，采用随机森林二值分类器对流场进行间歇点区域和非间歇点区域的检测。两个过渡性间歇因子回归因子分别在各自的区域内制作，从而促进了关键现象学细节的捕捉。选择三种不同迎角、马赫数和雷诺数的翼型几何形状来充分验证新开发的DaC模型。后验结果表明，DaC模型在全迎角范围内与基准模型一致，克服了非DaC模型在非定常翼型失速阶段的局限性。这种分而治之的指导框架可以推进基于机器学习的过渡模型在翼型设计工程中的应用，并有可能为复杂物理场景的建模建立一种可推广的策略。

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引用次数: 0

Corrigendum to “Enhanced High-Fidelity and Dynamic Modeling for Power Conditioning Units Synchronized with On-Orbit Satellites” [Aerospace Science and Technology, volume 162 (2025) 110213] “与在轨卫星同步的功率调节单元的增强高保真度和动态建模”的勘误[航空航天科学与技术，第162卷（2025）110213]

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-01 DOI: 10.1016/j.ast.2025.111338

Meng Wang , Guangquan Zhao , Xiyuan Peng

引用次数: 0

Multiple design parameters study on the flow characteristics of an inward turning detonation wave 内旋爆震波流动特性的多设计参数研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-01 DOI: 10.1016/j.ast.2026.111835

Haochen Xiong , Hao Yan , Tao Zhang , Yancheng You

In designing the basic detonation flow field, achieving high performance primarily depends on selecting appropriate geometric parameters. In this study, the effects of geometric parameters, including the projection length of the induced surface, reference wedge angle, height of combustion chamber, and initial wedge angle on the flow characteristics and performance of the basic axisymmetric inward-turning detonation flow field were analyzed in detail. The analysis was conducted by solving the unsteady two-dimensional axisymmetric Euler equations coupled with a detailed chemical reaction model. Since the basic detonation flow field is influenced by multiple geometric parameters, investigating their coupling relationships is essential for advancing detonation engine engineering and identifying the key parameters that govern overall performance. Based on a response surface model, the coupling effects of geometric parameters on performance parameters were analyzed, and the dominant geometric parameters influencing each performance parameter were determined. Furthermore, the optimal basic detonation flow field was obtained using the NSGA-II algorithm. Under the constraint of maintaining the combustion chamber weight, the optimal design achieved a 2.3 % increase in total pressure recovery and a 2.7 % improvement in thrust potential gain compared with the original design.

在基本爆轰流场的设计中，实现高性能主要取决于选择合适的几何参数。本文详细分析了诱导面投影长度、参考楔角、燃烧室高度、初始楔角等几何参数对基本轴对称内转爆轰流场流动特性和性能的影响。通过求解非定常二维轴对称欧拉方程，结合详细的化学反应模型进行了分析。由于基本爆震流场受到多个几何参数的影响，研究它们之间的耦合关系对于推进爆震发动机工程和确定控制整体性能的关键参数至关重要。基于响应面模型，分析了几何参数对性能参数的耦合效应，确定了影响各性能参数的主导几何参数。利用NSGA-II算法得到了最优的基本爆轰流场。在保持燃烧室重量的约束下，优化设计的总压恢复比原设计提高了2.3%，推力潜力增益提高了2.7%。

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引用次数: 0

Corrigendum to “Experimental Investigation of the Effect of Concave Endwall Profiling on the Aerodynamic Performance of a Transonic Highly-Loaded Turbine Cascade” [AESCTE 168 (2026) 111274] “凹端壁型线对跨音速高负荷涡轮叶栅气动性能影响的实验研究”[AESCTE 168(2026) 111274]的勘误

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-01 DOI: 10.1016/j.ast.2025.111568

Zhipeng Li, Yi Sun, Qinpeng Gu

引用次数: 0

Corrigendum to “A Comprehensive Contamination Assessment Methodology for Lunar Regolith on Spacecraft” “航天器月球风化层污染综合评估方法”的勘误表

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-01 DOI: 10.1016/j.ast.2025.111441

Daniel Bölke , Armen Jaworski , Bahar Kilitoglu , Joachim Vogt , Francesco Maurelli

引用次数: 0

Fracture analysis and design modification of the pintle in a thrust-controlled solid rocket motor: Experiments and numerical simulations 推力控制固体火箭发动机销轴断裂分析与设计改进：实验与数值模拟

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-01 DOI: 10.1016/j.ast.2026.111833

Duan Jianing , Feng Feng , Guan Yiwen

Pintle fracture failure is one of the critical failure modes in thrust-controlled solid rocket motors (TCSRM), and the unclear fracture mechanism has severely restricted their application. To clarify the underlying mechanism of pintle fracture, a failure analysis framework is proposed that combines fractography physicochemical experiments with multiphysics fluid-thermal-structural interaction (FSI) numerical simulations. First, a series of fractography physicochemical experiments, including macro- and micro-morphology observations, microstructural analysis, and chemical composition detection is conducted to determine the fracture process, causes, and mechanism of the pintle. Subsequently, one-way FSI simulations are performed to evaluate the fluid dynamics and the temperature, deformation, and stress distributions of the pintle, thereby clarifying the thermo-mechanical loading history associated with fracture. Finally, the pintle structure is modified, and the predictive simulations are validated through a ground firing test. The results show that the pintle failed by intergranular brittle fracture, with structural deficiency and severe thermal shock being the primary cause for failure. The FSI numerical simulations exhibit high consistency with the firing test of the TCSRM in predicting failure location and failure time of the pintle, as well as in assessing pintle structural integrity. The proposed framework provides a comprehensive understanding of the fracture failure mechanism and a quantitative numerical method for evaluating pintle structural integrity, offering practical guidance for the engineering design of pintles in TCSRM.

针状断裂失效是推力控制固体火箭发动机的一种重要失效形式，其断裂机理尚不清楚，严重制约了其应用。为了阐明针孔断裂的机理，提出了一种将断口物理化学实验与多物理场流-热-构造相互作用（FSI）数值模拟相结合的断裂分析框架。首先，进行一系列断口物理化学实验，包括宏观和微观形貌观察、微观组织分析和化学成分检测，以确定针孔断裂的过程、原因和机理。随后，进行单向FSI模拟，以评估流体动力学和轴的温度、变形和应力分布，从而阐明与破裂相关的热-机械加载历史。最后，对弹柱结构进行了改进，并通过地面发射试验对预测仿真结果进行了验证。结果表明：轴的破坏方式为晶间脆性断裂，结构缺陷和剧烈的热冲击是导致轴破坏的主要原因；FSI数值模拟结果与TCSRM点火试验结果在预测弹柱失效位置和失效时间以及评估弹柱结构完整性方面具有较高的一致性。该框架提供了对断裂破坏机制的全面认识和对销结构完整性评价的定量数值方法，可为TCSRM销的工程设计提供实用指导。

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引用次数: 0

Flow field created by a plasma actuator in quiescent air under the influence of a single sessile droplet 静空气中等离子体致动器在单个无底液滴作用下产生的流场

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-31 DOI: 10.1016/j.ast.2026.111824

Chang Li , Xin Zhang , Zhihong Zhou

The anti/de-icing technology using a DBD (dielectric barrier discharge) plasma actuator has attracted extensive attention. However, the underlying anti/de-icing mechanism of such plasma actuators remains insufficiently addressed, and the interaction between droplets and the plasma actuator has not been investigated in detail. To address the aforementioned research gaps, the flow field induced by a symmetric DBD plasma actuator in the presence of a single sessile droplet was studied using a high-speed particle image velocimetry (PIV) system. The results indicate that the droplet reduces the discharge intensity of the plasma actuator, leading to a decrease in the wall-jet velocity induced by the actuator during the droplet's stable stage. Nevertheless, the instability of the separated shear layer is enhanced, generating a series of roll-up vortices. Additionally, a train of coherent structures is formed near the wall during the droplet distortion stage. Notably, the broken droplet acts as a "virtual electrode" and alters the actuator's discharge position. Finally, in the water film stage, the broken droplet evolves into a water film-this not only shifts the discharge position but also transforms the discharge mode from steady (in the dry state) to unsteady within the water film.

采用介质阻挡放电（DBD）等离子体作动器的防除冰技术引起了广泛的关注。然而，这种等离子体致动器的潜在防/除冰机制仍然没有得到充分的研究，液滴与等离子体致动器之间的相互作用也没有得到详细的研究。为了解决上述研究空白，使用高速粒子图像测速（PIV）系统研究了对称DBD等离子体致动器在单个无底液滴存在下诱导的流场。结果表明，液滴降低了等离子体致动器的放电强度，导致致动器在液滴稳定阶段引起的壁面射流速度降低。然而，分离剪切层的不稳定性增强，产生一系列卷升涡。此外，在液滴变形阶段，在壁面附近形成一列相干结构。值得注意的是，破碎的液滴充当“虚拟电极”并改变执行器的放电位置。最后，在水膜阶段，破碎的液滴演变成水膜，这不仅改变了排放位置，而且将水膜内的排放模式从稳态（干燥状态）转变为非稳态。

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引用次数: 0

Transonic film cooling for future aviation gas turbines: A high-fidelity large eddy simulations reference 未来航空燃气轮机的跨音速气膜冷却：高保真大涡模拟参考

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-31 DOI: 10.1016/j.ast.2026.111801

Francesco De Vanna

This work presents a high-resolution large-eddy simulation (LES) database for transonic film cooling representative of modern aero-engine turbine environments. A canonical flat-plate configuration with a single round hole is investigated across six operating conditions that combine low, moderate, and high blowing ratios with two coolant-to-recovery temperature ratios. This parametric sweep isolates momentum- and buoyancy-driven mechanisms that govern jet attachment, plume lift-off, and surface protection. The simulations resolve the incoming turbulent boundary layer and the full jet-in-crossflow interaction, yielding scale-resolved wall-pressure spectra, spanwise energy distributions, and turbulent-kinetic-energy budgets. These diagnostics expose the spectral signatures of plume detachment, the redistribution of turbulent energy between inner and outer shear layers, and the wall-normal migration of peak production within the jet-film interface under transonic conditions. By removing geometric complexity and retaining the essential physics, the resulting dataset provides a rigorous reference for the calibration and assessment of RANS and hybrid RANS-LES closures, wall-model formulations with mass injection, and reduced-order strategies for future gas-turbine aerothermal design. All results are released openly.

本文提出了一个高分辨率的跨声速气膜冷却大涡模拟（LES）数据库，具有现代航空发动机涡轮环境的代表性。在低、中、高吹气比和两种冷却液与回收液温度比的六种工况下，研究了一种典型的单圆孔平板结构。这种参数扫描分离了动量和浮力驱动机制，这些机制控制着射流附着、羽流上升和表面保护。模拟解决了来流湍流边界层和横流中完整的射流相互作用，得到了尺度分辨的壁面压力谱、展向能量分布和湍流-动能收支。这些诊断揭示了跨音速条件下羽流分离的光谱特征，内外剪切层之间湍流能量的重新分配，以及射流膜界面内峰生产的壁向迁移。通过去除几何复杂性并保留基本的物理特性，所得数据集为RANS和混合RANS- les闭包的校准和评估、带质量注入的壁型公式以及未来燃气轮机气动热设计的降阶策略提供了严格的参考。所有结果都是公开公布的。

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引用次数: 0

Safety-critical model predictive control for quadcopter UAV subject to wind disturbances and measurement errors in confined environments 受限环境下受风干扰和测量误差影响的四旋翼无人机安全关键模型预测控制

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-31 DOI: 10.1016/j.ast.2026.111790

Hui Ye , Junjie Cao , Xiaofei Yang , Shuyi Shao

In practical engineering, the disturbances and measurement errors encountered by unmanned aerial vehicles (UAVs) flying in confined spaces significantly undermine the performance of safety-critical controllers. To address the issue of violating safety constraints in scenarios where both compound disturbances and measurement errors coexist, this paper presents a novel safety-critical control framework which integrates disturbance observer (DO), nonlinear model predictive control (NMPC), control barrier function (CBF) for UAV in the confined environments. Specifically, we employ a refined observer to estimate constant wind disturbance and time-varying airflow disturbance induced by blades in confined environments. Furthermore, to deal with measurement and observation errors, a measurement-robust tunable CBF is proposed. This proposed method, as a constraint condition, improves the safety margin of the system during flight by utilizing two upper bounds of errors. Finally, the effectiveness of the proposed NMPC-CBF-DO control framework is demonstrated in the simulation and the real-world experiments. In the comparative experiment, the proposed method increased the obstacle avoidance success rate by 20% in restricted scenarios.

在实际工程中，无人机在密闭空间飞行时遇到的干扰和测量误差严重影响了安全关键控制器的性能。为了解决复合扰动和测量误差并存的情况下无人机违反安全约束的问题，提出了一种集成扰动观测器（DO）、非线性模型预测控制（NMPC）和控制障碍函数（CBF）的受限环境下无人机安全关键控制框架。具体来说，我们使用了一个改进的观测器来估计在受限环境中由叶片引起的恒定风扰动和时变气流扰动。此外，为了处理测量和观测误差，提出了一种测量鲁棒可调CBF。该方法利用两个误差上界作为约束条件，提高了系统在飞行过程中的安全裕度。最后，通过仿真和实际实验验证了所提出的NMPC-CBF-DO控制框架的有效性。在对比实验中，该方法在受限场景下的避障成功率提高了20%。

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引用次数: 0

Research on the modeling method of unsteady aerodynamics for composite configuration based on the physics-embedded long short-term memory neural network 基于物理嵌入长短期记忆神经网络的复合材料构型非定常气动建模方法研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-31 DOI: 10.1016/j.ast.2026.111831

Xuan Bai , Baigang Mi

To address the aerodynamic modeling challenges posed by strong nonlinearities and hysteresis effects in high-angle-of-attack maneuvers, this study takes the prepositive elliptical wing-main wing composite flow control configuration as the research object. A method is proposed that explicitly embeds physical information into a conditional long short-term memory neural network for aerodynamic parameter identification and unsteady aerodynamic model construction. Taking the improved unsteady aerodynamic state-space equation of the composite configuration as the prior physical constraint, the conditional long short-term memory neural network is synchronously introduced to capture the temporal dependence relationship. The outputs of the two branches are dynamically fused through learnable weights to achieve the collaborative optimization of physical consistency and data fidelity. Taking the two-dimensional prepositive elliptical wing-main wing composite configuration as the research object, the neural network is trained and tested based on the dataset generated by computational fluid dynamics that covers multiple design parameters and working conditions. The results show that the root mean squared error of the intelligent modeling method proposed in this paper is reduced by more than 45% and 47% on the training set and the validation set respectively compared with the traditional single model. When verifying the generalization ability, whether for interpolation or extrapolation, the correlation coefficients of the aerodynamic coefficient prediction are all better than 0.999, and the average relative error is reduced by more than 20%. This framework combines physical interpretability and data adaptability, providing a new interpretable and transferable paradigm for the high-precision prediction of unsteady aerodynamics in complex flow environments.

为了解决大迎角机动中强非线性和滞后效应带来的气动建模挑战，本研究以正椭圆翼-主翼复合流动控制构型为研究对象。提出了一种将物理信息显式嵌入条件长短期记忆神经网络的方法，用于气动参数识别和非定常气动模型构建。以改进后的复合结构非定常气动状态空间方程为先验物理约束，同步引入条件长短期记忆神经网络捕捉二者的时间依赖关系。通过可学习权值动态融合两个分支的输出，实现物理一致性和数据保真度的协同优化。以二维正椭圆翼-主翼复合结构为研究对象，基于计算流体力学生成的涵盖多个设计参数和工况的数据集对神经网络进行训练和测试。结果表明，与传统的单一模型相比，本文提出的智能建模方法在训练集和验证集上的均方根误差分别降低了45%和47%以上。在验证泛化能力时，无论是内插还是外推，气动系数预测的相关系数均优于0.999，平均相对误差减小20%以上。该框架结合了物理可解释性和数据适应性，为复杂流动环境下非定常空气动力学的高精度预测提供了一种新的可解释和可转移的范式。

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