Aerospace Science and Technology最新文献_第10页

Aerodynamic performance of a non-slender delta wing modified with passive flow channels under ground effect 被动流道非细长三角翼在地面效应下的气动性能研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-04 DOI: 10.1016/j.ast.2026.111854

Resul Kurt , Hürrem Akbıyık

Understanding the flow characteristics and enhancing the aerodynamic characteristics of non-slender delta wings (NSDWs) is crucial for the design and performance of next generation unmanned aerial vehicles (UAVs). In this experimental study, the suction surface of a NSDW is modified with channels as a passive flow control technique. A 50-degree sweep angle and a 45-degree leeward bevel angle of the NSDW are chosen. The effects of the flow channels on the aerodynamic performance of the model were investigated at different angles of attack (AoA) and at various h/c ratios. Aerodynamic force measurements were performed for all models with a Re value of 1.5 × 10⁵, and surface oil flow visualization experiments based on titanium dioxide (TiO₂) were conducted. All experiments were conducted at the open suction wind tunnel for various attack angles between 0° and 40° with and increment of 5° and the distance (h/c) between the test model and ground is set as 0.1, 0.4, and out-of-ground effect (OGE) ratios. According to the experimental results, it is revealed that the channel structure as surface modification on the test models provides increase in lift coefficient (C_L) and decrease in drag coefficient (C_D). Thus, the improvement in aerodynamic performance of a non-slender delta wing is achieved. The lift-to-drag ratio (L/D) of the base model has been enhanced by about 17% with the surface modification, depending on the different h/c ratios. In the light of surface oil flow visualizations experiments, the flow structures on the modified delta wings are observed and monitored.

了解非细长三角翼的流动特性并提高其气动特性对下一代无人机的设计和性能至关重要。在本实验研究中，采用通道作为被动流动控制技术，对NSDW的吸力面进行了改造。选择NSDW的50度掠角和45度背风斜角。研究了不同迎角和不同h/c比下流道对模型气动性能的影响。所有模型的Re值均为1.5 × 10 5，进行了气动力测量，并进行了基于二氧化钛（TiO₂）的表面油流可视化实验。所有实验均在开式风洞中进行，攻角为0°~ 40°，增量为5°，试验模型与地面的距离（h/c）分别设为0.1、0.4和离地效应（OGE）比。实验结果表明，在试验模型上进行表面改性后的通道结构可以提高升力系数（CL），降低阻力系数（CD）。从而实现了非细长三角翼气动性能的改善。根据不同的h/c比，基本型号的升阻比（L/D）通过表面改性提高了约17%。结合表面油流可视化实验，对改进三角翼上的流动结构进行了观察和监测。

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引用次数: 0

A Set Theoretic approach for reducing critical load cases in aircraft structural design 飞机结构设计中减少临界载荷的集合理论方法

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-04 DOI: 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.

本文提出了一种通过集合理论优化来减少飞机结构分析中临界载荷案例数量的方法。分析开始于数百万个飞行条件的高维数据集，其中包含多个监测站的静态六自由度（6-DOF）负载响应。首先使用传统的极值选择方法确定临界负载情况。然后，根据定义的相似性阈值，通过收集附近的飞行条件，将每个选定的案例扩展为一组。为了获得跨越所有组的具有代表性的负载情况的最小集合，将问题表述为集合覆盖优化，并使用保证最优解的整数线性规划（ILP）进行求解。所提出的方法减少了结构尺寸所需的载荷案例总数，从而减少了计算工作量，同时通过精确和严格的数学公式确保了所有关键场景的完全覆盖。

引用次数: 0

Flexible composite phase change material with highly latent heat enables superior temperature uniformity for high-power batteries 具有高潜热的柔性复合相变材料为大功率电池提供了优越的温度均匀性

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-03 DOI: 10.1016/j.ast.2026.111811

Yuxiang Wang , Wei Wang , Yawei Xu , Yong Shuai

Extreme thermal control technology based on phase change heat storage has important scientific value and practical significance for ultra-high heat flux density thermal control serving aerospace, high-power electronic equipment, and semiconductor integrated circuits. This study addresses the critical limitations of traditional phase change materials (PCM), including low thermal conductivity and latent heat, leakage, and rigidity, by developing a novel flexible composite PCM (CPCM) for advanced thermal management. The CPCM was fabricated via a hybrid hot-press method using paraffin (PA) as the phase change matrix, olefin block copolymer (OBC) and styrene-ethylene-butylene-styrene (SEBS) as encapsulation supports, and expanded graphite (EG) as a thermal conductive filler. The optimized CPCM with a PA/OBC/SEBS ratio of 16:2:2 and containing 5 wt % EG exhibited a leakage rate of 4.75 % after 70 thermal cycles. Its mechanical flexibility was significantly enhanced, with the maximum strain increasing from 36 % to 122 %, while the thermal conductivity improved by 66.7 % to 0.60 W/(m·K), all while maintaining a high latent heat of up to 194 J/g. Numerical simulations of a battery pack consisting of 16 cells further demonstrate that, with PCM-based cooling, the average battery temperature can be effectively regulated and stabilized in the vicinity of the PCM melting temperature (35 °C), even under the 4C discharge condition. Specifically, the average temperature was maintained at 35.13 °C, which is 7.7 °C lower than that achieved using natural convection. These results demonstrate superior temperature uniformity and thermal management performance, highlighting the strong potential of the proposed CPCM for applications in high-power electronics and extreme operating environments.

基于相变蓄热的极端热控制技术对于服务于航空航天、大功率电子设备、半导体集成电路等领域的超高热流密度热控制具有重要的科学价值和现实意义。本研究通过开发一种用于高级热管理的新型柔性复合相变材料（CPCM），解决了传统相变材料（PCM）的关键局限性，包括低导热性和潜热、泄漏和刚性。以石蜡（PA）为相变基体，烯烃嵌段共聚物（OBC）和苯乙烯-乙烯-丁烯-苯乙烯（SEBS）为包封载体，膨胀石墨（EG）为导热填料，采用复合热压法制备CPCM。优化后的CPCM， PA/OBC/SEBS比为16:2:2，含5 wt % EG，经过70次热循环后，泄漏率为4.75 %。其机械柔韧性显著增强，最大应变从36 %增加到122 %，导热系数提高了66.7 %，达到0.60 W/(m·K)，同时保持了高达194 J/g的高潜热。对由16个电池组成的电池组的数值模拟进一步表明，即使在4C放电条件下，基于PCM的冷却可以有效地调节和稳定电池的平均温度在PCM熔化温度（35 °C）附近。具体而言，平均温度维持在35.13 °C，比自然对流低7.7 °C。这些结果证明了优越的温度均匀性和热管理性能，突出了所提出的CPCM在高功率电子和极端操作环境中的应用潜力。

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引用次数: 0

Off-design adjustment strategies and internal flow mechanisms of novel locally adjustable-thickness turbines in variable cycle engine system 变循环发动机系统中新型局部可调厚度涡轮的非设计调节策略及内部流动机理

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-03 DOI: 10.1016/j.ast.2026.111840

Mai Li , Jun Liu , Wenying Ju , Hang Yuan , Pei Wang , Pengfei Wang , Xingen Lu

Variable Geometry Turbines (VGTs) serve as core components of variable cycle engines. Conventional VGTs employ endwall-mounted adjustment mechanisms to achieve variable vane angles for off-design operation. However, under significant off-design conditions, strong separation induced by high-incidence inflow and enhanced endwall leakage flows due to excessive clearances lead to drastic loss increases. This study innovatively proposes a novel turbine blade adjustment scheme enabling localized thickness and throat area modulation through partial suction-side rotation. Using the high-load turbine cascade IET-LPTA as the research object, high-fidelity numerical methods validated by experimental data were employed. These methods were used to systematically investigate internal flow mechanisms under varying suction-side rotation angles (θ) and pivot positions. Detailed analyses of boundary layer, wake, and near-wall parameter variations were conducted, with flow regulation effectiveness and loss characteristics summarized. Results demonstrate that increased θ enhances blade loading, advances boundary layer separation-transition-reattachment events, enlarges separation bubbles, and significantly increases wake and turbulent dissipation losses. Pivot position critically influences separation bubble structure and location. Forward pivots (e.g., 0.6C_x) induce earlier separation and reorganize near-wall low-energy fluid into ‘separation-reattachment-secondary separation-transition-secondary reattachment’ patterns, forming bimodal bubble structures with reduced losses. Both θ and pivot adjustments enable flow regulation, exhibiting nonlinear coupled effects on losses. For flow variations ≤1.5%, θ adjustment optimizes loss performance; beyond this threshold, pivot adjustment proves superior. Mechanistically, the flow‑capacity variation is dominated by the effective throat‑area change, while the separation characteristics are governed by the redistribution of suction‑side adverse pressure gradient and the resulting boundary‑layer response. This research provides theoretical foundations and design guidelines for high-performance VGT development.

可变几何涡轮（vgt）是可变循环发动机的核心部件。传统的vgt采用端壁式调整机构来实现非设计操作的可变叶片角度。然而，在严重的非设计条件下，高入射流入引起的强分离和过大间隙引起的端壁泄漏流动增强导致损失急剧增加。本研究创新性地提出了一种新的涡轮叶片调节方案，通过部分吸力侧旋转实现局部厚度和喉道面积的调节。以高负荷涡轮叶栅IET-LPTA为研究对象，采用经实验数据验证的高保真数值方法。这些方法用于系统地研究不同吸侧旋转角度（θ）和支点位置下的内部流动机制。详细分析了边界层、尾迹和近壁参数的变化，总结了流动调节效果和损失特性。结果表明，θ的增加增加了叶片载荷，加速了边界层分离-过渡-再附着事件，增大了分离泡，并显著增加了尾迹和湍流耗散损失。支点位置对分离泡的结构和位置影响很大。正向支点（如0.6Cx）诱导了更早的分离，并将近壁低能流体重组为“分离-再附着-二次分离-过渡-二次再附着”模式，形成双峰气泡结构，减少了损失。θ和枢轴调节都可以调节流量，对损失表现出非线性耦合效应。当流量变化≤1.5%时，θ调节可优化损失性能；超过这个阈值，支点调整被证明是更好的。从机理上讲，流动能力的变化主要受有效喉道面积变化的支配，而分离特性则受吸力侧逆压梯度的重新分布和由此产生的边界层响应的支配。本研究为高性能VGT的开发提供了理论基础和设计指导。

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引用次数: 0

Fast trajectory optimization with time-varying chance-constrained model predictive control of quadcopters for dynamic collision avoidance 基于时变机会约束模型的四轴飞行器动态避碰快速轨迹优化预测控制

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-03 DOI: 10.1016/j.ast.2026.111815

D.M.K.K. Venkateswara Rao , Hamed Habibi , Holger Voos

In this paper, we propose a parallelized optimization-based framework for autonomous and safe control of quadrotor Unmanned Aerial Vehicles (UAVs). We achieve this by designing a real-time optimal trajectory planner and a time-varying collision chance-constrained model predictive controller. We consider an obstacle with unknown dynamics in the operational space of the UAV and plan time-optimal transfer maneuvers using the shifted Chebyshev pseudospectral method. We propose a novel sigmoid function-based approximation to the conditional collision avoidance constraint of UAV trajectory segments and enable automatic differentiation for achieving real-time implementation. Given the uncertain positions of the UAV and the obstacle, we propose a time-varying probability margin for the collision avoidance constraint and design a chance-constrained model predictive controller to track the reference optimal trajectory with minimum tracking error and avoid collisions in real-time. Moreover, we parallelize the trajectory planner and the controller to address their asynchronous computational execution. The scalability and effectiveness of the proposed architecture are evaluated by performance analysis through Monte Carlo and numerical simulations. Finally, the real-time feasibility of the integrated approach is validated by indoor high-speed maneuvers and dynamic collision avoidance experiments.

本文提出了一种基于并行优化的四旋翼无人机自主安全控制框架。我们通过设计实时最优轨迹规划器和时变碰撞机会约束模型预测控制器来实现这一目标。考虑无人机作战空间中存在未知动力学障碍，利用移位切比雪夫伪谱法规划时间最优转移机动。我们提出了一种新的基于s型函数的无人机轨迹段条件避碰约束近似方法，并实现了自动微分，实现了实时实现。针对无人机和障碍物位置的不确定性，提出了时变概率裕度的避碰约束，设计了机会约束模型预测控制器，以最小的跟踪误差跟踪参考最优轨迹，实现了实时避碰。此外，我们将轨迹规划器和控制器并行化，以解决它们的异步计算执行问题。通过蒙特卡罗性能分析和数值模拟，对该体系结构的可扩展性和有效性进行了评价。最后，通过室内高速机动和动态避碰实验验证了该综合方法的实时性可行性。

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引用次数: 0

Task allocation with communication coordination in UAV swarms via asynchronous multi-Objective policy optimization 基于异步多目标策略优化的无人机群通信协调任务分配

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-03 DOI: 10.1016/j.ast.2026.111760

Zehao Xiong, Yexun Xi, Yizhe Cao, Chuan Li, Rong Li, Jie Li

Task allocation in UAV swarms is becoming increasingly complex due to the complexity of tasks, communication limitations, and the robustness of the allocation algorithm. Combining reinforcement learning and task allocation demonstrates great potential in enhancing algorithm performance and optimizing communication. However, existing research has overlooked the structural conflict between task conflicts and communication overhead, which leads to significant challenges in exploration and training instability. To this end, this paper introduces the Task Allocation with Communication Coordination (TACC) method, which aims to train a gated mechanism strategy to coordinate communication timing while balancing transmission efficiency and allocation reliability. First, the TACC is formalized as a POMDP, for which the channel access and other features are designed to facilitate observations. Actions are inter-agent adaptive gating mechanisms, and the shared reward reflects global task conflicts. Second, to address the asynchronous learning under the CTDE, an asynchronous experience aggregation method is proposed to align trajectories from different agents. Then, the MOCPO is proposed, which applies constrained policy optimization directly to the policy gradient via a Lagrangian loss, thereby stabilizing gated communication early in training and enhancing sample efficiency and convergence. The computational complexity, boundary conditions, convergence, and communication complexity of the TACC are theoretically analyzed. Finally, sim-to-real experiments are conducted in the HIL environment, and the results demonstrate the optimal trade-off achieved by the proposed method and its overall state-of-the-art approaches. Ablation studies and hyperparameter experiments further validated the stability of MOCPO. Specifically, the communication strategy is effectively deployed in the RK3588 SOC, and the flight experiment demonstrates the superior scheduling outcomes of TACC within the ten-UAV swarm in the search and rescue scenario.

由于任务的复杂性、通信的局限性和分配算法的鲁棒性，无人机群中的任务分配变得越来越复杂。将强化学习与任务分配相结合，在提高算法性能和优化通信方面具有很大的潜力。然而，现有的研究忽略了任务冲突和通信开销之间的结构性冲突，这导致了探索和训练不稳定性方面的重大挑战。为此，本文引入了带有通信协调的任务分配（TACC）方法，该方法旨在训练一种门控机制策略来协调通信时序，同时平衡传输效率和分配可靠性。首先，将TACC形式化为POMDP，为POMDP设计通道访问和其他功能以方便观察。行为是agent间的自适应门控机制，共享奖励反映了全局任务冲突。其次，为了解决CTDE下的异步学习问题，提出了一种异步经验聚合方法来对齐来自不同智能体的轨迹。然后，提出了MOCPO算法，该算法通过拉格朗日损失直接对策略梯度进行约束策略优化，从而在训练早期稳定门控通信，提高样本效率和收敛性。从理论上分析了TACC的计算复杂度、边界条件、收敛性和通信复杂度。最后，在HIL环境中进行了模拟到真实的实验，结果证明了所提出的方法及其总体最新方法所实现的最佳权衡。烧蚀研究和超参数实验进一步验证了MOCPO的稳定性。具体而言，该通信策略在RK3588 SOC中得到了有效的部署，飞行实验验证了TACC在10架无人机群搜救场景下的优越调度效果。

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引用次数: 0

A General Analysis Framework for Multirotor Thrust-Vectoring Vehicles: From Configuration to Modeling to Data-Driven Approaches 多旋翼推力矢量飞行器的通用分析框架：从配置到建模再到数据驱动方法

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-03 DOI: 10.1016/j.ast.2026.111816

Yongjie Shu , Qingkai Meng , Shiyi Wei , Mingkai Ding , Yunyi Wang , Xixing Long , Zhifang Ke , Wei Wei

By actively modulating thrust directions, multi-rotor thrust-vector aerial vehicles (TVAVs) overcome the underactuation inherent in conventional coplanar multirotor systems, thereby enabling enhanced maneuverability, full-attitude control, and robust operation in confined or highly disturbed environments. With increasing structural complexity and actuation redundancy, research efforts have progressively evolved from configuration design and aerodynamic analysis toward system-level dynamic modeling and, more recently, data-driven methodologies. This paper presents a comprehensive review of the research evolution in multi-rotor TVAVs, beginning with a summary of configuration and structural analysis methods that explicitly consider thrust-vectoring layouts and aerodynamic effects, and their influence on attainable force spaces, aerodynamic force distribution, and control capabilities. Subsequently, dynamic modeling approaches and investigations into system dynamic properties are reviewed, together with model-based trajectory generation and full-attitude control methods that ensure dynamic feasibility. Furthermore, recent advances in data-driven and reinforcement learning–based methods are systematically discussed, highlighting their potential in addressing strong nonlinearities, model uncertainties, and aggressive maneuvering tasks. Finally, the advantages and limitations of different research paradigms are compared, and the central role of control allocation in thrust-vectoring control architectures is examined, with the aim of providing a structured perspective on the evolution from configuration analysis to dynamic modeling and data-driven methods, and of offering insights toward future unified frameworks that integrate structural constraints, aerodynamic characteristics, model-based design, and data-driven intelligence.

通过主动调节推力方向，多旋翼推力矢量飞行器（tvav）克服了传统共面多旋翼系统固有的欠驱动，从而增强了机动性、全姿态控制和在受限或高扰动环境下的鲁棒性。随着结构复杂性和驱动冗余的增加，研究工作逐渐从配置设计和空气动力学分析发展到系统级动态建模，以及最近的数据驱动方法。本文综述了多旋翼tvav的研究进展，首先总结了明确考虑推力矢量布局和气动效应的构型和结构分析方法，以及它们对可得力空间、气动力分布和控制能力的影响。随后，回顾了动态建模方法和对系统动态特性的研究，以及基于模型的轨迹生成和确保动态可行性的全姿态控制方法。此外，系统地讨论了数据驱动和基于强化学习的方法的最新进展，强调了它们在解决强非线性、模型不确定性和激进机动任务方面的潜力。最后，比较了不同研究范式的优势和局限性，并考察了控制分配在推力矢量控制体系结构中的核心作用，旨在为从配置分析到动态建模和数据驱动方法的演变提供结构化视角，并为整合结构约束、气动特性、基于模型的设计和数据驱动智能的未来统一框架提供见解。

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引用次数: 0

Static stability and control characteristics of the double-swept waveriders 双扫波器的静态稳定性及控制特性

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-03 DOI: 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.

双掠式乘波器在高速下保持了优异的空气动力学性能，同时通过涡流升力效应增强了低速特性，为跨宽飞行包线扩展乘波器的应用提供了一种有希望的方法。然而，现有的研究主要集中在基本的气动特性上，对稳定性和可控性的关注有限。为了解决这一问题，采用投影法设计了具有集成控制面的双扫描乘波器。系统分析了其升阻特性、静稳定性和多速度下的可控性。结果表明，该构型在纵向和方向上均保持稳定的静稳定性，而横向静稳定性相对较弱。与超音速和高超声速相比，纵向和方向控制性能在亚音速条件下被证明是优越的，而横向可控性在高超声速条件下显着提高。此外，方向舵偏转对俯仰和滚转通道的影响最小，而俯仰偏转对俯仰/偏航的耦合效应显著。

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引用次数: 0

Experimental optimization of novel B-shaped and C-shaped holes on flat plate and linear cascade models 平板上新型b形孔和c形孔的实验优化及线性级联模型

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-02 DOI: 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.

本研究对平板上的b形孔和c形孔以及线性叶栅模型进行了实验优化，以最大限度地提高冷却效果。通过压敏涂料实验测量绝热冷却效果，并采用响应面法进行冷却效果预测。此外，通过粒子图像测速实验对流场进行了分析。膜孔布置在平板上和叶片的四个流向位置，喷油角为45°，无复合角。吹风比为0.5至2.5，密度比为1.5。平板实验中基于孔径的主流雷诺数为10⁴，叶栅实验中基于弦长的主流雷诺数为10⁶。优化结果进一步证明了两种弯曲膨胀孔的冷却潜力。b型孔的效率提高幅度最大，为29.6%，c型孔的效率提高幅度最大，为46.7%。优化的b形孔和c形孔抑制了冷却剂的上升，实现了全膜覆盖。性能的提高主要是由于沿展向的出口宽度的增加，这引起了射流的分岔，并通过增强的反旋转涡对显著加强了冷却剂的横向扩散。吸力侧优化效果最高，平板次之，压力侧优化效果最低。结构参数对冷却效果的影响与壁面曲率无关，可以将平板优化结果应用于叶片。

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引用次数: 0

High-fidelity three-dimensional aerodynamic flow prediction on wings with physics-constrained dual-parallel attention UNet++ 基于物理约束的双平行注意unet++的高保真三维机翼气动流动预测

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-02 DOI: 10.1016/j.ast.2026.111846

Rongfeng Cui (崔榕峰) , Qiao Zhang (张巧) , Weiwei Zhang (张伟伟) , Wenbo Lu (鲁文博) , Liangjie Gao (高亮杰)

Accurate flow field data provide a robust foundation for analyzing concentrated force distribution and implementing flow control strategies. Nevertheless, current deep neural network methods exhibit limitations in accuracy when applied to reconstruct three-dimensional wing flow fields. To address this challenge, we propose an intelligent flow field reconstruction technique termed physics-constrained Dual-Parallel Attention UNet++ (DPAtt-UNet++). This method utilizes the Unet++ neural network architecture as its backbone, integrating a dual-parallel attention mechanism and nested network structure. Furthermore, a physics-constrained hierarchical loss function is introduced, incorporating the residuals of the governing Navier-Stokes equations as soft constraints to enforce physical consistency during training. Comprehensive evaluations demonstrate that the proposed DPAtt-UNet++ outperforms not only the baseline U-Net by approximately 10% in reconstruction accuracy, but also shows clear improvements over both standard UNet++ and a non-physics-constrained DPAtt-UNet++, validating the effectiveness of the integrated attention mechanism and physical constraints. Tests on wings constructed from different airfoil profiles confirm robust generalization capability across varying flow conditions and geometric shapes. Moreover, the method achieves approximately 2–3 orders of magnitude faster reconstruction speed compared to the Computational Fluid Dynamics (CFD) method in the online prediction phase. These results demonstrate the method can accurately and efficiently reconstruct flow fields for different geometries under various flow conditions.

准确的流场数据为分析集中力分布和实施流动控制策略提供了坚实的基础。然而，目前的深度神经网络方法在重建三维机翼流场时存在精度上的局限性。为了解决这一挑战，我们提出了一种智能流场重建技术，称为物理约束双并行注意力UNet++ (DPAtt-UNet++)。该方法以unet++神经网络架构为骨干，集成了双并行注意力机制和嵌套网络结构。此外，引入了物理约束的分层损失函数，将控制Navier-Stokes方程的残差作为软约束，以加强训练期间的物理一致性。综合评估表明，所提出的DPAtt-UNet++不仅在重建精度上优于基线U-Net约10%，而且在标准UNet++和非物理约束DPAtt-UNet++的基础上都有明显改进，验证了综合注意力机制和物理约束的有效性。对不同翼型结构的机翼进行了测试，证实了在不同流动条件和几何形状下的强大泛化能力。在在线预测阶段，该方法的重建速度比计算流体力学（CFD）方法快约2-3个数量级。结果表明，该方法可以准确、有效地重建不同几何形状、不同流动条件下的流场。

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引用次数: 0