Aerospace Science and Technology最新文献_第9页

Investigation on the cooling characteristics of turbine blades with bionic fractal channels under typical gas-thermal parameters 典型气热参数下仿生分形通道涡轮叶片冷却特性研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-02-02 DOI: 10.1016/j.ast.2026.111842

Xinzi Liu , Longfei Wang , Wang Lei , Junkui Mao , Chengliang Lv , Dewei Zhang , Yiming Liu , Zhongran Chi

Fractal channels, characterized by high surface-to-volume ratio and geometric flexibility, demonstrate significant potential in turbine blade cooling design. This study experimentally and numerically investigates a turbine blade equipped with a tree-like bionic fractal channel under multi-parameter coupling working conditions, focusing on the effects of blowing ratio, temperature ratio, and mainstream Reynolds number. The results indicate that the three parameters independently influence blade cooling effectiveness with minimal coupling interaction. As temperature ratio increases, the sensitivity of cooling effectiveness to blowing ratio amplifies significantly. Cooling effectiveness improves with higher blowing ratio and lower reynolds number, showing the greatest responsiveness to blowing ratio variations. Consequently, optimal design of bionic fractal cooling architectures must account for operational parameters. The spatial distribution density of tree-like bionic fractal channels at the mid-chord position notably affects localized cooling characteristics, with a 6.5 % enhancement observed in the test region upon increasing channel number. A systematic reduction in fractal channel inlet diameter along the chordwise direction regulates cooling air mass flow rate to match spatially varying heat loads, resulting in a 150 % disparity in internal wall heat transfer coefficients between the blade leading and trailing edges. These findings confirm that fractal channel configuration and geometric parameters are primary factors influencing cooling effectiveness distribution through localised flow modulation, establishing them as critical optimisation targets.

分形通道具有高表面体积比和几何灵活性的特点，在涡轮叶片冷却设计中显示出巨大的潜力。实验和数值研究了多参数耦合工况下具有树状仿生分形通道的涡轮叶片，重点研究了吹风比、温度比和主流雷诺数对叶片的影响。结果表明，三个参数对叶片冷却效果的影响是独立的，且耦合作用最小。随着温度比的增大，冷却效果对吹气比的敏感性显著增强。吹气比越高、雷诺数越低，冷却效果越好，对吹气比变化的响应性越强。因此，仿生分形冷却结构的优化设计必须考虑运行参数。中弦位置树形仿生分形通道的空间分布密度显著影响局部冷却特性，随着通道数量的增加，测试区域的局部冷却特性增强了6.5%。分形通道入口直径沿弦向的系统性减小调节了冷却空气质量流量，以匹配空间变化的热负荷，导致叶片前后缘的内壁传热系数相差150%。这些发现证实了分形通道结构和几何参数是影响局部流动调制冷却效率分布的主要因素，并将其作为关键优化目标。

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引用次数: 0

Geometry-informed neural operator for predicting surface flow field of 3D variable-geometry aerospace vehicles across a wide-speed range 三维变几何飞行器大速度范围表面流场预测的几何信息神经算子

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-31 DOI: 10.1016/j.ast.2026.111784

Yiwei Feng , Kai Chen , Hao Lou , Lili Lv , Liang Xu , Xiaoguang Hu , Bangcheng Ai

The rapid iteration of modern aerospace vehicle design necessitates fast and reliable aerodynamic evaluation during the conceptual design phase. Computational fluid dynamics (CFD) methods, while reliable, are computationally expensive for evaluating hundreds or thousands of configurations. This work presents a data-driven geometry-informed neural operator (GINO) for the end-to-end prediction of surface flow fields for a specific class of 3D aerospace vehicles across a wide-speed range. Specifically, in GINO, graph neural operators (GNOs) are employed to encode and address arbitrary vehicle topologies and surface flow fields, and Fourier neural operator (FNO) is utilized to approximate the solution operator of the Reynolds-Averaged Navier-Stokes (RANS) equations while capturing the multi-scale flow field features. The model is trained on a limited dataset consisting of 120 high-fidelity CFD samples. The dataset covers 5 different 3D vehicle geometries, each across a wide range of Mach numbers and angles of attack. The results demonstrate that the GINO model is able to handle variable geometries across subsonic, transonic, and supersonic speed regimes, and predicts flow fields that agree well with CFD simulations, successfully capturing key flow features and achieving acceptable accuracy in global aerodynamic drag coefficients C_D on both training and test sets. Notably, through operator fusion and other optimizations, GINO attains second-scale inference times for aerospace vehicles with hundreds of thousands of surface grid elements. The GINO model shows promising potential in terms of generalization capability and computational efficiency within the design space, and provides as an attractive alternative for rapid aerodynamic evaluation in the early-stage design of aerospace vehicles.

现代航空航天飞行器设计的快速迭代要求在概念设计阶段进行快速可靠的气动评估。计算流体动力学（CFD）方法虽然可靠，但对于评估数百或数千种配置来说，计算成本很高。这项工作提出了一种数据驱动的几何信息神经算子（GINO），用于在宽速度范围内对特定类别的3D航空航天飞行器的表面流场进行端到端预测。具体而言，在GINO中，利用图神经算子（GNOs）对任意车辆拓扑和表面流场进行编码和寻址，利用傅立叶神经算子（FNO）在捕获多尺度流场特征的同时逼近reynolds -平均Navier-Stokes （RANS）方程的解算子。该模型在由120个高保真CFD样本组成的有限数据集上进行训练。该数据集涵盖了5种不同的3D车辆几何形状，每种几何形状都跨越了马赫数和攻角的广泛范围。结果表明，GINO模型能够处理亚音速、跨音速和超声速范围内的可变几何形状，并且预测的流场与CFD模拟非常吻合，成功捕获了关键的流动特征，并在训练集和测试集上获得了可接受的全局气动阻力系数CD精度。值得注意的是，通过算子融合和其他优化，GINO获得了具有数十万个表面网格元素的航天飞行器的二级推理时间。GINO模型在设计空间内的泛化能力和计算效率方面显示出良好的潜力，为航空航天飞行器早期设计的快速气动评估提供了一种有吸引力的替代方案。

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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 : 2026-06-01 Epub 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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引用次数: 0

Fatigue-resistant structural optimization and vibration testing of a spherical tube fitting in liquid rocket engines 液体火箭发动机球形管件抗疲劳结构优化及振动试验

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-31 DOI: 10.1016/j.ast.2026.111802

Yuliang Wang , Wenjie Ma , Ridong Liao , Kun He , Xuefei Li

Vibration-induced fatigue at stress-concentrated regions is a critical concern for high-pressure pipeline fittings in aerospace propulsion systems. This study focuses on a spherical tube fitting widely used in liquid rocket engines, which experiences high bending stresses at the transition fillet due to assembly preload and dynamic vibration. To enhance its fatigue resistance, we propose a rapid structural optimization framework integrating Latin hypercube sampling, nonparametric regression, and multi-objective genetic algorithms. Two optimized designs were derived based on stiffness compensation and pressure redistribution strategies, reducing peak stress by 19.6% and 7.6%, respectively. A resonance-based vibration fatigue testing system was developed for experimental validation, and strain–life (ε–N) curves were constructed under fully reversed loading. The results confirm substantial improvements in fatigue life, with strain-based fatigue limits increased by 63.7% and 18.3%. The proposed design–test framework is broadly applicable for improving the reliability of vibration-sensitive components in rocket engines and other aerospace systems.

应力集中区域的振动诱发疲劳是航天推进系统中高压管道管件的关键问题。针对液体火箭发动机中广泛应用的一种球形管件进行了研究，该管件在过渡角处由于装配预紧力和动振动而产生了很高的弯曲应力。为了提高其抗疲劳性能，我们提出了一个结合拉丁超立方体采样、非参数回归和多目标遗传算法的快速结构优化框架。基于刚度补偿和压力重分配两种优化设计，峰值应力分别降低19.6%和7.6%。建立了基于共振的振动疲劳试验系统进行试验验证，构建了全反加载下的应变寿命（ε-N）曲线。结果证实了疲劳寿命的显著提高，基于应变的疲劳极限分别提高了63.7%和18.3%。所提出的设计-试验框架可广泛应用于提高火箭发动机和其他航天系统中振动敏感部件的可靠性。

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引用次数: 0

Stability analysis of periodic orbits in thermoacoustic oscillation using state space reconstruction with maximum predictability 基于状态空间重构的热声振荡周期轨道稳定性分析

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-30 DOI: 10.1016/j.ast.2026.111668

Zhuang Ma , Minglong Du , Jinxin Liu , Yun Wu

Combustion instability arises from the coupling between unsteady pressure fluctuations and heat release rate. Stability analysis provides an understanding of the factors that cause this instability. One of transition of stability occurs between discrete periodic oscillations, and previous studies addressing this issue have primarily relied on stability analysis of fixed points. In this study, pressure fluctuations measured in a Helmholtz pulse combustor are analyzed from the perspective of stability for periodic orbits, with experiments conducted by varying the fuel supply pressure from 4 to 23 kPa. To capture the nonlinear characteristics of combustion instability, the dimensionality of the pressure fluctuation series is enhanced using Takens’ embedding, and singular value decomposition is applied to the delay series to identify periodic orbits, focusing on the dominant factors driving combustion oscillations, while the stability of these periodic orbits is determined using Floquet exponents. The main conclusions are as follows: as the fuel supply pressure increases, the oscillations transition from low-amplitude to high-amplitude states(average pulsation value from 7.4 to 14.5 kPa), with the transition process exhibiting mixed-mode oscillations. For low-amplitude oscillations, the system exhibits multi-periodic orbits characterized by a pie-shaped phase space and a unimodal Floquet exponent distribution, confirming that temporal amplitude variations do not significantly alter the stability of the periodic oscillations. In contrast, high-amplitude oscillations approximate a unified limit cycle with a similarly unimodal Floquet exponent distribution, indicating stable periodic oscillations. The transition is marked by a sharp focusing of the period distribution, rapid synchronization, and eventual phase-locking into a unified stable limit cycle. The Floquet multiplier distribution shifts from a negative to a positive and back to a negative peak(-2 to +2 back to 1.8), while the number of dominant modes changes from two to one, clearly signifying that the transition is a dynamical bifurcation process driven by strong nonlinear effects. This phenomenon is explained by potential function.

燃烧不稳定性是由非定常压力波动和热释放速率之间的耦合引起的。稳定性分析提供了对导致这种不稳定性的因素的理解。稳定性的过渡之一发生在离散周期振荡之间，以往的研究主要依赖于不动点的稳定性分析。本研究从周期轨道稳定性的角度分析了亥姆霍兹脉冲燃烧室的压力波动，实验中燃料供应压力在4 ~ 23 kPa范围内变化。为了捕捉燃烧不稳定的非线性特征，采用Takens嵌入法增强压力波动序列的维数，并对延迟序列进行奇异值分解识别周期轨道，重点关注驱动燃烧振荡的主导因素，并利用Floquet指数确定周期轨道的稳定性。主要结论如下：随着供油压力的增大，振荡由低幅值向高幅值状态过渡（平均脉动值为7.4 ~ 14.5 kPa），过渡过程表现为混模振荡；对于低振幅振荡，系统表现出以饼状相空间和单峰Floquet指数分布为特征的多周期轨道，证实了时间振幅变化不会显著改变周期振荡的稳定性。相反，高振幅振荡近似于具有类似单峰Floquet指数分布的统一极限环，表明稳定的周期振荡。过渡的特点是周期分布的尖锐聚焦，快速同步，最终锁相到一个统一的稳定极限环。Floquet乘子分布由负向正，再由负向峰（-2→+2→1.8），主导模态数由2个变为1个，明显表明这种转变是一个受强烈非线性效应驱动的动态分岔过程。这种现象可以用势函数来解释。

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引用次数: 0

Clocking effect on endwall flow and losses in a two-stage low-pressure turbine 两级低压涡轮端壁流动和损失的时钟效应

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-30 DOI: 10.1016/j.ast.2026.111806

Miaoyi Zhu , Yanfeng Zhang , Yuxiang He , Yingqiang Zhang , Xu Dong , Junqiang Zhu

As aeroengines continue to develop toward higher efficiency and higher load, the efficiency of low-pressure turbines (LPTs) has reached a relatively high level, rendering further improvements in their operating efficiency increasingly challenging. The clocking effect has emerged as a potential means to enhance the performance of multistage turbines. On the basis of the unsteady Reynolds-averaged Navier‒Stokes (URANS) method, coupled with the shear stress transport (SST) turbulence model and gamma-theta transition model, this study conducts numerical investigations on a two-stage high-load LPT, focusing on exploring the influence mechanism of clocking on endwall secondary flow structures and loss generation mechanisms. The results demonstrate that the impact of the clocking effect exhibits significant spanwise inhomogeneity, with a prominent regulatory role in the blade tip endwall region. Entropy production analysis indicates that the optimal clocking position achieves spatiotemporal reconstruction of loss generation by delaying the intense dissipation process from the mid-section of the flow passage to the exit region. Vortex dynamics analysis further reveals that the vorticity stretching term of the clocking effect, rather than the baroclinic torque term, is the dominant mechanism governing the evolution of endwall flow. This study clarifies the regulatory mechanism of the clocking effect on endwall flow from the perspective of vortex dynamics, providing a new theoretical basis for the optimization of unsteady interstage flow in turbines.

随着航空发动机不断向高效率、高负荷方向发展，低压涡轮的效率已经达到了较高水平，进一步提高低压涡轮的运行效率越来越具有挑战性。时钟效应已成为提高多级涡轮性能的一种潜在手段。本研究基于非定常reynolds -average Navier-Stokes （URANS）方法，结合剪切应力输运（SST）湍流模型和gamma-theta转捩模型，对两级高负荷LPT进行了数值研究，重点探讨了时钟对端壁二次流结构的影响机理和损失产生机制。结果表明，时钟效应的影响表现出明显的跨向非均匀性，在叶尖端壁区域具有显著的调节作用。熵产分析表明，最佳时钟位置通过延迟从流道中部到出口区域的强烈耗散过程，实现了损失产生的时空重构。旋涡动力学分析进一步揭示了时钟效应的涡度拉伸项，而不是斜压转矩项，是控制端壁流动演变的主要机制。本研究从涡动力学角度阐明了时钟效应对端壁流动的调节机制，为涡轮非定常级间流动的优化提供了新的理论依据。

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引用次数: 0

Aerodynamic performance and loss mechanism analysis of a vaneless counter-rotating fan/compressor 无叶对转风机/压气机气动性能及损失机理分析

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-25 DOI: 10.1016/j.ast.2026.111771

Shi Xu, Teng Fei, Jiabin Li, Lucheng Ji

Vaneless counter-rotating fan/compressors offer potential advantages in reducing axial length and gyroscopic torque in aero-engines; however, the absence of stators can induce large incidence variations at the downstream rotor and degrade off-design performance, particularly under high tip Mach number conditions. To address this issue, the present study investigates a small-scale vaneless counter-rotating fan/compressor configuration that leverages the relatively low circumferential speed at the fan hub in small turbofan engines. A one-dimensional mean-line design coupled with steady RANS simulations in ANSYS CFX (SST k–ω) was used. At the design point, the fan and compressor rotated at 25,500 rpm and 33,000 rpm, with Reynolds numbers on the order of 10⁶ and relative inlet Mach numbers of about 1.1–1.7 in the first compressor rotor. The designed configuration achieved a total pressure ratio of 3.16 and an overall efficiency of 85.1 % at the design point, with a peak efficiency of 85.7 % and a near-stall pressure ratio of 3.24. Under variable back-pressure conditions, the variation in the relative inlet flow angle of the downstream rotor was limited to 25 %–66 % of that observed in a conventional compressor stage, indicating improved angular stability. However, the inlet velocity of the downstream rotor increased by a factor of 1.5–3, which imposed stricter incidence constraints and reduced adaptability at off-design conditions. Detailed flow-field and entropy analyses revealed that the first compressor rotor is the dominant source of aerodynamic loss. Strong shock systems and shock–boundary-layer interactions caused significant entropy generation, particularly in the tip region (85 %–100 % span), where shock–leakage-flow coupling further intensified losses. These results clarify the fundamental loss mechanisms and matching characteristics of small-scale vaneless counter-rotating fan/compressors and provide quantitative guidance for future optimization under compactness and high-Mach-number constraints.

无叶反向旋转风扇/压缩机在减少航空发动机轴向长度和陀螺仪扭矩方面具有潜在的优势；然而，没有定子会在下游转子处引起较大的入射变化，并降低非设计性能，特别是在高叶尖马赫数条件下。为了解决这个问题，本研究研究了一种小型无叶反旋转风扇/压气机配置，该配置利用了小型涡扇发动机风扇轮毂相对较低的周向速度。采用一维均线设计与ANSYS CFX （SST k -ω）稳态RANS仿真相结合。在设计点，风机和压气机分别以25,500 rpm和33,000 rpm转速旋转，压气机第一转子的雷诺数约为10 26，相对进口马赫数约为1.1-1.7。设计构型在设计点的总压比为3.16，总效率为85.1%，其中峰值效率为85.7%，近失速压比为3.24。在变背压条件下，下游转子相对进口气流角的变化被限制在常规压气机级的25%-66%，表明角稳定性得到改善。然而，下游转子的进口速度增加了1.5-3倍，这对入射约束施加了更严格的约束，降低了非设计条件下的适应性。详细的流场和熵分析表明，压气机第一转子是气动损失的主要来源。强激波系统和激波-边界层相互作用导致了显著的熵生成，特别是在尖端区域（85%-100%跨度），激波-泄漏-流动耦合进一步加剧了损失。这些结果阐明了小型无叶对转风机/压缩机的基本损失机制和匹配特性，并为未来在紧凑性和高马赫数约束下的优化提供了定量指导。

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引用次数: 0

A Weight Redistributed GM-PHD filter Accounting for Stochastic Missed Detection 一种考虑随机漏检的权重重分布GM-PHD滤波器

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-02-05 DOI: 10.1016/j.ast.2026.111849

Liu Zeya , Zhai Guang , Wei Shijun

Multi-Target tracking is significantly challenging due to the complicities of data association and trajectory correlation. Discontinuous observation sequences evidently cause interruptions on both data association and trajectory correlation, and finally resulting target tracking loss and missed alerts. The Gaussian Mixture Probability Hypothesis Density (GM-PHD) filter is commonly used in multi-target tracking. Under the assumption of constant target detection probability, GM-PHD filter accurately estimates the number of targets and their motion states. However, when the sensor experiences stochastic missed detection of any target member, traditional GM-PHD filter immediately terminates the corresponding trajectory, and subsequently results in target loss and missed alert. To eliminate the risk of missed alerts caused by missed detections, a GM-PHD filter characterized by weight-redistribution is proposed by introducing a dynamic adjustment mechanism on target detection probability, this robust filter guarantees both the estimate accuracy on target number and the tracking stability even stochastic missed detection occurs. Simulation results across multiple scenarios are carried out to demonstrate the significance of the proposed filter.

由于数据关联和轨迹关联的复杂性，多目标跟踪具有很大的挑战性。不连续的观测序列会导致数据关联和轨迹关联的中断，最终导致目标跟踪丢失和漏报。高斯混合概率假设密度滤波（GM-PHD）是多目标跟踪中常用的滤波算法。在目标检测概率恒定的假设下，GM-PHD滤波器能准确估计目标数量及其运动状态。然而，传统的GM-PHD滤波器在随机漏检到目标成员时，会立即终止相应的轨迹，导致目标丢失和漏检报警。为了消除因漏检而导致的漏检报警风险，通过引入目标检测概率的动态调整机制，提出了一种以权重重分配为特征的GM-PHD滤波器，该滤波器在随机漏检情况下，既保证了对目标数的估计精度，又保证了跟踪的稳定性。在多个场景下的仿真结果证明了所提出的滤波器的重要性。

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引用次数: 0

Scalable flexible membranes with photonic structures for aerospace radiative cooling in stratospheric environment 具有光子结构的可伸缩柔性薄膜在平流层环境中用于航空航天辐射冷却

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-21 DOI: 10.1016/j.ast.2026.111751

Chenrui Fu , Ming Zhu , Zhanpeng Ye , Da Zhao , Zhonghuai Wu , Dongxu Liu

Currently, radiative cooling technologies are widely applied in traditional ground-based applications such as buildings, clothing, and solar cells, but research on stratospheric applications remains limited. Compared to ground-based applications, stratospheric conditions are more extreme, and the radiative cooling effect is influenced by factors such as solar radiation, wind speed, humidity, and orientation. In this study, we designed multilayer nanoparticle-polymer metamaterials (MNPM) and silica/Ag specimens suitable for stratospheric environments, which were deployed on the top, side, and bottom of a high-altitude balloon platform with a propulsion system for flight tests. Under natural convection conditions, which do not consume propulsion power, the side-mounted MNPM achieved a maximum cooling of 21.2°C at noon compared to the silica/Ag. Under forced convection conditions, the side-mounted MNPM achieved a maximum cooling of 15.6°C at noon. When there were no cold clouds in the surrounding area at night, the bottom-mounted MNPM achieved a maximum cooling of 7°C. When influenced by radiation from cold clouds below at night, the top-mounted MNPM achieved a maximum cooling of 2.4°C. These results provide valuable insights into the feasibility of radiative cooling technology for stratospheric applications and lay the foundation for thermal management systems for future stratospheric vehicles that do not rely on external energy sources.

目前，辐射冷却技术广泛应用于传统的地面应用，如建筑物、服装和太阳能电池，但对平流层应用的研究仍然有限。与地面应用相比，平流层条件更为极端，辐射冷却效果受太阳辐射、风速、湿度和方向等因素的影响。在这项研究中，我们设计了适合平流层环境的多层纳米粒子-聚合物超材料（MNPM）和二氧化硅/银样品，并将其放置在带有推进系统的高空气球平台的顶部、侧面和底部进行飞行试验。在不消耗推进功率的自然对流条件下，与二氧化硅/Ag相比，侧面安装的MNPM在中午达到了21.2°C的最大冷却。在强制对流条件下，侧向安装的MNPM在中午达到15.6°C的最大冷却。当夜间周围无冷云时，底部安装的MNPM最大降温温度为7°C。当夜间受到下面冷云辐射的影响时，顶部安装的MNPM实现了2.4°C的最大冷却。这些结果为辐射冷却技术在平流层应用的可行性提供了宝贵的见解，并为未来不依赖外部能源的平流层飞行器的热管理系统奠定了基础。

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引用次数: 0

Heat and mass transfer characterization of gap and sealed porous media under hypersonic airflow 高超声速气流作用下间隙和密封多孔介质的传热传质特性

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-31 DOI: 10.1016/j.ast.2026.111836

Yihang Ren , Guiping Lin , Haichuan Jin , Kuiyuan Ma

Due to structural and functional requirements, the surfaces of hypersonic vehicles often incorporate gaps. External hypersonic flow environments facilitate heat and mass transfer through these gap structures and into the cabin interior. Porous sealing components are typically employed to seal the gap structures, yet current thermal sealing designs lack theoretical guidance. This study investigates the heat and mass transfer processes at hypersonic vehicle gap structures. Numerical simulations analyse the fluid-structure interaction heat transfer within the gap structure over 1200 s. Compared to scenarios that ignore structural deformation, deformation has a significant impact on heat and mass ingress, increasing them by 47.3% and 17.8%, respectively. Thus, deformation cannot be neglected for small-scale gap structures. By varying structural and operating parameters, this study elucidates the influence mechanisms of flow pressure, flow static temperature, Mach number, angle of attack, and initial gap width on heat and mass transfer within the gap flow. A porous medium seal component filled to a specific depth within the gap achieves thermal insulation efficiency of up to 88.3% and mass sealing efficiency of up to 92%. Building upon this, the study further investigates the effects of porosity and permeability on sealing performance. This research provides theoretical guidance for the design and optimization of gap thermal sealing structures for long-endurance hypersonic vehicles.

由于结构和功能的要求，高超声速飞行器的表面经常包含间隙。外部高超声速流动环境促进热量和质量通过这些间隙结构和进入机舱内部传递。多孔密封元件通常用于密封间隙结构，但目前的热密封设计缺乏理论指导。研究了高超声速飞行器间隙结构的传热传质过程。数值模拟分析了1200s间隙结构内流固耦合换热过程。与不考虑结构变形的情况相比，变形对热量和质量进入的影响显著，分别增加47.3%和17.8%。因此，对于小尺度间隙结构，变形是不可忽视的。通过改变结构参数和工作参数，研究了流动压力、流动静态温度、马赫数、攻角和初始间隙宽度对间隙流内部传热传质的影响机理。在间隙内填充一定深度的多孔介质密封元件，保温效率可达88.3%，质量密封效率可达92%。在此基础上，进一步研究了孔隙度和渗透率对密封性能的影响。该研究为长航时高超声速飞行器间隙热密封结构的设计与优化提供了理论指导。

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引用次数: 0