Aerospace Science and Technology最新文献

Drag dependency aspects in Hyperloop aerodynamics 超级高铁空气动力学中的阻力依赖性问题

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-11-13 DOI: 10.1016/j.ast.2024.109722

Domenik Radeck , João Nicolau , Vladislav Kukharskii , Lucía Ojer Guerra , Felix Herkenrath , Inés Velasco Martínez , Jonathan Pflüger , Agnes Jocher , Christian Breitsamter

The Hyperloop system is promising a viable solution for fast, sustainable, and economic travel between cities.

This paper investigates the challenging topic of Hyperloop aerodynamics via extensive numerical simulations. The study is divided based on the speed relative to the geometric Kantrowitz limit to manage the computational resources effectively. Below this limit, which marks the transition to choked flow, we conducted a cross-validation among an axisymmetric 2D model, a similar 3D geometry, and a realistic 3D geometry for blockage ratio 0.5 at several speeds. A definitive range for drag was determined, notably low absolute drag values were observed, and the 2D axisymmetric simplification was put into perspective.

Above the choked flow condition, we undertook two resource-intensive simulations of the 2D setup, accelerating through several kilometers of tube. This methodology allowed us to shed light on the drag behavior that emerges under transient conditions. The existence of three regimes outlined by literature is corroborated by our study. Nevertheless, distinct variations emerge between the analyses, notably in the configuration of the shock wave structure, the linear increment of drag at a constant velocity, and the influence of the pod's acceleration profile in the flow structure.

The study broadens the understanding of Hyperloop aerodynamics and offers realistic drag data for both choked and non-choked flow.

Hyperloop 系统有望成为城市间快速、可持续和经济旅行的可行解决方案。本文通过大量数值模拟研究了 Hyperloop 空气动力学这一具有挑战性的课题。为了有效管理计算资源，研究根据相对于几何康特洛维茨极限的速度进行划分。在此极限以下，即过渡到窒息流时，我们对轴对称二维模型、类似的三维几何图形和阻塞率为 0.5 的现实三维几何图形在几种速度下进行了交叉验证。我们确定了阻力的明确范围，观察到明显较低的绝对阻力值，并对二维轴对称简化进行了深入分析。在窒息流条件之上，我们对二维设置进行了两次资源密集型模拟，加速通过数公里长的管道。通过这种方法，我们得以了解瞬态条件下出现的阻力行为。我们的研究证实了文献中概述的三种状态的存在。尽管如此，分析结果之间仍存在明显差异，主要体现在冲击波结构的配置、匀速时阻力的线性递增以及吊舱加速度曲线对流动结构的影响。

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引用次数: 0

Effects of the rotor tip gap on the aerodynamic and aeroacoustic performance of a ducted rotor in hover 转子顶端间隙对悬停中管道式转子气动和气声性能的影响

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-11-13 DOI: 10.1016/j.ast.2024.109734

Reinier J. Goudswaard, Daniele Ragni, Woutijn J. Baars

Ducted rotors are configurations known to outperform their unducted reference baselines when aerodynamic performance is concerned. Aside from aerodynamic benefits in hover, a duct also affects acoustic emissions. One of the most contended design parameters of a duct-rotor assembly is the radial distance between the blade tip and the duct wall, referred to as the “tip gap”. The present study explains how the aerodynamic performance of a ducted-rotor system is affected by the tip-gap distance, taking into account the performance of the rotor and those of the duct's inlet lip and diffuser sections. Separate thrust measurements of the rotor and duct establish that the latter can generate up to half of the total thrust of the assembly. Static wall-pressure measurements along the inner wall of the duct reveal a low pressure suction zone over the duct's inlet lip area. This allows the assembly to generate more thrust than the rotor alone, even though the duct's diffuser section generates a drag component (negative thrust). From the velocity fields it is further shown that the performance-deterioration with an increasing tip gap distance is associated with a contraction of the rotor slipstream in the duct diffuser.

众所周知，在气动性能方面，有风道转子的配置优于无风道参考基线。除了悬停时的气动优势外，风道还会影响声发射。风道旋翼组件最受争议的设计参数之一是叶尖与风道壁之间的径向距离，称为 "叶尖间隙"。本研究解释了风道转子系统的气动性能如何受到叶尖间隙距离的影响，同时考虑了转子的性能以及风道入口唇和扩散器部分的性能。对转子和导管分别进行的推力测量结果表明，后者产生的推力最多可达组件总推力的一半。沿风道内壁进行的静态壁压测量显示，在风道的入口边缘区域有一个低压吸入区。这使得组件产生的推力大于转子单独产生的推力，即使风道的扩散器部分会产生阻力分量（负推力）。速度场进一步表明，随着顶端间隙距离的增加，性能下降与转子滑流在管道扩散器中的收缩有关。

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引用次数: 0

Quasi-static compression response of a novel multi-step auxetic honeycomb with tunable transition strain 具有可调过渡应变的新型多级辅助蜂窝的准静态压缩响应

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-11-13 DOI: 10.1016/j.ast.2024.109730

Shun Wang , Hai-Tao Liu

Auxetic honeycombs with multi-step deformation have received widespread attention due to their multifunctionality and superior mechanical properties. To improve the tunability of the auxetic honeycomb, a novel multi-step auxetic honeycomb (MSAH) is proposed by combining star-rhombic parts with crossed thin walls. MASH is characterized by multi-step deformation, and its stress-strain curve has three significant plateau stages. The strain during the transition between different deformation steps can be adjusted by designing unit cells with different geometrical parameters. In the compression process, the ordered contact of the cell walls of MASH is the critical reason for realizing the multi-step deformation. The quasi-static compression finite element model of MASH is established and verified by experiments. Quasi-static compression response and deformation mechanism of MASH are studied. Then, the effects of geometrical parameters on the compression response of MASH are investigated. The results show that the wall thickness has a greater effect on the compressive stress, and the cell-wall angle determines the deformation mode of MASH. Furthermore, the transition strain of MASH is theoretically analyzed and verified by numerical simulations. This study provides a reference for designing multi-step deformation honeycombs and applying multi-stage energy absorbers.

具有多级变形的助熔蜂窝因其多功能性和优异的机械性能而受到广泛关注。为了提高辅助蜂窝的可调性，我们提出了一种新型多级辅助蜂窝（MSAH），它将星形菱形部件与交叉薄壁结合在一起。MASH 具有多级变形的特点，其应力-应变曲线有三个重要的高原阶段。通过设计具有不同几何参数的单元格，可以调整不同变形步骤之间过渡阶段的应变。在压缩过程中，MASH 单元壁的有序接触是实现多级变形的关键原因。本文建立了 MASH 的准静态压缩有限元模型，并通过实验进行了验证。研究了 MASH 的准静态压缩响应和变形机理。然后，研究了几何参数对 MASH 压缩响应的影响。结果表明，壁厚对压缩应力的影响较大，细胞壁角度决定了 MASH 的变形模式。此外，还对 MASH 的过渡应变进行了理论分析和数值模拟验证。这项研究为设计多级变形蜂窝和应用多级能量吸收器提供了参考。

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引用次数: 0

Experimental and numerical characterization of E-glass/epoxy plain woven fabric composites containing void defects 含空隙缺陷的 E 玻璃/环氧平织布复合材料的实验和数值特性分析

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-11-13 DOI: 10.1016/j.ast.2024.109731

Nagappa Siddgonde , Vikas Kaushik , Anup Ghosh

The presence of voids in woven fabric composite (WFC) significantly affects the mechanical and thermomechanical properties. Void defects are introduced during the resin infiltration process due to various controlling parameters involved in the curing process, i.e., pressure, temperature, resin flow etc. In this study, the mechanical constants of 2D woven fabric composite were experimentally determined. A finite element (FE) based representative volume element (RVE) model has been validated against these experimental results. A multiscale-based FE model has been developed, and periodic boundary conditions are applied to the RVE model to evaluate the homogenized thermomechanical properties of WFC containing void defects. Present numerical model incorporates the geometrical microstructures of the post-cured woven composite and void contents obtained from X-ray microtomography. The influence of void defect and resin infiltration have been incorporated to evaluate the thermomechanical properties of plain WFC. A parametric study has been carried out with respect to the variation of void defects on thermoelastic properties of E-glass/epoxy plain WFC. The variation of void defects has been considered in micro and mesoscale models. Monte Carlo simulations further quantified the effects of void content on the thermomechanical constants of WFC. The presence of voids has been observed to have significant influences on the thermomechanical constants of yarn and woven fabric composites.

编织物复合材料（WFC）中存在的空隙会严重影响其机械和热机械性能。由于固化过程中涉及到各种控制参数，如压力、温度、树脂流量等，在树脂浸润过程中会产生空隙缺陷。本研究通过实验确定了二维编织物复合材料的机械常数。根据这些实验结果验证了基于有限元（FE）的代表性体积元素（RVE）模型。开发了基于多矢量的 FE 模型，并将周期性边界条件应用于 RVE 模型，以评估含有空隙缺陷的 WFC 的均质化热力学特性。本数值模型结合了固化后编织复合材料的几何微观结构和 X 射线显微层析成像获得的空隙含量。空隙缺陷和树脂渗透的影响已被纳入评估普通 WFC 热机械性能的范围。就空隙缺陷对 E 玻璃/环氧树脂普通 WFC 热弹性性能的影响进行了参数研究。在微观和中观模型中考虑了空隙缺陷的变化。蒙特卡罗模拟进一步量化了空隙含量对 WFC 热力学常数的影响。据观察，空隙的存在对纱线和编织物复合材料的热力学常数有显著影响。

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引用次数: 0

Transient gas path fault diagnosis of aero-engine based on domain adaptive offline reinforcement learning 基于域自适应离线强化学习的航空发动机瞬态气路故障诊断

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-11-12 DOI: 10.1016/j.ast.2024.109701

Jinghui Xu, Ye Wang, Zepeng Wang, Xizhen Wang, Yongjun Zhao

Real-time measurement parameters are crucial for diagnosing faults in aero-engine gas path performance, ensuring engine reliability, and mitigating potential economic losses. Traditional aero-engines performance diagnosis was mainly based on the measurements of steady-state condition and lacked the utilization of data under transient conditions. Gas path diagnosis of aero-engines under transient conditions is crucial for early fault detection and safety of flight within the envelope. The challenge lies in the inconsistent distribution of performance deviations caused by variable operating conditions, especially with complex fault types, which can undermine diagnostic credibility. To improve reliability of gas path diagnosis under transient conditions, an offline reinforcement learning fault diagnosis framework based on a transient aero-engine performance model is proposed. To address the issue of variable operating conditions during transient states, a domain adaptive approach is utilized to reconstruct the measurement baseline and facilitate the transfer of different performance deviation distributions. Additionally, by adding spool acceleration as a measurement parameter, the multi-component fault coupling is solved. Finally, validation with actual operating data simulates fault cases, demonstrating the proposed method's efficacy in quantitatively detecting gradual, sudden, and multiple component faults under transient conditions with high accuracy and efficiency. The method proposed in this study achieves a computational speed improvement by 64% compared to the conventional method, achieving a time of 0.13 seconds, with an average error of less than 0.00389%. Additionally, it demonstrates strong robustness in the presence of noise, with an average error of less than 0.03125%. This proposed method improves real-time fault detection under transient conditions for its higher accuracy and efficiency, and therefore significantly enhance gas path health monitoring and diagnosis capability.

实时测量参数对于诊断航空发动机气路性能故障、确保发动机可靠性和减少潜在经济损失至关重要。传统的航空发动机性能诊断主要基于稳态条件下的测量，缺乏对瞬态条件下数据的利用。瞬态条件下的航空发动机气路诊断对早期故障检测和包络线内的飞行安全至关重要。面临的挑战在于，不同的运行条件会导致性能偏差分布不一致，尤其是复杂的故障类型，这会影响诊断的可信度。为了提高瞬态条件下气路诊断的可靠性，提出了一种基于瞬态航空发动机性能模型的离线强化学习故障诊断框架。为解决瞬态期间工作条件多变的问题，采用了域自适应方法来重建测量基线，并促进不同性能偏差分布的转移。此外，通过添加阀芯加速度作为测量参数，解决了多组件故障耦合问题。最后，利用实际运行数据对故障案例进行了模拟验证，证明了所提出的方法在定量检测瞬态条件下的渐变、突变和多组件故障方面具有很高的准确性和效率。与传统方法相比，本研究提出的方法计算速度提高了 64%，耗时仅为 0.13 秒，平均误差小于 0.00389%。此外，该方法在存在噪声的情况下也表现出很强的鲁棒性，平均误差小于 0.03125%。该方法提高了瞬态条件下的实时故障检测精度和效率，从而显著增强了气体路径健康监测和诊断能力。

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引用次数: 0

Corrigendum to “Numerical Study of Cold Flow Characteristics of a New Integrated Afterburner with Strut Flame Stabilizer” [Aerospace Science and Technology 153C (2024) 109476] 带支柱火焰稳定器的新型集成式后燃烧器冷流特性的数值研究"[航天科技 153C (2024) 109476] 更正

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-11-12 DOI: 10.1016/j.ast.2024.109705

Minqiang Li , Zhiwu Wang , Junlin Li

引用次数: 0

Crashworthiness and stiffness improvement of a variable cross-section hollow BCC lattice reinforced with metal strips 用金属条加固的可变截面空心 BCC 网格的耐撞性和刚度改进

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-11-12 DOI: 10.1016/j.ast.2024.109732

Bo Li , Hua Liu , Qiao Zhang , Chuanguo Chai , Jie Wang , Jialing Yang , Xianfeng Yang

The ultra-lightweight structures with high mechanical properties and energy absorption behaviors are focused on the innovation structural design. The design strategy of implementing novel unit cells within architecture materials such as lattice materials enables the attainment of unparalleled combinations of mechanical properties and functionalities while minimizing weight. The most common method to design light-weight lattice materials is optimizing the geometric configurations of the unit cells. However, changing the geometric boundary of lattice structures can also be a good solution to improve the mechanical characteristics and energy absorption behaviors of the lattice materials. In this work, a novel variable cross-section hollow (VCH) lattice was established to improve the energy absorption capacity. By adding metal strips on the edge of the VCH lattices, a new reinforced variable cross-section hollow (RVCH) lattice with metal strips was developed to further enhance the stiffness and energy absorption capacity. The stainless VCH and RVCH lattices were additively manufactured by Selective Laser Melting (SLM) using an EP-M450H metal 3D printer. The quasi-static compressive characteristics and energy absorption behaviors of RVCH lattices were studied experimentally. Finite element modeling was implemented to study the energy absorption mechanism of RVCH lattices. A parametric analysis based on the finite element models was conducted to study the influence of different metal strips on the energy absorption capacity of RVCH lattices. The results show that the RVCH lattices with metal strips attaching to the vertical edges can signally enhance energy absorption of lattice structures with good load uniformity. Furthermore, the natural frequencies analysis indicate that the higher bending stiffness and the tensile stiffness can be achieved for RVCH lattices. This novel lattice is more stable as a load-bearing structure and more efficient as an energy absorber, which can provide guidance in designing innovative lattice structures with excellent mechanical properties and energy absorption capacity.

具有高机械性能和能量吸收性能的超轻结构是创新结构设计的重点。在晶格材料等建筑材料中采用新型单元格的设计策略，可以在最大程度减轻重量的同时，获得无与伦比的机械性能和功能组合。设计轻质晶格材料最常用的方法是优化单元格的几何配置。然而，改变晶格结构的几何边界也是改善晶格材料力学特性和能量吸收行为的一个好办法。本研究建立了一种新型可变截面空心（VCH）晶格，以提高能量吸收能力。通过在 VCH 晶格边缘添加金属条，开发出了一种带有金属条的新型增强型可变截面空心（RVCH）晶格，以进一步提高刚度和能量吸收能力。不锈钢 VCH 和 RVCH 晶格是使用 EP-M450H 金属三维打印机通过选择性激光熔融（SLM）快速制造的。实验研究了 RVCH 晶格的准静态压缩特性和能量吸收行为。通过有限元建模研究了 RVCH 晶格的能量吸收机制。在有限元模型的基础上进行了参数分析，研究了不同金属条对 RVCH 晶格能量吸收能力的影响。结果表明，在垂直边缘附着金属条的 RVCH 晶格能显著增强晶格结构的能量吸收能力，并具有良好的载荷均匀性。此外，固有频率分析表明，RVCH 晶格可以获得更高的弯曲刚度和拉伸刚度。这种新型晶格作为承重结构更稳定，作为能量吸收器更高效，可为设计具有优异力学性能和能量吸收能力的创新晶格结构提供指导。

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引用次数: 0

Corrigendum to “External loads identification and shape sensing on an aluminum wing box: An integrated approach” [Aerospace Science and Technology 114 (2021) 106743] 对 "铝翼盒上的外部载荷识别和形状传感：一种综合方法" [航空航天科学与技术 114 (2021) 106743]

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-11-10 DOI: 10.1016/j.ast.2024.109707

Marco Esposito , Marco Gherlone , Pier Marzocca

引用次数: 0

Fluid-thermal-structural coupled investigation on rudder leading edge with porous opposing jet in high-speed flow 高速流动中带有多孔对向射流的方向舵前缘的流体-热量-结构耦合研究

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-11-10 DOI: 10.1016/j.ast.2024.109725

Shaliang Li, Shibin Li, Wei Huang, Bing Liu

High-speed air rudders face extreme force/thermal environments, and the opposing jet can improve the thermal environment in the stationary point and leading edge. In order to investigate the effect and mechanism of porous opposing jet on the rudder leading edge, the numerical study is carried out by using SST k-ω turbulence model and a loose fluid-thermal-structural coupled approach. The drag reduction and thermal protection mechanism of porous jet with different pressure ratios (PRs) is comprehensively compared and analyzed. The obtained results show that the fluid-thermal-structural coupled approach is necessary for the precise aerodynamic heat prediction of air rudder. The lowest temperature regions distribute in the upstream of orifices due to the jet cooling effect and heat conduction in the solid structure. The PR is an important factor influencing the interaction between jets. The porous opposing jet can provide a good effect in both drag reduction and thermal protection, as the maximum temperature drops to about 40 % from no jet to porous jet. As PR increases, the maximum pressure and temperature also decrease to a larger extent. However, the most PR should be a balanced consideration among the flowfiled, thermal structure and coolant consume.

高速空气舵面临极端的力/热环境，而对向射流可以改善静止点和前缘的热环境。为了研究多孔对向射流对方向舵前缘的影响和机理，采用 SST k-ω 湍流模型和松散的流体-热力-结构耦合方法进行了数值研究。对不同压力比（PRs）的多孔射流的减阻和热保护机理进行了综合比较和分析。结果表明，流体-热力-结构耦合方法是精确预测空气舵气动热量的必要条件。由于喷流冷却效应和固体结构的热传导作用，最低温度区域分布在喷口上游。PR 是影响喷流之间相互作用的重要因素。多孔对向射流在减少阻力和热保护方面都有很好的效果，因为从无射流到多孔射流，最高温度下降了约 40%。随着 PR 的增加，最大压力和温度也会有较大程度的下降。不过，PR 的最大值应在流场、热结构和冷却剂消耗量之间进行平衡考虑。

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引用次数: 0

Aerodynamic study of a bifurcated turboprop engine inlet with a propeller for flow at ground suction conditions 带螺旋桨的分叉涡轮螺旋桨发动机进气口在地面吸力条件下流动的空气动力学研究

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-11-09 DOI: 10.1016/j.ast.2024.109720

Gaojie Zheng , Zhenlong Wu , Huijun Tan , Jiahao Ren , Yue Zhang , Ge Zhou

An advanced turboprop inlet with a bypass duct plays a crucial role in preventing foreign object damage and ensuring a high-quality airflow to the engine. However, it also introduces an increased flow complexity and design challenge due to the interaction between the propeller and the bifurcated ducts. To address these issues, a combined experimental and computational fluid dynamics (CFD) study was conducted on the aerodynamic performance and flowfield characteristics of a turboprop inlet equipped with a bypass duct considering the propeller interference. A ground suction test bench was utilized for generating the working conditions and the performance was measured by using total pressure rakes and pressure scanners. It is found that the rotational propeller on the one hand does work on and thus increases the total pressure recovery of the inlet, however, on the other hand causes a turning effect on the inlet flowfield structure along the direction of rotation and increases total pressure and swirling flow distortions in the engine duct. Besides, the engine duct and the bypass duct interact with each other. The combined influence of suction effect and the profile induction of the inlet leads to the majority of the shed vortices being drawn into the engine duct. Lastly, the presence of deflectors installed in the engine duct is found to effectively mitigate the secondary flow, thereby reducing the swirl distortion within the engine duct. This study may provide a significant reference to the design and optimization of advanced turboprop inlets with bypass ducts.

带旁通管道的先进涡轮螺旋桨飞机进气口在防止异物损坏和确保发动机获得高质量气流方面起着至关重要的作用。然而，由于螺旋桨和分叉管道之间的相互作用，它也增加了流动的复杂性和设计难度。为了解决这些问题，我们结合实验和计算流体动力学（CFD）研究了考虑螺旋桨干扰的涡轮螺旋桨进气口的气动性能和流场特性。利用地面吸力试验台生成工作条件，并使用总压耙和压力扫描仪测量其性能。结果发现，旋转螺旋桨一方面对进气口起作用，从而增加了进气口的总压恢复，但另一方面却对进气口流场结构产生了沿旋转方向的转向效应，增加了发动机风道中的总压和漩涡流变形。此外，发动机风道和旁通风道之间存在相互作用。在吸力效应和进气口轮廓感应的共同影响下，大部分脱落的漩涡被吸入发动机风道。最后，在发动机风道中安装导流板可有效缓解二次流，从而减少发动机风道内的漩涡变形。这项研究可为设计和优化带旁路风道的先进涡轮螺旋桨飞机进气口提供重要参考。

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引用次数: 0