Aerospace Science and Technology最新文献_第7页

Towards scalable on-orbit assembly: Reconfigurable hardware and algorithm design 面向可扩展在轨装配：可重构硬件和算法设计

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.2026.111788

Yao Jiang , Meibao Yao , Xueming Xiao , Huanfeng Zhao , Hutao Cui , Zexu Zhang

In a microgravity environment, modular self-reconfigurable robots can perform a range of on-orbit missions including solar-array deployment, serial-arm assembly, and failed-subsystem replacement, owing to their modular scalability and morphological versatility, tailored to mission-specific constraints and extended across these tasks. However, conventional cubic modules have rotational blind spots and pose-dependent interfaces that inflate alignment burden and trigger collisions and local deadlocks, especially for large-scale deployment. Due to the tight coupling of local motion feasibility in modular robotic systems, coupled with the connectivity and reachability requirements during reconfiguration, task allocation and decision sequencing for large-scale architecture are often NP-hard. To address these issues, we present an integrated reconfigurable hardware-algorithmic solution. Structurally, the concentric, nested spherical design with isotropic geometry and unified locking mechanism reduces sensitivity to pose alignment, mitigates collisions and deadlocks, and expands the reachable workspace. Algorithmically, reconfiguration planning is formulated as an integer programming problem, incorporating penalties to enforce connectivity and reachability constraints within a hierarchical framework. The top level determines the matching and reconfiguration sequence by the proposed Cross-correlation BFS-Tree Genetic Algorithm with Gaussian mutation (CBGA), and the lower level aims at path planning using the designed kinematics-aware parallel A*. Extensive simulation and experiments are conducted with varied number of modular robots. The results demonstrate that the proposed system maintains full connectivity and reachability while achieving rapid convergence with low relocation steps even for large-scale architecture. Such capability thereby establishes its practical viability for autonomous modular reconfiguration in on-orbit missions.

在微重力环境下，模块化自重构机器人可以执行一系列在轨任务，包括太阳能电池阵列部署、串联臂组装和故障子系统替换，因为它们具有模块化可扩展性和形态多功能性，可以根据任务特定的限制进行定制，并在这些任务中进行扩展。然而，传统的立方模块存在旋转盲点和姿态依赖接口，这会增加对齐负担，引发碰撞和局部死锁，特别是在大规模部署时。由于模块化机器人系统中局部运动可行性的紧密耦合，再加上重构过程中的连通性和可达性要求，大规模架构的任务分配和决策排序往往是np困难的。为了解决这些问题，我们提出了一个集成的可重构硬件算法解决方案。在结构上，具有各向同性几何和统一锁定机构的同心嵌套球形设计降低了位姿对准的敏感性，减轻了碰撞和死锁，扩大了可达工作空间。在算法上，重新配置规划被表述为一个整数规划问题，在层次框架中包含强制连接性和可达性约束的惩罚。顶层采用基于高斯突变的互相关BFS-Tree遗传算法（CBGA）确定匹配和重构序列，底层采用设计的运动感知并行算法A*进行路径规划。对不同数量的模块化机器人进行了广泛的仿真和实验。结果表明，该系统在保持完全的连通性和可达性的同时，即使对于大型架构，也能以较低的迁移步骤实现快速收敛。因此，这种能力确定了其在在轨任务中自主模块化重新配置的实际可行性。

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引用次数: 0

Experimental investigation of shock wave effects on transpiration cooling for porous flat plate in hypersonic flow 高超声速流动中激波对多孔平板蒸腾冷却影响的实验研究

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.2026.111837

Yishanchun Lu, Dundian Gang, Yuxin Zhao, Qi Mi, Yuan Feng, Zhiyao Yang, Shikang Chen

Transpiration cooling is widely applied in hypersonic aircraft due to its high cooling effectiveness. However, shock impingement significantly degrades cooling effectiveness. Therefore, investigation on the influence of shock wave on transpiration cooling for porous flat plates under hypersonic conditions is essential. This study focuses on the effects of shock wave intensity and coolant injection rate on transpiration cooling effectiveness at Mach 6. The temperature of the porous plate is measured by infrared thermometry, while the flow-field is observed using schlieren and the Nano-tracer Planar Laser Scattering (NPLS) technology. Results indicate that the cooling effectiveness degrades with the increasing shock intensity. The coolant injection rate non-linearly influences cooling effectiveness, as higher rates enhance mainstream flow interaction and intensify heat exchange. With the injection rate increasing from 0.1% to 1.0%, the cost-effectiveness ratio drops by 88.5% and the thickness of turbulent boundary layer grows by 58.7%. The results indicate that the increased wall recovery temperature is the primary factor in the reduction of transpiration cooling effectiveness.

蒸腾冷却因其冷却效率高而广泛应用于高超声速飞机。然而，冲击会显著降低冷却效果。因此，研究激波对高超声速条件下多孔平板蒸腾冷却的影响是十分必要的。本文主要研究了激波强度和冷却剂喷射速度对6马赫数下蒸腾冷却效果的影响。采用红外测温法测量多孔板的温度，采用纹影和纳米示踪平面激光散射（NPLS）技术观察多孔板的流场。结果表明，冷却效果随冲击强度的增大而降低。冷却剂喷射速率非线性地影响冷却效果，因为较高的速率增强了主流流的相互作用并加强了热交换。当注入量从0.1%增加到1.0%时，成本效益比下降了88.5%，湍流边界层厚度增加了58.7%。结果表明，壁面回收温度升高是导致蒸腾冷却效果降低的主要因素。

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引用次数: 0

Comparative aerothermoelastic performance assessment of advanced TPS materials for hypersonic vehicles 高超声速飞行器先进TPS材料气动热弹性性能比较评估

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.2026.111792

Muhammad Nasir , Dan Xie , Zijun Yi , Tamina Perveen , Adnan Maqsood

The design of Thermal Protection Systems (TPS) for hypersonic vehicles must simultaneously address extreme aerodynamic heating and ensure aerothermoelastic stability. Conventional approaches, as examined by Xie (2020), highlight that thickness distribution and material selection are critical to controlling flutter onset, stress evolution, and long-term structural safety. Yet, the performance of alternative advanced materials under fully coupled aerothermoelastic loading remains underexplored, leaving a gap in the development of next-generation TPS concepts. This study investigates the aerothermoelastic response of multilayer TPS panels by substituting the outer and insulation layers with three high-performance material combinations: (i) ZrBtwo/C/SiC with Silica Aerogel, (ii) C/SiC with AFRSI–2500, and (iii) Inconel 617 honeycomb with Cerrachrome Insulation, while retaining a Ti-6Al-2Sn-4Zr-2Mo structural panel. An aerothermoelastic MATLAB simulation framework, adapted from Xie (2020), was employed to evaluate baseline and selected thickness configurations (Cases 1, 2, and 7). Key outputs including transient deflection histories, temperature distributions, heat fluxes, thermal stresses, and flutter onset times are obtained and analyzed. The results indicate that the ZrBtwo/C/SiC + Silica Aerogel system provides the most favorable stability across cases, C/SiC + AFRSI–2500 offers intermediate performance, and Inconel 617 honeycomb + Cerrachrome Insulation tends to be least stable under the same loading, consistent with differences in thermal protection and temperature-dependent stiffness retention. Overall, the study highlights that while the emissivity of the outer radiation shield layer is important, the choice of insulation is decisive. Aerogel-based TPS shows strong potential for enhancing structural stability and thermal resilience in future hypersonic missions.

高超声速飞行器热防护系统（TPS）的设计必须同时解决极端气动加热和确保气动热弹性稳定性。正如Xie（2020）所研究的那样，传统方法强调厚度分布和材料选择对于控制颤振发作、应力演化和长期结构安全至关重要。然而，替代先进材料在完全耦合气热弹性载荷下的性能仍未得到充分探索，这给下一代TPS概念的发展留下了空白。本研究通过三种高性能材料组合(1)用二氧化硅气凝胶代替ZrBtwo/C/SiC，(2)用AFRSI-2500代替C/SiC，(3)在保留Ti-6Al-2Sn-4Zr-2Mo结构板的同时，用Cerrachrome绝热材料代替Inconel 617蜂窝材料，研究多层TPS板的气热弹性响应。采用自Xie（2020）改编的气动热弹性MATLAB仿真框架来评估基线和选定的厚度配置（案例1、2和7）。关键输出包括瞬态偏转历史，温度分布，热通量，热应力和颤振发作时间获得和分析。结果表明，在相同载荷下，ZrBtwo/C/SiC +二氧化硅气凝胶体系的稳定性最好，C/SiC + AFRSI-2500的性能中等，Inconel 617蜂窝+ Cerrachrome绝热材料的稳定性最差，这与热防护和温度相关刚度保持的差异是一致的。总的来说，该研究强调，虽然外层辐射屏蔽层的发射率很重要，但绝缘的选择是决定性的。气凝胶基TPS在未来高超声速任务中显示出增强结构稳定性和热弹性的强大潜力。

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引用次数: 0

Comprehensive analysis and performance optimization of different control parameters on an aviation heavy-fuel rotary engine 航空重燃料旋转发动机不同控制参数的综合分析与性能优化

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.2026.111853

Rui Liu , Siyu Liu , Zirui Fang , Jing Li , Lingfeng Zhong , Shen Xue

With the rapid development of the low-altitude economy and unmanned aerial vehicle (UAV) technology, aviation heavy-fuel rotary engines have re-emerged as a key power system, making the optimization of their control parameters crucial. This study established one-dimensional (1-D) and three-dimensional (3-D) numerical simulation models of an aviation heavy-fuel rotary engine, validated with experimental data, to investigate the effects of start of injection (SOI), injection pressure (P_inj), and trailing spark plug ignition timing (θ_ign) on the mixture formation, combustion, and emission. Results show that retarding SOI improves mixture homogeneity and reduces soot, while higher P_inj concentrates fuel in the chamber front, creating an over-rich zone. Advancing θ_ign causes a non-monotonic change in peak in-cylinder pressure (P_max), underscoring the need for careful timing selection. Based on these findings, the entropy weight technique for order preference by similarity to ideal solution (EW-TOPSIS) was employed to identify the optimal control scheme: SOI = –500°EA ATDC, P_inj = 0.3 MPa, and θ_ign = –10°EA ATDC. This configuration boosts P_max by 11.08 %, increases indicated mean effective pressure (IMEP) by 14.69 %, and reduces soot emissions by 42.14 % compared to the original scheme.

随着低空经济和无人机技术的快速发展，航空重燃料旋转发动机作为关键动力系统重新崛起，其控制参数的优化变得至关重要。本文建立了航空重燃油旋转发动机的一维（1-D）和三维（3-D）数值模拟模型，并通过实验数据进行验证，研究了喷射启动（SOI）、喷射压力（Pinj）和尾部火花塞点火正时（θign）对混合气形成、燃烧和排放的影响。结果表明：缓速SOI改善了混合气的均匀性，减少了烟尘，而较高的Pinj使燃料在燃烧室前部集中，形成过富区；推进θign会导致峰值缸内压力（Pmax）的非单调变化，强调需要仔细选择定时。在此基础上，采用近似理想解排序偏好熵权法（EW-TOPSIS）确定了最优控制方案：SOI = -500°EA ATDC, Pinj = 0.3 MPa, θign = -10°EA ATDC。与原方案相比，该方案使Pmax提高了11.08%，平均有效压力（IMEP）提高了14.69%，烟尘排放量减少了42.14%。

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引用次数: 0

An adaptive real-time forecasting framework for cryogenic fluid management in space systems 空间系统低温流体管理的自适应实时预测框架

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.2026.111851

Qiyun Cheng, Huihua Yang, Wei Ji

Accurate real-time forecasting of cryogenic tank behavior is essential for the safe and efficient operation of propulsion and storage systems in future deep-space missions. While cryogenic fluid management (CFM) systems increasingly require autonomous capabilities, conventional simulation methods remain hindered by high computational cost, model imperfections, and sensitivity to unanticipated boundary condition changes. To address these limitations, this study proposes an Adaptive Real-Time Forecasting Framework for Cryogenic Propellant Management in Space Systems, featuring a lightweight, non-intrusive method named ARCTIC (Adaptive Real-time Cryogenic Tank Inference and Correction). ARCTIC integrates real-time sensor data with precomputed nodal simulations through a data-driven correction layer that dynamically refines forecast accuracy without modifying the underlying model. Two updating mechanisms, auto-calibration and observation-correction, enable continuous adaptation to evolving system states and transient disturbances. The method is first assessed through synthetic scenarios representing self-pressurization, sloshing, and periodic operations, then validated using experimental data from NASA’s Multipurpose Hydrogen Test Bed and K-Site facilities. Results demonstrate that ARCTIC significantly improves forecast accuracy under model imperfections, data noise, and boundary fluctuations, offering a robust real-time forecasting capability to support autonomous CFM operations. The framework’s compatibility with existing simulation tools and its low computational overhead make it especially suited for onboard implementation in space systems requiring predictive autonomy.

在未来的深空任务中，低温储罐性能的准确实时预测对于推进和存储系统的安全高效运行至关重要。虽然低温流体管理（CFM）系统越来越需要自主能力，但传统的模拟方法仍然受到高计算成本、模型缺陷和对意外边界条件变化的敏感性的阻碍。为了解决这些限制，本研究提出了一个用于空间系统中低温推进剂管理的自适应实时预测框架，其特点是一种轻量级、非侵入式的方法，名为ARCTIC（自适应实时低温储罐推断和校正）。ARCTIC通过数据驱动的校正层将实时传感器数据与预先计算的节点模拟集成在一起，在不修改底层模型的情况下动态优化预测精度。两种更新机制，自动校准和观测校正，使持续适应不断变化的系统状态和瞬态干扰。该方法首先通过代表自加压、晃动和周期性操作的综合场景进行评估，然后使用NASA多用途氢试验台和K-Site设施的实验数据进行验证。结果表明，ARCTIC显著提高了模型缺陷、数据噪声和边界波动下的预测精度，提供了强大的实时预测能力，支持自主CFM操作。该框架与现有仿真工具的兼容性以及较低的计算开销使其特别适合在需要预测自主性的空间系统中实现。

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引用次数: 0

Parametric design for tip winglet in a subsonic compressor stage using SVR and NSGA-II 基于SVR和NSGA-II的亚音速压气机级叶尖小波参数化设计

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.2026.111855

Xinyu Jia , Jingjun Zhong , Wanyang Wu

In response to the design imperatives of highly-loaded compressor stages, there is an urgent requirement to formulate a more exhaustive parametric methodology for tip winglets. This study introduces an autonomously designed subsonic axial compressor as its subject and develops a parametric model for the suction side tip winglet configuration using Non-Uniform Rational B-Splines (NURBS). This model is integrated with a Support Vector Regression (SVR) surrogate model and the Non-dominated Sorting Genetic Algorithm II (NSGA-II) to establish a systematic parametric optimization design framework for tip winglets. Subsequent CFD simulations and flow field analyses of the optimized configurations were performed to explore the flow control mechanisms instigated by the winglet in the compressor tip region. The findings affirm that the optimization framework significantly enhances the design of tip winglet configurations, achieving a 9.13% improvement in the compressor’s stable operating margin while preserving the adiabatic efficiency and total pressure ratio nearly constant. Through a detailed comparative analysis of the flow fields associated with the optimized tip winglet configurations, the study elucidates the fundamental mechanism of stall margin enhancement facilitated by tip winglets in subsonic compressor stages. Specifically, the tip winglet structure not only mitigates the intensity of the leading edge tip leakage flow but also strengthens the wall-attached flow on the suction side near the leading edge, thereby improving flow conditions in this critical region.

为了响应高负荷压气机级的设计要求，迫切需要制定一种更详尽的叶尖小翼参数化方法。本文以自主设计的亚音速轴流压气机为研究对象，利用非均匀有理b样条（NURBS）建立了吸力侧尖端小翼结构的参数化模型。该模型结合支持向量回归（SVR）代理模型和非支配排序遗传算法II (NSGA-II)，建立了系统的叶尖小翼参数化优化设计框架。随后对优化后的结构进行了CFD模拟和流场分析，以探索小翼在压气机叶尖区域的流动控制机制。结果表明，优化框架显著提高了叶尖小翼结构的设计，在保持绝热效率和总压比基本不变的情况下，压气机的稳定运行裕度提高了9.13%。通过对优化后的叶尖小翼结构流场的详细对比分析，阐明了亚音速压气机级叶尖小翼增强失速裕度的基本机理。具体来说，叶尖小翼结构不仅减轻了前缘叶尖泄漏流动的强度，而且增强了前缘附近吸力侧的附壁流动，从而改善了该临界区域的流动条件。

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引用次数: 0

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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