Aerospace Science and Technology最新文献_第10页

Research on transfer and landing trajectory of a dual-asteroid system probe based on deep reinforcement learning (DDPG) 基于深度强化学习（DDPG）的双小行星系统探测器转移与着陆轨迹研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2025-09-03 DOI: 10.1016/j.ast.2025.110870

Linli Su, Lie Yang, Hanqing Zhao, Tengfei Guan, Zichen Fan, Mingying Huo, Naiming Qi

Asteroid landing exploration is one of the most direct, effective, and challenging methods to gather data on small celestial bodies, and it is a prominent topic in deep space exploration. Considering that a significant number of asteroids have moons, if a trajectory can be designed to transfer from one asteroid to another, it would enable rapid exploration of small celestial body systems. However, this problem involves high-dimensional, nonlinear dynamics such as modeling the complex space perturbation environment of small celestial bodies, describing the lander and asteroid's rugged surface, and analyzing the uncertain attitude and trajectory motions of the lander. These pose new challenges to space dynamics. To address this, this paper employs deep reinforcement learning (DRL) to tackle these challenges. The model consists of three main modules: the deep reinforcement learning module, the dual-asteroid simulation module, and the visualization module. By inputting the initial probe position, the initial states of the dual-asteroid system, and the target landing point coordinates, it outputs the probe's trajectory, control strategy, and energy consumption as performance indicators. This paper achieves data loading and preprocessing, builds the deep reinforcement learning model, develops the physical simulation module, and visualizes the modules. The results show that through reinforcement learning-based trajectory optimization, energy consumption in the transfer trajectory of the probe is significantly reduced (approximately 44.6 %), while maintaining good performance in final precision and reward. This demonstrates that combining the nearest approach tracking control with a deep reinforcement learning model can effectively improve the probe's energy efficiency.

小行星着陆探测是收集小天体数据最直接、最有效、最具挑战性的方法之一，是深空探测领域的一个突出课题。考虑到相当数量的小行星都有卫星，如果能够设计出从一颗小行星转移到另一颗小行星的轨道，将使对小天体系统的快速探索成为可能。然而，该问题涉及高维非线性动力学，如对小天体的复杂空间摄动环境进行建模，描述着陆器和小行星的崎岖表面，分析着陆器的不确定姿态和轨迹运动。这些都对空间动力学提出了新的挑战。为了解决这个问题，本文采用深度强化学习（DRL）来解决这些挑战。该模型由三个主要模块组成：深度强化学习模块、双小行星仿真模块和可视化模块。通过输入探测器的初始位置、双小行星系统的初始状态和目标着陆点坐标，输出探测器的轨迹、控制策略和能量消耗作为性能指标。本文实现了数据的加载和预处理，建立了深度强化学习模型，开发了物理仿真模块，并实现了模块的可视化。结果表明，通过基于强化学习的轨迹优化，探针传递轨迹能耗显著降低（约44.6% %），同时在最终精度和奖励方面保持良好的性能。这表明将最接近跟踪控制与深度强化学习模型相结合可以有效地提高探针的能量效率。

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引用次数: 0

Design and simulation research on local acceleration/deceleration profiles in supersonic flow 超声速流动中局部加减速剖面的设计与仿真研究

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.2026.111825

Saiqiang Zhang , Gang Li , Wanwu Xu , Jiarong Li

Supersonic airflow acceleration/deceleration profile design is often incorporated as part of nozzle design and widely applied in fields such as hypersonic wind tunnels and scramjet inlet design. However, detailed research on this topic is rarely found in current literature. Profile design methods typically utilize Method of characteristics theory(MOC), which is highly sensitive to the selection of initial value lines and directly impacts the profile characteristics. Starting from the axisymmetric characteristic line theory, this paper proposes and compares three methods for obtaining initial values. Among them, the flow field calculation method exhibits the best uniformity. When combined with this method, optimizing the aspect ratio of a supersonic annular nozzle to 8.24 results in optimal flow field uniformity, with the standard deviation of the exit Mach number being less than 0.002. A variable curvature transition profile design method is proposed, achieving acceleration of airflow from Mach 2 to Mach 4 while ensuring flow field uniformity. Finally, an inverse design approach is adopted for the acceleration profile, optimizing the traditional supersonic diffuser cone section into an isentropic contraction section. At a back pressure of 90 kPa, the total pressure recovery coefficient is 2.123% higher than that of the cone section. The research results demonstrate that the methods proposed in this paper effectively address issues related to flow field uniformity and total pressure loss. Their effectiveness and versatility have been verified in acceleration profiles, annular nozzles, and diffusers, providing reliable theoretical and methodological support for the design of hypersonic engineering equipment

超声速气流加减速型线设计通常作为喷管设计的一部分，广泛应用于高超声速风洞和超燃冲压发动机进气道设计等领域。然而，在目前的文献中，对这一主题的详细研究很少。轮廓线设计方法通常采用特征理论方法（MOC），该方法对初始值线的选取高度敏感，并直接影响轮廓线的特性。从轴对称特征线理论出发，提出并比较了三种求初值的方法。其中，流场计算方法的均匀性最好。结合该方法，将超声速环形喷管展弦比优化为8.24时，流场均匀性最佳，出口马赫数标准差小于0.002。提出了一种变曲率过渡型设计方法，在保证流场均匀性的同时，实现了从2马赫到4马赫的气流加速。最后，采用逆设计方法，将传统的超声速扩压锥段优化为等熵收缩段。在背压为90 kPa时，总压恢复系数比锥段高2.123%。研究结果表明，本文提出的方法有效地解决了流场均匀性和总压损失问题。它们的有效性和通用性已经在加速剖面、环形喷管和扩散器中得到验证，为高超声速工程设备的设计提供了可靠的理论和方法支持

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引用次数: 0

Data-driven selection and sequence optimization of aero-engine rotor blades based on LLM-guided simulated annealing algorithm 基于llm导向模拟退火算法的航空发动机转子叶片数据驱动选择与序列优化

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-27 DOI: 10.1016/j.ast.2026.111787

Haitao Xu , Jie Gao , Xu Yang , Jinsong Du , Wei Wang

To address the issues of missing error distribution modeling, inaccurate dynamic balance determination, and black-box decision-making processes in traditional blade sorting and sequence optimization methods, this paper proposes a data-driven approach for optimizing the selection and sequence of aero-engine rotor blades using an LLM-guided simulated annealing algorithm (LLM-SA). Firstly, an online-updated adaptive K-Means clustering model is established to achieve dynamic blade selection under multi-tolerance coupling. Secondly, a graph-enhanced long short-term memory network (GE-LSTM) is designed to model the dynamic balance qualification mechanism of rotors by integrating topological structure features and assembly positional features. Finally, domain knowledge is embedded into the optimization process using LLM-SA, generating interpretable assembly decision paths that bridge the gap between theoretical and practical decision-making. Experimental results demonstrate that GE-LSTM achieves 99.3% accuracy and a matthews correlation coefficient (MCC) of 0.983 in predicting rotor dynamic balancing rates. The blade sorting algorithm selects tens of thousands of blades within 11.041 s, achieving a 96% assembly accuracy. Using LLM-SA to sort blade sequences results in a rotor unbalance of 0.288 g·mm, representing an 95.8% improvement over SA. This approach provides theoretical foundations and technical support for the high-precision intelligent assembly of aero-engine rotors.

针对传统叶片排序和序列优化方法中存在的误差分布建模缺失、动平衡确定不准确、黑箱决策过程等问题，提出了一种基于llm引导的模拟退火算法（LLM-SA）的数据驱动的航空发动机转子叶片选择和序列优化方法。首先，建立在线更新的自适应K-Means聚类模型，实现多公差耦合下的动态叶片选择；其次，结合拓扑结构特征和装配位置特征，设计了图增强长短期记忆网络（GE-LSTM）对转子动平衡鉴定机制进行建模；最后，使用LLM-SA将领域知识嵌入到优化过程中，生成可解释的装配决策路径，弥合理论和实际决策之间的差距。实验结果表明，GE-LSTM预测转子动平衡率的准确率为99.3%，马修斯相关系数（MCC）为0.983。叶片排序算法在11.041 s内选择数万个叶片，装配精度达到96%。使用LLM-SA对叶片序列进行排序，转子不平衡为0.288 g·mm，比SA提高了95.8%。该方法为航空发动机转子高精度智能装配提供了理论基础和技术支持。

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引用次数: 0

Combustion efficiency characteristics of single aluminum particle in SRM via CFD-DEM 基于CFD-DEM的SRM中单铝颗粒燃烧效率特性研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-17 DOI: 10.1016/j.ast.2026.111735

He Chen , Xueting Wu , Wenjing Yang , Kaiwei Chu , Huangpeng Wang , Yan Ba , Peijin Liu

Aluminum is the most widely used metal additive in solid rocket motors, but its complex combustion behavior significantly impacts the motor’s energy conversion efficiency. This study employs a two-way coupling CFD-DEM framework to conduct high-fidelity numerical investigations on the combustion efficiency of single aluminum particles in solid rocket motors. Based on particle size (critical diameter D_c = 20 μm), a synergistic combustion model combining both diffusion-controlled and kinetics-controlled mechanisms is developed to address combustion dynamics related to particle size. The model incorporates the oxide cap formation mechanism during aluminum combustion, and a refined computational approach provides accurate and efficient predictions. Comparison with classical experimental data validates that this framework offers higher accuracy in predicting particle combustion times under varying environmental conditions compared to traditional diffusion-based models. Based on this, a parametric study of aluminum particle combustion efficiency is conducted, showing that combustion efficiency is significantly influenced by residence time and combustion duration. It is also found to be highly dependent on factors such as initial particle diameter, injection velocity, and axial injection position, which in turn affect the critical particle size required for complete combustion. This study provides a particle-resolved predictive tool for SRM optimization, emphasizing the necessity of particle size and spatial distribution strategy to maximize the utilization of aluminum particles.

铝是固体火箭发动机中应用最广泛的金属添加剂，但其复杂的燃烧特性对发动机的能量转换效率影响很大。本研究采用双向耦合CFD-DEM框架，对固体火箭发动机中单个铝颗粒的燃烧效率进行了高保真数值研究。基于颗粒尺寸（临界直径Dc = 20 μm），建立了扩散控制和动力学控制相结合的协同燃烧模型，以解决与颗粒尺寸相关的燃烧动力学问题。该模型结合了铝燃烧过程中氧化帽的形成机制，并采用精细的计算方法提供了准确有效的预测。与经典实验数据的对比验证了该框架在预测不同环境条件下颗粒燃烧时间方面比传统的基于扩散的模型具有更高的准确性。在此基础上，对铝颗粒燃烧效率进行了参数化研究，发现燃烧效率受停留时间和燃烧持续时间的影响较大。它还被发现高度依赖于诸如初始颗粒直径，喷射速度和轴向喷射位置等因素，这些因素反过来又影响完全燃烧所需的临界颗粒尺寸。该研究为SRM优化提供了一个颗粒分解的预测工具，强调了铝颗粒粒度和空间分布策略对最大限度地利用铝颗粒的必要性。

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引用次数: 0

Solar sail-based energy-efficient architecture for long-term mars orbit operations 基于太阳帆的长期火星轨道运行节能架构

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-26 DOI: 10.1016/j.ast.2026.111779

Jungju Bae , Jaeyoung Kang

This study presents a solar sail–based mission architecture for long-term Mars orbit operations with minimal energy and control input. While solar sails offer fuel-free, continuous thrust suitable for interplanetary transfers, their application in bounded planetary orbits—particularly around Mars—poses unique challenges due to persistent perturbations such as solar radiation pressure (SRP), eclipse effects, atmospheric drag, and gravity-gradient torques. The proposed strategy focuses on the post-insertion operational phase, wherein the spacecraft maintains a Mars-pointing attitude and stable orbit over extended durations. A yaw-biased attitude configuration is employed to reduce SRP-induced torque in the yaw axis, allowing passive stabilization through gravity-gradient alignment. The control system utilizes reaction wheels with a sliding-mode controller to support transient convergence, after which negligible torque and power are required. A comprehensive Mars-centered dynamic model is developed, coupling translational and rotational motion and incorporating eclipse-aware SRP and atmospheric drag effects. Simulation results demonstrate that uncontrolled attitude motion leads to rapid orbital degradation, but within a well-defined feasibility region—characterized by suitable insertion velocity and altitude—long-term stability is achievable. A 10-year simulation confirms that the proposed system maintains bounded orbital elements and attitude alignment, with root mean square control power below 0.00231 W. These findings highlight the strategic potential of solar sails as low-energy platforms for autonomous deep-space missions. The study emphasizes the importance of insertion geometry, quasi-equilibrium configurations, and minimal control design in enabling scalable, long-duration Mars orbit operations.

本研究提出了一种基于太阳帆的任务架构，以最小的能量和控制输入进行长期火星轨道操作。虽然太阳帆提供无燃料的、持续的推力，适合行星际传输，但由于太阳辐射压力（SRP）、日食效应、大气阻力和重力梯度扭矩等持续的扰动，它们在有限的行星轨道上的应用——特别是在火星周围——面临着独特的挑战。提出的策略侧重于插入后的操作阶段，其中航天器在较长时间内保持指向火星的姿态和稳定的轨道。偏航偏置姿态配置用于减少srp引起的偏航轴扭矩，通过重力梯度对准实现被动稳定。控制系统利用反作用力轮和滑模控制器来支持瞬态收敛，之后所需的扭矩和功率可以忽略不计。建立了一个以火星为中心的综合动力学模型，该模型耦合了平动和旋转运动，并考虑了日食感知SRP和大气阻力效应。仿真结果表明，不受控制的姿态运动导致轨道快速退化，但在一个明确的可行区域内——以适当的插入速度和高度为特征——可以实现长期稳定。经过10年的仿真验证，该系统保持了有界轨道元和姿态对准，均方根控制功率低于0.00231 W。这些发现突出了太阳帆作为自主深空任务的低能耗平台的战略潜力。该研究强调了插入几何、准平衡配置和最小控制设计在实现可扩展、长时间火星轨道操作中的重要性。

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引用次数: 0

Additive manufacturing of nitrate ester plasticized polyether solid propellants: Slurry characterization and mechanical performance evaluation 硝酸酯增塑聚醚固体推进剂的增材制造：浆料特性和力学性能评价

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-26 DOI: 10.1016/j.ast.2026.111774

Qili Qiu , Daolun Liang , Fanqin Xiong , Ji Li , Wendi Zhang , Danping Pan , Richen Lin , Dekui Shen

Nitrate Ester Plasticized Polyether (NEPE) propellants, as high-energy solid propellants with excellent performance, have significant application potential in aerospace and defense fields. However, traditional manufacturing methods face challenges such as limited geometric customization and defect formation. Additive manufacturing (AM) technology offers a promising solution to these issues. In this study, we focused on the additive manufacturing of NEPE propellants, systematically investigating the properties of high-energy solid propellant slurries tailored for AM.The propellant slurry was prepared with a specific formulation, and its precuring performance and viscosity characteristics were evaluated. The effects of ultraviolet (UV) resin content, solid content, temperature, and time on slurry viscosity were analyzed, and the formulation (Polyethylene terephthalate: diethyl phthalate: toluene diisocyanate: UV resin: fine ammonium perchlorate: coarse ammonium perchlorate: aluminum powder: melamine = 10: 10: 1: 4: 36.7: 18.3: 15: 5) with a solid content of 75 wt.% was determined. Mechanical properties, pore structures, and microscopic morphologies of printed and cast propellant samples were compared. The results showed that printed propellants exhibited significant advantages in tensile strength (1.25 MPa at 20°C) and porosity (0.43%) compared to cast samples. The fracture mechanism analysis revealed that the enhanced tensile strength of printed propellants was attributed to the cured UV resin system, while the presence of melamine and micropores influenced the fracture behavior. This study provides a foundation for the application of additive manufacturing in high-energy solid propellant production, contributing to the development of propellants with improved performance and geometric flexibility.

硝酸酯增塑聚醚推进剂作为一种性能优异的高能固体推进剂，在航空航天和国防领域具有重要的应用潜力。然而，传统的制造方法面临着几何定制限制和缺陷形成等挑战。增材制造（AM）技术为解决这些问题提供了一个很有前途的解决方案。在这项研究中，我们专注于NEPE推进剂的增材制造，系统地研究了为AM量身定制的高能固体推进剂浆料的性能。采用特定配方制备了推进剂浆料，并对其预固化性能和粘度特性进行了评价。分析了紫外树脂含量、固相含量、温度、时间对浆料粘度的影响，确定了固相含量为75 wt.%的配方（聚对苯二甲酸乙酯：邻苯二甲酸二乙酯：甲苯二异氰酸酯：紫外树脂：细过氯酸铵：粗过氯酸铵：铝粉：三聚氰胺 = 10:10:1:4:36.7:18.3:15:5）。比较了打印和铸造推进剂样品的力学性能、孔隙结构和微观形貌。结果表明，与铸造样品相比，打印推进剂在抗拉强度（20℃时为1.25 MPa）和孔隙率（0.43%）方面具有显著优势。断裂机理分析表明，打印推进剂的拉伸强度增强主要归因于固化的UV树脂体系，而三聚氰胺和微孔的存在影响了打印推进剂的断裂行为。本研究为增材制造技术在高能固体推进剂生产中的应用奠定了基础，有助于研制性能更高、几何柔韧性更强的推进剂。

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引用次数: 0

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

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-02-01 DOI: 10.1016/j.ast.2026.111835

Haochen Xiong , Hao Yan , Tao Zhang , Yancheng You

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

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

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引用次数: 0

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 : 2026-06-01 Epub 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

Experimental and numerical study on the aerodynamic characteristics of a scissors rotor in vertical descent flight 剪刀旋翼垂直下降飞行气动特性的实验与数值研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-16 DOI: 10.1016/j.ast.2026.111731

Chenkai Cao , Wangqing Zhu , Hongbo Gao , Guoqing Zhao , Qijun Zhao , Simeng Jing

This study investigates the aerodynamic characteristics of scissors rotors during vertical-descent flights by integrating wind tunnel experiments with high-fidelity CFD simulations. A wind tunnel test system, designed to adjust the scissors angles, has been developed to measure the aerodynamic loads and their unsteady fluctuations across various descent rates. A high-fidelity CFD methodology, specifically tailored to capture the flow field of scissors rotors in the vortex ring state, has been established and validated against experimental data. The influence of the scissors angle on rotor performance during descent is examined experimentally, while numerical simulations provide detailed insights into the evolution of vortex structures and their asymmetric interference mechanisms on the upper and lower rotors. Based on this mechanistic understanding, a novel scissors rotor configuration featuring differential blade pitch settings between the upper and lower rotors is proposed. The aerodynamic improvements achieved by this new design and the underlying physical mechanisms are systematically analyzed. It is found that the 30° scissors angle configuration exhibits the smallest aerodynamic loss during descent, whereas the 60° configuration delays the onset of peak force degradation to a higher descent rate. Owing to the axial spacing between the upper and lower rotors and their nonuniform interactions with the vortex structures, thrust loss occurs asynchronously across the two rotor discs. Furthermore, the proposed configuration, which incorporates an increased blade pitch on the lower rotor, effectively enhances aerodynamic performance under both hovering and descent flight conditions. The maximum thrust loss in the vortex ring state is reduced by 5% compared to that in the conventional symmetric configuration.

采用风洞实验和高保真CFD模拟相结合的方法，研究了剪刀旋翼垂直下降飞行时的气动特性。设计了一套可调节剪刀角的风洞试验系统，用于测量气动载荷及其在不同下降速率下的非定常波动。建立了一种高保真的CFD方法，专门用于捕获旋涡环状态下剪刀形转子的流场，并通过实验数据进行了验证。实验研究了下降过程中剪刀角对旋翼性能的影响，数值模拟详细揭示了旋翼上、下旋翼涡结构的演化及其不对称干涉机理。在此基础上，提出了一种基于上下转子桨距差设置的新型剪刀式转子结构。系统地分析了这种新设计所取得的空气动力学改进和潜在的物理机制。研究发现，30°剪刀角构型在下降过程中表现出最小的气动损失，而60°构型将峰值力退化的开始延迟到更高的下降速率。由于上下转子之间的轴向间距及其与涡结构的非均匀相互作用，使得推力损失在两个转子盘之间异步发生。此外，所提出的配置，包括增加桨叶俯仰在下旋翼，有效地提高了在悬停和下降飞行条件下的气动性能。旋涡环状态下的最大推力损失比传统对称配置下的最大推力损失降低了5%。

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引用次数: 0

Study on the flow and heat transfer characteristics of hydrocarbon fuel regenerative/transpiration combined cooling in the nozzle geometry 喷嘴几何结构下碳氢燃料再生/蒸腾联合冷却的流动和传热特性研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-19 DOI: 10.1016/j.ast.2026.111738

Jia-Chen Xu , Shen Du , Fei Qin , Ya-Ling He

Hydrocarbon fuel regenerative/transpiration combined cooling integrates the advantages of convective cooling and film cooling in the thermal protection system of air-breathing vehicles, representing a promising active cooling approach. This study propose a coupled computational method based on regenerative/transpiration combined cooling to simulate the heat transfer between the mainstream flow in the nozzle and the regenerative/transpiration combined cooling outside. This method captures the key features across the transonic region and analyzes the factors influencing the thermal-protection performance of regenerative/transpiration combined cooling by coupling regenerative cooling pyrolysis with oxidative cracking in the mainstream flow. The results show that combined cooling reduces wall heat-flux and achieves higher cooling efficiency at the same mass flow rate. As the allocation ratio of transpiration cooling increases, the peak heat-flux and coking rate decrease by 54.36 % and 90 %, respectively, while the average cooling efficiency improves by 9.78 %. Reducing the angle between the transpiration holes and the wall enhances the coverage of the boundary-layer film and improves local cooling efficiency. The oxidative cracking effect of hydrocarbon fuel increases heat-transfer capability near the wall, achieving local heat-transfer enhancement, with a peak temperature reduction of 90 K (corresponding to an 11 % increase in cooling efficiency).

碳氢燃料再生/蒸腾联合冷却将对流冷却和气膜冷却的优点集成到吸气式车辆热保护系统中，是一种很有前途的主动冷却方式。本文提出了一种基于蓄热/蒸腾联合冷却的耦合计算方法来模拟喷嘴内主流流与外蓄热/蒸腾联合冷却之间的换热。该方法捕捉了跨声速区域的关键特征，分析了蓄热/蒸腾联合冷却在主流流中耦合蓄热热解与氧化裂解的热防护性能的影响因素。结果表明，在相同质量流量下，复合冷却可以降低壁面热流密度，获得较高的冷却效率。随着蒸腾冷却分配比例的增加，峰值热流密度和结焦速率分别降低54.36%和90%，平均冷却效率提高9.78%。减小蒸腾孔与壁面之间的夹角可以增大边界层膜的覆盖范围，提高局部冷却效率。烃类燃料的氧化裂解效应增加了壁面附近的传热能力，实现了局部传热增强，峰值温度降低了90k（相当于冷却效率提高了11%）。

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