Aerospace Science and Technology最新文献

英文中文

Unstable Flow Mechanisms Guiding Early Warning in Axial Compressors: A Mechanism-Feature-Model Framework for Enhanced Robustness 轴流压气机不稳定流动机制预警：增强鲁棒性的机制-特征模型框架

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-14 DOI: 10.1016/j.ast.2026.111706

Wang Zhongyi, Li Zeyuan, Wang Meng, Wu Wanqiang

引用次数: 0

Aircraft engines dust ingestion in the Middle East 中东地区的飞机引擎灰尘摄入

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-14 DOI: 10.1016/j.ast.2026.111698

Daniel Rotherham, Antonio Filippone, Nicholas Bojdo

引用次数: 0

Bridging a Cu layer enables decent metallurgical bonding for wire-arc directed energy deposited Mg-Ti bimetals 桥接Cu层可以为线弧定向能沉积的Mg-Ti双金属提供良好的冶金结合

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-14 DOI: 10.1016/j.ast.2026.111707

Qifei Han, Jiayuan Cui, Ming Fan, Yuanxuan Zheng, Shuijun Ye, Yueling Guo, Changmeng Liu, En-Hou Han

引用次数: 0

Study of the influence of a non-axisymmetric stator on the aerodynamic performance of a fan–compressor system 非轴对称定子对风机-压气机系统气动性能影响的研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-14 DOI: 10.1016/j.ast.2026.111710

Junyang Yu , Peng Sun , Chunxue Wang , Wei Zhao , Hanbo Jiang

Fans and compressors are the core components of aviation engine compression systems, and the performance and stability of these components directly affect the efficiency and operational safety of an engine. In this study, the fan and compressor of a turbofan engine were taken as the research objects, and an integrated unsteady simulation was conducted for the intake, fan, and high-pressure compressor first stage. The influence of a non-axisymmetric stator (NAS) on the downstream flow field and the performance and stability of the compression components were both examined. The research results indicated that when the fan and compressor worked together, the NAS could significantly improve the fan performance under complex operating conditions and significantly enhance the aerodynamic performance and stability of the compressor. At the same corrected speed, the maximum total pressure ratio and the peak efficiency of the compressor were increased by 4.60% and 0.92%, respectively, and the stability margin was increased by 30.63%. After adopting the NAS, the non-uniformity of the inlet flow field of the compressor was significantly reduced, and the low-energy fluid in the compressor flow passage was effectively reduced. The flow separation near the pressure surface of some stator vanes is effectively suppressed, and the total pressure loss inside the compressor stator was reduced by 33.98%, which significantly improved the performance of the compressor.

风扇和压气机是航空发动机压缩系统的核心部件，这些部件的性能和稳定性直接影响到发动机的工作效率和运行安全。本研究以某涡扇发动机的风扇和压气机为研究对象，对进气、风扇和高压压气机一级进行了综合非定常仿真。研究了非轴对称定子对下游流场及压缩部件性能和稳定性的影响。研究结果表明，当风机与压气机协同工作时，NAS能够显著改善风机在复杂工况下的性能，显著提高压气机的气动性能和稳定性。在相同修正转速下，压缩机的最大总压比和峰值效率分别提高了4.60%和0.92%，稳定裕度提高了30.63%。采用NAS后，压气机进口流场的不均匀性明显降低，压气机流道中的低能流体得到有效减少。有效抑制了部分定子叶片压力面附近的流动分离，压气机定子内部总压损失降低了33.98%，压气机性能得到显著改善。

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引用次数: 0

Performance analysis of boosted centrifugal separators and matching characteristics with ventilation systems in aero-engine 航空发动机增压式离心分离器性能分析及其与通风系统的匹配特性

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-14 DOI: 10.1016/j.ast.2026.111715

Yanjun Li , Le Jiang , Yibiao Chen , Yiming Chen , Daopeng Fu , Shixuan Ren

The efficient and stable operation of an aero-engine lubrication system heavily depends on a comprehensive understanding of the working mechanisms of its key components, among which the centrifugal separator plays a pivotal role in regulating the pressure balance within the bearing chambers and controlling oil consumption. This study investigates the structure-performance correlation of a boosted centrifugal separator and its coupling characteristics with the ventilation system. The internal flow and separation characteristics of the separator are thoroughly analyzed, and a one-dimensional fluid network model is employed to evaluate the pressure matching behavior of the ventilation system. The results indicate that increasing the separator’s rotational speed and reducing the air flow rate both contribute to enhancing its oil-air separation efficiency. For separators configured with round-hole and straight-slot oil discharge structures, the aerodynamic boosting capability shows a positive correlation with rotational speed and a negative correlation with air flow rate. The round-hole oil discharge structure demonstrates the highest aerodynamic boosting performance, with separation efficiency intermediate between those of the inclined-slot and straight-slot structures. The inclined-slot oil discharge structure achieves the highest separation efficiency but exhibits the weakest aerodynamic boosting performance. The implementation of the boosted centrifugal separator effectively reduces bearing chamber pressure and increases the sealing pressure difference of sealing devices. Under low-speed conditions, the sealing pressure difference can be improved by over 50%, substantially reducing the risk of oil leakage through the seal devices. The multiphase simulation and the developed one-dimensional system-level matching approach provide valuable methodological support for improving the reliability and performance of aero-engine.

航空发动机润滑系统的高效稳定运行在很大程度上取决于对其关键部件的工作机理的全面了解，其中离心分离器在调节轴承腔内压力平衡和控制油耗方面起着关键作用。研究了升压式离心分离器的结构-性能关系及其与通风系统的耦合特性。深入分析了分离器内部流动和分离特性，并采用一维流体网络模型评价了通风系统的压力匹配行为。结果表明，提高分离器转速和减小空气流量都有助于提高其油气分离效率。对于配置圆孔和直槽排油结构的分离器，气动增压能力与转速呈正相关，与气流流量负相关。圆孔排油结构的气动增压性能最好，排油效率介于斜槽和直槽结构之间。斜槽排油结构的分离效率最高，但气动增压性能最差。升压式离心分离器的实施有效降低了轴承腔压力，增大了密封装置的密封压差。在低速工况下，密封压差可提高50%以上，大大降低了通过密封装置漏油的风险。多相仿真和一维系统级匹配方法为提高航空发动机的可靠性和性能提供了有价值的方法支持。

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引用次数: 0

Nonlinear dynamic modeling and analysis of rigid-flexible coupling spacecrafts with time-varying temperature distribution 时变温度分布刚柔耦合航天器的非线性动力学建模与分析

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-13 DOI: 10.1016/j.ast.2026.111667

Bingxin Zhao , Xudong Gu , Rongchun Hu , Sihan Wu , Zichen Deng

When establishing the dynamic model of a rigid-coupled spacecraft, the traditional linear method requires the flexible structure to satisfy the small deformation assumption. However, the wide range of motion of the large spacecraft may lead to nonlinear deformation of the flexible structure. In this paper, the nonlinear dynamic model of the rigid-flexible coupling spacecraft is established during in-orbit operation. Firstly, the kinetic energy of the rigid-flexible spacecraft is derived by incorporating the nonlinear deformations with second-order coupling terms. Secondly, the total potential energy of the system is obtained by thermal analysis, including deformation potential energy and gravitational potential energy. Then, the nonlinear time-varying coupled dynamics equations of the rigid-flexible coupling spacecraft are obtained by the Hamilton’s variational principle. The discrete equations are derived by using the assumed modal method (AMM). Finally, the results obtained through numerical calculations indicate that the nonlinear model accurately predicts the dynamical stiffening phenomenon as the attitude rotational velocity of the rigid hub increases. At the same time, the effects of the gravity gradient (GG), the structure size and the temperature on the response of the spacecraft are obtained.

在建立刚耦合航天器动力学模型时，传统的线性方法要求柔性结构满足小变形假设。然而，大型航天器的大运动范围可能导致柔性结构的非线性变形。建立了刚柔耦合航天器在轨运行时的非线性动力学模型。首先，将非线性变形与二阶耦合项结合，推导出刚柔航天器的动能；其次，通过热分析得到系统的总势能，包括变形势能和重力势能。然后，利用Hamilton变分原理得到刚柔耦合航天器的非线性时变耦合动力学方程。采用假设模态法（AMM）推导了离散方程。最后，数值计算结果表明，该非线性模型准确地预测了刚性轮毂随着姿态转速的增加而出现的动态加筋现象。同时，得到了重力梯度、结构尺寸和温度对航天器响应的影响。

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引用次数: 0

Influence of loading distribution on corner separation in high-subsonic compressor cascades under low Reynolds number condition 低雷诺数条件下高亚音速压气机叶栅加载分布对转角分离的影响

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-13 DOI: 10.1016/j.ast.2026.111705

Yi Wang , Yuping Li , Chuangxin Zhou , Xiaoping Tian , Zan Yang

In the domain of modern high-load aero-engine design, corner separation is prone to occur in the compressor, which can significantly influence the aerodynamic performance of compressor blades at low Reynolds numbers. This study adopts a quantitative modeling approach to blade loading distribution and aims to examine the influence of loading distribution on corner separation. Adjustments are performed to the V103-B blade profile curvature, and compressor blade cascades with diverse loading distribution coefficients (Ω) are obtained. Numerical simulations are conducted to investigate the influence of loading distribution on corner separation of compressor stator under low Reynolds number condition. The simulation results reveal that a front-loaded blade configuration can effectively reduce stator losses. Nevertheless, as the loading distribution shifts forward, laminar flow separation on the suction surface occurs earlier. When the loading distribution is excessively forward (Ω = 1.36), the axial adverse pressure gradient region at the onset of laminar flow separation merges with that near the leading edge, forming a cross-channel axial adverse pressure gradient region. This significantly hinders the incoming flow from entering the cascade passage, causing corner separation to evolve into corner stall and reducing the range of stable operating angles for the cascade. This discovery demonstrates the influence of loading distribution on three-dimensional corner separation, offering insights for subsequent compressor blade profile design.

在现代高负荷航空发动机设计中，压气机内部容易发生转角分离，这对压气机叶片在低雷诺数下的气动性能有重要影响。本研究采用叶片载荷分布的定量建模方法，旨在研究载荷分布对转角分离的影响。对V103-B叶片型线曲率进行调整，得到了不同载荷分布系数的压气机叶片叶栅（Ω）。通过数值模拟研究了低雷诺数条件下载荷分布对压气机定子角分离的影响。仿真结果表明，叶片前置结构能有效降低静叶损耗。然而，随着载荷分布的前移，吸力面层流分离发生的时间提前。当载荷分布过于前向（Ω = 1.36）时，层流分离开始时的轴向逆压梯度区域与前缘附近的轴向逆压梯度区域合并，形成跨通道轴向逆压梯度区域。这极大地阻碍了来流进入叶栅通道，导致角分离演变为角失速，减小了叶栅稳定运行角的范围。这一发现证明了载荷分布对三维角分离的影响，为后续压气机叶片型线设计提供了见解。

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引用次数: 0

Spacecraft rendezvous and precise landing in the cislunar region with a LiDAR 利用激光雷达在月月区域进行航天器交会和精确着陆

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-13 DOI: 10.1016/j.ast.2026.111635

Seur Gi Jo , Justin Schmitt , David Canales , Axel Garcia

With recent advancements in the space industry, numerous missions involving rendezvous, proximity operations, and lunar landings in the cislunar region are being actively planned and executed. Due to the combined gravitational influences of the Earth and Moon, the dynamical environment in this region is highly nonlinear. Additionally, significant distances from Earth demand robust state estimation and control algorithms that rely on onboard sensors. To address the challenges of autonomous navigation and control in the cislunar environment, this paper presents an integrated framework for full-state estimation and adaptive control within the circular restricted full three-body problem (CRF3BP) using LiDAR sensing. The proposed method begins by utilizing LiDAR measurements to generate point cloud data of the target spacecraft or landing site. This data is then processed using the generalized iterative closest point (G-ICP) algorithm to estimate the relative position and attitude. A full 12-dimensional state vector, including both translational and angular velocities, is subsequently estimated via an unscented Kalman filter (UKF). Based on the estimated state, an adaptive controller is designed to achieve robust performance despite uncertainties in the inertia tensor. Numerical simulations validate the proposed approach, demonstrating its effectiveness in achieving precise relative navigation and control in the nonlinear cislunar environment.

随着最近空间工业的进步，许多涉及交会、近距离操作和在地月区域登月的任务正在积极规划和执行。由于地球和月球引力的共同影响，该区域的动力环境是高度非线性的。此外，距离地球很远，需要依靠机载传感器的鲁棒状态估计和控制算法。为了解决地月环境下自主导航和控制的挑战，本文提出了一种基于激光雷达传感的圆形受限全三体问题（CRF3BP）全状态估计和自适应控制的集成框架。该方法首先利用激光雷达测量数据生成目标航天器或着陆点的点云数据。然后使用广义迭代最近点（G-ICP）算法对这些数据进行处理，以估计相对位置和姿态。一个完整的12维状态向量，包括平移和角速度，随后通过无气味卡尔曼滤波器（UKF）估计。在估计状态的基础上，设计了一种自适应控制器，使系统在惯性张量存在不确定性的情况下仍然具有鲁棒性。数值仿真验证了该方法在非线性地月环境下实现精确相对导航和控制的有效性。

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引用次数: 0

PPO-PF: An aero-engine performance degradation state calibration algorithm for turbine blade service loadings assessment PPO-PF：一种用于涡轮叶片服役负荷评估的航空发动机性能退化状态标定算法

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-13 DOI: 10.1016/j.ast.2026.111674

Ruoqi Chen , Dianyin Hu , Yan Zhao , Xiaojie Zhang , Tianbao Shen , Gaoxiang Chen

To address the problem of calibrating the degraded state of engine components under the condition of limited number of sensors, this paper proposes a calibration framework based on deep reinforcement learning and particle filtering. Firstly, the degraded state is inherited from the previous flight cycle through imitation learning, and combined with an improved PPO algorithm to output the a priori distribution of the degraded state; then a filtering algorithm generates a posteriori distributions that consider model error; finally, an improved reward and advantage function guides the agent to calibrate health parameters online. Ablation experiments show a maximum inference error of performance degradation parameters is only 0.048 in multiple failure modes, comprehensive consideration of model and sensor uncertainties, and enhanced robustness to performance models with varying accuracies. In addition, the full process from on-board sensor signals to turbine blade load assessment is demonstrated on turbine-failure flight data, capturing degradation impacts with an average assessment time of 46.13 s. It is demonstrated that this fusion strategy can link complete engine health monitoring with structural-load monitoring of critical components, supporting refined damage assessment of these components during the operation and maintenance phase.

针对传感器数量有限的情况下发动机部件退化状态的标定问题，提出了一种基于深度强化学习和粒子滤波的标定框架。首先，通过模仿学习从前一个飞行周期中继承退化状态，并结合改进的PPO算法输出退化状态的先验分布；然后，滤波算法生成考虑模型误差的后验分布；最后，利用改进的奖励和优势函数指导智能体在线标定健康参数。烧蚀实验表明，在多种失效模式下，综合考虑了模型和传感器的不确定性，性能退化参数的最大推理误差仅为0.048，增强了对不同精度性能模型的鲁棒性。此外，在涡轮故障飞行数据上演示了从机载传感器信号到涡轮叶片载荷评估的整个过程，捕获了退化影响，平均评估时间为46.13 s。结果表明，该融合策略可以将发动机整体健康监测与关键部件的结构载荷监测联系起来，支持在运行和维护阶段对这些部件进行精确的损伤评估。

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引用次数: 0

Autonomous low-thrust trajectory optimization in cislunar space via attention-augmented reinforcement learning 基于注意增强强化学习的地月空间自主低推力轨迹优化

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-12 DOI: 10.1016/j.ast.2026.111673

Izhar Ul Haq , Honghua Dai , Chongrui Du

The push for a sustained human and robotic presence in cislunar space creates a critical need for robust and autonomous trajectory optimization capabilities within the chaotic multi-body dynamics of the Earth-Moon system. This challenge is especially pronounced for low-thrust spacecraft, where traditional methods often struggle to converge and typically require expert-provided initial guesses. We address this challenge with Attention-Augmented Proximal Policy Optimization (A2PPO), a novel deep reinforcement learning (DRL) framework that integrates a directional cross-attention mechanism into an actor-critic policy. When paired with a progressive curriculum learning strategy, A2PPO autonomously learns continuous control policies for precise low-thrust transfers between periodic orbits in the Earth-Moon Circular Restricted Three-Body Problem (CR3BP), balancing transfer time and fuel consumption without relying on any initial guess. We validate A2PPO on four challenging low-thrust transfer scenarios in the Earth-Moon CR3BP and compare its performance with classical optimization methods and state-of-the-art autonomous approaches. In a comparative study of a representative scenario, we demonstrate that the attention mechanism in A2PPO enables the policy to focus on critical state features, yielding faster convergence and higher reward than a standard baseline. Monte Carlo analysis shows that the learned policies exhibit strong robustness, maintaining a 100% success rate under significant initial state perturbations and tolerating up to 32% deterministic thrust degradation without retraining. The A2PPO framework thus represents an important advancement in robust and autonomous trajectory optimization methods that can enhance spacecraft autonomy for low-thrust missions in cislunar space.

推动人类和机器人在地月空间的持续存在，在地月系统的混沌多体动力学中产生了对强大和自主轨迹优化能力的迫切需求。这一挑战对于低推力航天器来说尤其明显，传统方法往往难以收敛，通常需要专家提供初步猜测。我们通过注意力增强近端策略优化（A2PPO）解决了这一挑战，这是一种新的深度强化学习（DRL）框架，将定向交叉注意机制集成到行为者批评策略中。当与渐进式课程学习策略相结合时，A2PPO能够自主学习连续控制策略，实现地月圆受限三体问题（CR3BP）周期轨道间精确低推力转移，在不依赖任何初始猜测的情况下平衡转移时间和燃料消耗。我们在地月CR3BP的四种具有挑战性的低推力转移场景中验证了A2PPO，并将其性能与经典优化方法和最先进的自主方法进行了比较。通过对一个典型场景的比较研究，我们证明了A2PPO中的注意力机制使策略能够专注于关键状态特征，比标准基线产生更快的收敛速度和更高的回报。蒙特卡罗分析表明，学习到的策略具有很强的鲁棒性，在显著的初始状态扰动下保持100%的成功率，并且无需再训练即可承受高达32%的确定性推力退化。因此，A2PPO框架代表了鲁棒自主轨迹优化方法的重要进步，可以增强航天器在地月空间低推力任务中的自主性。

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