Aerospace Science and Technology最新文献

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Physics-Informed Sparse Reinforcement Learning for Hybrid VTOL UAV Control:HILS Verification and Tethered Hover Benchmarking 混合垂直起降无人机控制的物理信息稀疏强化学习：HILS验证和系留悬停基准测试

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-16 DOI: 10.1016/j.ast.2026.111646

Mohammed Osman, Yuanqing Xia, Mohammed Mahdi, Tayyab Manzoor, Ghulam E. Mustafa Abro, Abdulrahman H. Bajodah

引用次数: 0

Dynamic Task Allocation for Multi-UAVs in Disaster Scenarios: A Novel Two-Level Optimization Method with Forecasting 灾害场景下多无人机动态任务分配：一种带预测的两级优化方法

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-16 DOI: 10.1016/j.ast.2026.111711

Quancheng Pu, Lu Yang, Tieshan Li

引用次数: 0

Dynamic Time-Window Nash Equilibrium Strategies for UAV Pursuit-Evasion Games Under Incomplete Strategies 不完全策略下无人机追逃博弈的动态时窗纳什均衡策略

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-16 DOI: 10.1016/j.ast.2026.111651

Lei Sun, Yuhui Wang, Mou Chen

引用次数: 0

Study on flow characteristics of squealer tip configuration with coolant injection in a transonic turbine 跨声速涡轮喷注冷却剂尖叶结构流动特性研究

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-16 DOI: 10.1016/j.ast.2026.111729

Chen Yao, Nan Xu, Wei Du, Lei Luo, Han Yan, Yong Shuai

引用次数: 0

Vortex Breakdown Suppression in a Compressor Cascade Using an L-shaped Groove via Flow Deflection 利用流动偏转的l型槽抑制压气机叶栅涡击穿

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-16 DOI: 10.1016/j.ast.2026.111709

Xiang Zhang, Yanhui Wu, Ziyun Zhang, Dong Wang, Chongshan Liu

引用次数: 0

Task Allocation without Direct Communication: Graphical Game based Swarm Interception Allocation 没有直接通信的任务分配：基于图形游戏的群体拦截分配

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-16 DOI: 10.1016/j.ast.2026.111712

Kun Yang, Chenggang Bai, Quan Quan

引用次数: 0

Numerical Investigation of the Partition Rib Design and Loss Reduction Mechanism in Squealer Blade Tip 叶片尖部隔板设计及减损机理的数值研究

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-16 DOI: 10.1016/j.ast.2026.111730

Yun Jin, Hongmei Li, Shaopeng Lu, Yushi Bai, Jinfang Teng

引用次数: 0

Fuzzy adaptive prescribed performance fault-tolerant control of hypersonic vehicles with multiple faults and input saturation 多故障输入饱和高超声速飞行器模糊自适应预定性能容错控制

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-16 DOI: 10.1016/j.ast.2025.111442

Jun Wang, Cheng Zhang, Chenming Zheng, Jiayu Bao, Zhangyao Zheng, Xinwan Kong

引用次数: 0

Numerical study on the effect of surface pulsed arc discharge on the aerodynamic characteristics of the hypersonic airfoil 表面脉冲电弧放电对高超声速翼型气动特性影响的数值研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-15 DOI: 10.1016/j.ast.2026.111724

Xi Geng , Liang Hu , Zhikun Sun , Zidong Gan , Keming Cheng , Da Huang

Surface Pulsed Arc Discharge (SPAD) plasma actuators have demonstrated significant potential for active flow control in high-speed flow environments. The paper studies the impact of SPAD on the aerodynamic performance of hypersonic airfoils in a Mach 5 flow field through numerical simulations. The results reveal that both the geometric placement of the actuator and its discharge parameters have a critical influence on the actuation efficacy in enhancing aerodynamic performance. Specifically, the aerodynamic control effect of SPAD is primarily manifested in two complementary aspects: lift enhancement and drag reduction. Notably, actuator configurations dominated by lift increase induce substantial alterations in the airfoil’s pitching moment. When the SPAD is deployed within the airfoil’s transitional region, peak improvements are achieved: a maximum lift-to-drag ratio enhancement of up to 20.7% and a corresponding maximum aerodynamic performance change of 24.9%. Under a constraint of fixed total electrical energy input, optimal aerodynamic outcomes can be achieved by tuning the discharge frequency and pulse width. At low discharge frequencies, the flow structures generated by individual pulses exhibit minimal temporal interference, allowing their aerodynamic effects to accumulate nearly linearly over successive pulses. This quasi-independent pulse interaction enables a time-additive control strategy that effectively enhances overall performance. The findings provide valuable insights and practical guidelines for designing and implementing SPAD-based flow control systems in hypersonic applications, highlighting its promise as a versatile and energy-efficient actuation technology for next-generation high-speed vehicles.

表面脉冲电弧放电（SPAD）等离子体致动器在高速流动环境中已被证明具有显著的主动流动控制潜力。本文通过数值模拟研究了在5马赫流场中SPAD对高超声速翼型气动性能的影响。结果表明，作动器的几何位置及其放电参数对作动器的气动性能有重要影响。具体来说，SPAD的气动控制效果主要表现在增升力和减阻两个互补的方面。值得注意的是，由升力增加主导的致动器配置诱导了翼型俯仰力矩的实质性变化。当SPAD部署在翼型的过渡区域时，达到了峰值改进：最大升阻比提高高达20.7%，相应的最大气动性能变化为24.9%。在总电能输入固定的约束下，通过调整放电频率和脉冲宽度可以获得最佳的气动效果。在低放电频率下，单个脉冲产生的流动结构表现出最小的时间干扰，使其气动效应在连续脉冲中几乎呈线性累积。这种准独立的脉冲相互作用实现了时间加性控制策略，有效地提高了整体性能。该研究结果为高超声速应用中基于spad的流量控制系统的设计和实施提供了有价值的见解和实用指南，突出了其作为下一代高速飞行器通用和节能驱动技术的前景。

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引用次数: 0

Experimental investigation on the inlet shock wave/boundary layer interaction controlled by pulsed arc plasma discharge 脉冲电弧等离子体放电控制进口激波/边界层相互作用的实验研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-15 DOI: 10.1016/j.ast.2026.111722

Xinyu Kong , Zhi Su , Biao Wei , Hua Liang , Haohua Zong , Dongshen Zhang , Heseng Yang , Min Jia

Shock wave/boundary layer interaction (SWBLI) is a prevalent phenomenon in supersonic and hypersonic inlets. This interaction induces significant degradation in aircraft propulsion system performance. To address this challenge, experiments utilizing pulsed arc discharge plasma actuation are conducted in a two-dimensional simplified inlet at Mach 4. The response of the inlet SWBLI is examined from multiple perspectives, including time-averaged flow field characteristics, evolution mechanisms of flow structure and shock wave unsteady motion. Based on these examinations, a comprehensive analysis of the flow control mechanism was performed. Results show that plasma actuation can produce fast pressure waves and controlling gas bubbles (CGBs), which control the complex SWBLI system in sequence. Specifically, the pressure waves initially disturb the incident shock wave, causing it to shorten and bend. Then, the controlling gas bubbles (CGBs) decompose both the separation shock wave and the reattachment shock wave into multiple weaker compression waves. This decomposition effectively weakens or even eliminates their fundamental roots. Analysis of the power spectrum shows that the unsteady motion of the shock wave is suppressed through coupling plasma actuation with the oscillation frequency of the incident shock wave. The control effects along the y-axis on the incident shock wave occur in three regions: no-effect, linear increase, and saturation. Nearly half of the incident shock wave is influenced, which helps prevent flow separation. The effects of plasma actuation on the intensity of the incident shock wave increase as the distance to the wall decreases. Within a wide frequency range of 500 Hz to 8 kHz, the unsteady motion of the incident shock wave can be weakened and shifted downstream.

激波/边界层相互作用（SWBLI）是超声速和高超声速进气道中普遍存在的现象。这种相互作用导致飞机推进系统性能显著下降。为了解决这一挑战，利用脉冲电弧放电等离子体驱动的实验在4马赫的二维简化进气道中进行。从时间平均流场特征、流动结构演化机制和激波非定常运动等多个角度对进气道SWBLI的响应进行了研究。在此基础上，对流动控制机理进行了全面分析。结果表明，等离子体驱动可以产生快速压力波和控制气泡，从而对复杂的SWBLI系统进行有序控制。具体来说，压力波最初会干扰入射冲击波，使其缩短和弯曲。然后，控制气泡将分离激波和再附着激波分解成多个较弱的压缩波。这种分解有效地削弱甚至消除了它们的根本根源。功率谱分析表明，等离子体驱动与入射激波的振荡频率耦合抑制了激波的非定常运动。沿y轴方向对入射激波的控制作用发生在无效应、线性增加和饱和三个区域。近一半的入射激波受到影响，有助于防止流动分离。等离子体驱动对入射激波强度的影响随着离壁距离的减小而增大。在500hz ~ 8khz的宽频率范围内，入射激波的非定常运动可以被减弱并向下游移动。

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