Aerospace Science and Technology最新文献_第2页

Numerical and experimental investigation of multifunctional high-efficiency anti-icing nickel-plated carbon fiber heating elements for wing-shaped composite airfoils 翼型复合材料翼型多功能高效防冰镀镍碳纤维加热元件的数值与实验研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-23 DOI: 10.1016/j.ast.2025.110249

Won Tae Lee , Dong Jun Hong , Young Woo Nam , Rho Shin Myong

{"title":"Numerical and experimental investigation of multifunctional high-efficiency anti-icing nickel-plated carbon fiber heating elements for wing-shaped composite airfoils","authors":"Won Tae Lee , Dong Jun Hong , Young Woo Nam , Rho Shin Myong","doi":"10.1016/j.ast.2025.110249","DOIUrl":"10.1016/j.ast.2025.110249","url":null,"abstract":"<div><div>This study introduces wing-shaped composite airfoils integrated with high-efficiency, multifunctional anti-icing heating elements composed of nickel-plated carbon fiber. The anti-icing performance of these airfoils was evaluated through experiments conducted in an Icing Research Tunnel (IRT) under representative glaze icing conditions. These results indicate that the nickel-plated carbon fiber exhibits an electrothermal conversion efficiency of 0.1 W/℃ and a heating rate of 0.64 ℃/s. In particular, icing wind tunnel tests conducted at a power density of 9.0 kW/m² demonstrated that the heating zone remained above the freezing point, thereby preventing ice accretion, while runback ice formed in the region c orresponding to X/<em>C</em> ≈ 24–32 % during a 300 s accretion period. The experimental results demonstrated high reliability and accuracy, showing a temperature difference of <0.5 °C compared to the surface temperature predicted by the multiphysics anti-icing simulation under identical conditions.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110249"},"PeriodicalIF":5.0,"publicationDate":"2025-04-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143894887","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Event-triggered three-dimensional adaptive anti-disturbance IGC method for a class of flight vehicles 一类飞行器的事件触发三维自适应抗干扰IGC方法

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-23 DOI: 10.1016/j.ast.2025.110233

Zheng Wang , Yanghong Qiu , Yuting Hao , Yunfei Bai , Likuan Qiu , Gaopeng Zhang

{"title":"Event-triggered three-dimensional adaptive anti-disturbance IGC method for a class of flight vehicles","authors":"Zheng Wang , Yanghong Qiu , Yuting Hao , Yunfei Bai , Likuan Qiu , Gaopeng Zhang","doi":"10.1016/j.ast.2025.110233","DOIUrl":"10.1016/j.ast.2025.110233","url":null,"abstract":"<div><div>This paper presents a novel event-triggered three-dimensional integrated guidance and control (IGC) methodology for flight vehicles, designed to address unmodeled dynamic disturbances and stringent state constraints. A hyperbolic tangent function is used to estimate the bounds of unmodeled disturbances, effectively managing time-varying and multi-source uncertainties. To enforce state constraints, the IGC model is augmented with a defined set of admissible states and incorporates a nonlinear transformation function, thus establishing a state-constrained integrated guidance and control (SCIGC) model. Event-triggered criteria are then developed to reduce the update rate of control commands, and the stability of the proposed event-triggered guidance and control methodology is rigorously analyzed. Additionally, it is demonstrated that the proposed event-triggered method avoids Zeno behavior. To prevent instability and numerical issues arising from the differentiation of virtual controllers, a low-pass filter is introduced. Finally, the efficacy of the proposed method is validated through Lyapunov functions and its capability to intercept tactical ballistic targets is confirmed by numerical simulations.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110233"},"PeriodicalIF":5.0,"publicationDate":"2025-04-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143879103","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Low computational sequential optimization for large-scale satellite formation reconfiguration 大规模卫星编队重构的低计算顺序优化

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-23 DOI: 10.1016/j.ast.2025.110232

Jihe Wang , Qiaoling Zeng , Chenglong Xu , Chengxi Zhang , Jinxiu Zhang

{"title":"Low computational sequential optimization for large-scale satellite formation reconfiguration","authors":"Jihe Wang , Qiaoling Zeng , Chenglong Xu , Chengxi Zhang , Jinxiu Zhang","doi":"10.1016/j.ast.2025.110232","DOIUrl":"10.1016/j.ast.2025.110232","url":null,"abstract":"<div><div>Large-scale satellite formations enhance mission flexibility and redundancy but also increase challenges in coordination, computational load and collision risks. This paper develops a low computational sequential optimization method for fuel-efficient and passively-safe reconfiguration. We propose using an optimal three-impulse analytical solution to identify passively unsafe satellites, thereby reducing the number of satellites that require further optimization. This analytical solution also serves as an initial guess, shrinking the search space for the optimization. The problem is then decomposed into multiple single-satellite reconfiguration subproblems, which are optimized in parallel to improve computational efficiency. Two optimization strategies for subproblems are proposed: fuel-optimal and fuel-suboptimal optimization. When passive safety requirements are not met in certain iterations, the optimization relaxes fuel constraints to prioritize safety. The sequential constraint management process dynamically adjusts the trade-off between fuel costs and passive safety based on the current scenarios. This flexibility allows the method to adapt the varying reconfiguration scenarios, since not all scenarios can meet the passive safety requirements under fuel-optimal conditions. This method provides a more scalable and flexible solution to large-scale satellite formation reconfiguration optimization over traditional centralized methods. It is particularly beneficial for medium to large satellite formations (≥100 satellites). Finally, a numerical simulation is given to verify the computational efficiency and passive safety improvements of the proposed method. The algorithm is tested on a 100-satellite formation. The passive safety parameter improved from 0.0189 to 21.1165 m, and runtime was reduced by 67% compared to centralized optimization result.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110232"},"PeriodicalIF":5.0,"publicationDate":"2025-04-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143879102","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

A new distributionally robust optimization method and its application to rotor-stator clearance 一种新的分布鲁棒优化方法及其在转子-定子间隙中的应用

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-23 DOI: 10.1016/j.ast.2025.110248

Xiao-Le Guan , Zhen-Xing Zeng , Hong-Shuang Li , Yuan-Zhuo Ma

{"title":"A new distributionally robust optimization method and its application to rotor-stator clearance","authors":"Xiao-Le Guan , Zhen-Xing Zeng , Hong-Shuang Li , Yuan-Zhuo Ma","doi":"10.1016/j.ast.2025.110248","DOIUrl":"10.1016/j.ast.2025.110248","url":null,"abstract":"<div><div>Robust design optimization is crucial for ensuring the normal and stable operational performance of engineering structures by considering the effects of uncertainties inherent in the production and manufacturing processes of structural components. However, current robust design optimization methods are still relatively conservative, time-consuming, and often necessitate significant sacrifice in structural performance to achieve robustness. In response to these issues, the present study proposes a novel distributionally robust optimization (DRO) method based on a two-level Kriging surrogate model. The first-level Kriging model is constructed to replace the relationship between design variables and structural response, thereby enabling the construction of ambiguity sets based on the Euclidean norm and Kullback–Leibler (KL) divergence. This transforms the inner maximization problem into a deterministic optimization. Subsequently, the second-level Kriging model is constructed to approximate the relationship between design variables and the maximum expected value so that the outer minimization problem is also degenerated into a deterministic optimization, which is then solved by subset simulation optimization. The performance of the proposed method is preliminarily validated through a numerical examples, after which its engineering practicability is demonstrated by comparing the results of DRO with those of deterministic optimization for the variation in rotor-stator clearance in a small turbine engine.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110248"},"PeriodicalIF":5.0,"publicationDate":"2025-04-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143888062","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Total energy control system-based interval type-3 fuzzy logic controller for fixed-wing unmanned aerial vehicle longitudinal flight dynamics 基于总能量控制系统的区间3型模糊逻辑控制器用于固定翼无人机纵向飞行动力学

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-23 DOI: 10.1016/j.ast.2025.110253

Abdessamad El Mobaraky , Khalid Kouiss , Ahmed Chebak

{"title":"Total energy control system-based interval type-3 fuzzy logic controller for fixed-wing unmanned aerial vehicle longitudinal flight dynamics","authors":"Abdessamad El Mobaraky , Khalid Kouiss , Ahmed Chebak","doi":"10.1016/j.ast.2025.110253","DOIUrl":"10.1016/j.ast.2025.110253","url":null,"abstract":"<div><div>Traditional longitudinal flight controllers for fixed-wing unmanned aerial vehicles (FW UAVs) assume a decoupling of airspeed and flight path angle dynamics, leading to stability degradations in challenging conditions. The total energy control system (TECS), a multi-input, multi-output (MIMO) flight controller, computes thrust commands based on the total energy requirements for the desired flight path (altitude) and airspeed while adjusting the elevators for energy distribution errors. Although it provides coupled control of flight path angle and airspeed to meet flight requirements, it faces challenges in handling model uncertainties and environmental disturbances. Therefore, this paper presents a novel interval type-3 fuzzy logic controller (IT3 FLC) for the longitudinal flight dynamics of an FW UAV. The controller consists of an inner loop with an IT3 fuzzy proportional-integral-derivative (IT3 FPID) controller for pitch dynamics and an outer loop with an IT3 fuzzy TECS (IT3 FTECS) for flight path and airspeed. The optimization of the scaling factors and all the fuzzy system parameters in the proposed controller was achieved using the grey wolf optimizer (GWO) algorithm. The proposed strategy, tested under ideal conditions, wind disturbances, model parameter variations, and a comprehensive statistical analysis under stochastic uncertainties and turbulent winds, shows superior performance in dealing with uncertainties and nonlinearities in UAV dynamics compared to a type-2 FLC (T2 FLC), a TECS, and a PID-based successive loop closure (PID-SLC). The results also demonstrate accurate tracking of the desired altitude while minimizing airspeed deviation and vice versa.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110253"},"PeriodicalIF":5.0,"publicationDate":"2025-04-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143888065","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Fault-tolerant target tracking control for the USV-UAV platform via the visual-based guidance and fault-tolerant control 基于视觉制导和容错控制的USV-UAV平台容错目标跟踪控制

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-22 DOI: 10.1016/j.ast.2025.110230

Guoqing Zhang, Chuanjie Lin, Jiqiang Li, Wenjun Zhang, Xianku Zhang

{"title":"Fault-tolerant target tracking control for the USV-UAV platform via the visual-based guidance and fault-tolerant control","authors":"Guoqing Zhang, Chuanjie Lin, Jiqiang Li, Wenjun Zhang, Xianku Zhang","doi":"10.1016/j.ast.2025.110230","DOIUrl":"10.1016/j.ast.2025.110230","url":null,"abstract":"<div><div>This paper investigates a new cooperative trajectory tracking framework for the USV-UAV platform that uses a visual-based inversion guidance principle and sensor fault-tolerant control mechanism in the presence of external disturbances. This provides a new strategy for the platform independent of traditional navigation sensor. In the visual guidance module, the reference path of the USV-UAV would be calculated by utilization of the mapping technique according to the sampled images of the target vehicle obtained by an UAV. Further, the desired guidance signals are provided on basis of the fixed position relative to the target vessel. Associate with the developed guidance signal, a robust adaptive fault-tolerant control algorithm is designed to execute a tracking and monitoring mission of the unsupervised vehicles, where the constant and time-varying attitude sensor faults can be addressed by an application of the adaptive observer technique. Besides, the robust neural damping and dynamic surface control techniques are also introduced for tackling the problems of the model uncertainties, external disturbances and computational burden. Through the Lyapunov theorem, the semi-global uniformly ultimately bounded (SGUUB) stability property is proved. The advantages and the effectiveness of the proposed algorithm are evaluated using the numerical simulations.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110230"},"PeriodicalIF":5.0,"publicationDate":"2025-04-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143859401","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Investigation on same-track multirotor separation using CFD simulated flow field and software in the loop stability analysis 利用CFD模拟流场和软件对同轨多转子分离进行回路稳定性分析

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-22 DOI: 10.1016/j.ast.2025.110225

C.H. John Wang , Joshua Christian Nathanael , Kin Huat Low , Mir Feroskhan

{"title":"Investigation on same-track multirotor separation using CFD simulated flow field and software in the loop stability analysis","authors":"C.H. John Wang , Joshua Christian Nathanael , Kin Huat Low , Mir Feroskhan","doi":"10.1016/j.ast.2025.110225","DOIUrl":"10.1016/j.ast.2025.110225","url":null,"abstract":"<div><div>An important factor of maintaining modern air traffic safety is the determination and enforcement of separation minima. Two major factors affect the determination of separation minima in civil aviation: the radar separation to manage uncertainties due to communication, navigation, and surveillance performance, and the wake separation due to aircraft instability when encountering aircraft generated wake turbulence. Similar implementation would be needed in urban airspace for unmanned aerial system traffic management (UTM) given the elevated risk to third-parties population that could result from a mid-air collision. With the widespread use of satellite-based navigation and transponder-based surveillance in UAS, the uncertainties contributing to CNS separation would greatly reduce. However, the physical forces driving the need for wake separation remains, and could be the dominating factors in UTM separation requirements. Comparing to their fixed-wing counterpart, few studies have been conducted on wake turbulence profile of the multirotor UAS, and even fewer on the stability of multirotor following a wake encounter. This paper investigates the consequence of multirotor encountering wake produced by another multirotor using a combination of CFD and software in the loop simulation with Pixhawk4 flight controller. The results suggest that while larger multirotor has greater wake turbulence strength hence greater hazard upon encounter, the larger initial separation gap between the vortex structures could also create a safe passage for multirotor with sufficiently small arm-span.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110225"},"PeriodicalIF":5.0,"publicationDate":"2025-04-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143882064","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Flow mechanisms and loss analysis of cavity leakage flow in a 1.5-stage axial compressor 1.5级轴流压气机空腔泄漏流流动机理及损失分析

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-22 DOI: 10.1016/j.ast.2025.110245

Hao Liu , Guoqing Li , Chenyang Kang , Yunhong Ruan , Ziliang Li , Xingen Lu

{"title":"Flow mechanisms and loss analysis of cavity leakage flow in a 1.5-stage axial compressor","authors":"Hao Liu , Guoqing Li , Chenyang Kang , Yunhong Ruan , Ziliang Li , Xingen Lu","doi":"10.1016/j.ast.2025.110245","DOIUrl":"10.1016/j.ast.2025.110245","url":null,"abstract":"<div><div>Due to the coupled effects of various cavity leakage flows, the loss mechanisms induced by leakage flow in multi-stage compressors remain insufficiently understood. Investigating leakage flow within a stage environment is crucial for revealing these mechanisms. In this paper, a 1.5-stage compressor without and with a labyrinth seal is modeled to elucidate the flow propagation mechanisms of leakage flow on the upstream and downstream rotors. Performance testing of a multi-stage compressor with labyrinth seals is conducted to validate the accuracy of numerical method. Furthermore, by introducing local entropy generation rates, a sub-regional method for quantifying losses originating from different sources is proposed. The results reveal a surprising finding: leakage flow reduces the downstream rotor losses by 1.14 %. This reduction is attributed to the improved flow field in the midspan region and the accumulation of low-energy fluid, which leads to a 0.08 % reduction in boundary layer loss. The mixing of leakage flow with the mainstream occurs at the stator leading edge, significantly altering the stator flow field. The newly generated cavity leakage vortex and the enlarged corner vortex increase secondary flow loss by 0.53 %, while the accumulation of low-energy fluid in the hub region raises mainstream loss by 2 %. This study offers valuable insights into mitigating losses caused by leakage flow and provides a theoretical foundation for controlling the impact of leakage flow in compressors.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110245"},"PeriodicalIF":5.0,"publicationDate":"2025-04-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143877274","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Air system optimization coupled with electric supercharger matching of a two-stroke aircraft engine based on machine learning and NSGA-III 基于机器学习和NSGA-III的二冲程航空发动机空气系统优化与电动增压器匹配

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-21 DOI: 10.1016/j.ast.2025.110234

Lingfeng Zhong , Qianfan Xin , Rui Liu , Raihanul Islam , Md Saiful Islam , Yufeng Chen

{"title":"Air system optimization coupled with electric supercharger matching of a two-stroke aircraft engine based on machine learning and NSGA-III","authors":"Lingfeng Zhong , Qianfan Xin , Rui Liu , Raihanul Islam , Md Saiful Islam , Yufeng Chen","doi":"10.1016/j.ast.2025.110234","DOIUrl":"10.1016/j.ast.2025.110234","url":null,"abstract":"<div><div>To increase the flight altitude of small unmanned aerial vehicles (UAVs), achieving power recovery at high altitudes through supercharging is crucial. A spark ignition two-stroke engine model was developed in GT-POWER and calibrated using experimental data. Engine performance with an electric supercharger was analyzed. The coupling mechanism of the intercooler in the intake system, the exhaust resonance pipe in the exhaust system, and the electrically supercharged two-stroke engine were studied. The results demonstrated that the supercharged two-stroke engine with the intercooler successfully maintained pwer at alitudes between 1,000 and 6,000 m without degradation, despite the decrease in power-to-weight ratio due to the intercooler. The nondominated sorting genetic algorithm-III (NSGA-III) and machine learning were used to optimize geometry parameters of the exhaust resonance pipe. Brake specific fuel consumption (BSFC), compressor power, and exhaust temperature were selected as optimization objectives. The Pareto solution set revealed significant tradeoff relationships among the objectives. In the Pareto solution set, the optimal values of BSFC, compressor power consumption, and exhaust gas temperature are 389.6 [g/(kW·h)], 1.31 kW, and 604.1 K, respectively. The optimized exhaust resonance pipe can maintain engine and compressor performance in a wide altitude range, allowing the engine to maintain power at higher altitudes.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110234"},"PeriodicalIF":5.0,"publicationDate":"2025-04-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143869558","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Uncertainty effect of leading edge fouling on aerodynamic performance of compressor cascades 前缘结垢对压气机叶栅气动性能的不确定性影响

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-21 DOI: 10.1016/j.ast.2025.110235

Panpan Tu , Guang Yang , Limin Gao , Tantao Liu , Song Yang

引用次数: 0