Aerospace Science and Technology最新文献_第3页

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

Investigation on the effect of geometric configuration on the flow field morphology and propulsive performance of oblique detonation combustor 几何构造对斜爆燃器流场形态和推进性能影响的研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-20 DOI: 10.1016/j.ast.2025.110227

Haoran Yan, Xin Han, Tao Zhang, Chongguang Shi, Yancheng You

{"title":"Investigation on the effect of geometric configuration on the flow field morphology and propulsive performance of oblique detonation combustor","authors":"Haoran Yan, Xin Han, Tao Zhang, Chongguang Shi, Yancheng You","doi":"10.1016/j.ast.2025.110227","DOIUrl":"10.1016/j.ast.2025.110227","url":null,"abstract":"<div><div>This study conducts numerical simulations of Oblique Detonation Wave (ODW) flow fields in confined spaces, focusing on how variations in the combustor’s initial wedge angle and expansion angle affect flow field morphology and propulsion performance. A new initiation mechanism induced by small wedge angles has been identified, enabling the transition from shock-induced combustion to oblique detonation combustion. A simplified model was developed to predict the position and height of the Mach Stem (MS) in the detonation flow field, providing insights into the regulation of the transition from normal detonation combustion to oblique detonation combustion. The study confirms that the incident wave’s intensity and the separation zone's geometric parameters are the two critical factors governing MS dynamics. Furthermore, the downstream parameter variations associated with shock-induced combustion, oblique detonation combustion, and normal detonation combustion are analyzed, explaining the relationship between propulsion performance and flow field structure. Adjusting wall curvature to reduce detonation wave overdrive is found to improve the combustor’s propulsion performance significantly. This research establishes a clear link between detonation flow fields and combustor geometry, offering valuable insights into the dynamic regulation of Oblique Detonation Engines (ODEs) under near-realistic operating conditions.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110227"},"PeriodicalIF":5.0,"publicationDate":"2025-04-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143859399","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

Experimental investigation on the flow mixing and core length of a supersonic multiple jet configuration using cross-wire as vortex generators 以交叉丝为涡发生器的超声速多射流结构流动混合及芯长实验研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-19 DOI: 10.1016/j.ast.2025.110214

Mohammed Faheem , Sher Afghan Khan , Mohammad Mukhtar Alam , Beena Stanislaus Arputharaj , Fayaz Hussain , Qasem M. Al-Mdallal

{"title":"Experimental investigation on the flow mixing and core length of a supersonic multiple jet configuration using cross-wire as vortex generators","authors":"Mohammed Faheem , Sher Afghan Khan , Mohammad Mukhtar Alam , Beena Stanislaus Arputharaj , Fayaz Hussain , Qasem M. Al-Mdallal","doi":"10.1016/j.ast.2025.110214","DOIUrl":"10.1016/j.ast.2025.110214","url":null,"abstract":"<div><div>Many Engineering applications use multi-jet systems, such as aircraft propulsion units and spacecraft. A complex aerodynamic flow field occurs when multiple jets are close to each other. This study experimentally examines the supersonic jets' mean flow field and mixing characteristics from one, two, and three different converging-diverging nozzles placed in close vicinity. The cross-wire is used as a passive control technique to investigate the impact of the control on the flow field and the core length. The nozzle is designed for Mach number <em>M</em> = 1.5, with an inter-nozzle positioning equal to twofold the nozzle exit diameter. The typical contact procedure and the triple jet's growth are discussed using cross-sectional contour patterns and transverse pressure profiles. The effect of leading parallel jets on local flow field features, comprising shock wave structure, supersonic core, and jet spread, is observed by measuring pressure beside the jet axes. Similarly, the flow spread rate declines when the quantity of jet flow increases- this is mainly owed to a decrease in attuning; subsequently, the jet decays more slowly, and the core length decreases. Schlieren's pictures of triple, twin, and single jets reveal that the core of the supersonic jet varies in triple and twin jets compared to single jets.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110214"},"PeriodicalIF":5.0,"publicationDate":"2025-04-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143877472","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

Adaptive attitude tracking control for reusable launch vehicle with actuator and sensor faults 可重复使用运载火箭执行器和传感器故障的自适应姿态跟踪控制

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-17 DOI: 10.1016/j.ast.2025.110226

Wenting Li, Jinsong Zhao, Chen Sun, Shanwei Su, Yan Lin

引用次数: 0

Inviscid information-embedded machine learning for the airfoil inverse mapping 用于翼型逆映射的无粘信息嵌入机器学习

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-17 DOI: 10.1016/j.ast.2025.110219

Ruopeng Yan, Jiayi Zhao, Diangui Huang

{"title":"Inviscid information-embedded machine learning for the airfoil inverse mapping","authors":"Ruopeng Yan, Jiayi Zhao, Diangui Huang","doi":"10.1016/j.ast.2025.110219","DOIUrl":"10.1016/j.ast.2025.110219","url":null,"abstract":"<div><div>The mapping process within the airfoil inverse design is to derive airfoil geometry based on the prescribed surface aerodynamic distribution, typically the pressure coefficient (C<sub>p</sub>) distribution. Recent studies have used neural networks (C<sub>p,v</sub>-y models) to rapidly predict airfoil shapes according to the designed C<sub>p</sub> distributions which consider viscosity (C<sub>p,v</sub>). However, the complex relationship between C<sub>p,v</sub> and airfoil geometry challenges surrogate models, often requiring extensive training data to achieve sufficient accuracy. This study employs inviscid C<sub>p</sub> distribution (C<sub>p,i</sub>) as an intermediate bridge between C<sub>p,v</sub> and airfoil geometry. The proposed C<sub>p,v</sub>-C<sub>p,i</sub>-y model simplifies the mapping learned by neural network through converting C<sub>p,v</sub>-y into C<sub>p,v</sub>-C<sub>p,i</sub>. And the C<sub>p,i</sub>-y is achieved via parametric airfoil iteration based on potential flow theory (panel method). Results demonstrate that the new model reduces airfoil prediction errors by 25–40 % on average compared with two existing C<sub>p,v</sub>-y models. Notably, 100–500 % reduction in maximum relative error, which often occurs at the critical parts in airfoil design such as the maximum thickness and shape of leading edge under C<sub>p,v</sub> models, can be observed in the test samples. And the better generalization ability is further validated through the flatter minima and less non-convexity of the loss surface under C<sub>p,v</sub>-C<sub>p,i</sub>-y model compared with the one under C<sub>p,v</sub>-y model. The idea of introducing C<sub>p,i</sub> provides insights into addressing the issue of large prediction errors caused by strong nonlinear mappings in the traditional C<sub>p,v</sub>-y models and has the potential to handle similar issues like cascade or three-dimensional inverse problems.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110219"},"PeriodicalIF":5.0,"publicationDate":"2025-04-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143891859","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

Drag and overall aeroheating reduction of a dual-disk-dual-jet in rarefied hypersonic flow in near space 近空间稀薄高超声速流动中双盘双射流的阻力和整体气动加热减小

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-16 DOI: 10.1016/j.ast.2025.110229

Chen Ye, Shuzhou Fang, Zijian Ni, Tianwei Liu, Shenxing Luo

{"title":"Drag and overall aeroheating reduction of a dual-disk-dual-jet in rarefied hypersonic flow in near space","authors":"Chen Ye, Shuzhou Fang, Zijian Ni, Tianwei Liu, Shenxing Luo","doi":"10.1016/j.ast.2025.110229","DOIUrl":"10.1016/j.ast.2025.110229","url":null,"abstract":"<div><div>Based on the direct simulation Monte Carlo method (DSMC), this paper studies the near-space hypersonic rarefied flowfield around the dual-disk with and without jet. The research extends the dual-disk-dual-jet configuration to near space and finds that only increasing the number of disks will no longer be a good solution for reducing drag in hypersonic rarefied flow. The study proposes a comprehensive evaluation of blunt body and forebody shock control devices for aeroheating reduction. A key finding is that an opposing jet on the first disk is crucial for the aeroheating protection of the spike-disk itself, while eliminating or weakening stagnation points on disks. The research further demonstrates that allocating the fixed jet mass flow rate to the opposing and lateral jet is an optimal strategy in hypersonic rarefied flow. This paper also shows that the jet only needs a lower mass flow rate in rarefied flow. This study investigates the performance of a dual-disk-dual-jet model in hypersonic rarefied flow in near space. Compared to the dual-disk without jet (base model), in the studied parameter range, when the pressure ratio is 0.08, the total mass flow rate of the jet is 0.0427kg/s, the drag and aeroheating reduction of the blunt body in the dual-disk-dual-jet model are reduced by 64.3 % and 86.8 %, respectively.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110229"},"PeriodicalIF":5.0,"publicationDate":"2025-04-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143859400","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