The Aeronautical Journal最新文献_第3页

Flight performance analysis of aerial fire fighting 空中灭火的飞行性能分析

The Aeronautical Journal Pub Date : 2024-04-11 DOI: 10.1017/aer.2024.29

A. Struminska, A. Filippone

{"title":"Flight performance analysis of aerial fire fighting","authors":"A. Struminska, A. Filippone","doi":"10.1017/aer.2024.29","DOIUrl":"https://doi.org/10.1017/aer.2024.29","url":null,"abstract":"\u0000 This paper investigates the operational patterns and techniques of aerial fire fighting. It is demonstrated that manoeuvrability and endurance are the main characteristics when choosing air tactical aircraft; focus is on load capability for helicopters and air tankers. Water tank filling and deployment techniques are evaluated. Aircraft using pressure deployment systems are found to produce more uniform and heavy coverage in comparison with gravity systems. ADS-B open source data of flight operations and performance was collected. Operational patterns are found to be independent on the size of particular aircraft category (non-amphibious and amphibious air tanker, helicopter, air-tactical aircraft). Effectiveness and cost are modelled using the retardant dropped per operation and the average number of daily missions. The largest aircraft, Type-I helicopters and very large air tankers (VLAT) are found to be the most effective water- and retardant-dropping aircraft. The best cost-to-litre-dropped ratio for water-dropping aircraft is attributed to Type-III helicopters and amphibious Type-III aircraft; for retardant-dropping aircraft, VLAT are most effective. To maximise fire fighting effectiveness, Type-I helicopters and VLAT should be used as far as possible, with pressure deployment systems.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"20 6","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140714983","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Experimental studies on the Hartmann tube 哈特曼管实验研究

The Aeronautical Journal Pub Date : 2024-04-11 DOI: 10.1017/aer.2024.34

E. Rathakrishnan

{"title":"Experimental studies on the Hartmann tube","authors":"E. Rathakrishnan","doi":"10.1017/aer.2024.34","DOIUrl":"https://doi.org/10.1017/aer.2024.34","url":null,"abstract":"\u0000 The effect of tube depth, the separation distance between the tube and nozzle exit, and the nozzle pressure ratio on the characteristics of the flow coming out of the Hartmann tube was studied experimentally. The configuration used in this work consists of an underexpanded sonic jet emanating from a convergent nozzle directed into a closed-ended cylindrical tube of the same diameter (D) as the nozzle exit. The nozzle was operated at two levels of underexpansion corresponding to nozzle pressure ratio (NPR) 3 and 5. The distance (S) from nozzle exit and tube inlet was varied from 0.4D to 4D. Discrete high-amplitude tones (the jet regurgitant, JRG) were produced, only at certain (periodic) intervals (near the shock-cell terminations) of spacing for NPR 3, while for NPR 5 the JRG tones are produced at all points beyond the first shock-cell. For locations other than these, high-frequency tones (screech mode) were observed. The connection between the jet structure and operating modes revealed that the location of standoff shock ahead of the tube with respect to the jet structure plays a dominant role in the observed ‘modes’ rather than the nozzle tube separation. The results reveal that the frequency response of longer tubes in JRG mode approaches their quarter wave frequencies. The high-frequency oscillations observed in the screech mode showed independency with cavity (pipe) depth, contrary to the available literature, the transition between ‘different modes’ oscillation is a function of cavity depth.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"61 2","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140713583","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Neural network-based robust adaptive super-twisting sliding mode fault-tolerant control for a class of tilt tri-rotor UAVs with unmodeled dynamics 基于神经网络的鲁棒自适应超扭曲滑模容错控制，适用于一类具有未建模动态特性的倾斜三旋翼无人机

The Aeronautical Journal Pub Date : 2024-04-08 DOI: 10.1017/aer.2024.19

L. Chao, Y. Bai, Z. Wang, Y. Yin

{"title":"Neural network-based robust adaptive super-twisting sliding mode fault-tolerant control for a class of tilt tri-rotor UAVs with unmodeled dynamics","authors":"L. Chao, Y. Bai, Z. Wang, Y. Yin","doi":"10.1017/aer.2024.19","DOIUrl":"https://doi.org/10.1017/aer.2024.19","url":null,"abstract":"\u0000 Aiming at alleviating the adverse influence of coupling unmodeled dynamics, actuator faults and external disturbances in the attitude tracking control system of tilt tri-rotor unmanned aerial vehicle (UAVs), a neural network (NN)-based robust adaptive super-twisting sliding mode fault-tolerant control scheme is designed in this paper. Firstly, in order to suppress the unmodeled dynamics coupled with the system states, a dynamic auxiliary signal, exponentially input-to-state practically stability and some special mathematical tools are used. Secondly, benefiting from adaptive control and super-twisting sliding mode control (STSMC), the influence of the unexpected chattering phenomenon of sliding mode control (SMC) and the unknown system parameters can be handled well. Moreover, NNs are employed to estimate and compensate some unknown nonlinear terms decomposed from the system model. Based on a decomposed quadratic Lyapunov function, both the bounded convergence of all signals of the closed-loop system and the stability of the system are proved. Numerical simulations are conducted to demonstrate the effectiveness of the proposed control method for the tilt tri-rotor UAVs.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"33 20","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140728230","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

FEM-based eigenstructure recovery of a space truss with active members 基于有限元的带活动构件空间桁架特征结构复原

The Aeronautical Journal Pub Date : 2024-04-08 DOI: 10.1017/aer.2024.31

L. Boni, G. Mengali, A. Quarta, M. Bassetto

{"title":"FEM-based eigenstructure recovery of a space truss with active members","authors":"L. Boni, G. Mengali, A. Quarta, M. Bassetto","doi":"10.1017/aer.2024.31","DOIUrl":"https://doi.org/10.1017/aer.2024.31","url":null,"abstract":"\u0000 Large truss structures have many potential applications in space, such as antennas, telescopes and space solar power plants. In this scenario, a natural concern is the susceptibility of these lightweight structures to be damaged during their operational life, due to impacts, transient thermal states and fatigue phenomena. The inclusion of active elements, equipped with sensor/actuator systems capable of modulating their shape and strength, makes it possible to transform the truss into a smart structure capable of remedying the damage, once it is detected. In this paper, a procedure is described that is capable of restoring at least the basic functionality of a composite truss for space applications, starting with the observation that damage has occurred, regardless of its specific location. The system eigenstructure is used as a benchmark for damage detection, as well as a target characteristic for the subsequent restoration activity. The observer/Kalman filter identification algorithm (OKID), in cascade with the eigensystem realization algorithm (ERA), is adopted to reconstruct, from sensor recordings, the dynamic response of the truss in terms of system state-space representation and eigen-characteristics. Finally, a static output feedback control is developed to recover the low-frequency dynamic behaviour of the truss. The entire procedure is tested using finite element analysis. All activities are coordinated in an innovative procedure that, within a unique Python language code, automatically generates finite element (FE) models, launches finite element analysis (FEA), extracts output data, implements OKID-ERA, processes the control law and applies it to the final FE simulation.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"21 3","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140729067","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Improvement of UAV thrust using the BSO algorithm-based ANFIS model 使用基于 BSO 算法的 ANFIS 模型改进无人飞行器的推力

The Aeronautical Journal Pub Date : 2024-04-02 DOI: 10.1017/aer.2024.30

M. Konar, S. ARIK HATİPOĞLU, M. Akpınar

{"title":"Improvement of UAV thrust using the BSO algorithm-based ANFIS model","authors":"M. Konar, S. ARIK HATİPOĞLU, M. Akpınar","doi":"10.1017/aer.2024.30","DOIUrl":"https://doi.org/10.1017/aer.2024.30","url":null,"abstract":"\u0000 Unmanned aerial vehicles (UAVs), which are available in our lives in many areas today, bring with them new expectations and needs along with developing technology. In order to meet these expectations and needs, main subjects such as reducing energy consumption, increasing thrust and endurance, must be taken into account in UAV designs. In this study, Backtracking search optimisation (BSO) algorithm-based adaptive neuro-fuzzy inference system (ANFIS) model is proposed for the first time to improve UAV thrust. For this purpose, first, different batteries and propellers were tested on the thrust measuring device and a data set was obtained. Propeller diameter and pitch, current, voltage and the electronic speed controller (ESC) signal were selected as input, and UAV thrust was selected as output. ANFIS was used to relate input and output parameters that do not have a direct relationship between them. In order to determine the ANFIS parameters at the optimum value, ANFIS was trained with the obtained data set by using BSO algorithm. Then, the objective function based on the optimum ANFIS structure was integrated into BSO algorithm, and the input values that gave the optimum thrust were calculated using BSO algorithm. Simulation results, in which parameters such as engine, battery and propeller affecting the thrust are taken into account equally, emphasise that the proposed method can be used effectively in improving the UAV thrust. This hybrid method, consisting of ANFIS and BSO algorithm, can reduce the cost and time loss in UAV designs and allows many possibilities to be tested.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"47 ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140752579","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

A Monte Carlo approach for capacity and delay analyses of multiple interacting airports in Istanbul metroplex 对伊斯坦布尔都会区多个相互影响的机场进行容量和延误分析的蒙特卡罗方法

The Aeronautical Journal Pub Date : 2024-04-01 DOI: 10.1017/aer.2024.24

Z. Kaplan, C. Çetek

{"title":"A Monte Carlo approach for capacity and delay analyses of multiple interacting airports in Istanbul metroplex","authors":"Z. Kaplan, C. Çetek","doi":"10.1017/aer.2024.24","DOIUrl":"https://doi.org/10.1017/aer.2024.24","url":null,"abstract":"\u0000 The Istanbul metroplex airspace, home to Atatürk (LTBA), Sabiha Gökçen (LTFJ), and Istanbul (LTFM) international airports, is a critical hub for international travel, trade and commerce between Europe and Asia. The high air traffic volume and the proximity of multiple airports make air traffic management (ATM) a significant challenge. To better manage this complex air traffic, it is necessary to conduct detailed analyses of the capacities of these airports and surrounding airspace. In this study, Monte Carlo simulation is used to determine the ultimate and practical capacities of the airport and surrounding airspace and compare them to identify any differences or limitations. The traffic mix, runway occupancy time and traffic distribution at airspace entry points are randomised variables that directly impact airport and airspace capacities and delays. The study aims to determine the current capacities of the runways and routes in the metroplex airspace and project the future capacities with the addition of new facilities. The results demonstrated that the actual bottleneck could be experienced in airspace, rather than runways, which was the focus of the previous literature. Thus, this study will provide valuable insights for stakeholders in the aviation industry to effectively manage air traffic in the metroplex airspace and meet the growing demand.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"46 9","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140771277","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Controlling roll-yaw coupling with aileron and twist design 利用副翼和扭转设计控制滚转-偏航耦合

The Aeronautical Journal Pub Date : 2024-03-27 DOI: 10.1017/aer.2024.21

J. Brincklow, Z.S. Montgomery, D. F. Hunsaker

引用次数: 0

Concept of operations for the Neptune system mission Arcanum – CORRIGENDUM 海王星系统任务 Arcanum 的行动构想 - CORRIGENDUM

The Aeronautical Journal Pub Date : 2024-03-27 DOI: 10.1017/aer.2024.26

J.E. McKevitt, S. Beegadhur, L. Ayin-Walsh, T. Dixon, F. Criscola, D. Patadia, S. Bulla, J. Galinzoga, B. Wadsworth, C. Bornberg, R. Sharma, O. Moore, J. Kent, A. Zaripova, J. Parkinson-Swift, A. Laad

引用次数: 0

Reinforcement learning-based adaptive spiral-diving Manoeuver guidance method for reentry vehicles subject to unknown disturbances 基于强化学习的受未知干扰再入飞行器自适应螺旋下潜机动制导方法

The Aeronautical Journal Pub Date : 2024-03-19 DOI: 10.1017/aer.2024.17

T. Wu, Z. Wang

引用次数: 0

Attitude maneuver planning and robust tracking control for flexible satellite 灵活卫星的姿态机动规划和稳健跟踪控制

The Aeronautical Journal Pub Date : 2024-03-18 DOI: 10.1017/aer.2024.18

L. Sun, S. Duan, H. Huang, T. Zhang, X. Zhao

{"title":"Attitude maneuver planning and robust tracking control for flexible satellite","authors":"L. Sun, S. Duan, H. Huang, T. Zhang, X. Zhao","doi":"10.1017/aer.2024.18","DOIUrl":"https://doi.org/10.1017/aer.2024.18","url":null,"abstract":"\u0000 In this paper, we investigate the attitude manoeuver planning and tracking control of the flexible satellite equipped with a coilable mast. Due to its flexible beamlike structure, the coilable mast experiences bending and torsional modal vibrations in multi-direction. The complex nonlinear coupling and other external disturbances significantly impact the achievement of high-precision attitude control. To overcome these challenges, a robust attitude tracking controller is proposed for easy implementation by the Attitude Determination and Control System (ADCS). The controller consists of a disturbance compensator, feedforward controller and output feedback controller. The compensator, based on a Nonlinear Disturbance Observer (NDO), effectively compensates for the cluster disturbances caused by vibrations, environmental factors and parameter perturbations. The feedforward controller tracks the desired path in the nominal satellite model. Furthermore, the output feedback controller enables large-angle manoeuver control of the satellite and evaluates the suppression effect of the controlled output on the observation error of cluster disturbances used the \u0000 \u0000 \u0000 \u0000${L_2}$\u0000\u0000 \u0000 -gain. Simulation results demonstrate that the proposed controller successfully achieves high-precision attitude tracking control during large-angle manoeuvering.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"35 11","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-03-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140234520","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0