The Aeronautical Journal最新文献_第6页

Finite-time attitude tracking control of stratospheric airship in the presence of multiple disturbances 存在多重干扰时平流层飞艇的有限时间姿态跟踪控制

The Aeronautical Journal Pub Date : 2024-02-01 DOI: 10.1017/aer.2024.4

Z.B. Li, D. He, J.Q. Zhang, X.R. Meng

{"title":"Finite-time attitude tracking control of stratospheric airship in the presence of multiple disturbances","authors":"Z.B. Li, D. He, J.Q. Zhang, X.R. Meng","doi":"10.1017/aer.2024.4","DOIUrl":"https://doi.org/10.1017/aer.2024.4","url":null,"abstract":"\u0000 This paper proposes a composite non-singular fast terminal sliding mode attitude control scheme based on a reduced-order extended state observer for the stratospheric airship’s attitude system affected by multiple disturbances. First, the feedback linearisation method is applied to address the nonlinearity of the attitude motion model and achieve decoupling of the model in three channels. Second, the overall disturbances, encompassing airship parameter perturbations and external disturbances, are treated as an aggregate. A reduced-order extended state observer is designed for each channel to formulate a composite non-singular fast terminal sliding mode surface. In the control design phase, the hyperbolic sine function is adopted as replacement for the sign function to ensure the continuity of the control signal. The estimated disturbances are incorporated in the control law design to directly offset the effects of multiple disturbances on the attitude motion of the airship. Third, based on Lyapunov theory, it has been proven that the control law can drive the attitude tracking error to converge to zero within a finite time. Simulation results demonstrate that the proposed control scheme exhibits favorable disturbance rejection capability, as well as higher tracking accuracy and faster response speed.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"43 22","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139829813","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

Plume flow characteristics of rectangular exhaust nozzles in a micro-jet engine 微型喷气发动机矩形排气喷嘴的烟流特性

The Aeronautical Journal Pub Date : 2024-01-24 DOI: 10.1017/aer.2023.86

C. Lee, S.M. Choi

{"title":"Plume flow characteristics of rectangular exhaust nozzles in a micro-jet engine","authors":"C. Lee, S.M. Choi","doi":"10.1017/aer.2023.86","DOIUrl":"https://doi.org/10.1017/aer.2023.86","url":null,"abstract":"\u0000 The flow characteristics of the plume ejected from a micro-jet engine’s rectangular exhaust nozzle have been studied by conducting experimental and numerical analyses. The radiated infrared signature of a plume ejected from a rectangular exhaust nozzle with a large aspect ratio in a jet propulsion engine is known to be significantly lower than that of a plume ejected from a circular exhaust nozzle. The velocity and temperature distributions, which are the flow characteristics of the jet, were measured to investigate this phenomenon. For this purpose, we installed a circular nozzle and a rectangular exhaust nozzle with an aspect ratio of five to a micro-jet engine. The results showed that the plume spreads wider as it moves away from the nozzle exit and that the velocity rapidly decreases in the case of the rectangular nozzle, contrary to the case of the circular nozzle. Similar tendencies were observed for the temperature distribution and magnitude of the ejected plume. Thus, we concluded that the flow distribution caused by the nozzle shape induces a greater drop in the radiated infrared signature of the plume ejected from the rectangular nozzle than the circular nozzle. Flow analysis was conducted to evaluate the flow in and outside the exhaust nozzle; results similar to those of the experiment were obtained. These results show that the ejecting jet has a greater mixing effect on the air outside when using the rectangular nozzle than the circular nozzle.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"18 5","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-01-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139599920","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

Shock train response to pulse backpressure forcing 冲击系对脉冲背压强迫的响应

The Aeronautical Journal Pub Date : 2024-01-17 DOI: 10.1017/aer.2023.107

X. Ma (马晓敏), Y. Zhang (张永辉), J. Yuan (袁菁涛), W. Fan (范玮)

{"title":"Shock train response to pulse backpressure forcing","authors":"X. Ma (马晓敏), Y. Zhang (张永辉), J. Yuan (袁菁涛), W. Fan (范玮)","doi":"10.1017/aer.2023.107","DOIUrl":"https://doi.org/10.1017/aer.2023.107","url":null,"abstract":"\u0000 Transient numerical simulations were conducted to investigate the influence of large amplitude and fast impact backpressure on a shock train. The fundamental problem consists of a shock train within a constant-area channel with a Ma=1.61 inflow and a pulse backpressure applied to the outlet. The pressure disturbance in the isolator has an intense forcing-response lag. From the moment of the backpressure peak appearance, it takes 36 times the backpressure duration for the pressure disturbance to reach the upstream end. It moves upstream with time in the form of a normal shock wave. As time progresses, the normal shock degenerates into a \u0000 \u0000 \u0000 \u0000$lambda $\u0000\u0000 \u0000 shock and a compression wave behind due to the action of viscous dissipation in the boundary layer. Eventually, a multi-stage shock train is formed. The maximum backpropagation distance is a quadratic function of both the pulse backpressure peak and duration, and the relationship between these variables was determined by fitting. When the integral value of backpressure to time is fixed, reducing the backpressure peak while increasing the duration will reduce the backpressure pulsation at the isolator outlet, which will be more conducive to shortening the maximum backpropagation distance than reducing the duration and increasing the backpressure peak. The values of backpressure peak and duration are obtained from the detonation combustion case, which ensures the authenticity of backpressure characteristics. The relevant research conclusions can provide a reference for the design of the isolator of pulse detonation ramjet.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"39 12","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-01-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139527282","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

Rapid generation of time-optimal rendezvous trajectory based on convex optimisation and DNN 基于凸优化和 DNN 快速生成时间最优交会轨迹

The Aeronautical Journal Pub Date : 2024-01-09 DOI: 10.1017/aer.2023.110

R.D. Zhang, W.W. Cai, L.P. Yang

引用次数: 0

Numerical simulation of droplet impingement and film flow for three-dimensional wings 三维机翼液滴撞击和薄膜流动的数值模拟

The Aeronautical Journal Pub Date : 2024-01-08 DOI: 10.1017/aer.2023.117

Z. Xu, X. Zeng, S. Yang, J. Yang

引用次数: 0

Disturbance observer-based fixed-time control for hypersonic morphing vehicles with uncertainties 基于扰动观测器的具有不确定性的高超音速变形飞行器固定时间控制

The Aeronautical Journal Pub Date : 2024-01-08 DOI: 10.1017/aer.2023.116

H. Zhang, P. Wang, G. Tang, W. Bao

引用次数: 0

An experimental investigation on the aerodynamic characteristics and vortex dynamics of a flying wing 飞翼气动特性和涡流动力学实验研究

The Aeronautical Journal Pub Date : 2024-01-08 DOI: 10.1017/aer.2023.115

V. Kumar, A. C. Mandal, K. Poddar

{"title":"An experimental investigation on the aerodynamic characteristics and vortex dynamics of a flying wing","authors":"V. Kumar, A. C. Mandal, K. Poddar","doi":"10.1017/aer.2023.115","DOIUrl":"https://doi.org/10.1017/aer.2023.115","url":null,"abstract":"\u0000 In this paper, we present a detailed experimental investigation mainly on the vortical flow fields and the associated vortex breakdown phenomena over a non-slender flying wing (sweep angle, \u0000 \u0000 \u0000 \u0000${rm{Lambda }}$\u0000\u0000 \u0000 = 53°). In the process, the aerodynamic coefficients were also determined using a six-component force balance. Surface oil flow visualisation, surface pressure measurements and particle image velocimetry (PIV) measurements, in various crossflow planes and in a longitudinal plane passing through the leading-edge vortex core, were carried out at various Reynolds numbers to understand the flow field over the non-slender flying wing. Aerodynamic characteristics of the flying wing show local peaks and valleys in the pitching moment coefficient. The surface flow visualisation reveals that the nonlinearity of the pitching moment curve is due to the complex nature of vortical flow structures. The flow visualisation also demonstrates the presence of a wave-like surface pattern, and its size is found to reduce with increasing Reynolds numbers. The present PIV measurements confirm that this wave-like surface pattern is associated with vortex breakdown phenomena. These measurements also reveal that the vortex breakdown has not reached the apex of the wing, even at post-stall angle-of-attack. For pre-stall (\u0000 \u0000 \u0000 \u0000$alpha $\u0000\u0000 \u0000 = 20°) flow regimes, it is observed that the location of the vortex breakdown moves downstream as the Reynolds number increases, but this influence is minimised at near-stall (\u0000 \u0000 \u0000 \u0000$alpha $\u0000\u0000 \u0000 = 25°) and post-stall (\u0000 \u0000 \u0000 \u0000$alpha $\u0000\u0000 \u0000 = 30°) flow regimes. Reconstructed velocity field using the first 10 dominant proper orthogonal decomposition (POD) modes reveals that the nature of the vortex breakdown over the flying wing is a spiral-type vortex breakdown.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"58 7","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-01-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139447762","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

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

The Aeronautical Journal Pub Date : 2023-12-20 DOI: 10.1017/aer.2023.114

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

Wind tunnel test of full-scale wing-propeller system of a eVTOL aircraft 全尺寸 eVTOL 飞机机翼-螺旋桨系统风洞试验

The Aeronautical Journal Pub Date : 2023-12-12 DOI: 10.1017/aer.2023.112

L. Riccobene, D. Grassi, J. Braukmann, M. Kerho, G. Droandi, A. Zanotti

引用次数: 0

The effects of crew resource management on flight safety culture: corporate crew resource management (CRM 7.0) 机组资源管理对飞行安全文化的影响：企业机组资源管理 (CRM 7.0)

The Aeronautical Journal Pub Date : 2023-12-12 DOI: 10.1017/aer.2023.113

M. Terzioğlu

引用次数: 0