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Experimental investigation of a Y-shaped engine inlet at subsonic flow conditions Aeronaut. J. (IF 1.4) Pub Date : 2024-04-24 U.C. Küçük
In this paper, the results of an experimental investigation for a Y-shaped engine inlet are presented. The experiment is performed at subsonic flow conditions. The main focus is given to time-dependent total pressures measured at the aerodynamic interface plane. Distinctive frequencies carrying high energy contents of the fluctuating total pressures are given and the relation between time-dependent
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Gas turbine prognostics via Temporal Fusion Transformer Aeronaut. J. (IF 1.4) Pub Date : 2024-04-24 A.D. Fentaye, K.G. Kyprianidis
Gas turbines play a vital role in various industries. Timely and accurately predicting their degradation is essential for efficient operation and optimal maintenance planning. Diagnostic and prognostic outcomes aid in determining the optimal compressor washing intervals. Diagnostics detects compressor fouling and estimates the trend up to the current time. If the forecast indicates fast progress in
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Pilot performance during simulated point and boundary avoidance tracking tasks Aeronaut. J. (IF 1.4) Pub Date : 2024-04-24 Q. Xia, D. Marchesoli, P. Masarati, M. Liu
Helicopters are used in complex and harsh operational environments, such as search and rescue missions and firefighting, that require operating in ground proximity, tracking targets while avoiding impacting obstacles, namely a combination of point tracking (positive) and boundary avoidance (negative) objectives. A simulation task representing simplified helicopter dynamics is used to investigate point
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Rapid dynamic aeroelastic response analysis of the highly flexible wing with distributed propellers influence Aeronaut. J. (IF 1.4) Pub Date : 2024-04-24 X. Wu, Z. Zhou, Z.P. Wang
A rapid nonlinear aeroelastic framework for the analysis of the highly flexible wing with distributed propellers is presented, validated and applied to investigate the propeller effects on the wing dynamic response and aeroelastic stability. In the framework, nonlinear beam elements based on the co-rotational method are applied for the large-deformation wing structure, and an efficient cylinder coordinate
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Prediction of wrinkle patterns in tensioned thin-film structures containing rigid elements Aeronaut. J. (IF 1.4) Pub Date : 2024-04-19 P. Sun, J. Huang, J.Y. Zhang, F.B. Meng, P.B. Zhao
With the in-depth study of thin-film structures, nonuniform thin films with rigid elements have been applied in the aerospace and flexible electronics industries. For thin-film structures with rigid elements, there is an interaction force between the rigid element and the thin film; therefore, the wrinkling mode of the thin film changes under the influence of the interaction force. In this study, a
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Altering flight stability characteristics of a high-performance aircraft through wing strake modification Aeronaut. J. (IF 1.4) Pub Date : 2024-04-18 H. Raza, A. Maqsood, J. Masud
Changes in flight stability characteristics at the advanced stage of aircraft design are complex and require thorough investigations. This paper examines the impact of wing strake modification on high-performance aircraft using computational fluid dynamics (CFD). The dynamic behaviour is calculated using the forced oscillation technique, while the effect of geometric variation on longitudinal stability
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Aerodynamic characteristics of different configurations of mechanically deployable aerodynamic decelerator in subsonic region Aeronaut. J. (IF 1.4) Pub Date : 2024-04-16 C. Yun, D. Liu
The deceleration effect of the deployable aerodynamic decelerator is not as good as a parachute in the subsonic region. This paper proposes a novel concept of using a parachute-like configuration (PLC) to enhance the deceleration performance of the mechanically deployable aerodynamic decelerator (MDAD) through structural transformation. The MDAD turned into the PLC from the sphere cone configuration
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Distributed digital twins for health monitoring: resource constrained aero-engine fleet management Aeronaut. J. (IF 1.4) Pub Date : 2024-04-15 A. Hartwell, F. Montana, W. Jacobs, V. Kadirkamanathan, N. Ameri, A. R. Mills
Sensed data from high-value engineering systems is being increasingly exploited to optimise their operation and maintenance. In aerospace, returning all measured data to a central repository is prohibitively expensive, often causing useful, high-value data to be discarded. The ability to detect, prioritise and return useful data on asset and in real-time is vital to move toward more sustainable maintenance
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Aerothermal and aerodynamic characteristics of reusable hypersonic vehicles with heat transfer minimised sweepback Aeronaut. J. (IF 1.4) Pub Date : 2024-04-11 R.B. Shilwant, S.P. Mahulikar
Establishing aerothermal criteria for swept leading-edge hypersonic vehicle design is the predominant purpose of this work. This study is focused on two different configurations of vehicles based on the swept-back angle ( $\varLambda$ ) viz. minimum drag ( $\varLambda$ Drag-min ), and minimum heat transfer to vehicle ( $\varLambda$ HT-min ). Maximum wall temperatures obtained from the simulation performed
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Experimental studies on the Hartmann tube Aeronaut. J. (IF 1.4) Pub Date : 2024-04-11 E. Rathakrishnan
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
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Flight performance analysis of aerial fire fighting Aeronaut. J. (IF 1.4) Pub Date : 2024-04-11 A. Struminska, A. Filippone
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
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FEM-based eigenstructure recovery of a space truss with active members Aeronaut. J. (IF 1.4) Pub Date : 2024-04-08 L. Boni, G. Mengali, A.A. Quarta, M. Bassetto
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
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Neural network-based robust adaptive super-twisting sliding mode fault-tolerant control for a class of tilt tri-rotor UAVs with unmodeled dynamics Aeronaut. J. (IF 1.4) Pub Date : 2024-04-08 L. Chao, Y. Bai, Z. Wang, Y. Yin
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
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Abating CO2 and non-CO2 emissions with hydrogen propulsion Aeronaut. J. (IF 1.4) Pub Date : 2024-04-02 C. Mourouzidis, G. Singh, X. Sun, J. Huete, D. Nalianda, T. Nikolaidis, V. Sethi, A. Rolt, E. Goodger, P. Pilidis
This contribution focuses on the abatement with hydrogen of CO2 and non-CO2 emissions. It is agenda-setting in two respects. Firstly, it challenges the globally accepted hydrocarbon sustainable aviation fuel (SAF) pathway to sustainability and recommends that our industry accelerates along the hydrogen pathway to ‘green’ aviation. Secondly, it reports a philosophical and analytical investigation of
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Improvement of UAV thrust using the BSO algorithm-based ANFIS model Aeronaut. J. (IF 1.4) Pub Date : 2024-04-02 M. Konar, S. Arık Hatipoğlu, M. Akpınar
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
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A Monte Carlo approach for capacity and delay analyses of multiple interacting airports in Istanbul metroplex Aeronaut. J. (IF 1.4) Pub Date : 2024-04-01 Z. Kaplan, C. Çetek
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
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Controlling roll-yaw coupling with aileron and twist design Aeronaut. J. (IF 1.4) Pub Date : 2024-03-27 J.R. Brincklow, Z.S. Montgomery, D.F. Hunsaker
Most simple ailerons produce adverse yaw. However, with proper aileron placement and wing twist, an aileron can produce proverse or neutral yaw, eliminating the need for aileron-rudder mixing, differential aileron deflection or Frise ailerons. The relationship between wing planform, aileron placement and lift distribution is studied here for a special class of optimal lift distributions that minimise
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Aeroelastic tailoring of stiffened cantilever plate using composites and structural layouts: A parametric study Aeronaut. J. (IF 1.4) Pub Date : 2024-03-19 B.I. Fraihat, R.M. Ajaj
This paper studies the aeroelasticity of a stiffened cantilever plate using composite material and novel structural layouts. A comprehensive parametric study is conducted to determine the influence of different design parameters on the aeroelastic boundaries. Design parameters include plate sweep angle, ply orientation, stringer cross-section and stringer sweep angle. Nastran is used to run the aeroelastic
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Reinforcement learning-based adaptive spiral-diving Manoeuver guidance method for reentry vehicles subject to unknown disturbances Aeronaut. J. (IF 1.4) Pub Date : 2024-03-19 T. Wu, Z. Wang
This paper proposed a reinforcement learning-based adaptive guidance method for a class of spiral-diving manoeuver guidance problems of reentry vehicles subject to unknown disturbances. First, the desired proportional navigation guidance law is designed for the vehicle based on the initial conditions, terminal constraints and the curve involute principle. Then, the first-order multivariable nonlinear
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Attitude maneuver planning and robust tracking control for flexible satellite Aeronaut. J. (IF 1.4) Pub Date : 2024-03-18 L. Sun, S. Duan, H. Huang, T. Zhang, X. Zhao
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
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Analysis of cross-border free route implementation: A case for Turkish and Ukrainian airspaces Aeronaut. J. (IF 1.4) Pub Date : 2024-03-14 I. A. Ozcan, F. Aybek Çetek
Free route airspace (FRA) are increasingly widespread in European countries. A step further, cross-border FRA aims to implement FRA in a seamless,defragmented airspace in Europe. This study aims to bring a different perspective by extending the scope of cross-border FRA applications beyond socioeconomic status (SES) countries. In the study, analyses were made using fast-time simulation outputs for
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Electromechanical ice protection system: de-icing capability prediction considering impedance matching effect Aeronaut. J. (IF 1.4) Pub Date : 2024-03-01 B. Miao, L. Yuan, C.L. Zhu
Due to the safety threats caused by icing, the de-icing system is essential in the aviation industry. As an effective method, the electromechanical de-icing system (EDS) is a new ice-protection system based on mechanical vibration principles. For the majority of the current research on system de-icing capability estimation, the effect of impedance-matching is not considered. Impedance matching plays
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Ground collision avoidance system with multi-trajectory risk assessment and decision function Aeronaut. J. (IF 1.4) Pub Date : 2024-02-29 R. Chen, L. Zhao
The traditional ground collision avoidance system (GCAS) makes avoidance decisions based on predicted collision time, without considering the impact of terrain environment and dynamic changes in load factor on avoidance decisions. This increases the risk of ground collisions for the aircraft. To solve the problem, a GCAS with multi-trajectory risk assessment and decision function is proposed. Firstly
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Attitude modelling and real-time robust control of a 3-DoF quadcopter UAV test bench Aeronaut. J. (IF 1.4) Pub Date : 2024-02-28 S.M. Ahmad, S. Fareed
In this work, a three degrees-of-freedom (3-DoF) static quadcopter unmanned aerial vehicle (UAV) test-rig of a pendulum-type configuration is custom-designed, developed, instrumented, and interfaced with a PC. The rig serves as a test bed to develop high-fidelity mathematical models as well as to investigate autopilot designs and real-time closed-loop controllers’ performances. The Simulink Desktop
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On the conditions for absolute minimum fuel burn for turbofan powered, civil transport aircraft and a simple model for wave drag Aeronaut. J. (IF 1.4) Pub Date : 2024-02-26 D.I.A. Poll, U. Schumann
In a recent series of papers, Poll and Schumann have been developing a simple model for estimating fuel burn for turbofan powered, civil transport aircraft for a given mass, Mach number and flight level and in a specified ambient temperature profile for all phases of flight. This paper focuses upon the combination of Mach number and flight level at which an aircraft cruises with the absolute minimum
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Fixed-time anti-saturation control with concise system structure for the 6-DOF motion of spacecraft Aeronaut. J. (IF 1.4) Pub Date : 2024-02-21 X. Wei, Y. Tian, S. Wu, D. Zhang, X. Shao, L. Chen
This paper proposes a fixed-time anti-saturation (FT-AS) control scheme with a simple control loop for the 6-Degree-of-Freedom tracking (6-DOF) control problem of spacecraft with parameter uncertainties, external disturbances and input saturation. Considering the external disturbance and parameter uncertainties, the dynamical model of the tracking error is established. The traditional methods of handling
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Jet-induced vortices of a row of distributed engines at vertical take-off condition Aeronaut. J. (IF 1.4) Pub Date : 2024-02-12 C. Bai, C. Zhou
The aerodynamic performance of a wing model with a row of distributed engines are investigated at the vertical take-off condition. The engines are installed near the trailing edge of the wing. During vertical take-off, the jets exit from the engines and impinge perpendicularly to the ground, providing a thrust for the aircraft. Due to the ground effects, complex vortex structures are induced by the
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Autonomous predictive maintenance of quadrotor UAV with multi-actuator degradation Aeronaut. J. (IF 1.4) Pub Date : 2024-02-08 F.-y. Shen, W. Li, D.-n. Jiang, H.-j. Mao
With the wide application of quadrotor unmanned aerial vehicles (UAVs), the requirements for their safety and reliability are becoming increasingly stringent. In this paper, based on the feedback of airframe performance health perception information and the predictive function control strategy, the autonomous maintenance of a quadrotor UAV with multi-actuator degradation is realised. Autonomous maintenance
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Design and dynamic analysis of supporting mechanism for large scale space deployable membrane sunshield Aeronaut. J. (IF 1.4) Pub Date : 2024-02-08 B.Y. Chang, X. Guan, D. Liang, S.J. Yan, G.G. Jin
Stray light from the sun is one of the most significant factors affecting image quality for the optical system of a spacecraft. This paper proposes a method to design a deployable supporting mechanism for the sunshield based on origami. Firstly, a new type of space mechanism with single-closed loop was proposed according to thick-panel origami, and its mobility was analysed by using the screw theory
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On the secondary stall of a wing in tandem configuration Aeronaut. J. (IF 1.4) Pub Date : 2024-02-08 S.H.R. Shah, A. Ahmed
The aerodynamic response of a NACA0012 wing section was investigated at a Reynolds number of 100,000 in an open return wind tunnel in the presence of a second wing in tandem. The angle-of-attack of the front wing ranged from −5° to 90° while the rear wing remained at zero incidence. The presence of the downstream wing significantly altered the post-stall behaviour of the upstream wing in the form of
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Use of VEGA data to analyse balloon options for possible subsequent long endurance Venus cloud layer missions Aeronaut. J. (IF 1.4) Pub Date : 2024-02-08 G.E. Dorrington
The vertical motions and buoyancy variations of the two VEGA super-pressure balloons, flown in the middle cloud layer of Venus, are discussed. Using data derived from these 1985 nightside flights, estimates are made of the energy required to operate some alternative balloon platform schemes under consideration for future-proposed Venus-atmosphere in situ science missions. Despite the dissimilarity
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Aerodynamic design of a high-efficiency two-stage axial turbine, using streamline curvature method and performance optimisation by clocking of stator blades Aeronaut. J. (IF 1.4) Pub Date : 2024-02-01 R. Taghavi Zenouz, S.M.M. Abiri
Aerodynamic design of a high-efficiency two-stage axial turbine is carried out using a hybrid method through implantation of a two-step design procedure. In the first step, the well-known streamline curvature (SLC) and free vortex (FV) methods are properly combined to establish three-dimensional geometries of the blades at each row and to obtain the flow field properties. The second step is provided
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Finite-time attitude tracking control of stratospheric airship in the presence of multiple disturbances Aeronaut. J. (IF 1.4) Pub Date : 2024-02-01 Z.B. Li, D.P. He, J.Q. Zhang, X.R. Meng
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
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Improving pilots’ tactical decisions in air combat training using the critical decision method Aeronaut. J. (IF 1.4) Pub Date : 2024-02-01 H. Mansikka, K. Virtanen, T. Lipponen, D. Harris
In fighter pilot training, much of upgrade pilots’ (UPs’) learning takes place during mission debriefs. A debrief provides instructor pilots (IPs) the opportunity to correct situation awareness (SA) upon which the UPs base their tactical decisions. Unless the debrief is conducted with proper depth and breadth, the IPs’ feedback on UPs’ SA and tactical decision-making may be incomplete or false, resulting
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Plume flow characteristics of rectangular exhaust nozzles in a micro-jet engine Aeronaut. J. (IF 1.4) Pub Date : 2024-01-24 C. Lee, S.M. Choi
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
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Shock train response to pulse backpressure forcing Aeronaut. J. (IF 1.4) Pub Date : 2024-01-17 X. Ma (马晓敏), Y. Zhang (张永辉), J. Yuan (袁菁涛), W. Fan (范玮)
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
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Rapid generation of time-optimal rendezvous trajectory based on convex optimisation and DNN Aeronaut. J. (IF 1.4) Pub Date : 2024-01-09 R.D. Zhang, W.W. Cai, L.P. Yang
The minimum flight time of spacecraft rendezvous is one of the fundamental indexes for mission design. This paper proposes a rapid trajectory planning method based on convex optimisation and deep neural network (DNN). The time-optimal trajectory planning problem is reconstructed into a double-layer optimisation framework, with the inner being a convex optimisation problem and the outer being a root-finding
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An experimental investigation on the aerodynamic characteristics and vortex dynamics of a flying wing Aeronaut. J. (IF 1.4) Pub Date : 2024-01-08 V. Kumar, A.C. Mandal, K. Poddar
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, ${\rm{\Lambda }}$ = 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
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Disturbance observer-based fixed-time control for hypersonic morphing vehicles with uncertainties Aeronaut. J. (IF 1.4) Pub Date : 2024-01-08 H. Zhang, P. Wang, G. Tang, W. Bao
The attitude-tracking problem of hypersonic morphing vehicles (HMVs) is investigated in this research. After introducing variable-span wings, the optimal aerodynamic shape is available throughout the entire flight mission. However, the morphing wings cause significant changes in aerodynamic coefficients and mass distribution, challenging the attitude control. Therefore, a complete design procedure
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Numerical simulation of droplet impingement and film flow for three-dimensional wings Aeronaut. J. (IF 1.4) Pub Date : 2024-01-08 Z. Xu, X. Zeng, S. Yang, J. Yang
In order to investigate the three-dimensional effects on the flow characteristics of the thin water film for the three-dimensional wings, the numerical simulation of the droplet impingement and film flow on the MS-0317 wing is implemented based on the open-source package OpenFOAM. The simulation focuses on the effects of the angle-of-attack and the angle of sweepback. The movement and impingement of
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Concept of operations for the Neptune system mission Arcanum Aeronaut. J. (IF 1.4) Pub Date : 2023-12-20 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
The Arcanum mission is a proposed L-class mother-daughter spacecraft configuration for the Neptunian system, the mass and volume of which have been maximised to highlight the wide-ranging science the next generation of launch vehicles will enable. The spacecraft is designed to address a long-neglected but high-value region of the outer Solar System, showing that current advances make such a mission
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The effects of crew resource management on flight safety culture: corporate crew resource management (CRM 7.0) Aeronaut. J. (IF 1.4) Pub Date : 2023-12-12 M. Terzioğlu
The main purpose of crew resource management (CRM) is to ensure safe flights by preventing possible errors with the effective use of non-technical skills. The aim of the current study is to examine the effects of CRM on flight safety culture (FSC) with the help of the structural equation model with 451 airline pilots. As a result of the analysis, it was determined that there was a significant correlation
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Wind tunnel test of full-scale wing-propeller system of a eVTOL aircraft Aeronaut. J. (IF 1.4) Pub Date : 2023-12-12 L. Riccobene, D. Grassi, J.N. Braukmann, M. Kerho, G. Droandi, A. Zanotti
The present paper describes the results of an experimental wind tunnel test campaign aimed at investigating the aerodynamic performance and flow physics related to a wing section equipped with two propellers mounted on a boom. The configuration investigated is meant to be representative of a full-scale eVTOL aircraft in cruise flight condition. The use of full-scale components of an eVTOL aircraft
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Predictive methods for initiation of delamination and intra-laminar damage in carbon fibre reinforced polymer laminates subject to impact Aeronaut. J. (IF 1.4) Pub Date : 2023-12-04 H. Raza, O. Rodera, K. Carpenter, T. Pärnänen, J. Jokinen, M. Kanerva, J. Bayandor
A comparison of the modelling methodologies to capture the damage onset and delamination initiation in Abaqus and LS-Dyna is presented. A quasi-isotropic carbon fibre reinforced polymer laminate is modelled under a low-energy impact scenario. Hashin, Puck and Cuntze criteria are implemented for assessing intra-laminar damage in Abaqus in the linear elastic regime without damage evolution, with Virtual
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Development of a design space for dissimilar materials joining in aerospace applications Aeronaut. J. (IF 1.4) Pub Date : 2023-11-29 S. Ahmad Khan, H. Liaqat, F. Akram, H. Ali Khan
This research paper presents an application of the integrated process and product design (IPPD) approach for selecting the best joint configuration for dissimilar material joining in the early product design phase. The proposed methodology integrates the multi-criteria decision making (MCDM) approach with quality function deployment (QFD) to identify the key criteria for joint selection, including
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Thermal management system design for a series hybrid-electric propulsion architecture Aeronaut. J. (IF 1.4) Pub Date : 2023-11-29 M. Potamiti, V.G. Gkoutzamanis, A.I. Kalfas
The current paper is focused on the conceptual design of a thermal management system with a liquid working medium for a commuter hybrid-electric aircraft, featuring a series propulsion configuration. Regarding the system’s architecture, parametric analyses are conducted, by altering the number of heat exchangers. To clarify, a centralised and a decentralised thermal management system architecture are
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Aircraft fleet availability optimisation: a reinforcement learning approach Aeronaut. J. (IF 1.4) Pub Date : 2023-11-29 K. Vos, Z. Peng, E. Lee, W. Wang
A fleet of aircraft can be seen as a set of degrading systems that undergo variable loads as they fly missions and require maintenance throughout their lifetime. Optimal fleet management aims to maximise fleet availability while minimising overall maintenance costs. To achieve this goal, individual aircraft, with variable age and degradation paths, need to operate cooperatively to maintain high fleet
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Bespoke stability analysis tool in next-generation computational fluid dynamics solver Aeronaut. J. (IF 1.4) Pub Date : 2023-11-23 U S Vevek, J. Houtman, S. Timme
This paper presents some of the first results of global linear stability analyses performed using a bespoke eigensolver that has recently been implemented in the next generation flow solver framework CODA. The eigensolver benefits from the automatic differentiation capability of CODA that allows computation of the exact product of the Jacobian matrix with an arbitrary complex vector. It implements
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Attitude tracking control of hypersonic vehicle based on an improved prescribed performance dynamic surface control Aeronaut. J. (IF 1.4) Pub Date : 2023-11-10 Z.Y. Yin, B. Wang, R.T. Xiong, Z. Xiang, L. Liu, H.J. Fan, C.L. Xue
In this paper, we investigate the constrained attitude control problem of hypersonic vehicles (HVs). An improved prescribed performance dynamic surface control method is proposed based on an adaptive scaling strategy. Because of the uncertain time-varying disturbances, the controlled state may violate the constraint in the prescribed performance control (PPC) framework. An adaptive scaling strategy
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Analysis of modern fan manufacturing variations and their links to Jet-engine performance Aeronaut. J. (IF 1.4) Pub Date : 2023-11-09 S. Shahpar
Every manufacturing procedure is subject to tolerance variations. Over the years, a set of key characteristic features (KCF) that can explain the effect of manufacturing variations on the aero-mechanical performance of a fan blade has been devised and monitored to ensure conformality and good performance. The KCFs are derived from a cloud of coordinate measurement machine (CMM) points and are defined
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Effect of oxygen shielding on the tensile and fatigue performance of 300M repaired through laser-directed energy deposition Aeronaut. J. (IF 1.4) Pub Date : 2023-11-03 C. Barr, R.A.R. Rashid, S. Palanisamy, N. Matthews, M. Brandt
Laser-directed energy deposition (L-DED) is a key enabling technology for the repair of high-value aerospace components, as damaged regions can be removed and replaced with additively deposited material. While L-DED repair improves strength and fatigue performance compared to conventional subtractive techniques, mechanical performance can be limited by process-related defects. To assess the role of
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Ensemble approaches for leveraging machine learning models in load estimation Aeronaut. J. (IF 1.4) Pub Date : 2023-11-03 C. Cheung, E. Seabrook, J.J. Valdés, Z.A. Hamaimou, C. Biondic
Helicopter component load estimation can be achieved through a variety of machine learning techniques and algorithms. A range of ensemble integration techniques were investigated in order to leverage multiple machine learning models to estimate main rotor yoke loads from flight state and control system parameters. The techniques included simple averaging, weighted averaging and forward selection. Performance
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Methodology for shape prediction and conversion of a conventional aerofoil to an inflatable baffled aerofoil Aeronaut. J. (IF 1.4) Pub Date : 2023-11-03 S.R. Mistri, C.S. Yerramalli, R.S. Pant, A. Guha
Inflatable wings for UAVs are useful where storage space is a severe constraint. Literature in the field of inflatable wings often assumes an inflated aerofoil shape for various analyses. However, the flexible inflatable aerofoil fabric might deform to another equilibrium shape upon inflation. Hence accurate shape prediction of the inflated aerofoil is vital. Further, no standardised nomenclature or
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Deployable optics for the Buccaneer Main Mission (BMM) Aeronaut. J. (IF 1.4) Pub Date : 2023-10-31 F. Agenbag, P.S. Alvino, D.C. Bandara, H.E. Bennett, M. Hollick, A.M. James, J. Kaduparambil-Jose, D.M. Lingard, F. Lorenzin, B. Lucas, A. McKinnon, J.D. Nelson, C.V. Peck, C. Raddock, A. Raj, P.C.L. Stephenson, A. Strachan, T. Teske, P. Thornton
Defence Science and Technology Group (DSTG) is currently preparing for the launch of the Buccaneer Main Mission (BMM) satellite, the successor to the Buccaneer Risk Mitigation Mission (BRMM). BMM hosts a high-frequency (HF) antenna and receiver to contribute to the calibration of the Jindalee Operational Radar Network (JORN). Verification of the successful deployment and stability of the large HF antenna
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A review of physiological measures for mental workload assessment in aviation: A state-of-the-art review of mental workload physiological assessment methods in human-machine interaction analysis Aeronaut. J. (IF 1.4) Pub Date : 2023-10-25 G. Luzzani, I. Buraioli, D. Demarchi, G. Guglieri
The relevant growth of human-machine interaction (HMI) systems in recent years is leading to the necessity of being constantly aware of the cognitive workload level of an operator, especially in a safety-critical context such as aviation. Since the confusion in the definition of this concept, this paper clarifies this terminology and also highlights its relationship with stress. Thus, we analysed the
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An improved crack tip location algorithm using the principles of thermoelastic stress analysis Aeronaut. J. (IF 1.4) Pub Date : 2023-10-20 L. Button, J. Codrington, C. Brooks, N. Rajic
A novel method of determining the crack tip location from a thermoelastic quadrature signal is presented. The method is utilised for crack tip locations within complex stress fields, namely within fastened aircraft lap joints. Coupled structural-thermal finite element modelling was undertaken to investigate the thermal response field around the crack tip location and develop the algorithmic principles
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Fixed-time control for free-floating space manipulators with prescribed constraints and input saturation Aeronaut. J. (IF 1.4) Pub Date : 2023-10-20 Y.X. Yan, H.T. Cui, P. Han
This paper investigates the issue of tracking control for a free-floating space manipulator with prescribed performance constraints, considering the inertia uncertainties, internal disturbances and input saturation. An inherently continuous adaptive controller is proposed by incorporating non-singular fixed-time sliding mode control, prescribed performance control (PPC), and auxiliary compensation
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High-fidelity post-impact residual strength assessment for composite aircraft sustainment Aeronaut. J. (IF 1.4) Pub Date : 2023-10-20 K. Jacobs, A.B. Harman, R.B. Ladani, R. Das, A.C. Orifici
High-fidelity simulation tools have significant potential to support composite aircraft sustainment, though further study is required on incorporating the complex impact damage field. In this paper, compressive residual strength assessment is investigated using the high-fidelity computational tool BSAMTM. The experimental impact damage was mapped and modelled at a high-fidelity level, which included
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Prediction of aerodynamic characteristics of high-lift Common Research Model in ground effect Aeronaut. J. (IF 1.4) Pub Date : 2023-10-20 M. Sereez, N. Abramov, M. Goman
Reynolds Averaged Navier-Stokes (RANS) simulations are performed to investigate the aerodynamic characteristics of the NASA Common Research Model (CRM) in its high-lift (HL) configuration in close proximity to the ground. The RANS simulations are conducted at a moderate Reynolds number of $Re = 5.49 \times {10^6}$ and $M = 0.2$ with the use of the Spalart-Allmaras (SA) turbulence model. out of ground
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Full envelope nonlinear flight controller design for a novel electric VTOL (eVTOL) air taxi Aeronaut. J. (IF 1.4) Pub Date : 2023-10-19 E.C. Suiçmez, A.T. Kutay
On-demand urban air transportation gains popularity in recent years with the introduction of the electric VTOL (eVTOL) aircraft concept. There is an emerging interest in short/medium range eVTOL air taxi considering the critical advantages of electric propulsion (i.e. low noise and carbon emission). Using several electric propulsion systems (distributed electric propulsion (DEP)) has further advantages