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Experimental investigation of rotating instability in a contra-rotating axial flow compressor Aeronaut. J. (IF 0.663) Pub Date : 2021-01-22 S. Yue; Y. Wang; Z. Zhang; L. Wei; H. Wang
The rotating instability in a contra-rotating axial flow compressor is investigated by experiments. Twenty-four pressure sensors were installed on the casing to capture the unsteady flow in the rotor tip region simultaneously. A double-phase-locking technique suitable for the contra-rotating compressor was proposed to characterise the static pressure contours of the rotor tip. The mean and root-mean-square
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A novel optimal route planning algorithm for searching on the sea Aeronaut. J. (IF 0.663) Pub Date : 2021-01-20 Y. Yang; Y. Mao; R. Xie; Y. Hu; Y. Nan
Emergency search and rescue on the sea is an important part of national emergency response for marine perils. Optimal route planning for maritime search and rescue is the key capability to reduce the searching time, improve the rescue efficiency, as well as guarantee the rescue target’s safety of life and property. The main scope of the searching route planning is to optimise the searching time and
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An estimation method for the fuel burn and other performance characteristics of civil transport aircraft during cruise: part 2, determining the aircraft’s characteristic parameters Aeronaut. J. (IF 0.663) Pub Date : 2020-12-02 D.I.A. Poll; U. Schumann
A simple yet physically comprehensive and accurate method for the estimation of the cruise fuel burn rate of turbofan powered transport aircraft operating in a general atmosphere was developed in part 1. The method is built on previously published work showing that suitable normalisation reduces the governing relations to a set of near-universal curves. However, to apply the method to a specific aircraft
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Gust load alleviation for flexible aircraft using discrete-time preview control Aeronaut. J. (IF 0.663) Pub Date : 2020-12-18 A. Khalil; N. Fezans
Turbulence and gusts cause variations in the aerodynamic forces and moments applied to the structure of aircraft, resulting in passenger discomfort and dynamic loads on the structure that it must be designed to support. By designing Gust Load Alleviation (GLA) systems, two objectives can be achieved: first, realizing higher passenger comfort; and second, reducing the dynamic structural loads, which
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Research on head cooling of high-speed aircraft by liquid nitrogen Aeronaut. J. (IF 0.663) Pub Date : 2020-12-02 H.X. Xiong; S.H. Yi; H.L. Ding; L. Jin; J.J. Huo
In the development process of high-speed aircraft, the head of the aircraft is subject to high temperatures and high speed flows, supporting the maximum heat flow and thus requiring a reliable cooling system. A new type of head cooling system is proposed herein. An internal flow channel model of the heat transfer in a ball head made from high-temperature alloy steel is constructed, then an experimental
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ATCO radar training assessment and flight efficiency: the correlation between trainees’ scores and fuel consumption in real-time simulations Aeronaut. J. (IF 0.663) Pub Date : 2020-12-21 T. Rogošić; B. Juričić; F. Aybek Çetek; Z. Kaplan
Air traffic controller training is highly regulated but lacks prescribed common assessment criteria and methods to evaluate trainees at the level of basic training and consideration of how trainees in fluence flight efficiency. We investigated whether there is a correlation between two parameters, viz. the trainees’ assessment score and fuel consumption, obtained and calculated after real-time human-in-the-loop
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A framework for enhanced decision-making in aircraft conceptual design optimisation under uncertainty Aeronaut. J. (IF 0.663) Pub Date : 2020-12-21 D.H.B. Di Bianchi; N.R. Sêcco; F.J. Silvestre
This paper presents a framework to support decision-making in aircraft conceptual design optimisation under uncertainty. Emphasis is given to graphical visualisation methods capable of providing holistic yet intuitive relationships between design, objectives, feasibility and uncertainty spaces. Two concepts are introduced to allow interactive exploration of the effects of (1) target probability of
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Enabling robust and accurate navigation for UAVs using real-time GNSS precise point positioning and IMU integration Aeronaut. J. (IF 0.663) Pub Date : 2020-10-19 C. Chi; X. Zhan; S. Wang; Y. Zhai
Accurate navigation is required in many Unmanned Aerial Vehicle (UAV) applications. In recent years, GNSS Precise Point Positioning (PPP) has been recognised as an efficient approach for providing precise positioning services. In contrast to the widely used Real-Time Kinematic (RTK), PPP is independent of reference stations, which greatly broadens its scope of application. However, the accuracy and
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Structural performance envelopes in load space Aeronaut. J. (IF 0.663) Pub Date : 2020-11-17 A. Dharmasaroja; C.G. Armstrong; A. Murphy; T.T. Robinson; N.L. Iorga; J.R. Barron
Visualising the loads that a structure can tolerate provides a key insight into the structural design process, especially for materials and structures that are governed by complex failure criteria. This paper proposes a general method for efficient construction of performance envelopes in load space, and demonstrates the approach with two examples. The performance envelope identifies all possible failure
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Modeling and control schedule design of a two-dimensional thrust-vectoring nozzle and aeroengine Aeronaut. J. (IF 0.663) Pub Date : 2020-12-11 Y. Liu; M. Chen; H. Tang
For advanced operational aircraft, the two-dimensional (2-D) thrust-vectoring (TV) nozzle effectively improves the flight mobility and post-stall manoevrability. However, its flow capacity decreases when deflecting and cooling air is injected, which impacts the engine’s operating state, including decreasing the fan surge margin and increasing the turbine inlet temperature. Therefore, in order to improve
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A non-iterative design for aileron to rudder interconnect gain Aeronaut. J. (IF 0.663) Pub Date : 2020-12-09 J. Myala; V.V. Patel; G.K. Singh
Aileron to Rudder Interconnect (ARI) gain is implemented on most fighter aircraft, primarily to reduce the side slip produced due to adverse yaw from pilot lateral control stick input and to improve the turn rate response. A systematic and non-iterative design procedure for ARI gain is proposed herein based on the evaluation of a transfer function magnitude at the aircraft roll mode frequency. The
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Fast and accurate quasi-3D aerodynamic methods for aircraft conceptual design studies Aeronaut. J. (IF 0.663) Pub Date : 2020-12-02 O. Şugar-Gabor; A. Koreanschi
In this paper, recent developments in quasi-3D aerodynamic methods are presented. At their core, these methods are based on the lifting-line theory and vortex lattice method, but with a relaxed set of hypotheses, while also considering the effect of viscosity (to a certain degree) by introducing a strong non-linear coupling with two-dimensional viscous aerofoil aerodynamics. These methods can provide
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Trajectory optimisation of satellite launch vehicles using network flow-based algorithm Aeronaut. J. (IF 0.663) Pub Date : 2020-10-02 R. Zardashti; S. Rahimi
A trajectory optimisation procedure is addressed to generate a reference trajectory for Satellite Launch Vehicles (SLVs). Using a grid-based discrete scheme, a Modified Minimum Cost Network Flow (MCNF)-based algorithm over a large-scale network is proposed. By using the network grid around the Earth and the discrete dynamic equations of motion, the optimum trajectory from a launch point to the desired
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Off-equilibrium linearisation-based nonlinear control of turbojet enginese with sum-of-squares programming Aeronaut. J. (IF 0.663) Pub Date : 2020-09-28 Y. Tang; Y. Li; T. Cui; Y. Zheng
In conventional linear parameter-varying (LPV) modelling and gain scheduling control design for turbojet engines, the linearisation is performed at a set of equilibrium points, and the validity of such LPV models is ensured near the equilibria. However, the linear model can only provide an approximate description of the engine’s state when the system operates away from equilibrium. In this paper, it
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Using shock control bumps to improve engine intake performance and operability Aeronaut. J. (IF 0.663) Pub Date : 2020-11-23 A. John; J. Bower; N. Qin; S. Shahpar; A. Smith
Shock control bumps can be used to control and weaken the shock waves that form on engine intakes at high angles of attack. In this paper, it is demonstrated how shock control bumps applied to an engine intake can reduce or eliminate shock-induced separation at high incidence, and also increase the incidence at which critical separation occurs. Three-dimensional Reynolds-average Navier–Stokes (RANS)
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A comparative assessment of flutter prediction techniques Aeronaut. J. (IF 0.663) Pub Date : 2020-10-27 U.P.V. Sudha; G.S. Deodhare; K. Venkatraman
To establish flutter onset boundaries on the flight envelope, it is required to determine the flutter onset dynamic pressure. Proper selection of a flight flutter prediction technique is vital to flutter onset speed prediction. Several methods are available in literature, starting with those based on velocity damping, envelope functions, flutter margin, discrete-time Autoregressive Moving Average (ARMA)
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Obstacle avoidance in V-shape formation flight of multiple fixed-wing UAVs using variable repulsive circles Aeronaut. J. (IF 0.663) Pub Date : 2020-10-23 A. Mirzaee Kahagh; F. Pazooki; S. Etemadi Haghighi
A formation control and obstacle avoidance algorithm has been introduced in this paper for the V-shape formation flight of fixed-wing UAVs (Unmanned Aerial Vehicles) using the potential functions method. An innovative vector approach has been suggested to fix the conventional challenge in employing the artificial potential field (APF) approach (the creation of local minimums). A method called variable
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Air pollutant emissions from aircraft landing and take-off cycles at Chinese airports Aeronaut. J. (IF 0.663) Pub Date : 2020-11-20 J.-I. Yu; Q. Jia; C. Gao; H.-q. Hu
Research on flight emissions at airports is very important for environmental policymaking. This study analysed the trend of aircraft air pollutant emissions at mainland China airports from 1990 to 2017, mainly focusing on standard landing and take-off (LTO) cycles. Total flight movements increased 29-fold from 1990 to 2017 at Chinese airports. Over the same period, the emissions of NOx, SOx, CO, hydrocarbons
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Enhanced cruise range prediction for narrow-body turbofan commercial aircraft based on QAR data Aeronaut. J. (IF 0.663) Pub Date : 2020-11-05 V.E. Atasoy; C. Cetek
Aircraft performance parameters play a critical role in maintaining economic and environmental sustainability in aviation. Furthermore, the ability to calculate aircraft performance parameters accurately for the cruise range contributes to aviation in areas such as the preliminary design of aircraft and air traffic management. This study is focused on cruise range performance, as this is critical to
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Influence of distorted inflows on the performance of a contra-rotating fan Aeronaut. J. (IF 0.663) Pub Date : 2020-11-04 M.P. Manas; A.M. Pradeep
A contra-rotating fan offers several aerodynamic advantages that make it a potential candidate for future aircraft engine configurations. Stall in a contra-rotating axial fan is interesting since instabilities could arise from either or both of the rotors. In this experimental study, a contra-rotating axial fan is analysed under clean or distorted inflow conditions to understand its performance and
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Estimation of aerodynamic parameters near stall using maximum likelihood and extreme learning machine-based methods Aeronaut. J. (IF 0.663) Pub Date : 2020-10-23 H.O. Verma; N.K. Peyada
The stability and control derivatives are essential parameters in the flight operation of aircraft, and their determination is a routine task using classical parameter estimation methods based on maximum likelihood and least-squares principles. At high angle-of-attack, the unsteady aerodynamics may pose difficulty in aerodynamic structure determination, hence data-driven methods based on artificial
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Predicting the fuel flow rate of commercial aircraft via multilayer perceptron, radial basis function and ANFIS artificial neural networks Aeronaut. J. (IF 0.663) Pub Date : 2020-10-19 T. Baklacioglu
A first attempt is made to use recently developed, non-conventional Artificial Neural Network (ANN) models with Multilayer Perceptron (MLP), Radial Basis Function (RBF) and Adaptive Neuro-Fuzzy Interference System (ANFIS) architectures to predict the fuel flow rate of a commercial aircraft using real data obtained from Flight Data Records (FDRs) of the cruise, climb and descent phases. The training
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The formulation of the RANS equations for supersonic and hypersonic turbulent flows Aeronaut. J. (IF 0.663) Pub Date : 2020-10-12 H. Zhang; T.J. Craft; H. Iacovides
Accurate prediction of supersonic and hypersonic turbulent flows is essential to the design of high-speed aerospace vehicles. Such flows are mainly predicted using the Reynolds-Averaged Navier–Stokes (RANS) approach in general, and in particular turbulence models using the effective viscosity approximation. Several terms involving the turbulent kinetic energy (k) appear explicitly in the RANS equations
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Mechanical properties of UN-5100 envelope material for stratospheric airship Aeronaut. J. (IF 0.663) Pub Date : 2020-10-12 W.-c. Xie; X.-l. Wang; D.-p. Duan; J.-w. Tang; Y. Wei
Stratospheric airships are promising aircraft, usually designed as a non-rigid airship. As an essential part of the non-rigid airship, the envelope plays a significant role in maintaining its shape and bearing the external force load. Generally, the envelope material of a flexible airship consists of plain-weave fabric, composed of warp and weft fibre yarn. At present, biaxial tensile experiments are
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Optimisation of interval management – speed planning using SMPSO Aeronaut. J. (IF 0.663) Pub Date : 2020-08-13 T. Riedel; M. Takahashi; E. Itoh
Recent research on Flight-deck Interval Management (FIM), a modern technology for increasing safety and improving airspace and runway utilisation through self-spacing, has led to the development of a new rule-based logic for FIM, namely Interval Management – Speed Planning (IM-SP). In an initial benchmark study, IM-SP showed good spacing performance with a significant reduction in speed commands, a
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Review of microwave techniques used in the manufacture and fault detection of aircraft composites Aeronaut. J. (IF 0.663) Pub Date : 2020-10-07 Z. Li; P. Wang; A. Haigh; C. Soutis; A. Gibson
Microwaves are a form of electromagnetic radiation commonly used for telecommunications, navigation and food processing. More recently microwave technologies have found applications in fibre-reinforced polymer composites, which are increasingly used in aircraft structures. Microwave energy can be applied with low power (up to milliwatts) for non-destructive testing and high power (up to kilowatts)
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Flow field reconstruction method based on array neural network Aeronaut. J. (IF 0.663) Pub Date : 2020-10-02 W. Yuqi; Y. Wu; L. Shan; Z. Jian; R. Huiying; Y. Tiechui; K. Menghai
Multi-dimensional aerodynamic database technology is widely used, but its model often has the curse of dimensionality. In order to solve this problem, we need projection to reduce the dimension. In addition, due to the lack of traditional method, we have improved the traditional flow field reconstruction method based on artificial neural networks, and we proposed an array neural network method. In
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Development of a fire detection and suppression system for a smart air cargo container Aeronaut. J. (IF 0.663) Pub Date : 2020-10-01 Q. Zhang; Y.C. Wang; C. Soutis; M. Gresil
This study investigates and proposes a fire detection and suppression system for a smart air cargo container. A series of smoke spread and fire evolution numerical models are executed to assess the performance of container-based fire detection in various fire scenarios. This is to identify the worst case and optimise the location and threshold setting of fire detection sensors, achieving the shortest
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Research on the design of smart morphing long-endurance UAVs Aeronaut. J. (IF 0.663) Pub Date : 2020-09-25 T. Ma; Y. Liu; D. Yang; Z. Zhang; X. Wang; S. Hao
To improve the endurance performance of long-endurance Unmanned Aerial Vehicles (UAVs), a smart morphing method to adjust the UAV and flight mode continuously during flight is proposed. Using this method as a starting point, a smart morphing long-endurance UAV design is conducted and the resulting improvement in the endurance performance studied. Firstly, the initial overall design of the smart morphing
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Neuroadaptive output-feedback trajectory tracking control for a stratospheric airship with prescribed performance Aeronaut. J. (IF 0.663) Pub Date : 2020-07-09 Y. Wu; Q. Wang; D. Duan; W. Xie; Y. Wei
In this article, we investigate the horizontal trajectory tracking problem for an underactuated stratospheric airship subject to nonvanishing external disturbances and model uncertainties. By transforming the tracking errors into new virtual error variables, we can specify the transient and steady-state tracking performance of the resulting nonlinear system quantitatively, which means that under the
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Loss determination at a linear cascade under consideration of thermal effects Aeronaut. J. (IF 0.663) Pub Date : 2020-07-06 S. Aberle-Kern; R. Niehuis; T. Ripplinger
Targeting higher efficiencies and lower fuel consumption of turbomachines, heat transfer and profile loss are research topics of particular interest. In contrast to that, the interaction of both was, so far, rarely investigated, but gains in importance in recent research activities. The profile loss of engine components can be characterised by the airfoil wakes at the blade rows utilising established
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AeroVR: An immersive visualisation system for aerospace design and digital twinning in virtual reality Aeronaut. J. (IF 0.663) Pub Date : 2020-06-25 S.K. Tadeja; P. Seshadri; P.O. Kristensson
One of today’s most propitious immersive technologies is virtual reality (VR). This term is colloquially associated with headsets that transport users to a bespoke, built-for-purpose immersive 3D virtual environment. It has given rise to the field of immersive analytics—a new field of research that aims to use immersive technologies for enhancing and empowering data analytics. However, in developing
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Comparative study on analytical and computational aerodynamic models for flapping wings MAVs Aeronaut. J. (IF 0.663) Pub Date : 2020-07-07 M.F. Valdez; B. Balachandran; S. Preidikman
A range of quasi-steady and unsteady aerodynamic models are used to predict the aerodynamic forces experienced by a flapping wing and a detailed comparison amongst these predictions in provided. The complexity of the models ranges from the analytical potential flow model to the computational Unsteady Vortex Lattice Method (UVLM), which allows one to describe the motion of the wake and account for its
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The aerodynamic optimisation of a low-Reynolds paper plane with adjoint method Aeronaut. J. (IF 0.663) Pub Date : 2020-08-24 Y. Zhang; X. Zhang; G. Chen
The aerodynamic performance of a deployable and low-cost unmanned aerial vehicle (UAV) is investigated and improved in present work. The parameters of configuration, such as airfoil and winglet, are determined via an optimising process based on a discrete adjoint method. The optimised target is locked on an increasing lift-to-drag ratio with a limited variation of pitching moments. The separation that
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Energy acquisition of a small solar UAV using dynamic soaring Aeronaut. J. (IF 0.663) Pub Date : 2020-08-20 S. Liu; J. Bai; C. Wang
Dynamic soaring improves the endurance of Unmanned Aerial Vehicles (UAVs) by obtaining energy from the horizontal wind shear gradient. The use of dynamic soaring in small solar UAVs can mitigate the trade-off between energy capacity and battery weight to achieve continuous all-day flight. The goal of this study is to determine the optimal energy acquisition methods for small solar UAVs using dynamic
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Ferrofluid thin films for aerofoil lift enhancement and delaying flow separation Aeronaut. J. (IF 0.663) Pub Date : 2020-08-18 F.J. Arias
In this work, consideration is given to a novel concept for aerofoil lift enhancement and delaying flow separation. Here, lift enhancement is attained by preventing the growth of the boundary layer through the elimination of the zero-slip condition between the wing surface and the air stream. The concept would simulate all the effects of a moving wall, leading to the appearance of a slip velocity at
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Development of an actuated corrugated laminate for morphing structures Aeronaut. J. (IF 0.663) Pub Date : 2020-08-17 A. Airoldi; D. Rigamonti; G. Sala; P. Bettini; E. Villa; A. Nespoli
This paper presents the design, manufacturing and experimental assessment of a morphing element consisting of a composite corrugated panel that hosts a diffused actuation system based on Shape Memory Alloy (SMA) actuators. The characterisation of the SMA actuators is reported and the system performance is predicted through an analytical model and finite element analyses. Two versions of the actuated
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Effect of chordwise deformation on propulsive performance of flapping wings in forward flight Aeronaut. J. (IF 0.663) Pub Date : 2020-08-17 T. Lin; W. Xia; S. Hu
Lack of flexibility limits the performance enhancement of man-made flapping wing Micro Air Vehicles (MAVs). Active chordwise deformation (bending) is introduced into the flapping wing model at low Reynolds number of Re = 200 in the present study. The lattice Boltzmann method with immersed boundary is adopted in the numerical simulation. The effects of the bending amplitude, bending frequency and phase
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Analyses of criticality for multiple-site delaminations in the flap spar of Finnish F/A-18 aircraft Aeronaut. J. (IF 0.663) Pub Date : 2020-08-13 J. Jokinen; M. Kanerva; M. Wallin; O. Saarela
Metal-composite airframes will suffer various defects during their lifetime. One category of defects is composite laminate delamination. This study evaluates the criticality of delaminations existing around adjacent fastener holes in the carbon-fibre-reinforced plastic spar web of the F/A-18 aircraft’s trailing-edge flap. The evaluation is based on experiments and analyses. First, an intensive experimental
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Aircraft sequencing and scheduling in TMAs under wind direction uncertainties Aeronaut. J. (IF 0.663) Pub Date : 2020-08-13 R.K. Cecen; C. Cetek; O. Kaya
Aircraft sequencing and scheduling within terminal airspaces has become more complicated due to increased air traffic demand and airspace complexity. A stochastic mixed-integer linear programming model is proposed to handle aircraft sequencing and scheduling problems using the simulated annealing algorithm. The proposed model allows for proper aircraft sequencing considering wind direction uncertainties
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CFD study of oil-jet gear interaction flow phenomena in spur gears Aeronaut. J. (IF 0.663) Pub Date : 2020-06-10 M.C. Keller; C. Kromer; L. Cordes; C. Schwitzke; H.-J. Bauer
Oil-jet lubrication and cooling of high-speed gears is frequently employed in aeronautical systems, such as novel high-bypass civil aero engines based on the geared turbofan technology. Using such oil-jet system, practitioners aim to achieve high cooling rates on the flanks of the highly thermally loaded gears with minimum oil usage. Thus, for an optimal design, detailed knowledge about the flow processes
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Supporting multi-point fan design with dimension reduction Aeronaut. J. (IF 0.663) Pub Date : 2020-07-27 P. Seshadri; S. Yuchi; G.T. Parks; S. Shahpar
Motivated by the idea of turbomachinery active subspace performance maps, this paper studies dimension reduction in turbomachinery 3D CFD simulations. First, we show that these subspaces exist across different blades—under the same parametrisation—largely independent of their Mach number or Reynolds number. This is demonstrated via a numerical study on three different blades. Then, in an attempt to
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A semi-analytical approach for flutter analysis of a high-aspect-ratio wing Aeronaut. J. (IF 0.663) Pub Date : 2020-08-07 R.F. Latif; M.K.A. Khan; A. Javed; S.I.A. Shah; S.T.I. Rizvi
We present a hybrid, semi-analytical approach to perform an eigenvalue-based flutter analysis of an Unmanned Aerial Vehicle (UAV) wing. The wing has a modern design that integrates metal and composite structures. The stiffness and natural frequency of the wing are calculated using a Finite Element (FE) model. The modal parameters are extracted by applying a recursive technique to the Lanczos method
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Uncertainty analysis and robust shape optimisation for laminar flow aerofoils Aeronaut. J. (IF 0.663) Pub Date : 2020-08-03 J. Hollom; N. Qin
Uncertainty in the critical amplification factor ( $N_{cr}$ ) of the $e^N$ transition model is used to approximate the uncertainty in the surface and flow quality of natural laminar flow (NLF) aerofoils. The uncertainty in $N_{cr}$ is represented by a negative half-normal probability distribution that descends from the largest $N_{cr}$ achievable with an ideal surface and flow quality. The uncertainty
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Combustor-inlet interactions in a low-order dynamic model of ramjet engines Aeronaut. J. (IF 0.663) Pub Date : 2020-07-29 K. Liu; T. Cui
The coexistence of multiple stable states is indicative of self-organising processes occurring in the course of the combustor-inlet interactions in a ramjet engine and give rise to the appearance of various nonlinear phenomena. This paper provides a dynamic model that can describe the multiple stable states and the corresponding nonlinear effects to further investigate the dynamic interactions between
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Numerical modelling of thin anisotropic membrane under dynamic load Aeronaut. J. (IF 0.663) Pub Date : 2020-07-21 V.V. Aksenov; A.V. Vasyukov; I.B. Petrov
This work aims to describe a mathematical model and a numerical method to simulate a thin anisotropic membrane moving and deforming in 3D space under a dynamic load of an arbitrary time and space profile. The anisotropic continuum medium model described in the article can be used to model a membrane made of composite material using its effective elastic parameters. The model and the method allow the
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An estimation method for the fuel burn and other performance characteristics of civil transport aircraft in the cruise. Part 1 fundamental quantities and governing relations for a general atmosphere Aeronaut. J. (IF 0.663) Pub Date : 2020-07-20 D.I.A. Poll; U. Schumann
This paper is one of a series addressing the need for simple, yet accurate, methods for the estimation of cruise fuel burn and other important aircraft performance parameters. Here, a previously published, constant Reynolds number model for turbofan-powered, civil transport aircraft is extended to include Reynolds number effects. Provided the variation of temperature with pressure is known, the method
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Time-domain non-linear aeroelastic analysis via a projection-based reduced-order model Aeronaut. J. (IF 0.663) Pub Date : 2020-07-20 S. Lee; H. Cho; H. Kim; S.-J. Shin
The aeroelastic phenomenon of limit-cycle oscillations (LCOs) is analysed using a projection-based reduced-order model (PROM) and Navier–Stokes computational fluid dynamics (CFD) in the time domain. The proposed approach employs incompressible Navier–Stokes CFD to construct the full-order model flow field. A proper orthogonal decomposition (POD) of the snapshot matrix is conducted to extract the POD
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Endurance improvement by battery dumping strategy considering Peukert effect for electric-powered disposable UAVs Aeronaut. J. (IF 0.663) Pub Date : 2020-07-16 X. Feng; Y. Sun; M. Chang; J. Bai
Electric-powered disposable unmanned aerial vehicles (UAVs) have wide applications due to their advantages in terms of long time flight and load capacity. Thus, improving their endurance has become an important task to enhance the performance of these UAVs. To achieve this, we investigated a battery dumping strategy which splits the battery into several packs that are used and dumped in sequence to
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Design and implementation of a power distribution system adopting overcurrent protection Aeronaut. J. (IF 0.663) Pub Date : 2020-07-15 M. Bekhti; M. Bensaada; M. Beldjehem
One of the most critical aspects of a small satellite is the electrical power system (EPS) since the electrical power is necessary for the satellite to operate correctly during its predefined lifetime. The electrical power system consists mainly of solar cells, batteries, voltage converters and protection circuits. The electrical power system is responsible of providing stable power to the rest of
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Body-force and mean-line models for the generation of axial compressor sub-idle characteristics Aeronaut. J. (IF 0.663) Pub Date : 2020-07-07 M. Righi; L.E. Ferrer-Vidal; V. Pachidis
This paper describes the application of low-order models to the prediction of the steady performance of axial compressors at sub-idle conditions. An Euler body-force method employing sub-idle performance correlations is developed and presented alongside a mean-line approach employing the same set of correlations. The low-order tools are used to generate the characteristic lines of the compressor in
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Model for sectional leading-edge vortex lift for the prediction of rotating samara seeds performance Aeronaut. J. (IF 0.663) Pub Date : 2020-05-05 D. Rezgui; I.H. Arroyo; R. Theunissen
This article presents a development of a simple analytical aerodynamic model capable of describing the effect of leading-edge vortices (LEVs) on the lift of rotating samara wings. This analytical model is based on the adaptation of Polhamus’ method to develop a sectional two-dimensional lift function, which was implemented in a numerical blade element model (BEM) of a rotating samara blade. Furthermore
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Modelling performance an air transport network operated by subsonic and supersonic aircraft Aeronaut. J. (IF 0.663) Pub Date : 2020-07-03 M. Janić
This paper deals with modelling the performance of an air transport network operated by existing subsonic and the prospective supersonic commercial aircraft. Analytical models of indicators of the infrastructural, technical/technological, operational, economic, environmental, and social performance of the network relevant for the main actors/stakeholders involved are developed. The models are applied
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Demonstration of a prototype design synthesis capability for space access vehicle design Aeronaut. J. (IF 0.663) Pub Date : 2020-06-30 L. Rana; B. Chudoba
The early conceptual design (CD) phase of space access vehicles (SAVs) is the most abstract, innovative and technologically challenging phase of the entire aerospace design life cycle. Although the design decision-making during this phase influences around 80 percent of the overall life cycle cost, it is the most abstract and thus least understood phase of the entire design life cycle. The history
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Finite-element modelling of NiTi shape-memory wires for morphing aerofoils Aeronaut. J. (IF 0.663) Pub Date : 2020-06-24 W.L.H. Wan A. Hamid; L. Iannucci; P. Robinson
This paper presents the development and implementation of a user-defined material (UMAT) model for NiTi Shape-Memory Alloy (SMA) wires for use in LS-DYNA commercial explicit finite-element analysis software. The UMAT focusses on the Shape-Memory Effect (SME), which could be used for actuation of aerostructural components. The actuation of a fundamental structure consisting of an SMA wire connected
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Rotorcraft systems for urban air mobility: A reality check Aeronaut. J. (IF 0.663) Pub Date : 2020-06-24 A. Filippone; G.N. Barakos
“Urban air vehicles” have been hailed as the next revolution in aviation. Prototypes of various sizes have been flown to demonstrate basic flight (hover and climb), but in most cases there is no demonstration of full flight capability, for example conversion from vertical to level flight (conversion corridor). There are proposals for vehicles in a wide range of scales: from drones specifically designed
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The vibration suppression of solar panel based on smart structure Aeronaut. J. (IF 0.663) Pub Date : 2020-06-22 G. Ma; M. Xu; J. Tian; X. Kan
This paper provides a solution to the active vibration control of a microsatellite with two solar panels. At first, the microsatellite is processed as a finite element model containing a rigid body and two flexible bodies, according to the principles of mechanics, and that the dynamic characteristics are solved by modal analysis. Secondly, the equation involving vibration control is established according
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Bilevel programming model and algorithms for flight gate assignment problem Aeronaut. J. (IF 0.663) Pub Date : 2020-05-19 J. Lin; X. Ding; H. Li; J. Zhou
Considering the decision-making requirements of airport, airlines and passengers, a bilevel programming model which contains two parts was proposed in this paper. One part is to improve the utilization of gates of the airport (upper level), so the objective function of the upper level to the minimum overall variance of slack time between two consecutive air crafts at the same gate. The other part looks
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Synthetic photometric landmarks used for absolute navigation near an asteroid Aeronaut. J. (IF 0.663) Pub Date : 2020-05-13 O. Knuuttila; A. Kestilä; E. Kallio
The need for autonomous location estimation in the form of optical navigation is an essential requirement for forthcoming deep space missions. While crater-based navigation might work well with larger bodies littered with craters, small sub-kilometer bodies do not necessarily have them. We have developed a new pose estimation method for absolute navigation based on photometric local feature extraction
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CAA research programme – Helicopter Operations to Moving Offshore Helidecks: Part A: Modelling the on-deck helicopter Reserve Of Stability (ROS) Aeronaut. J. (IF 0.663) Pub Date : 2020-05-11 A. Scaperdas; D. Howson
The oil and gas industry relies heavily on helicopters for transporting personnel and cargo to and from offshore installations and support vessels. A growing number of offshore helicopter operations are to moving helidecks, which include large vessels such as FPSOs, drill ships, and semi-submersibles, as well as smaller service vessels. Landing a helicopter on a moving helideck presents additional
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