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  Subjects -> AERONAUTICS AND SPACE FLIGHT (Total: 99 journals)
Showing 1 - 30 of 30 Journals sorted alphabetically
Acta Astronautica     Hybrid Journal   (Followers: 332)
Advances in Space Research     Full-text available via subscription   (Followers: 344)
Aerospace     Open Access   (Followers: 40)
Aerospace and Electronic Systems, IEEE Transactions on     Hybrid Journal   (Followers: 216)
Aerospace Science and Technology     Hybrid Journal   (Followers: 309)
Aerospace Scientific Journal     Open Access   (Followers: 2)
AIAA Journal     Full-text available via subscription   (Followers: 777)
Air Force Magazine     Full-text available via subscription   (Followers: 9)
Air Medical Journal     Hybrid Journal   (Followers: 5)
Aircraft Engineering and Aerospace Technology     Hybrid Journal   (Followers: 166)
American Journal of Space Science     Open Access   (Followers: 127)
Annual of Navigation     Open Access   (Followers: 21)
Artificial Satellites : The Journal of Space Research Centre of Polish Academy of Sciences     Open Access   (Followers: 19)
ASTRA Proceedings     Open Access   (Followers: 1)
Aviation     Hybrid Journal   (Followers: 11)
Aviation Psychology and Applied Human Factors     Hybrid Journal   (Followers: 19)
Aviation Week     Full-text available via subscription   (Followers: 244)
Aviation, Space, and Environmental Medicine     Full-text available via subscription   (Followers: 8)
Canadian Aeronautics and Space Journal     Full-text available via subscription   (Followers: 28)
CEAS Aeronautical Journal     Hybrid Journal   (Followers: 28)
Chinese Journal of Aeronautics     Open Access   (Followers: 18)
Ciencia y Poder Aéreo     Open Access   (Followers: 1)
Civil Aviation High Technologies     Open Access  
Control Systems     Hybrid Journal   (Followers: 196)
Cosmic Research     Hybrid Journal   (Followers: 3)
COSPAR Colloquia Series     Full-text available via subscription   (Followers: 7)
Egyptian Journal of Remote Sensing and Space Science     Open Access   (Followers: 19)
Elsevier Astrodynamics Series     Full-text available via subscription   (Followers: 9)
Fatigue of Aircraft Structures     Open Access   (Followers: 12)
Frontiers in Aerospace Engineering     Open Access   (Followers: 11)
Frontiers in Astronomy and Space Sciences     Open Access   (Followers: 9)
Gyroscopy and Navigation     Hybrid Journal   (Followers: 193)
IEEE Aerospace and Electronic Systems Magazine     Full-text available via subscription   (Followers: 140)
IEEE Transactions on Circuits and Systems I: Regular Papers     Hybrid Journal   (Followers: 30)
International Journal of Aeroacoustics     Hybrid Journal   (Followers: 33)
International Journal of Aerodynamics     Hybrid Journal   (Followers: 20)
International Journal of Aerospace Engineering     Open Access   (Followers: 66)
International Journal of Aerospace Sciences     Open Access   (Followers: 23)
International Journal of Applied Geospatial Research     Hybrid Journal   (Followers: 3)
International Journal of Aviation Management     Hybrid Journal   (Followers: 4)
International Journal of Aviation Psychology     Hybrid Journal   (Followers: 14)
International Journal of Aviation Technology, Engineering and Management     Full-text available via subscription   (Followers: 5)
International Journal of Crashworthiness     Hybrid Journal   (Followers: 9)
International Journal of Micro Air Vehicles     Full-text available via subscription   (Followers: 8)
International Journal of Satellite Communications Policy and Management     Hybrid Journal   (Followers: 9)
International Journal of Space Science and Engineering     Hybrid Journal   (Followers: 8)
International Journal of Space Structures     Full-text available via subscription   (Followers: 9)
International Journal of Space Technology Management and Innovation     Full-text available via subscription   (Followers: 5)
International Journal of Sustainable Aviation     Hybrid Journal   (Followers: 2)
International Journal of Turbo & Jet-Engines     Hybrid Journal   (Followers: 4)
Journal of Aeronautical Materials     Open Access   (Followers: 6)
Journal of Aeronautics & Aerospace Engineering     Open Access   (Followers: 15)
Journal of Aerospace Engineering     Full-text available via subscription   (Followers: 58)
Journal of Aerospace Engineering & Technology     Full-text available via subscription   (Followers: 11)
Journal of Aerospace Information Systems     Full-text available via subscription   (Followers: 11)
Journal of Aerospace Technology and Management     Open Access   (Followers: 4)
Journal of Aircraft     Full-text available via subscription   (Followers: 208)
Journal of Airline and Airport Management     Open Access   (Followers: 7)
Journal of Astrobiology & Outreach     Open Access   (Followers: 1)
Journal of Aviation Technology and Engineering     Open Access   (Followers: 10)
Journal of Guidance, Control, and Dynamics     Full-text available via subscription   (Followers: 137)
Journal of Konbin : The Journal of Air Force Institute of Technology     Open Access   (Followers: 2)
Journal of Navigation     Hybrid Journal   (Followers: 198)
Journal of Propulsion and Power     Full-text available via subscription   (Followers: 370)
Journal of Space Safety Engineering     Hybrid Journal  
Journal of Space Weather and Space Climate     Open Access   (Followers: 21)
Journal of Spacecraft and Rockets     Full-text available via subscription   (Followers: 546)
Journal of Spatial Science     Hybrid Journal   (Followers: 3)
Journal of the American Helicopter Society     Full-text available via subscription   (Followers: 5)
Journal of the Astronautical Sciences     Hybrid Journal   (Followers: 5)
Journal of Wind Engineering and Industrial Aerodynamics     Hybrid Journal   (Followers: 7)
Life Sciences in Space Research     Hybrid Journal   (Followers: 2)
MAD - Magazine of Aviation Development     Open Access   (Followers: 1)
Microgravity Science and Technology     Hybrid Journal   (Followers: 1)
New Space     Hybrid Journal   (Followers: 4)
Nonlinear Dynamics     Hybrid Journal   (Followers: 15)
npj Microgravity     Open Access   (Followers: 1)
Population Space and Place     Hybrid Journal   (Followers: 5)
Problemy Mechatroniki. Uzbrojenie, lotnictwo, inżynieria bezpieczeństwa / Problems of Mechatronics. Armament, Aviation, Safety Engineering     Open Access   (Followers: 1)
Proceedings of the Human Factors and Ergonomics Society Annual Meeting     Hybrid Journal   (Followers: 10)
Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering     Hybrid Journal   (Followers: 41)
Progress in Aerospace Sciences     Full-text available via subscription   (Followers: 72)
Propulsion and Power Research     Open Access   (Followers: 25)
REACH - Reviews in Human Space Exploration     Full-text available via subscription   (Followers: 2)
Recent Patents on Space Technology     Full-text available via subscription   (Followers: 3)
Research & Reviews : Journal of Space Science & Technology     Full-text available via subscription   (Followers: 9)
RocketSTEM     Free   (Followers: 3)
Russian Aeronautics (Iz VUZ)     Hybrid Journal   (Followers: 23)
Science and Education : Scientific Publication of BMSTU     Open Access  
Space and Polity     Hybrid Journal   (Followers: 4)
Space Policy     Hybrid Journal   (Followers: 25)
Space Research Today     Full-text available via subscription   (Followers: 43)
Space Safety Magazine     Free   (Followers: 43)
Space Science Reviews     Hybrid Journal   (Followers: 94)
SpaceNews     Free   (Followers: 537)
Transport and Aerospace Engineering     Open Access   (Followers: 5)
Transportmetrica A : Transport Science     Hybrid Journal   (Followers: 5)
Unmanned Systems     Hybrid Journal   (Followers: 3)
Вісник Національного Авіаційного Університету     Open Access   (Followers: 1)
Journal Cover CEAS Aeronautical Journal
  [SJR: 0.499]   [H-I: 6]   [28 followers]  Follow
   Hybrid Journal Hybrid journal (It can contain Open Access articles)
   ISSN (Print) 1869-5582
   Published by Springer-Verlag Homepage  [2353 journals]
  • Time-domain output error system identification of iced aircraft
    • Authors: Christoph Deiler
      Pages: 231 - 244
      Abstract: Abstract A \(\Delta\) -model approach to characterize changed aircraft dynamics due to icing is analytically derived and its parameters are estimated. The model extension is formulated as a separate module in the aircraft flight mechanics simulation and can be used in existing simulation models. The application of the output error method in time domain allows to satisfactorily match model outputs and measurements as well as calculated aerodynamic derivatives. Using available flight data of a light business jet with different ice accumulation cases provided by EMBRAER, model parameters of the \(\Delta\) -model are determined and interpreted pertaining to the aerodynamic degradation caused by icing. The results show good promise that the combination of modeling approach and estimation technique could be applicable to extend existing simulator models providing a basis for pilot training under icing conditions.
      PubDate: 2017-06-01
      DOI: 10.1007/s13272-016-0231-2
      Issue No: Vol. 8, No. 2 (2017)
  • Numerical investigation of the vortex roll-up from a helicopter blade tip
           using a novel fixed-wing adaptation method
    • Authors: Antoine Joulain; Damien Desvigne; David Alfano; Thomas Leweke
      Pages: 245 - 260
      Abstract: Abstract This contribution relates to the simulation of the flow around the tip of a helicopter rotor blade in hovering flight conditions. We here propose a new methodology of framework adaptation, using a comprehensive rotor code and high-fidelity numerical simulations. We construct an equivalent fixed-wing configuration from a rotating blade, in which centrifugal and Coriolis forces are neglected. The effect of this approximation on the solution is analyzed. The method is validated by a detailed comparison with wind tunnel data from the literature, concerning aerodynamic properties and tip vortex roll-up. This validation also includes variations of the pitch angle and rotational speed, up to transonic tip velocities. Compared to previously published methods of framework adaptation, the new hybrid method is found to reproduce more accurately the flow around a rotating-blade tip.
      PubDate: 2017-06-01
      DOI: 10.1007/s13272-016-0234-z
      Issue No: Vol. 8, No. 2 (2017)
  • Towards the development of a flight training programme for future personal
           aerial vehicle users
    • Authors: Philip Perfect; Michael Jump; Mark D. White
      Abstract: Abstract Interest in personal aerial vehicles (PAVs) is resurgent with several flying prototypes made possible through advances in the relevant technologies. Whilst the perceived wisdom is that these vehicles will be highly automated or autonomous, the current regulatory framework assumes that a human will always be able to intervene in the operation of the flight. This raises the possibility of manually operated PAVs and the requirement for an occupant flying training programme. This paper describes the development of training requirements for PAV pilots. The work includes a training needs analysis (TNA) for a typical PAV flight. It then describes the development of a training programme to develop the skills identified by the TNA. Five participants with no real flying experience, but varying levels of driving experience, undertook the training programme. Four completed the programme through to a successful simulation flight test of a commuter flight scenario. These participants evaluated the effectiveness of the training programme using the first three Levels of Kirkpatrick’s method. The evaluation showed that the developed training programme was effective, in terms of both trainee engagement and development of the handling skills necessary to fly PAV mission-related tasks in a flight simulator. The time required for the four successful participants to develop their core flying skills was less than 5 h. This duration indicates that future simulation PAV training would be commensurate with the training duration for current personal transportation modes.
      PubDate: 2017-07-17
      DOI: 10.1007/s13272-017-0255-2
  • Motion cueing optimisation applied to rotorcraft flight simulation
    • Authors: Michael Jones
      Abstract: Abstract Achieving good motion cueing in rotorcraft flight simulation is a long-standing challenge in the simulation community. The current reliance upon subjective opinion leads to a wide range of motion configurations, which almost certainly do not offer the optimal level of vestibular cueing. Furthermore, without the understanding of the optimal motion settings, objective criteria are difficult to apply. This paper presents a new method designed to optimise and evaluate the response of any motion platform, based upon the input to the system and the given motion system constraints. The method is utilised to tune the motion platform of the air vehicle simulator. Results show promise for the use of the optimisation, as good fidelity is shown through pilot subjective comments and ratings.
      PubDate: 2017-07-14
      DOI: 10.1007/s13272-017-0256-1
  • Comparison of the NASA Common Research Model European Transonic Wind
           Tunnel test data to NASA National Transonic Facility test data
    • Authors: Melissa Rivers; Jürgen Quest; Ralf Rudnik
      Abstract: Abstract Experimental aerodynamic investigations of the NASA Common Research Model have been conducted in the NASA Langley National Transonic Facility and the European Transonic Wind Tunnel. Data have been obtained at chord Reynolds numbers of 5, 19.8 and 30 million for the wing/body/tail = 0° incidence configuration in the National Transonic Facility and in the European Transonic Wind Tunnel. Force and moment, surface pressure, wing bending and twist, and surface flow visualization data were obtained in both facilities but only the force and moment, and surface pressure data are presented herein.
      PubDate: 2017-07-12
      DOI: 10.1007/s13272-017-0250-7
  • Investigation of the small-scale statistics of turbulence in the Modane
           S1MA wind tunnel
    • Authors: M. Bourgoin; C. Baudet; S. Kharche; N. Mordant; T. Vandenberghe; S. Sumbekova; N. Stelzenmuller; A. Aliseda; M. Gibert; P.-E. Roche; R. Volk; T. Barois; M. Lopez Caballero; L. Chevillard; J.-F. Pinton; L. Fiabane; J. Delville; C. Fourment; A. Bouha; L. Danaila; E. Bodenschatz; G. Bewley; M. Sinhuber; A. Segalini; R. Örlü; I. Torrano; J. Mantik; D. Guariglia; V. Uruba; V. Skala; J. Puczylowski; J. Peinke
      Abstract: Abstract This article describes the planning, set-up, turbulence characterization and analysis of measurements of a passive grid turbulence experiment that was carried out in the S1MA wind-tunnel from ONERA in Modane, in the context of the ESWIRP European project. This experiment aims at a detailed investigation of the statistical properties of turbulent flows at large Reynolds numbers. The primary goal is to take advantage of the unequaled large-scale dimensions of the ONERA S1MA wind-tunnel facility, to make available to the broad turbulence community high-quality experimental turbulence data with unprecendented resolution (both spatial and temporal) and accuracy (in terms of statistical convergence). With this goal, we designed the largest grid-generated turbulence experiment planned and performed to date. Grid turbulence is a canonical flow known to produce almost perfectly homogeneous and isotropic turbulence (HIT) which remains a unique framework to investigate fundamental physics of turbulent flows. Here, we present a brief description of the measurements, in particular those based on hot-wire diagnosis. By comparing results from classical hot-wires and from a nano-fabricated wire (developed at Princeton University), we show that our goal of resolving down to the smallest dissipative scales of the flow has been achieved. We also present the full characterization of the turbulence here, in terms of turbulent energy dissipation rate, injection and dissipation scales (both spatial and temporal) and Reynolds number.
      PubDate: 2017-07-11
      DOI: 10.1007/s13272-017-0254-3
  • Numerical simulation of flexible aircraft structures under ditching loads
    • Authors: M. H. Siemann; D. Kohlgrüber; H. Voggenreiter
      Abstract: Abstract Aircraft certification requires demonstrating an aircraft’s structural capacity to withstand hydrodynamic loads as experienced during an emergency landing on water known as ditching. Currently employed means to analyze ditching comprise comparison with previously certified aircraft, sub-scale experimental testing, and semi-analytical as well as uncoupled computational methods; all of these are subject to simplifications that limit their predictability and accuracy. Therefore, there is the motivation to employ advanced, coupled numerical simulations to enhance the analysis capabilities. This paper presents a numerical simulation approach combining Smoothed Particle Hydrodynamics and Finite Element method, which permits investigating the structural behavior under ditching loads within one simulation. Comprehensive validation studies based on comparison with experimental results from novel guided ditching experiments of generic panels in aeronautical design have been undertaken and high accuracy has been achieved regarding acting force and strain time histories. Additionally, the profound analysis of the structural behavior of flexible panels allows assessing the main mechanisms that cause the acting hydrodynamic loads to increase significantly when the structure is being deformed. Presented results extend the fundamental knowledge in this field. The validated simulation approach is finally applied to analyze the structural behavior of a detailed stringer-frame-reinforced panel representing a generic aircraft bottom fuselage structure. Comparison between the structural behavior of the generic panels and the aft fuselage structure is established. Furthermore, conclusions with regard to ditching simulations involving larger or even full aircraft structures are drawn.
      PubDate: 2017-07-11
      DOI: 10.1007/s13272-017-0257-0
  • Aerodynamic assessment of nozzle area variation by core fairing modulation
    • Authors: Chetan Kumar Sain; Klaus Hoeschler
      Abstract: Abstract This paper describes the aerodynamic assessment of a particular variable area fan nozzle (VAFN) concept. This concept offers a variation in the fan nozzle throat area by displacing the inner fairing structure (IFS), which is also known as the core fairing structure. A few different design configurations were developed through the variation in the design parameters. The aim of the assessment was to perform a comparative aerodynamic study by evaluating the main performance parameters such as the nozzle thrust coefficient, nozzle discharge coefficient and the after-body drag at different flight conditions. The required boundary conditions and the magnitudes of the variation in the nozzle throat area were defined following the performance calculations of the whole engine.
      PubDate: 2017-07-05
      DOI: 10.1007/s13272-017-0253-4
  • Aeroelastic tailoring of an NLF forward swept wing
    • Authors: Tobias Wunderlich; Sascha Dähne
      Abstract: Abstract This article introduces the application of a multidisciplinary analysis process chain based on high-fidelity simulation methods for the aeroelastic tailoring of an natural laminar flow (NLF) forward swept wing. With this approach the interactions between aerodynamics, loads and structural sizing are considered in the wing analysis. The resulting process enables an integrated aerostructural wing design including aeroelastic tailoring using carbon fiber reinforced plastics. The main feature of the process chain is the hierarchical decomposition of the problem into two levels. On the highest level, the orthotropy direction of the composite structure will be analyzed. The lower level includes the wing box sizing for essential load cases considering the static aeroelastic deformations. Thereby, the wing box sizing can be performed with a given ply share of the laminate or a ply share optimization. Additionally, the airfoil shapes are transferred from a given NLF wing design. The natural laminar flow is considered by prescribing laminar–turbulent transition locations. The process chain evaluates the wing mass, the lift-to-drag ratio under cruise flight conditions and the corresponding design mission fuel consumption. Results of aerostructural wing design studies and optimizations are presented for an NLF forward swept wing aircraft configuration. The aerostructural wing optimization with 3 orthotropy angles as design parameters shows a wing mass reduction in the order of 8% and a design mission fuel consumption reduction in the order of 4% in comparison to the aeroelastic tailored wing design of the reference aircraft.
      PubDate: 2017-06-30
      DOI: 10.1007/s13272-017-0251-6
  • Automated trajectory generation and airport selection for an emergency
           landing procedure of a CS23 aircraft
    • Authors: Arno Fallast; Bernd Messnarz
      Abstract: Abstract Aircraft in general aviation usually are operated in single pilot mode. Especially, in case of an incapability of the pilot to control the aircraft, an automated emergency procedure is desirable in order to reduce the risk of fatalities. The finding of a solution for an emergency landing maneuver includes preselecting possible landing sites with regard to the available aircraft capabilities and creation of feasible trajectories to these sites. A search tree in four-dimensional search space with an efficient implementation of a rapidly exploring random tree algorithm (RRT*) is created. The algorithm performance is increased by use of basic geometrical sets to construct the final route as a combination of Dubins path segments. To further reduce the route length, a gradient based local optimization routine is added after completion of the RRT* algorithm. At the moment of creation, terrain avoidance is verified and accordance with legal airspace structure is considered. An emergency procedure is created by combining a selected landing site and a flyable trajectory to this site. Each of these combinations is scored, and the most promising emergency landing procedure is chosen and delivered to flight management system of the aircraft. The flight management system controls a full-authority auto-flight system that is capable of performing en-route flight and auto-land procedures as well.
      PubDate: 2017-06-30
      DOI: 10.1007/s13272-017-0252-5
  • Numerical and experimental investigations of the propeller characteristics
           of an electrically powered ultralight aircraft
    • Authors: M. Stuhlpfarrer; A. Valero-Andreu; C. Breitsamter
      Abstract: Abstract The performance and efficiency of a propeller is crucial for electrically powered propulsion systems. Since the energy of the batteries is limited, it is important to develop propellers with high efficiency. Therefore, numerical and experimental investigations of the propeller characteristics are performed. The wind tunnel experiments are performed on a fuselage–propeller configuration. The electrical motor, batteries, and control units are designed to be integrated in the fuselage. Furthermore, force measurements are conducted to provide a data base for the validation of the numerical results. Two different numerical approaches are presented. First, the propeller is fully resolved by applying a rotational domain and a sliding mesh interface. Second, an actuator disk approach including blade element theory with a panel method one-way coupled with a boundary layer integration method is presented. The latter shall be used to reduce computational and mesh generation costs. The thrust, efficiency as well as pressure distribution and the flow field downstream of the propeller are analyzed. The obtained numerical results show a good agreement with the experimental data for the integral values over a wide operating range. Moreover, the results of the inter-method comparison of the two numerical approaches are in a good accordance regarding the local effects for the two highlighted operating points.
      PubDate: 2017-06-16
      DOI: 10.1007/s13272-017-0245-4
  • A numerical approach for assessing slotted wall interference using the CRM
           model at ETW
    • Authors: I. A. Kursakov; A. R. Gorbushin; S. M. Bosnyakov; S. A. Glazkov; A. V. Lysenkov; S. V. Matyash; A. V. Semenov; J. Quest
      Abstract: Abstract This paper is devoted to the assessment of wall interference in the slotted wall test section of the European Transonic Windtunnel (ETW) over a wide range of Reynolds numbers. The experimental part of the investigation was performed in February 2014 by testing the NASA Common Research Model mounted on a fin-sting support. These tests were carried out within the scope of the ESWIRP project funded by the European Commission in the 7th framework program. The numerical research was based on the Electronic WindTunnel (EWT-TsAGI) software with a cryogenic solver. The assessed Mach number influence on the wall signatures revealed a very similar effect to applying the classical Prandtl–Glauert rule over the investigated Mach number range. Practically, no Reynolds number effects on the wall pressure distributions generated by the model and its support system could be identified over the wide range of Re numbers investigated. The first attempt of the EWT-TsAGI code application for a simulation of ETW tests featuring the model in the slotted wall tunnel showed a fair coincidence of the pressure coefficient distribution on test section walls in the model region, on the wing-root sections and the drag polar at moderate lift coefficient values.
      PubDate: 2017-06-12
      DOI: 10.1007/s13272-017-0248-1
  • Experimental study of two electro-mechanical de-icing systems applied on a
           wing section tested in an icing wind tunnel
    • Authors: M. Endres; H. Sommerwerk; C. Mendig; M. Sinapius; P. Horst
      Abstract: Abstract Two electro-mechanical de-icing systems are presented, which are applied to a test specimen consisting of a wing section with an NACA0012 profile. The test specimen is of a modular design to be able to substitute the leading edge section for investigating the different de-icing systems. The de-icing tests are performed in the icing wind tunnel of the Institute of Fluid Mechanics of the TU Braunschweig. The first de-icing concept is an electro-mechanical system based on structural vibrations of the unstiffened sections. Due to piezoceramic actuators and their positions, the skin is excited at its natural frequency. The actuators are placed at the inner side of the leading edge. The second system under investigation is the Electro-Impulse De-Icing concept. Coils placed underneath the upper and lower aluminum skin are supplied with short, high-current impulses which produce opposing time-dependent magnetic fields around coil and skin. The resulting magnetic forces repel the structure which leads to a damped oscillation of the skin. The first aim of this work is to investigate the performance of the two electro-mechanical de-icing systems under various icing conditions. Operational parameters like temperature and liquid water content are varied. The test results show that the de-icing performance of both systems mainly depends on the ice layer thickness and the environmental temperature. The second aim of this work is to investigate the de-icing mechanism of the accumulated ice. Therefore, the de-icing procedure is recorded with a high-speed camera.
      PubDate: 2017-06-09
      DOI: 10.1007/s13272-017-0249-0
  • APIAN-INF: an aerodynamic and aeroacoustic investigation of
           pylon-interaction effects for pusher propellers
    • Authors: Tomas Sinnige; Daniele Ragni; Anwar M. N. Malgoezar; Georg Eitelberg; Leo L. M. Veldhuis
      Abstract: Abstract Advanced propellers promise significant fuel-burn savings compared to turbofans. When installed on the fuselage in a pusher configuration, the propeller interacts with the wake of the supporting pylon. This paper presents an experimental analysis of the aerodynamic and aeroacoustic characteristics of this pylon–propeller interaction. An isolated propeller was operated in undisturbed flow and in the wake of an upstream pylon at the large low-speed facility of the German–Dutch wind tunnels (DNW-LLF). Measurements of the pylon-wake characteristics showed that the wake width and velocity deficit decreased with increasing thrust due to the suction of the propeller. The installation of the pylon led to a tonal noise penalty of up to 24 dB, resulting from the periodic blade-loading fluctuations caused by the wake encounter. The noise penalty peaked in the upstream direction and became increasingly prominent with decreasing propeller thrust setting, due to the associated reduction of the steady blade loads. The integral propeller performance was not significantly altered by the pylon-wake encounter process. However, at sideslip angles of ±6°, the effective advance ratio of the propeller was modified by the circumferential velocity components induced by the pylon tip vortex. The propeller performance improved when the direction of rotation of the propeller was opposite to that of the pylon tip vortex. Under this condition, a reduction was measured in the noise emissions due to a favorable superposition of the angular-inflow and pylon-wake effects.
      PubDate: 2017-06-02
      DOI: 10.1007/s13272-017-0247-2
  • Component-wise vibration analysis of stiffened plates accounting for
           stiffener modes
    • Authors: Tommaso Cavallo; Enrico Zappino; Erasmo Carrera
      Abstract: Abstract This work has the aims to assess and compare the behavior of different finite element models in a free-vibration analysis of reinforced structures. The effects of the aspect ratio and cross-sectional shape of the stringers have been analyzed using both classical and refined FE. One- and two-dimensional classical finite element models, as well as refined one-dimensional elements, derived using the Carrera Unified Formulation, have been considered in an analysis of reinforced structures. The accuracy and efficiency of these models have been investigated. A three-dimensional model has been used as a reference solution. Three different modeling approaches have been considered in the present work. Two approaches are based on classical models provided by commercial tools: the first uses two-dimensional elements for both a plate and stringers, while the second uses two-dimensional elements to simulate the plate and the beam elements for the stringers. The third approach uses a refined one-dimensional model, based on the Carrera Unified Formulation. This refined one-dimensional model considers a variable kinematic displacement field over the beam cross section. In the present work, Lagrange polynomials are used to describe the cross-sectional displacement field. The use of a component-wise modeling approach allows the stiffeners to be modeled as independent entities. The component-wise approach was first assessed and convergence was then evaluated. The performances of these models in the analysis of reinforced structure were then compared with those from classical models. The use of refined one-dimensional models allows stiffener modes to be investigated. The results show that this approach is comparable to a full three-dimensional solution. The use of classical one- and two-dimensional models does not allow the local deformation of reinforcements to be taken into account. Therefore, these models cannot be considered accurate when the aim of the analysis is to investigate the local mode.
      PubDate: 2017-04-04
      DOI: 10.1007/s13272-017-0244-5
  • Impact of climate costs on airline network and trajectory optimization: a
           parametric study
    • Authors: Judith Rosenow; Martin Lindner; Hartmut Fricke
      Abstract: Abstract Today’s airline industry is facing a highly competitive market, so network and trajectory optimization is driven by fuel and time costs, constrained by air traffic management capacity. The resulting climate effects on global warming and on environmental health are reflected in the emission trading system (ETS) certificates. However, the climate impact of air traffic depends on the locality of the emissions. Hence, even the airline network structure affects the air traffic climate impact. This paper presents an approach of the back coupling of network and trajectory optimization, aiming to minimize both climate effects and costs. First, an optimized air traffic network with respect to minimum fuel consumption and minimum climate costs due to latitude-dependent effects of nitric oxides is compared with a fuel burn optimized network. Second, a lateral trajectory optimization gives the horizontally shortest flight path with respect to minimum costs due to the latitude-dependent effects of nitric oxides. In a third step, vertical trajectory optimization is applied within the optimized routing structure. The calculated amount of emissions is transferred into carbon dioxide equivalent emissions using the global warming potential. Finally, the emissions are expressed in costs considering the effect of the emissions on global warming with the help of the ETS. These costs are used to evaluate both networks, with and without nitric oxide consideration.
      PubDate: 2017-03-30
      DOI: 10.1007/s13272-017-0239-2
  • Assessment and development of a ROM for linearized aeroelastic analyses of
           aerospace vehicles
    • Authors: P. Castronovo; F. Mastroddi; F. Stella; M. E. Biancolini
      Abstract: Abstract In the present work, a reduced order model (ROM) for aeroelastic analysis linearized around non-linear steady solutions has been assessed and implemented to perform high-fidelity predictions, in particular for transonic flow. The ROM has been specifically adopted for identifying the unsteady aerodynamics by means of a modal-based approach. This goal has been achieved by performing a series of prescribed modal-transient boundary conditions on a Euler-based computational fluid-dynamics code and then post-processing the input/output data in the frequency domain. A fast and efficient morphing code based on the use of radial basis functions has been introduced at this phase of the procedure to reach a wide range of applicability for significant cases with complex geometries as in the case of aeronautical and space vehicles. Flutter boundaries have been investigated by capturing the so-called transonic dip phenomenon, mainly due to compressibility and evidenced in the literature also by wind tunnel tests. Comparisons of the present results with linear lower fidelity approaches, based on potential flows, have demonstrated the capabilities of the proposed ROM. Finally, in order to show the general-purpose applicability of the proposed approach, the method has been applied to the aeroelastic analysis of a launch vehicle. For this application no commercial codes for linear aeroelastic analysis are available for comparisons.
      PubDate: 2017-03-27
      DOI: 10.1007/s13272-017-0243-6
  • In-flight remote sensing and identification of gusts, turbulence, and wake
           vortices using a Doppler LIDAR
    • Authors: N. Fezans; J. Schwithal; D. Fischenberg
      Abstract: Abstract In this paper, in-flight remote sensing technologies are considered for two applications: active load alleviation of gust and turbulence and wake impact alleviation. The paper outlines the strong commonalities in terms of sensors and measurement post-processing algorithms and presents also the few differences and their consequences in terms of post-processing. The way the post-processing is being made is detailed before showing results for both applications based on a complete and coupled simulation (aircraft reaction due to disturbances and control inputs during the simulation is influencing the sensor measurements). The performances in terms of wind reconstruction quality for the gust/turbulence case and in terms of wake impact alleviation performance for the wake vortex case are shown based on simulations and are very promising.
      PubDate: 2017-03-21
      DOI: 10.1007/s13272-017-0240-9
  • Progress in studying passive and active devices for fuselage noise
           reduction for next generation turboprop
    • Authors: M. Arena; A. De Fenza; M. Di Giulio; A. Paonessa; F. Amoroso
      Abstract: Abstract Over the years, the interior noise levels have been improved, and nowadays a high acoustical comfort is of major importance for the commercial success of propeller aircraft. The use and development of high vibro-acoustic performance devices and their integration on the primary structure are, therefore, among the most critical topics in the greening of the next generation air transportation. The purpose of this research was properly focused on the analysis of a dynamic control system appointed to increase the noise attenuation transmitted in the propeller aircraft fuselage. Passive and active dynamic devices have been studied and characterized in this work. Simulations and tests performed on the first stage demonstrator structure highlighted how the passive tuned vibration absorber increases the comfort controlling the structural behaviour of the fuselage at the first blade pass frequency. Further improvements of fuselage comfort can be reached using active devices. A conceptual design of a hybrid active device able to act on the first three blade pass frequencies has been outlined. The characterization of the whole active noise control system has been described and its effect on noise reduction in fuselage of propeller aircraft has been evaluated.
      PubDate: 2017-03-20
      DOI: 10.1007/s13272-017-0242-7
  • A methodology to enable automatic 3D routing of aircraft Electrical Wiring
           Interconnection System
    • Authors: Z. Zhu; G. La Rocca; M. J. L. van Tooren
      Abstract: Abstract Harness 3D routing is one of the most challenging steps in the design of aircraft Electrical Wiring Interconnection System (EWIS). This is due not only to the intrinsic complexity of the EWIS, but also to the increasing number of applying design constraints and its dependency on any change in the design of the airframe and installed systems. The current routing process employed by EWISdesign is largely based on the manual work of expert engineers, partially supported by conventional CAD systems. As a result, the routing process is quite inefficient, error prone and unable to deliver optimal solutions. Although many harness components are selected from catalogues and the design process is largely repetitive and rule based, it has been found that none or very limited automation solutions, which can significantly decrease the workload of engineers and increase their efficiency, are currently available. In this paper, an innovative approach is proposed to solve the 3D routing automation as an optimization problem. Knowledge Based Engineering (KBE) and optimization methods are proposed to achieve minimum cost routing solutions that satisfy all relevant design rules and constraints. The proposed solution is scalable in terms of constraints, can be deployed on any type of routing environment, and, thanks to the achieved level of automation, able to reduce the process lead time drastically. The basic idea is to achieve optimal EWIS routing solutions by optimizing the position of the harnesses clamping points, which are used as way-points to route the harnesses inside the aircraft digital mock-up. The challenge to solve this optimization problem is that the number and initial value of design variables, namely the number and position of clamping points, are not known a priori. To handle this challenge, a two-step, hybrid optimization strategy has been devised. The first step, called Initialization, uses a road map based path finding method to generate a preliminary harness definition, including the required number and preliminary position of its clamping points. The second step, called Refinement, uses a conventional optimization method to move the position of the clamps and refine the preliminary harness definition aiming for the minimum cost and the satisfaction of all the design constraints. This approach has been implemented into a KBE application connected with a commercial optimization package and tested on several routing cases. The results demonstrate that the proposed method is capable of handling cases of representative geometric complexity and design constraints and delivering proper 3D harness models in full automation.
      PubDate: 2017-03-10
      DOI: 10.1007/s13272-017-0238-3
School of Mathematical and Computer Sciences
Heriot-Watt University
Edinburgh, EH14 4AS, UK
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