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  Subjects -> AERONAUTICS AND SPACE FLIGHT (Total: 98 journals)
Showing 1 - 30 of 30 Journals sorted alphabetically
Acta Astronautica     Hybrid Journal   (Followers: 323)
Advances in Space Research     Full-text available via subscription   (Followers: 338)
Aerospace     Open Access   (Followers: 39)
Aerospace and Electronic Systems, IEEE Transactions on     Hybrid Journal   (Followers: 215)
Aerospace Science and Technology     Hybrid Journal   (Followers: 309)
Aerospace Scientific Journal     Open Access   (Followers: 1)
AIAA Journal     Full-text available via subscription   (Followers: 764)
Air Force Magazine     Full-text available via subscription   (Followers: 8)
Air Medical Journal     Hybrid Journal   (Followers: 5)
Aircraft Engineering and Aerospace Technology     Hybrid Journal   (Followers: 170)
American Journal of Space Science     Open Access   (Followers: 116)
Annual of Navigation     Open Access   (Followers: 21)
Artificial Satellites : The Journal of Space Research Centre of Polish Academy of Sciences     Open Access   (Followers: 18)
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: 231)
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: 170)
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: 8)
Fatigue of Aircraft Structures     Open Access   (Followers: 11)
Frontiers in Aerospace Engineering     Open Access   (Followers: 11)
Frontiers in Astronomy and Space Sciences     Open Access   (Followers: 9)
Gyroscopy and Navigation     Hybrid Journal   (Followers: 197)
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: 27)
International Journal of Aeroacoustics     Hybrid Journal   (Followers: 32)
International Journal of Aerodynamics     Hybrid Journal   (Followers: 20)
International Journal of Aerospace Engineering     Open Access   (Followers: 65)
International Journal of Aerospace Sciences     Open Access   (Followers: 22)
International Journal of Applied Geospatial Research     Hybrid Journal   (Followers: 3)
International Journal of Aviation Management     Hybrid Journal   (Followers: 5)
International Journal of Aviation Psychology     Hybrid Journal   (Followers: 15)
International Journal of Aviation Technology, Engineering and Management     Full-text available via subscription   (Followers: 4)
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: 8)
International Journal of Space Science and Engineering     Hybrid Journal   (Followers: 7)
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: 3)
Journal of Aeronautical Materials     Open Access   (Followers: 5)
Journal of Aeronautics & Aerospace Engineering     Open Access   (Followers: 15)
Journal of Aerospace Engineering     Full-text available via subscription   (Followers: 57)
Journal of Aerospace Engineering & Technology     Full-text available via subscription   (Followers: 10)
Journal of Aerospace Information Systems     Full-text available via subscription   (Followers: 10)
Journal of Aerospace Technology and Management     Open Access   (Followers: 4)
Journal of Aircraft     Full-text available via subscription   (Followers: 207)
Journal of Airline and Airport Management     Open Access   (Followers: 8)
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: 131)
Journal of Konbin : The Journal of Air Force Institute of Technology     Open Access   (Followers: 1)
Journal of Navigation     Hybrid Journal   (Followers: 200)
Journal of Propulsion and Power     Full-text available via subscription   (Followers: 366)
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: 530)
Journal of Spatial Science     Hybrid Journal   (Followers: 3)
Journal of the American Helicopter Society     Full-text available via subscription   (Followers: 4)
Journal of the Astronautical Sciences     Hybrid Journal   (Followers: 4)
Journal of Wind Engineering and Industrial Aerodynamics     Hybrid Journal   (Followers: 6)
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: 3)
Nonlinear Dynamics     Hybrid Journal   (Followers: 14)
npj Microgravity     Open Access   (Followers: 1)
Population Space and Place     Hybrid Journal   (Followers: 4)
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: 9)
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: 71)
Propulsion and Power Research     Open Access   (Followers: 25)
REACH - Reviews in Human Space Exploration     Full-text available via subscription   (Followers: 1)
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: 8)
RocketSTEM     Free   (Followers: 2)
Russian Aeronautics (Iz VUZ)     Hybrid Journal   (Followers: 24)
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: 42)
Space Science Reviews     Hybrid Journal   (Followers: 95)
SpaceNews     Free   (Followers: 525)
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  [2345 journals]
  • Time-domain output error system identification of iced aircraft
    • Authors: Christoph Deiler
      Pages: 231 - 244
      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: 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)
  • State estimation for reactive Euler equation by Kalman Filtering
    • Authors: Jan- Simon Schäpel; Sascha Wolff; Philipp Schulze; Phillip Berndt; Rupert Klein; Volker Mehrmann; Rudibert King
      Pages: 261 - 270
      Abstract: In this article, we present a state estimation method for an approximately constant volume combustion process. This is an Unscented Kalman Filter used to estimate quantities which are of interest for the combustion process inside the considered combustion tube, i.e., the pressure, velocity and temperature field. This algorithm relies only on a small number of discrete pressure measurements along the combustion tube. The proposed methods are applied in numerical simulations to demonstrate their effectiveness. In a one-dimensional simulator, the flow field in the tube is described by the one-dimensional Euler equations with chemical source terms. To keep the computational effort on a manageable level, the Kalman Filter is built based on a reduced model. Thus, the model reduction for the Euler equations in combination with chemical kinetics is another focus of this contribution.
      PubDate: 2017-06-01
      DOI: 10.1007/s13272-016-0229-9
      Issue No: Vol. 8, No. 2 (2017)
  • Reduction of dynamic stall using a back-flow flap
    • Authors: A. D. Gardner; S. Opitz; C. C. Wolf; C. B. Merz
      Pages: 271 - 286
      Abstract: A back-flow flap attached to the suction side of an airfoil is investigated in both passively and actively actuated modes for the control of dynamic stall. This method of dynamic stall control has low power requirements and no parasitic drag when not actuated. Experiments in a low-speed wind tunnel at 50 m/s were used to characterize the reduction in dynamic stall hysteresis using pressure measurements on the midline airfoil section. It was found that the pitching moment peak is reduced by an average of 25% for all deep stall test cases for active actuation of the flap, while for passive actuation the pitching moment peak is reduced by 19%. In each case the maximum lift remained the same, while the peak drag increased by an average of 2.5% for the active flap, and by 0.9% for the passive flap. With the flap closed at low angles of attack, the reference values of the airfoil are retained.
      PubDate: 2017-06-01
      DOI: 10.1007/s13272-017-0237-4
      Issue No: Vol. 8, No. 2 (2017)
  • Experimental aerodynamic assessment and evaluation of an agile highly
           swept aircraft configuration
    • Authors: Kerstin C. Huber; Andreas Schütte; Martin Rein; Thomas Löser
      Pages: 17 - 29
      Abstract: Extensive experimental and numerical investigations on a highly swept generic unmanned combat aerial vehicle (UCAV) configuration of lambda type with a variable leading edge contour have been conducted. Within these investigations, it was shown that the flow field is dominated by complex vortex systems including vortex-to-vortex and vortex-to-boundary layer interactions. The vortex-dominated flow field has a strong nonlinear influence on the aerodynamic behavior of the configuration. Hence, controllability is demanding and poses a real challenge in the design of these kinds of configurations. Especially, the dimensioning of the control surfaces, for the lateral- and longitudinal stability of tailless configurations of low aspect ratio and high leading-edge sweep, poses a challenging task which is not yet solved. To understand the problem of lacking lateral- and longitudinal stability for these kinds of configurations, experiments in the subsonic and transonic flow regime have been conducted for the Stability and Control Configuration (SACCON), which has a leading edge sweep of 53°, to assess the control surface effectiveness of conventional trailing-edge control devices. The present study reviews the experimental investigations conducted with the highly swept generic UCAV configuration SACCON.
      PubDate: 2017-03-01
      DOI: 10.1007/s13272-016-0219-y
      Issue No: Vol. 8, No. 1 (2017)
  • Adaptive internal model control research in autonomous landing phase for a
           fixed-wing UAV
    • Authors: Jiu-zhou Gao; Hong-guang Jia
      Pages: 45 - 51
      Abstract: Autonomous landing is a very complex phase of flight for unmanned aerial vehicle (UAV). Adaptive internal model control (AIMC) is proposed and applied on autonomous landing control system in this paper. Controllers are designed based on the decoupled and linearized models of a sample UAV. Estimation of process model is carried out to enhance system robustness, and filter parameter adjustment is proposed to achieve a good dynamic performance. Control effects are compared and analyzed between IMC and AIMC in different wind conditions which demonstrate that AIMC has better performances than IMC. At last, Monte Carlo simulations prove the system stability.
      PubDate: 2017-03-01
      DOI: 10.1007/s13272-016-0216-1
      Issue No: Vol. 8, No. 1 (2017)
  • Numerical and experimental investigations of the propeller characteristics
           of an electrically powered ultralight aircraft
    • Authors: M. Stuhlpfarrer; A. Valero-Andreu; C. Breitsamter
      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: 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: 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: 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
  • Impact of turbulence and degraded visual environment on pilot workload
    • Authors: Paul H. Lehmann; Michael Jones; Marc Höfinger
      Abstract: Offshore helicopter operations are frequently conducted in both turbulent and degraded visual environments (DVE). This investigation assesses the combined influence of turbulence and DVEs on pilot workload to identify first limits for safe operations. Flight tests using a simulation model of the research helicopter ACT/FHS (active control technology/flying helicopter simulator) flight mechanics model were conducted in the air vehicle simulator (AVES) at DLR Braunschweig. Tests were completed using four pilots, and results show the effects on pilot workload, task performance and control input activity. It was found that DVE and turbulence increase the workload and reduce task performance, but each in a different manner. Furthermore, the impact on control activity and pilot-induced oscillation tendencies are shown to have dependency upon the environmental conditions.
      PubDate: 2017-06-01
      DOI: 10.1007/s13272-017-0246-3
  • Component-wise vibration analysis of stiffened plates accounting for
           stiffener modes
    • Authors: Tommaso Cavallo; Enrico Zappino; Erasmo Carrera
      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: 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: 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
  • Design of an automatic load positioning system for hoist operations
    • Authors: Hyun-Min Kim
      Abstract: The operation of a helicopter with an externally slung load is highly demanding for the flight crew. Without having a direct view on the load, the pilot needs assistance by a crew member for load handling, e.g., load positioning. During helicopter hoist operations (HHO), the hoist operator gives instructions to the pilot and stabilizes the load motion. An automatic load positioning system for HHO is designed with the aim to reduce the workload of the flight crew and to improve the load handling performance. The control system consists of a multiloop architecture that is designed using multi-objective optimization. The system was designed to achieve best performance in load positioning for the entire cable length range of the rescue hoist. Load positioning performance is a function of the cable length; faster automatic load positioning can be achieved with the shorter cable lengths. This paper describes the overall design process covering the tools, the control law architecture and optimization, and the validation using DLR’s simulator.
      PubDate: 2017-03-23
      DOI: 10.1007/s13272-017-0241-8
  • In-flight remote sensing and identification of gusts, turbulence, and wake
           vortices using a Doppler LIDAR
    • Authors: N. Fezans; J. Schwithal; D. Fischenberg
      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: 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: 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
  • Thanks to our Reviewers
    • PubDate: 2017-01-31
      DOI: 10.1007/s13272-017-0236-5
  • Fan casing contouring under consideration of aeroacoustics, mechanics,
           aeroelasticity, and whole engine performance
    • Authors: A.-L. Aulich; T. Sauer; S. Iseni; A. Moreau; D. Peitsch; R. Mailach; D. Micallef; L. Enghardt; E. Nicke
      Abstract: Aircraft propulsion will continue to rely on gas turbine technology for the next decades to come. Thus, to achieve environmental agreements, ensure engine safety, and retain economic competitiveness, ongoing development with a multidisciplinary design approach is indispensable. In the present study, the multi-criteria analysis of the fan, a decisive component in modern aero engines, is examined. In particular, the interaction of the fan blades with the fan casing is analyzed and an appropriate design approach, including automatic optimization, is used. As one part of the disciplines conjunction, an automated aeroacoustic approach is realized. The aerodynamic and acoustic fitness functions and constraints are based on Reynolds-Averaged Navier–Stokes (RANS) simulations of the fan stage. PropNoise, a fast analytical prediction tool for fan noise, is used. It has been under development since recent years and is already validated on several test cases. Preliminary studies have shown that the flow in the rotor tip region is a major contributor to the broadband noise emission. Based on this, the optimization process focuses on the variation of the casing contour around the fan blades. The impact of the modified flow field in the rotor tip region concerning the aeroelastic behavior is also investigated. As aeroelastic evaluation requires a high level of know-how and is very time consuming, it is linked to the optimization process chain by a discrete evaluation of selected members. This allows a simultaneous adjustment of the design in case of aeroelastic issues. Furthermore, the impact of the fan modifications regarding the overall engine performance is evaluated. Off-design cycle calculations allow incorporating such detailed studies in a global engine optimization.
      PubDate: 2016-12-08
      DOI: 10.1007/s13272-016-0226-z
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