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  Subjects -> AERONAUTICS AND SPACE FLIGHT (Total: 86 journals)
Acta Astronautica     Hybrid Journal   (Followers: 269)
Advances in Space Research     Full-text available via subscription   (Followers: 284)
Aeronautica     Open Access   (Followers: 4)
Aerospace     Open Access   (Followers: 3)
Aerospace and Electronic Systems, IEEE Transactions on     Hybrid Journal   (Followers: 50)
Aerospace Science and Technology     Hybrid Journal   (Followers: 299)
Affective Computing, IEEE Transactions on     Hybrid Journal   (Followers: 6)
AIAA Journal     Full-text available via subscription   (Followers: 457)
Air Force Magazine     Full-text available via subscription   (Followers: 3)
Air Medical Journal     Hybrid Journal   (Followers: 2)
Aircraft Engineering and Aerospace Technology     Hybrid Journal   (Followers: 116)
American Journal of Space Science     Open Access   (Followers: 32)
Artificial Satellites     Open Access   (Followers: 13)
Aviation     Hybrid Journal   (Followers: 3)
Aviation in Focus - Journal of Aeronautical Sciences     Open Access   (Followers: 1)
Aviation Psychology and Applied Human Factors     Hybrid Journal   (Followers: 5)
Aviation Week     Full-text available via subscription   (Followers: 8)
Aviation, Space, and Environmental Medicine     Full-text available via subscription   (Followers: 5)
Canadian Aeronautics and Space Journal     Full-text available via subscription   (Followers: 12)
CEAS Aeronautical Journal     Hybrid Journal   (Followers: 20)
Chinese Journal of Aeronautics     Open Access   (Followers: 10)
Control Systems     Hybrid Journal   (Followers: 18)
Cosmic Research     Hybrid Journal   (Followers: 2)
COSPAR Colloquia Series     Full-text available via subscription  
Egyptian Journal of Remote Sensing and Space Science     Open Access   (Followers: 4)
Elsevier Astrodynamics Series     Full-text available via subscription   (Followers: 1)
Fatigue of Aircraft Structures     Open Access   (Followers: 4)
Frontiers in Aerospace Engineering     Open Access   (Followers: 3)
Gyroscopy and Navigation     Hybrid Journal   (Followers: 10)
IEEE Aerospace and Electronic Systems Magazine     Full-text available via subscription   (Followers: 33)
IEEE Transactions on Circuits and Systems I: Regular Papers     Hybrid Journal   (Followers: 9)
International Journal of Aeroacoustics     Full-text available via subscription   (Followers: 6)
International Journal of Aerodynamics     Hybrid Journal   (Followers: 11)
International Journal of Aerospace Engineering     Open Access   (Followers: 38)
International Journal of Aerospace Innovations     Full-text available via subscription   (Followers: 10)
International Journal of Applied Geospatial Research     Full-text available via subscription   (Followers: 4)
International Journal of Aviation Management     Hybrid Journal  
International Journal of Aviation Psychology     Hybrid Journal   (Followers: 4)
International Journal of Aviation Technology, Engineering and Management     Full-text available via subscription  
International Journal of Crashworthiness     Hybrid Journal   (Followers: 5)
International Journal of Flow Control     Full-text available via subscription   (Followers: 2)
International Journal of Hypersonics     Full-text available via subscription   (Followers: 3)
International Journal of Micro Air Vehicles     Full-text available via subscription   (Followers: 3)
International Journal of Satellite Communications Policy and Management     Hybrid Journal  
International Journal of Space Science and Engineering     Hybrid Journal   (Followers: 2)
International Journal of Space Structures     Full-text available via subscription   (Followers: 2)
International Journal of Sustainable Aviation     Hybrid Journal  
International Journal of Turbo & Jet-Engines     Full-text available via subscription  
ISRN Astronomy and Astrophysics     Open Access   (Followers: 11)
Journal of Aerospace Computing, Information, and Communication     Full-text available via subscription   (Followers: 12)
Journal of Aerospace Engineering     Full-text available via subscription   (Followers: 112)
Journal of Aerospace Engineering & Technology     Full-text available via subscription  
Journal of Aerospace Operations     Hybrid Journal   (Followers: 3)
Journal of Aerospace Technology and Management     Open Access   (Followers: 1)
Journal of Aircraft     Full-text available via subscription   (Followers: 256)
Journal of Airline and Airport Management     Open Access   (Followers: 2)
Journal of Aviation Technology and Engineering     Open Access   (Followers: 6)
Journal of Guidance, Control, and Dynamics     Full-text available via subscription   (Followers: 49)
Journal of Konbin     Open Access  
Journal of Navigation     Hybrid Journal   (Followers: 18)
Journal of Propulsion and Power     Full-text available via subscription   (Followers: 206)
Journal of Space Weather and Space Climate     Open Access   (Followers: 3)
Journal of Spacecraft and Rockets     Full-text available via subscription   (Followers: 306)
Journal of Spatial Science     Hybrid Journal   (Followers: 1)
Journal of the American Helicopter Society     Full-text available via subscription   (Followers: 1)
Journal of the Astronautical Sciences     Hybrid Journal  
Microgravity Science and Technology     Hybrid Journal  
New Space     Hybrid Journal   (Followers: 2)
Nonlinear Dynamics     Hybrid Journal   (Followers: 5)
Population Space and Place     Hybrid Journal   (Followers: 2)
Proceedings of the Human Factors and Ergonomics Society Annual Meeting     Hybrid Journal  
Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering     Hybrid Journal   (Followers: 19)
Progress in Aerospace Sciences     Full-text available via subscription   (Followers: 43)
Propulsion and Power Research     Open Access   (Followers: 1)
Recent Patents on Space Technology     Full-text available via subscription  
Russian Aeronautics (Iz VUZ)     Hybrid Journal   (Followers: 12)
Space and Polity     Hybrid Journal   (Followers: 2)
Space Communications     Hybrid Journal   (Followers: 2)
Space Policy     Hybrid Journal   (Followers: 15)
Space Research Today     Full-text available via subscription   (Followers: 24)
Space Safety Magazine     Free   (Followers: 3)
Space Science Reviews     Hybrid Journal   (Followers: 9)
SpaceNews     Free   (Followers: 199)
Transportmetrica A : Transport Science     Hybrid Journal   (Followers: 1)
Вісник Національного Авіаційного Університету     Open Access   (Followers: 2)
Вестник УГАТУ     Open Access  
Journal Cover CEAS Aeronautical Journal
   [22 followers]  Follow    
   Hybrid Journal Hybrid journal (It can contain Open Access articles)
     ISSN (Print) 1869-5582
     Published by Springer-Verlag Homepage  [2208 journals]
  • Comparison of real-time flight loads estimation methods
    • Abstract: Abstract Nowadays flight load exceedance monitoring is an important task to both: the aircraft manufacturer as well as the operator. The estimation of flight loads is required in several phases during development and operation of an aircraft. The requirements are usually different, for e.g. calculation of design loads for certification and operational loads monitoring of stress and fatigue. The ability to determine aircraft operational loads (more) precisely may reduce the time in maintenance. Being able to detect critical load exceedance events during flight or in a post-process is also an enabler for e.g. loads/fatigue monitoring at operator level. In this paper, a novel system identification method named local model networks is applied to the field of flight loads estimation and compared to approaches based on artificial neural networks as found in the literature. The presented approach tries to overcome some limitations with respect to model creation, robustness, inter- and extrapolation.
      PubDate: 2014-07-24
       
  • Model order reduction for steady aerodynamics of high-lift configurations
    • Abstract: Abstract In aerodynamic applications, many model reduction methods use proper orthogonal decomposition (POD). In this work, a POD-based method, called missing point estimation (MPE), is modified and applied to steady-state flows with variation of the angle of attack. The main idea of MPE is to select a subset of the computational grid points (control volumes) and to limit the governing equations to this subset. Subsequently, the limited equations are projected onto the POD subspace. This approach has the advantage that the nonlinear right-hand side of the governing equations has to be evaluated only for a small number of points (control volumes) in contrast to POD, for which the full right-hand side has to be evaluated. An error estimation for MPE in the continuous ODE setting is tackled. Numerical results are presented for the Navier–Stokes equations for two different industrially relevant, two-element high-lift airfoils, one which is normally adopted during landing and the other during take-off.
      PubDate: 2014-07-23
       
  • Development of a wind tunnel experiment for vortex dominated flow at a
           pitching Lambda wing
    • Abstract: Abstract A half wing model, a test rig and new wind tunnel walls were designed to study the vortex development at a lambda wing. The model has a sweep angle of 53° and a round leading edge. It is designed for pitching oscillations around a mean angle of attack of up to 20° up to a free stream Mach number of 0.7. Unsteady aerodynamic load data shall be delivered for aeroelastic simulations of Unmanned Combat Aerial Vehicles. Due to the highly nonlinear aerodynamic character, the design and sizing of the model had to take into account load cases with beginning and fully developed vortices. Furthermore, the different characters at subsonic and transonic speeds had to be included. Coupled simulations with a finite element model including the mounting and the connection to the actuation system were performed to assess the stability and the dynamic response of the model. Furthermore, the test concept and the process of the design of the model will be described.
      PubDate: 2014-07-19
       
  • Revised approach procedures to support optimal descents into Malta
           International Airport
    • Abstract: Abstract This paper presents a proposal for new approach procedures for the most commonly used runways at Malta International Airport, runways 31 and 13, as a basis to facilitate the introduction of optimal descents in Maltese airspace. In addition, a standard arrival, one from the north from where the large majority of aircraft approach Malta, linking to runway 31 is proposed. The design, following ICAO recommendations, is described in detail. Current practice of aircraft inbound from the same entry point, observed using ADS-B recorded data, is also presented in a discussion leading to the identification of gains that could result from flying the proposed arrival and approach routes optimally.
      PubDate: 2014-07-18
       
  • Vortical flow prediction for the design of a wind tunnel experiment with a
           pitching lambda wing
    • Abstract: Abstract The IWEX wind tunnel model (Instationäres Wirbelexperiment, German for: Unsteady Vortex Experiment) was developed to study vortical flow at static and oscillating angles of attack. Numerical computations were performed beforehand to study important aerodynamic aspects. The focus of this paper is on those results that were affecting the design of the model. The experimental concept of a new test rig, wind tunnel walls and the new half wing model is briefly described. The lambda wing has a purely round leading edge with a constant nose radius to chord ratio of 0.5 %. The flow characteristics of the main vortex, generated at the nose of the main wing, and the smaller tip vortex are specified. The inboard motion of the main vortex with increasing angle of attack and the consequences for the load distribution are described. The free stream Mach number range of the test envelope is from 0.3 to 0.7. Therefore, transonic effects, especially shock–vortex interactions triggering vortex development, had to be analyzed for a safe design of the model. A peniche was designed to minimize the differences of the flow character compared to reference results of the model without wind tunnel walls. The effects of corner separation and displacement are specified at different stages of the iterative process. Finally, basic results for a pitching motion are discussed, based on global and distributed coefficients.
      PubDate: 2014-07-11
       
  • Correction of aerodynamic influence matrices for transonic flow
    • Abstract: Abstract The authors present a novel correction approach for the doublet-lattice method in this paper. The doublet-lattice method is a standard tool for calculating unsteady aerodynamic loads in aeroelasticity. It solves the linear potential equations and is thus valid only at subsonic flow conditions. Hence, corrections have to be applied for transonic flow. The proposed correction method, CREAM (CorREction of Aerodynamic Matrices), uses surface pressure distributions obtained using computational fluid dynamics (CFD) simulations for the correction. It is based on a Taylor expansion of the aerodynamic influence coefficient matrix, where the Taylor coefficients are corrected successively. The approach can be applied to quasi-steady as well as to unsteady aerodynamic calculations. The method is demonstrated on the AGARD LANN wing at transonic attached flow conditions and compared to linearized unsteady CFD computations. Two different correction orders are examined: a “zeroth order correction” with a quasi-steady CFD sample as correction input and a “first order correction” with an additional unsteady CFD sample. It is shown that CREAM gives improved results for small reduced frequencies, where the first-order correction is always superior to the zeroth order correction.
      PubDate: 2014-06-22
       
  • Design and aeroelastic assessment of a forward-swept wing aircraft
    • Abstract: Abstract Aeroelastic effects strongly influence the design of an aircraft. To be able to assess those effects early on, reliable simulation models representing the global aeroelastic properties of a new design are required. At a conceptual or a pre-design stage, an intelligent parameterization concept allows for limited changes of the configuration while the simulation models are adapted accordingly. In the DLR project Integrated Green Aircraft, the goal was to investigate the impact of technologies for the reduction of fuel consumption on the aeroelastic properties of aircraft. One main aspect was the influence of laminar wing design on divergence, flutter and dynamic loads. As the reference aircraft in the project, the concept of a forward-swept wing aircraft with rear-mounted engines has been analysed. An aeroelastic model has been built up in the project. The model design procedure is based on the DLR in-house tool set MONA (ModGen/NASTRAN). Focus of this design process is the generation of a parameterized structural model, representing the global dynamic properties of the elastic aircraft, but as detailed as reasonable to capture relevant local effects and to result in a feasible structural design. In the article, the aircraft design is presented. The modelling and sizing process for the structure is described. Results of the loads analysis as well as of the aeroelastic stability analyses are discussed.
      PubDate: 2014-06-21
       
  • SFB 880: aeroacoustic research for low noise take-off and landing
    • Abstract: Abstract This paper gives an overview about prediction capabilities and the development of noise reduction technologies appropriate to reduce high lift noise and propeller noise radiation for future low noise transport aircraft with short take-off and landing capabilities. The work is embedded in the collaborative research centre SFB 880 in Braunschweig, Germany. Results are presented from all the acoustics related projects of SFB 880 which cover the aeroacoustic simulation of the effect of flow permeable materials, the characterization, development, manufacturing and operation of (porous) materials especially tailored to aeroacoustics, new propeller arrangements for minimum exterior noise due to acoustic shielding as well as the prediction of vibration excitation of aircraft structures, reduced by porous materials.
      PubDate: 2014-06-19
       
  • Enhancement of aircraft wake vortex decay in ground proximity
    • Abstract: Abstract Aircraft wake vortex evolution in ground proximity is investigated experimentally in a water towing tank, as well as numerically with wall-resolved large eddy simulation (LES). With these complementary instruments the enhancement of wake vortex decay by obstacles, introduced at the ground surface, is analyzed. The experimental methods include time-resolved stereo particle image velocimetry and vortex core visualization. For comparison with the experiment, the LES considers the turbulent wake of the strut, holding the towed aircraft model. Wake vortex trajectories and circulation decay are compared at different distances from the obstacle. Tracers are employed to visualize the obstacle’s effects on the vortex core, in LES and experiment. The experimentally obtained trajectories and decay characteristics are reproduced qualitatively by simulations, whereas the agreement is degraded at later times. Beyond that, the vortex dynamics, deduced from the LES results, help to understand the experimental observations. The obstacles trigger helical secondary vortex structures, propagating along the primary vortices. The observed propagation speed of the helical disturbance is fairly well predicted by the suggested simple model. It is shown that the obstacles significantly modify the vortex interaction with the ground and substantially accelerate vortex decay. Two neighboring obstacles lead to colliding disturbances that further enhance vortex decay rates.
      PubDate: 2014-06-01
       
  • A reduced-order model for the investigation of the aeroelasticity of
           circulation-controlled wings
    • Abstract: Abstract The application of active circulation control allows shortening of runways which can be significant in particular cases. The goal of the present paper is to study the influence of the circulation control on the aeroelastic behaviour of wings. For numerical analyses, a simplified computational model is presented, which allows for systematic parameter variations. The model is based on model reduction using modal analysis, so that an efficient performance of numerical studies is possible as well as the integration of the aeroelasticity into a flight dynamics model.
      PubDate: 2014-06-01
       
  • System architecture of HALAS—a helicopter slung load stabilisation
           and positioning system
    • Abstract: Abstract To support helicopter pilots during slung load operations currently a pilot assistance system called Hubschrauber-Außenlast-Assistenzsystem (HALAS) is being developed within a cooperation of the German Aerospace Centre (DLR) and iMAR Navigation GmbH. The objective of this research is the demonstration of an automatic slung load stabilisation and positioning system during the flight test with DLR’s research helicopter Active Control Technology/Flying Helicopter Simulator (ACT/FHS). The automatic slung load control system is being designed to extend the functionalities of the helicopter’s stability, control and augmentation system. The control system will be able to handle the challenges of rescue hoist operations. This means compensation of additional roll, pitch and yaw moments created by a significant distance of the load suspension point to the helicopter’s centre of gravity and the handling of a variable cable length. To measure the slung load motion, an optical-inertial sensor is being developed by iMAR Navigation GmbH. In this paper, the overall system architecture of HALAS as well as the hardware integration into the ACT/FHS is explained. The optical-inertial sensor used for the slung load dynamics measurement and estimation is described in detail. Furthermore, a first system analysis of a simulation model used for the later controller design is presented. The focus of the stability analysis is laid on variations of cable length, load mass and load suspension point position. The control law development process itself is not part of this paper but will be published later.
      PubDate: 2014-06-01
       
  • Semi-empirical modeling of fuselage–rotor interference for
           comprehensive codes: the fundamental model
    • Abstract: Abstract The flow field around the isolated HART II fuselage is computed by a computational fluid dynamics code. Velocities normal to the rotor rotational plane are extracted in a volume around the rotor as a data basis. A simple semi-empirical analytical formulation of the fuselage-induced velocities, based on parameter identification from computational fluid dynamics or measured data, is developed for use in comprehensive rotor codes. This model allows the computation of fuselage–rotor interferences on the rotor blade element level. It also allows the prediction of the rotor wake geometry deformation due to the presence of the fuselage in both prescribed wake and free-wake codes. Its impact on rotor thrust, power and trim is evaluated analytically using blade element momentum theory and by DLR’s comprehensive rotor code.
      PubDate: 2014-05-30
       
  • Assessment of leading-edge devices for stall delay on an airfoil with
           active circulation control
    • Abstract: Abstract The use of active, internally blown high-lift flaps causes the reduction of the stall angle of attack, because of the strong suction peak generated at the leading-edge. This problem is usually addressed by employing movable leading-edge devices, which improve the pressure distribution, increase the stall angle of attack, and also enhance the maximum lift coefficient. Classical leading-edge devices are the hinged droop nose or the more effective slat with a gap. The flow distortions generated by the gap become an important source of noise during approach and landing phases. Based on these considerations, the present work aims at evaluating the potentials of gap-less droop nose devices designed for improving the aerodynamics of airfoils with active high lift. Both conventional leading-edge flaps and flexible droop noses are investigated. Flexible droop nose configurations are obtained by smoothly morphing the baseline leading-edge shape. Increasing the stall angle of attack and reducing the power required by the active high-lift system are the main objectives. The sensitivities of the investigated geometries are described, as well as the physical phenomena that rule the aerodynamic performance. The most promising droop nose configurations are compared with a conventional slat device as well as with the clean leading-edge. The response of the different configurations to different blowing rates and angles of attack are compared and the stalling mechanisms are analyzed.
      PubDate: 2014-05-27
       
  • Data parser approaches for (online) parameter estimation
    • Abstract: Abstract Finding maneuvers for parameter estimation in flight data records is a laborious task and traditionally performed post-flight on ground. Two different data parser approaches to automatically detect these maneuvers in flight are presented. Both methods search the control input signals for significant changes that correspond to test maneuvers. The first algorithm is based on the signal time derivative of the input signal whereas the second method uses a fast orthogonal wavelet transform. Both algorithms are tested with flight test data recorded with the DLR research aircraft ATTAS. Performance results are compared and potential problems when applying the parsers to other data are discussed. Results indicate that both methods are applicable in an online parameter estimation tool. The intention of the work in this paper is to develop an algorithm with a high level of automation for in-flight use, but both approaches could also be applied to offline flight data mining problems.
      PubDate: 2014-05-17
       
  • Conceptual aircraft design with hybrid laminar flow control
    • Abstract: Abstract This paper describes a methodology for conceptual design and optimization of aircraft with hybrid laminar flow control (HLFC) systems integrated into wing and tails. An existing conceptual aircraft design platform is enhanced by the necessary methods for sizing of HLFC system architecture and prediction of aerodynamic drag polars. These include transonic drag characteristics as well as transition prediction by analysing boundary layer instability mechanisms. The implemented methods are described and its sensitivities against relevant aircraft design parameters are discussed. The integrated sizing methodology allows to assess the net benefit of HLFC system integration on overall aircraft level and to minimize aircraft fuel consumption by variation of aircraft design parameters, cruise conditions and HLFC system parameters. To demonstrate the applicability of the developed methodology in conceptual aircraft design it is used for design and assessment of an HLFC long-range passenger aircraft. The influence of the HLFC main drivers Mach number and wing sweep angle on aerodynamics, systems and aircraft design characteristics is investigated. Further, aircraft component resizing is analysed to further exploit the fuel reduction potential of the HLFC technology.
      PubDate: 2014-05-15
       
  • Comparative assessment of transient characteristics of conventional and
           hybrid gas turbine engine
    • Abstract: Abstract Reduction of CO2 emission of future aircraft is the main objective of agreements like Flightpath 2050 from the European Commission and the Vision 2020 from the ACARE. For achieving these emission reduction goals, hybrid propulsion systems are considered as a meantime solution on the way to universally electric propulsion systems and are hence the subject of numerous investigations. These studies, however, almost exclusively focus on steady-state behaviour and energy analysis and leave out the benefit on transient performance that comes from hybridisation. To assess the benefit of the hybridisation on a gas turbine engine, multiple simulations of conventional engines and their hybrid versions are performed with a Matlab Simulink® model and the results are compared with time response diagrams and commonly used metrics. It could be shown that the acceleration time of a hybrid gas turbine engine can be reduced by half compared when the shaft power share of the electric motor is 25 %. Furthermore, the study shows that the primary benefit of the hybridisation comes from the larger torque range of the electric motor compared to the turbine.
      PubDate: 2014-02-27
       
  • Development of a tunnel-in-the-sky display for helicopter noise abatement
           procedures
    • Abstract: Abstract Research on helicopter noise abatement at DLR has led to the development of a pilot assistant display for following prescribed noise-optimised landing procedures. An intuitive tunnel-in-the-sky display was chosen in order to reduce pilot workload during complex manoeuvres. The tunnel representation allows the pilot to anticipate the coming flight path. This has led to improvements in flight path accuracy compared to flights with a standard primary flight display with target indicators only. Trajectory generation is performed partly during flight which allows the update of the displayed trajectory relative to the current helicopter position. After selecting the desired noise abatement procedure, landing place and approach direction, a transition trajectory is generated that leads the pilot to the entrance point of the actual procedure. Performance of the tunnel-in-the-sky display has successfully been demonstrated during ground-based simulator tests with two pilots and in first airborne test flights. The display will be used for upcoming flight test campaigns with DLR’s research helicopter ACT/FHS.
      PubDate: 2014-02-26
       
  • Experimental investigation of high-pressure pulsed blowing for dynamic
           stall control
    • Abstract: Abstract Dynamic stall control using pulsed blowing is compared with control by constant blowing for an OA209 airfoil. Flow control was by blowing from 42 portholes, flush with the airfoil surface, of diameter 1 % chord positioned at 10 % chord and with separation 6.7 % chord. Light stall at Mach 0.3 could be fully suppressed by constant blowing, and for deep stall a pitching moment peak reduction of 65% was seen. For the jet configuration and test cases investigated in this paper, pulsed blowing at 100–500 Hz was found to be at best as effective as constant blowing with the same mass flux for the control of dynamic stall.
      PubDate: 2014-02-20
       
  • Numerical and experimental investigation of an impeller tip clearance
           variation in an aero-engine centrifugal compressor with close-coupled
           pipe-diffuser
    • Abstract: Abstract The subject of this paper is the experimental and numerical investigation of the influence of impeller tip clearance on the aerodynamics of a high-pressure transonic centrifugal compressor used in an aero-engine application. The overall change in aerodynamic performance of the stage, the isolated impeller and the isolated diffuser is analyzed. Local flow phenomena, responsible for the change in performance, are examined in closer detail. Experimental data from a state-of-the-art test rig, containing detailed 2D particle-image-velocimetry measurements, are used. 3D Reynolds-averaged Navier–Stokes simulations are conducted with the CFD solver turbo-machinery research aerodynamics computational environment to get a detailed insight into the flow field. This study contributes towards a better understanding of the principal flow phenomena of a centrifugal compressor with a close-coupled pipe-diffuser and the additional losses introduced in the individual compressor components by an increased impeller tip clearance.
      PubDate: 2014-02-12
       
  • Optimum number of engines for transport aircraft employing electrically
           powered distributed propulsion
    • Abstract: Abstract Realizing a significant reduction of enroute emissions with respect to greenhouse gases is one major challenge in aircraft design today. Conventional kerosene propulsion systems are going to reach their efficiency limits in near future and it will be very ambitious to fulfill the requirements for future aircraft transportation using conventional engines. Consequently, new approaches for propulsion system design and integration are required to further improve aircraft efficiency through synergy effects. In this paper, a universally electric, short-haul, medium-capacity aircraft utilizing electric motors and battery for motive power is used as datum. The focus lies on the impact of a distributed propulsion system on the aircraft design and flight performance and will not discuss the advantages and disadvantages of the used reference aircraft configuration. Initial studies were performed identifying that the critical design cases for electric motor sizing are the one-engine-inoperative (OEI) flight segments, i.e., the climb gradients required at take-off and landing as well as field length requirements. By increasing the number of installed engines (i.e., motor–fan combinations) the OEI performance requirements may be satisfied with a reduced amount of installed motor and battery system power. An integrated aircraft performance analysis is conducted to estimate the possible net benefit in terms of increased aircraft range when increasing the number of installed engines. Aerodynamic efficiency degradation is considered as well as weight impacts due to electric motor scaling and necessary system architecture modifications. The analysis shows that a 6 % increase in aircraft design range can be achieved when going from 2 to 4 installed propulsive devices.
      PubDate: 2014-01-15
       
 
 
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