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 Subjects -> AERONAUTICS AND SPACE FLIGHT (Total: 98 journals)
 Acta Astronautica       (Followers: 275) Advances in Aerospace Engineering       (Followers: 5) Advances in Space Research       (Followers: 272) Aeronautica       (Followers: 7) Aerospace       (Followers: 12) Aerospace and Electronic Systems, IEEE Transactions on       (Followers: 130) Aerospace Science and Technology       (Followers: 313) Affective Computing, IEEE Transactions on       (Followers: 10) AIAA Journal       (Followers: 543) Air Force Magazine       (Followers: 4) Air Medical Journal       (Followers: 3) Aircraft Engineering and Aerospace Technology       (Followers: 143) American Journal of Space Science       (Followers: 38) Annual of Navigation       (Followers: 2) Artificial Satellites       (Followers: 14) ASTRA Proceedings Aviation       (Followers: 7) Aviation in Focus - Journal of Aeronautical Sciences       (Followers: 5) Aviation Psychology and Applied Human Factors       (Followers: 12) Aviation Week       (Followers: 22) Aviation, Space, and Environmental Medicine       (Followers: 6) Canadian Aeronautics and Space Journal       (Followers: 22) CEAS Aeronautical Journal       (Followers: 24) Chinese Journal of Aeronautics       (Followers: 14) Control Systems       (Followers: 30) Cosmic Research       (Followers: 2) COSPAR Colloquia Series       (Followers: 1) Egyptian Journal of Remote Sensing and Space Science       (Followers: 5) Elsevier Astrodynamics Series       (Followers: 1) Fatigue of Aircraft Structures       (Followers: 7) Frontiers in Aerospace Engineering       (Followers: 6) Frontiers in Astronomy and Space Sciences Gyroscopy and Navigation       (Followers: 142) IEEE Aerospace and Electronic Systems Magazine       (Followers: 46) IEEE Transactions on Circuits and Systems I: Regular Papers       (Followers: 12) International Journal of Aeroacoustics       (Followers: 23) International Journal of Aerodynamics       (Followers: 14) International Journal of Aerospace Engineering       (Followers: 45) International Journal of Aerospace Innovations       (Followers: 13) International Journal of Aerospace Sciences       (Followers: 17) International Journal of Applied Geospatial Research       (Followers: 4) International Journal of Aviation Management       (Followers: 4) International Journal of Aviation Psychology       (Followers: 12) International Journal of Aviation Technology, Engineering and Management       (Followers: 2) International Journal of Crashworthiness       (Followers: 7) International Journal of Flow Control       (Followers: 4) International Journal of Hypersonics       (Followers: 3) International Journal of Micro Air Vehicles       (Followers: 4) International Journal of Satellite Communications Policy and Management International Journal of Space Science and Engineering       (Followers: 2) International Journal of Space Structures       (Followers: 3) International Journal of Space Technology Management and Innovation       (Followers: 3) International Journal of Sustainable Aviation       (Followers: 1) International Journal of Turbo & Jet-Engines       (Followers: 1) Journal of Aerodynamics Journal of Aeronautical Materials       (Followers: 1) Journal of Aeronautics & Aerospace Engineering       (Followers: 3) Journal of Aerospace Engineering       (Followers: 56) Journal of Aerospace Engineering & Technology       (Followers: 1) Journal of Aerospace Information Systems       (Followers: 1) Journal of Aerospace Technology and Management       (Followers: 2) Journal of Aircraft       (Followers: 215) Journal of Airline and Airport Management       (Followers: 6) Journal of Astrobiology & Outreach Journal of Aviation Technology and Engineering       (Followers: 9) Journal of Guidance, Control, and Dynamics       (Followers: 125) Journal of Konbin Journal of Navigation       (Followers: 130) Journal of Propulsion and Power       (Followers: 204) Journal of Space Weather and Space Climate       (Followers: 4) Journal of Spacecraft and Rockets       (Followers: 309) Journal of Spatial Science       (Followers: 1) Journal of the American Helicopter Society       (Followers: 1) Journal of the Astronautical Sciences       (Followers: 2) Journal of Wind Engineering and Industrial Aerodynamics       (Followers: 6) Life Sciences in Space Research Microgravity Science and Technology New Space       (Followers: 2) Nonlinear Dynamics       (Followers: 5) Population Space and Place       (Followers: 2) Proceedings of the Human Factors and Ergonomics Society Annual Meeting       (Followers: 6) Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering       (Followers: 32) Progress in Aerospace Sciences       (Followers: 55) Propulsion and Power Research       (Followers: 4) Recent Patents on Space Technology Research & Reviews : Journal of Space Science & Technology       (Followers: 1) Russian Aeronautics (Iz VUZ)       (Followers: 20) Space and Polity       (Followers: 2) Space Policy       (Followers: 16) Space Research Today       (Followers: 29) Space Safety Magazine       (Followers: 4) Space Science Reviews       (Followers: 14) SpaceNews       (Followers: 209) Transport and Aerospace Engineering       (Followers: 1) Transportmetrica A : Transport Science       (Followers: 3) Unmanned Systems Вісник Національного Авіаційного Університету       (Followers: 1) Вестник УГАТУ
 CEAS Aeronautical Journal   [24 followers]  Follow         Hybrid journal (It can contain Open Access articles)    ISSN (Print) 1869-5582    Published by Springer-Verlag  [2276 journals]
• Central Reference Aircraft data System (CeRAS) for research community
• Abstract: Abstract This paper gives an overview and presents the results of the project CeRAS, which stands for “Central Reference Aircraft data System”. CeRAS is intended to serve as an open platform hosting reference aircraft data and methods that can be used by a research community in aeronautic research projects. The technical topics of the addressed user group lie in the field of overall aircraft design as well as technology integration and evaluation on aircraft level. To enable the communication within the research community the CeRAS homepage has been created (http://ceras.ilr.rwth-aachen.de/) and filled with a first short-range reference aircraft dataset. The research community can contribute to and communicate via the CeRAS homepage that is intended to serve as living “open source” platform. The first reference aircraft is called CSR-01 and has been designed with the ILR aircraft design platform MICADO. The aircraft design characteristics are presented and discussed within this paper. Furthermore, common standards for monetary assessment methodologies are presented that have already been established and agreed within the CeRAS research community.
PubDate: 2015-11-20

• A knowledge-based integrated aircraft conceptual design framework
• Abstract: Abstract The conceptual design is the early stage of aircraft design process where results are needed fast, both analytically and visually so that the design can be analyzed and eventually improved in the initial phases. Although there is no necessity for a CAD model from the very beginning of the design process, it can be an added advantage to have the model to get the impression and appearance. Furthermore, this means that a seamless transition into preliminary design is achieved since the CAD model can guardedly be made more detailed. For this purpose, knowledge-based aircraft conceptual design applications Tango (Matlab) and RAPID (CATIA) are being developed at Linköping University. Based on a parametric data definition in XML, this approach allows for a full 3D CAD integration. The one-database approach, also explored by many research organizations, enables the flexible and efficient integration of the different multidisciplinary processes during the whole conceptual design phase. This paper describes the knowledge-based design automated methodology of RAPID, data processing between RAPID and Tango and its application in the courses “Aircraft conceptual design” and “Aircraft project course” at Linköping University. A multifaceted user interface is developed to assist the whole design process.
PubDate: 2015-11-19

• Abstract: Abstract A command system for manual control of the longitudinal load factor in flight path direction of an aircraft is designed that completes existing flight control command systems (e.g. with sidesticks that command normal load factor). The system is called nxControl. It aims to assist pilots during manual flight by reducing the workload for monitoring flight parameters as well as for controlling thrust and airbrakes. Important for the nxControl concept is the direct flight mechanical relation between longitudinal load factor and changes of the total aircraft energy. This paper presents the system concept and a prototype realization. The nxControl system consists of the control law that combines the actuation commands for engines and airbrakes, a new input device for the longitudinal load factor command and augmented display elements informing pilots about aircraft energy states to assure situation awareness. In order to investigate the feasibility of the concept as well as to evaluate consequences on human performance, a flight simulator study with airline pilots was conducted. The nxControl prototype was used by the pilots as expected. Changes in instrument scanning behaviour and thrust lever usage confirmed this. After just a short familiarization and practice, the pilots were able to perform standard flight tasks with nxControl without exceeding given tolerance limits. So, the results provide first evidence for the feasibility of the concept.
PubDate: 2015-11-19

• About the interaction between composition and performance of alternative
jet fuels
• Abstract: Abstract Since the last decade, the aviation sector is looking for alternatives to kerosene derived from crude oil triggered also by commitments and policy packages, such as the ‘Flightpath 2050’ initiative and the comprehensive alternative fuels strategy, both released by the European Commission. An aircraft need with regard to a fuel is very strict, with severe constraints to ensure a safe and reliable operation for the whole flight envelope. When synthesizing a jet fuel from scratch, two important aspects need to be addressed: First, the safety aspect—the new fuel candidate must be certified, qualifying through several well-defined cost and time expensive tests, according to the approval protocol; secondly, the environmental aspect. Alternative aviation fuels alike Jet A-1 are composed of hydrocarbons; however, the amount and type of hydrocarbons (chemical family) differ considerably. The question is how the composition of the fuel will affect its suitability and performance: (i) thermo-physical and thermo-chemical properties of the new components to exclude any shortcomings with respect to performance and safety issues, and (ii) the new fuel combustion characteristics, i.e., ignition, flame speed, and emission pattern (pollutants), in particular. These issues are addressed in the present study. Thus, the road will be paved for developing a generalize science-based tool to investigate in an efficient way if a new fuel candidate may meet the fuel specifications.
PubDate: 2015-11-18

• Active flow control system integration into a CFRP flap
• Abstract: Abstract Investigations in the past show the considerable potential of active flow control (AFC) to enhance the aircraft aerodynamic performance. This publication describes the work carried out regarding the integration of an AFC system into a CFRP flap for Next Generation Aircraft considering operational aspects. Based on a two-stage fluidic AFC actuator, a system integration concept is developed. Robustness, simplicity and maintainability are the main drivers for the integration work. Using genetic and evolutionary multi-objective optimization the most promising flap concept regarding lightweight design and integration is developed at TU Dresden ILR. This concept is numerically sized and designed in detail. The concept feasibility is shown by a 2-m span full-scale demonstrator at Airbus Group Innovations. This demonstrator is successfully tested regarding system operational capability as well as for static and fatigue performance. To investigate the structural influence of AFC blowout slits within the upper flap surface, an extensive static and dynamic coupon test program is conducted at TU Dresden ILK and TU Braunschweig IFL. In parallel, analytic and numeric methods are used to verify stress concentration within the slotted area by TU Dresden ILR.
PubDate: 2015-11-14

• Propagation of localized, unsteady heat loads in aircraft cabin air flows
• Abstract: Abstract We studied experimentally the propagation of heat, released from a local source, in aircraft cabin air flow using two different ventilation systems. Besides the state-of-the-art mixing ventilation system, a ceiling-based cabin displacement ventilation system was employed. As test environment we used the Do 728 test facility of the German Aerospace Center in Göttingen. To measure the response of the cabin temperatures to the released heat, we evaluated the cross-correlation function between the local temperatures and the normalized surface temperature of the heat source. The latter was heated periodically at three different nominal heating powers, ranging from 100 W through 400 W. By analyzing the data, we could observe the gradual change of the temperature from a passive to an active scalar. While the two ventilation systems reveal a similar behavior at the lower source powers, the distinguished air-guiding principles of the momentum-driven mixing ventilation and the buoyancy-driven ceiling-based cabin displacement ventilation imply different propagation paths at higher power settings of the heat source. For the first time, the spatial spreading of locally released heat in mixing ventilation and in ceiling-based displacement ventilation was determined in an aircraft cabin.
PubDate: 2015-11-03

• Structural modeling and validation of an active twist model rotor blade
PubDate: 2015-11-02

• Prediction and uncertainty propagation of correlated time-varying
quantities using surrogate models
• Abstract: Abstract The identification of correlated quantities is of particular interest in several fields of engineering and physics, for example in the development of reliable structural designs. When ‘time-varying’ quantities are analysed, pairs of correlated interesting quantities (IQs), e.g. bending moments, torques, etc., can be displayed by plotting them against each other, and the critical conditions determined by the extreme values of the envelope (convex hull). In this paper, a reduced order singular value-based modelling technique is developed that enables a fast computation of the correlated loads envelope for systems where the effect of variation of design parameters needs to be considered. The approach is extended to efficiently quantify the effects of uncertainty in the system parameters. The effectiveness of the method is demonstrated by consideration of the gust loads occurring from the aeroelastic numerical model of a civil jet airliner.
PubDate: 2015-10-22

• Implementation of a simple and reliable human model to evaluate thermal
cabin comfort using CFD methods
• Abstract: Abstract The optimization of thermal comfort in buildings and passenger cabins has become one of the major aspects during the conception phase of HVAC systems. The static PMV model is among the most recognized thermal comfort models and depends besides the dry air temperature, radiant temperature, humidity and air velocity also on the activity level and the clothing of the human. The aim of this investigation is the application of a simple and reliable model of human metabolism based on Olesen combined with CFD simulations to attain a sufficiently accurate reflection of the human heat exchange to evaluate the PMV index and predict thermal comfort in a fast and cost-effective way by CFD simulations. Basis of the CFD model developed in the current investigations are measurement results obtained during experimental investigations inside a cabin mock-up model placed in a controlled climatic chamber under various pre-defined steady-state environmental conditions. The cabin mock-up model is equipped with a radial-flow fan for influencing convective flow inside the cabin and a temperature control system for adjusting the ceiling surface temperature to obtain mainly the impact of radiant temperature on the thermal comfort. Depending on the activity level, the local clothing and ambient conditions such as the flow structure inside the cabin, the local human heat flux due to convection and radiation is examined within a steady-state, two-way-coupled CFD simulation coupling human and environment with one continuous fluid phase (dry air) and the usage of the discrete transfer radiation model.
PubDate: 2015-10-06

• Analytic Rayleigh pressure loss model for high-swirl combustion in a
rotating combustion chamber
• Abstract: Abstract This paper considers the effect of excessive total pressure losses for heat transfer problems in fluid flows with a high circumferential swirl component. At the Institute of Jet Propulsion and Turbomachinery at RWTH Aachen University, a novel gas generator concept is under research. This design avoids some disadvantages of small gas turbines and uses a rotating combustion chamber. During the pre-design of the rotating combustion chamber using CFD tools, unexpected high total pressure losses were detected. To analyze this unknown phenomenon, a gas-dynamic model of the rotating combustion chamber has been developed to explain the unexpected high Rayleigh pressure losses. The derivation of the gas-dynamic model, the physical phenomenon related to the high total pressure losses in high-swirl combustion, the influencing factors, as well as thermodynamic interpretation of the Rayleigh pressure losses, are presented in this paper. The results presented here are of possible interest for a wide range of applications, since these fundamental findings can be transferred to all heat transfer problems in fluid flows with a high circumferential swirl component.
PubDate: 2015-10-05

• Impact of short- to medium-haul aircraft block time changes on airline
yields
• Abstract: Abstract According to various studies, significant reductions of mission fuel burn might be achieved by lowering cruise speeds using different aircraft technologies. The change of cruise speed will have an impact on aircraft operations, mainly on block times, airline networks and hence a possible impact on airline yields. Therefore, this paper describes the effect of changed block times on passenger demand and airline yields. The used methodology is based on the discrete choice theory and is applied to simulate passenger choice in airline networks using 2004 data from the US airline market. With a change of cruise speeds and corresponding block times, analyses showed an increase of average yields by +2 % with a decrease of block times by −10 %. With an increase of block times by +20 %, a decrease of average yields by −4 % was identified. Also non-linearities between changes of yields and load factors could be observed. Changes to yields are heavily depending on origin–destination (OD) characteristics and are mainly driven by available flight alternatives.
PubDate: 2015-09-22

• Flutter of circulation-controlled wings
• Abstract: Abstract The application of active circulation control gives rise to a substantial increase in lift compared to conventional wings. Initial studies of the aeroelastic behaviour of a circulation-controlled wing have shown additional instabilities due to the active circulation control. Besides the heave flutter phenomenon, further investigation also reveals a destabilising effect of the aerodynamic derivatives related to pitch, which is peculiar to circulation-controlled wings. The goal of the present paper is to investigate these phenomena in detail.
PubDate: 2015-09-20

• Experimental investigation of turbulent boundary layers over transversal
moving surfaces
• Abstract: Abstract The influence of a spanwise traveling transversal surface wave on the near-wall flow field of turbulent boundary layers is investigated by particle-image velocimetry (PIV) and micro-particle tracking velocimetry (μ-PTV). The experimental setup consists of a flat plate equipped with an insert to generate a transversal spanwise traveling wave of an aluminum surface. PIV and μ-PTV measurements are conducted for three Reynolds numbers based on the freestream velocity and momentum thickness immediately downstream of the actuated surface Re θ  = 1200, 1660, and 2080. The transversal traveling wave is generated by a newly developed electromagnetic actuator system underneath the aluminum surface. Three amplitudes A = 0.25, 0.30, and 0.375 mm at a wave length of $$\lambda \, = \,160\,{\text{mm}}$$ and a frequency of f = 81 Hz are investigated. The detailed analysis of the velocity profile shows the transversal traveling surface motion to redistribute the velocity in the viscous sublayer and in the logarithmic region of the turbulent boundary layer. The streamwise and wall-normal velocity fluctuations in the outer boundary layer are increased and the streamwise momentum in the near-wall regime is lowered. The drag reduction ratio (DR) due to the actuation is determined by the velocity gradient in the viscous sublayer. At the lowest Reynolds number the drag-reducing impact is proportional to the amplitude of the wave. That is, the higher the amplitude, the more pronounced the drag reduction resulting in a friction drag reduction up to 3.4 % compared to the non-actuated configuration.
PubDate: 2015-09-01

• PACS: numerical approach and evaluation of a concept for dimensioning
pressure-actuated cellular structures
• Abstract: Abstract A biologically inspired concept is investigated which can be utilized to develop energy efficient, and lightweight adaptive structures for various applications. Summarizing basic demands and barriers regarding shape-changing structures, the basic challenges of designing morphing structures are listed. The analytical background describing the physical mechanisms of PACS is presented in detail. This work focuses on the numerical approach of calculating the geometrically, highly nonlinear deformation states of pressure-actuated cellular structures. Beyond the calculation of equilibrium states, a form-finding algorithm is presented, which allows determining structural designs following predefined target shapes. Initially made assumptions are dropped incrementally to show the effects on the accuracy of the modeling. Finite element method-based calculations and experimental test results provide the computational target data for the varying grade of simplifications. Representative of more complex structures, like aircraft control surfaces, the examined geometries are chosen to evaluate the generic numerical methods and to validate the functionality of the basic working principle.
PubDate: 2015-08-23

• Semi-empirical modeling of fuselage–rotor interference for
comprehensive codes: influence of angle of attack
• Abstract: Abstract The flow field around the isolated Bo105 fuselage including the tail boom and empennage is computed by an unsteady panel code. Velocities normal to the rotor rotational plane are extracted in a volume around the rotor as a data base. A simple semi-empirical analytical formulation of the fuselage-induced velocities, based on parameter estimation from the panel code data, is extended to include rotor shaft angles of attack from $$\alpha =-90^{\circ }$$ (hover, vertical climb) to +90° (vertical descent) for use in comprehensive rotor codes. This model allows the computation of fuselage–rotor interferences on the rotor blade element level in a simplified form, thus eliminating the need for costly CFD computation (of this effect). 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 estimated analytically using blade element momentum theory.
PubDate: 2015-08-18

• Investigation into the effects of fiber waviness in standard notched
composite specimens
• Abstract: Abstract This study presents a numerical and experimental evaluation of the standardized material testing specimens (tension and compression) used for determining the strength of composite materials in the presence of defects. The composite specimens contain through the thickness fiber waviness and a circular cutout. The intentional waviness levels have been applied in the out-of-plane direction of the multi and unidirectional laminate during the curing process. The standardized face-stabilized open-hole compression test based on ASTM D6484 and the open-hole tension test according to ASTM D5766 are used for evaluating the interaction of the fiber waviness and the circular cutouts. Temporal evaluations of the load-deformation response in the specimens are coupled with optical microscopy to understand the failure modes and damage progression. Laminates with multidirectional layups show different failure modes and a different damage trajectory when compared with the response in the unidirectional laminates. The damage trajectory is dominated by the notch region and also influenced by notch size and free edge effects.
PubDate: 2015-08-15

• Sensor fusion and flight path reconstruction of the ACT/FHS rotorcraft
• Abstract: Abstract DLR’s active control technology/flying helicopter simulator (ACT/FHS) research rotorcraft supports research in a variety of fields. This paper presents the flight path reconstruction (FPR) of the ACT/FHS for post-flight data processing and its online sensor fusion during flight. Both are fundamental for system identification and flight control research. First, the ACT/FHS rotorcraft, its system architecture and the used sensor instrumentation are described. Then, the implemented unscented and extended Kalman filters are briefly explained and the applied kinematic and measurement models of the FPR are introduced. The wind estimation performance of the FPR is evaluated using simulation and flight test data accordingly. Subsequently, the online sensor fusion is motivated and its behaviour following a simulated differential GPS failure is analysed and explained.
PubDate: 2015-08-08

• New Orientation of the Editorial Board
• PubDate: 2015-08-05

• Compressor map computation based on 3D CFD analysis
• Abstract: Abstract The focus of the paper is on procedures and strategies to compute high-fidelity compressor maps for aero engines based on 3D CFD. The developed automatic process starts with an operation point analysis where a convergence checker terminates the running 3D flow analysis as soon as physical quantities such as mass flow or aerodynamic blade row loss have converged. Subsequently, the corresponding compressor speed line is determined, where operation limits like surge and choke are detected by solving optimization and root search problems, respectively. Such speed lines also have to be calculated for various other shaft speeds to obtain the whole performance map. This is achieved by adjusting shaft speed and boundary conditions, where the mesh for variable stator vanes and the amount of bleed mass flow are adapted automatically according to given schedules. Finally, the developed process is applied to a 4.5-stage axial compressor to demonstrate feasibility of the proposed strategies.
PubDate: 2015-07-25

• Flap efficiency analysis for the SAGITTA diamond wing demonstrator
configuration
• Abstract: Abstract The efficiency of deflected midboard flaps is investigated on a diamond wing-shaped unmanned aerial vehicle, the SAGITTA demonstrator configuration. The Reynolds-Averaged Navier-Stokes equations are applied to compute numerical results for a variety of flight conditions with varying angle of attack, sideslip angle, and midboard flap deflection. Low-speed wind tunnel conditions are regarded to compare the results to existing experimental data. The focus is particularly laid on the analysis of the aerodynamic coefficients and derivatives in both the longitudinal and the lateral motion. The occurring flow phenomena are motivated and discussed by flow field illustrations that are available from the numerical computations. The results show at small to moderate angles of attack linear flap characteristics, since the overall flow field is dominated by attached flow. With increasing angle of attack and additional sideslip angle, however, the leading-edge vortex originating from the inboard sharp leading edge and the wing tip separation region affect the midboard flap efficiency. Non-linear coupling effects become obvious, which particularly affect the roll and pitch control effectiveness.
PubDate: 2015-07-03

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