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 Subjects -> AERONAUTICS AND SPACE FLIGHT (Total: 97 journals)
 Showing 1 - 30 of 30 Journals sorted alphabetically Acta Astronautica       (Followers: 227) Advances in Aerospace Engineering       (Followers: 17) Advances in Space Research       (Followers: 246) Aeronautica       (Followers: 9) Aerospace       (Followers: 22) Aerospace and Electronic Systems, IEEE Transactions on       (Followers: 123) Aerospace Science and Technology       (Followers: 253) AIAA Journal       (Followers: 537) Air Force Magazine       (Followers: 6) Air Medical Journal       (Followers: 3) Aircraft Engineering and Aerospace Technology       (Followers: 99) American Journal of Space Science       (Followers: 47) Annual of Navigation       (Followers: 14) Artificial Satellites : The Journal of Space Research Centre of Polish Academy of Sciences       (Followers: 14) ASTRA Proceedings Aviation       (Followers: 9) Aviation in Focus - Journal of Aeronautical Sciences       (Followers: 6) Aviation Psychology and Applied Human Factors       (Followers: 12) Aviation Week       (Followers: 67) Aviation, Space, and Environmental Medicine       (Followers: 6) Canadian Aeronautics and Space Journal       (Followers: 25) CEAS Aeronautical Journal       (Followers: 25) Chinese Journal of Aeronautics       (Followers: 13) Control Systems       (Followers: 49) Cosmic Research       (Followers: 2) COSPAR Colloquia Series       (Followers: 3) Egyptian Journal of Remote Sensing and Space Science       (Followers: 13) Elsevier Astrodynamics Series       (Followers: 1) Fatigue of Aircraft Structures       (Followers: 7) Frontiers in Aerospace Engineering       (Followers: 7) Frontiers in Astronomy and Space Sciences       (Followers: 3) Giroskopiya i Navigatsiya Gyroscopy and Navigation       (Followers: 172) IEEE Aerospace and Electronic Systems Magazine       (Followers: 91) IEEE Transactions on Circuits and Systems I: Regular Papers       (Followers: 17) International Journal of Aeroacoustics       (Followers: 26) International Journal of Aerodynamics       (Followers: 13) International Journal of Aerospace Engineering       (Followers: 57) International Journal of Aerospace Innovations       (Followers: 13) International Journal of Aerospace Sciences       (Followers: 18) International Journal of Applied Geospatial Research       (Followers: 1) International Journal of Aviation Management       (Followers: 4) International Journal of Aviation Psychology       (Followers: 11) International Journal of Aviation Technology, Engineering and Management       (Followers: 3) International Journal of Crashworthiness       (Followers: 7) International Journal of Flow Control       (Followers: 3) International Journal of Hypersonics       (Followers: 4) International Journal of Micro Air Vehicles       (Followers: 5) International Journal of Satellite Communications Policy and Management       (Followers: 2) International Journal of Space Science and Engineering       (Followers: 3) International Journal of Space Structures       (Followers: 5) International Journal of Space Technology Management and Innovation       (Followers: 4) International Journal of Sustainable Aviation       (Followers: 1) International Journal of Turbo & Jet-Engines       (Followers: 3) Journal of Aeronautical Materials       (Followers: 2) Journal of Aeronautics & Aerospace Engineering       (Followers: 5) Journal of Aerospace Engineering       (Followers: 49) Journal of Aerospace Engineering & Technology       (Followers: 5) Journal of Aerospace Information Systems       (Followers: 1) Journal of Aerospace Technology and Management       (Followers: 2) Journal of Aircraft       (Followers: 156) Journal of Airline and Airport Management       (Followers: 6) Journal of Aviation Technology and Engineering       (Followers: 9) Journal of Guidance, Control, and Dynamics       (Followers: 100) Journal of Konbin Journal of Navigation       (Followers: 156) Journal of Propulsion and Power       (Followers: 265) Journal of Space Weather and Space Climate       (Followers: 8) Journal of Spacecraft and Rockets       (Followers: 385) Journal of Spatial Science       (Followers: 1) Journal of the American Helicopter Society       (Followers: 3) Journal of the Astronautical Sciences       (Followers: 3) Journal of Wind Engineering and Industrial Aerodynamics       (Followers: 3) Life Sciences in Space Research Microgravity Science and Technology New Space       (Followers: 2) Nonlinear Dynamics       (Followers: 5) npj Microgravity 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: 38) Progress in Aerospace Sciences       (Followers: 60) Propulsion and Power Research       (Followers: 15) Recent Patents on Space Technology Research & Reviews : Journal of Space Science & Technology       (Followers: 3) Russian Aeronautics (Iz VUZ)       (Followers: 22) Space and Polity       (Followers: 2) Space Policy       (Followers: 18) Space Research Today       (Followers: 34) Space Safety Magazine       (Followers: 32) Space Science Reviews       (Followers: 19) SpaceNews       (Followers: 352) Transport and Aerospace Engineering       (Followers: 2) Transportmetrica A : Transport Science       (Followers: 5) Unmanned Systems       (Followers: 1) Вісник Національного Авіаційного Університету       (Followers: 1) Вестник УГАТУ
 CEAS Aeronautical Journal   [25 followers]  Follow         Hybrid journal (It can contain Open Access articles)    ISSN (Print) 1869-5582    Published by Springer-Verlag  [2335 journals]
• Propeller and inflow vortex interaction: vortex response and impact on the
propeller performance
• Abstract: Abstract The aerodynamic operating conditions of a propeller can include complex situations where vorticity from sources upstream can enter the propeller plane. In general, when the vorticity enters in a concentrated form of a vortex, the interaction between the vortex and blade is referred to as blade–vortex interaction or BVI. The interaction may affect the propeller performance as well as its noise production. In the present paper, investigations of the interaction of a wing tip vortex generated by a lifting surface upstream of the rotor plane and an eight-bladed propeller are reported. Utilizing two ends of an upstream wing with non-symmetrical airfoil, the rotation of the incoming vortex could be made to co-rotate or to contra-rotate with the propeller. The ensuing velocity fields were quantified with the help of particle image velocimetry (PIV), and the propeller performance was evaluated with the help of a rotating shaft balance (RSB) mounted on the propeller shaft. The results describe the displacement of the vortex core, as it moves through the rotor plane as well as the positive effect on the thrust and torque of the contra-rotating vortex and the opposite of it in the case of the co-rotating vortex. The current research could be applied to analyse the influence of the incoming vortex on the propeller, e.g., ground vortex, tip vortex shed from a control surface, etc.
PubDate: 2016-06-23

• Investigation of an automated dry fiber preforming process for an aircraft
fuselage demonstrator using collaborating robots
• Abstract: Abstract High-performance carbon fiber-reinforced plastics (CFRP) see a continuous growth of their share in structural weight. In particular, in Aerospace, this includes the production of large components, where the key issue of significant high costs remains persistent. The Center for Lightweight Production Technologies in Augsburg as a part of the German Aerospace Center (DLR) addresses this problem with solutions for process automation to increase repeatability, process robustness, and cost-efficiency. This paper presents an approach for automated preforming of large CFRP parts by means of collaborative robots. Investigations include process development for robotic handling of large-carbon fiber cut- pieces and validation on a full-scale demonstrator. The experimental verification is focused on a demonstrator geometry that represents a fuselage section of a typical short- to mid-range aircraft. The work is completed by a discussion about the challenges, solution approaches, and observations. The presented semi-automated preforming process with collaborating robots is an important intermediate step on the way to a fully automated production process for large Aerospace parts made of CFRP.
PubDate: 2016-06-23

• Assessment of a state-space aeroelastic rotor model for rotorcraft flight
dynamics
• Abstract: Abstract The aim of the paper is the assessment of a methodology for the identification of a helicopter rotor aeroelastic operator in state-space form relating airframe motion and blade controls perturbations to corresponding hub loads, as extracted from a high-fidelity rotor aeroelastic solver. It is suited for helicopter flight dynamics stability and real-time commands response analyses, as well as for control laws synthesis.The identification method consists of a three-step process, starting with evaluation of responses to small perturbation harmonic inputs, followed by their spectral analysis and rational form approximation of corresponding transfer functions. Considering a Bo-105-type helicopter, numerical investigation is focused on: analysis of critical parameters affecting accuracy and efficiency of transfer functions identification, interpretation of the additional states introduced by rational approximation, validation of rotor finite-state aeroelastic representation.
PubDate: 2016-06-15

• Integration of a visibility graph based path planning method in the
ACT/FHS rotorcraft
• Abstract: Abstract This work presents recent progress at the German Aerospace Center (DLR) in landing guidance for helicopter approaches to landing sites without prior reconnaissance. During the project ALLFlight, DLRs research rotorcraft Advanced Control Technology/Flying Helicopter Simulator (ACT/FHS) has been equipped with a sensor suite including a LIDAR sensor, a forward looking RADAR, an infrared camera and a TV camera to provide sensor-based situational awareness. Using the information acquired by the LIDAR, a method for planning an initial flight path from previously unknown landing entry points to the landing point is presented. It is based on a previously developed method using a vehicle point representation, geo-referenced flight surfaces and visibility graphs. A second mode to provide re-planning capabilities in-flight is described. First results of flight tests conducted in 2013 are presented and discussed. Using the data recorded during these approaches, an improved re-planning strategy for the final approach based on so called visibility hulls is presented. This work continues recent research at DLR’s Institute of Flight Systems helicopter department for flight under degraded visual environment (DVE) for a full-scale helicopter.
PubDate: 2016-06-13

• Semi-empirical modeling of fuselage–rotor interference for
comprehensive codes: influence of side-slip angle
• Abstract: Abstract A semi-empirical and physics-based analytical formulation of the induced velocities generated by the fuselage shell of the Bo105 wind tunnel model in the volume around the rotor is derived from velocity data computed by a panel code. The reduced-order analytical model is several orders of magnitude faster than the panel code and thus is predestinated for use in comprehensive rotor codes. Angle of attacks investigated include vertical descent, shallow descent, level flight and climb to vertical ascent. Side-slip angles range from forward to quartering flight. The analytical induced velocity model can be directly used to account for the inflow at the blade elements and also allows for analytical or numerical integration of rotor wake convection to compute the associated displacements of rotor blade tip vortices travelling downstream within this velocity field. This model will be used to replace a fully panelized fuselage (and thus significantly reduce the computational effort) throughout a simulation with an aeromechanics code to account for the influence of the fuselage (e.g., in a design stage). The usage within an aerodynamics code (e.g., a panel code) reduces the panelization to the rotor blades only, leaving the computation of the fuselage-induced velocities to the model. The focus of this paper is the analytical evaluation of fuselage–rotor interference in side-slip angles on rotor trim controls, using blade element momentum theory. The results are compared to the influence of thrust-induced inflow gradients on rotor trim.
PubDate: 2016-06-08

• On the history and prospects of three-dimensional human–computer
interfaces for the provision of air traffic control services
• Abstract: Abstract This paper is an essay on the history and prospects of three-dimensional (3D) human–computer interfaces for the provision of air traffic control services. Over the past 25 years, many empirical studies have addressed this topic. However, the results have been deemed incoherent and self-contradictory and no common conclusion has been reached. To escape from the deadlock of the experimental approach, this study takes a step back into the conceptual development of 3D interfaces, addressing the fundamental benefits and drawbacks of 3D rendering. Under this light, many results in the literature start to make sense and some conclusions can be drawn. Also, with an emphasis on the future of air traffic control, this research identifies a set of tasks wherein the intrinsic weaknesses of 3D rendering can be minimized and its advantages can be exploited. These are the ones that do not require accurate estimates of distances or angles. For future developments in the field of 3D interfaces for air traffic control operators, we suggest focusing on those tasks only.
PubDate: 2016-06-01

• Bürgernahes flugzeug: testing technology for the high power propeller
of a wind tunnel model
• Abstract: Abstract The research project “Bürgernahes Flugzeug (BNF)”, funded by the federal state of Lower Saxony, is set to study future commercial aircraft. Main task is the development of technologies for quiet aircraft with short take-off and landing capability. A wind tunnel model is built for testing the active high-lift system on a semispan wing, equipped with a scaled high power propeller which is driven by an electric motor. The electric motor was specially developed to meet the required high power density. In 2012 and 2013 several measurement campaigns were carried out in the Low Speed Wind Tunnel Braunschweig (NWB) of the German-Dutch Wind Tunnels (DNW). An operation procedure was set for the measurement campaigns, which allowed testing on varying operation points.
PubDate: 2016-06-01

• Initial flight tests of an automatic slung load control system for the
ACT/FHS
PubDate: 2016-06-01

• Numerical investigations of Fenestron™ noise characteristics using a
hybrid method
• Abstract: Abstract The present article gives an overview of numerical investigations performed during a research project aimed at in-depth understanding of noise generation mechanisms of a shrouded helicopter tail rotor such as Airbus Helicopters Fenestron $$^\mathrm{TM}$$ . Both aerodynamic and aeroacoustic studies are performed based on a full-scale lightweight transport helicopter configuration with detailed geometry of the Fenestron $$^\mathrm{TM}$$ and by neglecting of the main rotor downwash effect. Analysis is carried out by using a hybrid method, combining Unsteady Reynolds-Averaged Navier-Stokes (URANS) simulation with Ffowcs Williams and Hawkings (FW-H) acoustic analogy. Two representative helicopter flight conditions, namely fast forward flight and hovering, are considered. Thereby, it is intended to assess the influence of cross flow in forward flight condition on the Fenestron $$^\mathrm{TM}$$ acoustic property. Effect of turbulence model on the accuracy of noise prediction is also investigated by comparing the Shear Stress Transport (SST) turbulence model with the Scale Adaptive Simulation (SAS). The capability of the applied hybrid methodology is estimated by means of flight test measurements. A good agreement is found between the predicted and measured sound spectra in terms of blade passing frequency (BPF) and its corresponding sidebands for both flight conditions investigated.
PubDate: 2016-06-01

• A parametric aircraft fuselage model for preliminary sizing and
crashworthiness applications
• Abstract: Abstract The aircraft design process generally comprises three consecutive phases: conceptual, preliminary and detailed design phase. In the conceptual design phase a basis aircraft layout is defined using multidisciplinary analysis procedures. For the structural layout, however, the preliminary design phase is of particular interest as more detailed calculations are introduced to enhance the basic design of the primary structure. Up to date, semi-analytical methods are widely used in this design stage to estimate the structural mass. Although these methods lead to adequate results for the major aircraft components of standard configurations, the evaluation of new configurations (e.g., box wing, blended wing body) or specific structural components with complex loading conditions (e.g., center wing box) is very challenging and demands higher fidelity approaches based on Finite Elements (FE). To accelerate FE model generation in a multidisciplinary design environment, automated processes based on a parametric model description have been introduced. To easily couple in- and output of different tools, a standardized data format—CPACS (Common Parametric Aircraft Configuration Schema)—is used. The versatile structural description in CPACS, the implementation in model generation tools, but also current limitations and future enhancements will be discussed. Recent development on the progress of numerical process chains for structural sizing and crashworthiness applications on solid ground and on water (ditching) are presented in this paper.
PubDate: 2016-05-07

• Preparation and execution of the NICETRIP low- and high-speed wind tunnel
tests
• Abstract: Abstract The present paper reports the preparation and execution of high- and low-speed wind tunnel tests of the tilt-rotor project NICETRIP. Within the NICETRIP project (Novel Innovative Competitive Effective Tilt Rotor Integrated Project), co-funded by the EU, wind tunnel tests were conducted for a heavily instrumented 1:5 scale model of a tilt-rotor aircraft (3.5 m wingspan, 1.48 m diameter rotors) based on the ERICA concept (Enhanced Rotorcraft Innovative Concept Achievement). The current paper provides an overview of the contributions of DLR to the low- and high-speed wind tunnel tests performed at DNW-LLF (German-Dutch Wind Tunnels Large Low-speed Facility) in 2013 and at ONERA-S1MA in 2014. It gives detailed information about the preparation activities, the model hardware and its control, the necessary adaptations for the model preparation at DLR, and results of the ground vibration tests. Additionally, the data acquisition and monitoring during the wind tunnel experiments, the trimming of the model in the wind tunnel and the conducted tests are described, including encountered problems and how they were solved. In the last section, some representative test results are shown.
PubDate: 2016-04-01

• Possibilities and difficulties for rotorcraft using variable transmission
drive trains
• Abstract: Abstract This publication shows advantages and possible applications for variable transmission drivetrains within rotorcraft. The power requirement of a generic helicopter with constant and variable rotor speed was calculated. Various drive train technologies that support a variable transmission were described. The prospects of this technology, its influence on the dynamic behaviour of a rotor and further areas that need to be investigated extensively are presented. This technology is applicable to some rotorcraft architecture. Requests from the rotorcraft industry underline the necessity for future rotorcraft using variable rotational speeds. However, the A160 or the EC145 and Mi-8 already show the potential of this technique. Reduction of required power of the rotor should be possible and also an extension of the flight envelope towards higher flight speeds, higher altitudes, better manoeuvrability, etc. By using a variable transmission gearbox, turbine and auxiliary units can still be driven at their design point, independent of the current rotor speed. Excessive loads may occur when discrete speed transmission are used. Frictional or fluid transmissions with continuous variable ratio may fail due to overheating. Other continuous concepts are favoured. The design of a variable speed rotor focuses specifically on its dynamic behaviours and on structural and geometrical optimisation to avoid operation at rotational speed resonance frequencies. Morphing structures may support this. Some rotorcraft architectures can benefit from a variable speed rotor technology. It probably will increase efficiency, decrease noise levels, fuel consumption and CO2 production, and the flight envelope may be extended.
PubDate: 2016-03-31

• SPYDER: a software package for system diagnosis engineering
• Abstract: Abstract Modern aircraft systems comprise hardware and software with high complexity. In order to assure an operation at high availability and low maintenance cost, diagnosis functions become essential. These functions detect faults and failures, identify sources of faults and failures and assess the current state of health. A reduction in operating cost, better planning of maintenance actions, and new business cases for operator and equipment manufactures are gained as a result. A systematic approach for the design and test of diagnosis functions supported by an integrated model-based tool chain is introduced in this paper. That is the SPYDER concept, a Software Package for sYstem Diagnosis EngineeRing. Embedded into the general system development process, a stepwise design and test of diagnosis functions is performed. It focuses on failures and starts with failure–effect analysis, continues with sensor placement and proceeds further to configuration and testing. The method has been applied to multifunctional fuel cell systems that are used as illustrative examples.
PubDate: 2016-03-28

• Validation of a nonlinear observer implementation for empennage loads
estimation
PubDate: 2016-03-25

• Economic optimization of cargo airships
• Abstract: Abstract Historical strengths and weaknesses of airships were investigated to determine a mission suited for airships. The transatlantic cargo mission was selected to take advantage of the high payload and endurance qualities of airships while minimizing the frequency of ground handling. An optimization was performed to minimize the cost per ton mile of the airship with maximum velocity as the variable. Other design parameters were held constant and based on historical airship studies. The cost per ton mile and von Karman efficiency were used to compare the optimized airship designs with other modes of cargo transportation. An airship with a volume of 200,000 m3, which was the volume of the Hindenburg, would achieve a cost per ton mile of \$1.03. This value equates to about 85 % the cost of an airplane, and five times the cost of a truck. A graph of von Karman efficiency showed that the airships proposed by this study could occupy a niche market between airplanes and trucks in terms of both efficiency and velocity.
PubDate: 2016-03-08

• Numerical assessment of the vibration control effects of porous liners on
an over-the-wing propeller configuration
• Abstract: Abstract An over-the-wing position of propellers comes with noise shielding and significantly reduced sound emission to the ground. A drawback of this configuration may be the additional impact due to the passing propeller blades on the airfoil’s surface inducing structure-borne sound in the wing. This structural sound propagates within the wing and the fuselage and can radiate further into the cabin as airborne sound. In order not to trade the advantage of reduced noise transmission to the ground with higher sound pressure levels within the cabin, a remedy is proposed, which consists in placing a poroelastic liner on the wing’s surface below the rotor where the blade tips move closely to the airfoil’s skin. In this work, a numerical approach to assess the effects of porous liners for an over-the-wing propeller configuration is presented. A simplified generic channelwing structure is exposed to pressure fluctuations on its surface which are caused by an over-the-wing propeller. Porous liners are applied to the wing’s surface where the blade tips pass in close proximity. Structural vibrations are determined using the finite element method in frequency domain. Surface data is obtained from CFD computations. The porous material is represented by Biot’s theory.
PubDate: 2016-03-01

• System analysis of aircraft with natural laminar flow and forward swept
wings
• Abstract: Abstract The objective of this paper is an enhanced analysis and assessment of a short-to-medium range aircraft configuration with natural laminar flow (NLF) and forward swept wings (FSW) designed by DLR. It is intended to show how the proposed aircraft concept could contribute to a more economic and ecologic operation. By implementing a multidisciplinary simulation and assessment framework, the net-benefit on air transportation system level is evaluated from airline perspective under consideration of realistic airline network conditions. Therefore operational aspects (e.g. stage length) and environmental factors (e.g. insect contamination, cloud encounter) which affect the aircraft effectiveness are included into the assessment. Apart from modeling the technology intended effect of fuel saving on airline economics, the study also aims to determine unintentional repercussions (e.g. change in maintenance effort, emissions, noise) which arise due to the design and the operation of the FSW–NLF concept. The overall goal of the paper is to provide aircraft operators with a better understanding of the behavior of NLF aircraft under realistic operational boundary conditions as well as to demonstrate resulting trade-offs between economical and ecological effectiveness.
PubDate: 2016-02-29

• Automated manufacturing of large, three-dimensional CFRP parts from dry
textiles
• Abstract: Abstract At present, the manufacturing of large parts from carbon fiber reinforced plastic in aerospace is mostly done by manual labor. One of the objectives of The Center of Lightweight Production Technology in Augsburg, Germany, is to transfer manual production methods into automated processes. This work addresses the process chain starting with dry textiles, via production integrated quality assurance, to a cured part. A gripper system is required to handle the pliable and delicate dry carbon fiber textiles in the preforming process. The project aims to develop such a system and establish an automated application. A final demonstration of the system’s capabilities allows evaluation of the current level of maturity and usability. Sensor technology is to be integrated into the production process for quality assurance purposes. The position and draping of cut-pieces are determined by laser light section technique and fiber angle measurement. This allows detection of process parameters and potential deviations in the production chain. Corrections can be applied early, which offers a clear advantage over the current inspection of the finished component. Yet another focus is the enhancement of the setup for resin infusion. The application of a pre-tailored VAP membrane using a mechanized lay-up system allows for fast, robust and repeatable vacuum bagging with a significant reduction of manual labor. The presentation will give insight to the development of the gripper system, quality assurance measures, and semi-automated vacuum bagging including their current level of maturity.
PubDate: 2016-02-19

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• PubDate: 2016-01-29

• 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

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