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  Subjects -> AERONAUTICS AND SPACE FLIGHT (Total: 98 journals)
Acta Astronautica     Hybrid Journal   (Followers: 209)
Advances in Aerospace Engineering     Open Access   (Followers: 7)
Advances in Space Research     Full-text available via subscription   (Followers: 218)
Aeronautica     Open Access   (Followers: 7)
Aerospace     Open Access   (Followers: 15)
Aerospace and Electronic Systems, IEEE Transactions on     Hybrid Journal   (Followers: 105)
Aerospace Science and Technology     Hybrid Journal   (Followers: 243)
Affective Computing, IEEE Transactions on     Hybrid Journal   (Followers: 11)
AIAA Journal     Full-text available via subscription   (Followers: 505)
Air Force Magazine     Full-text available via subscription   (Followers: 4)
Air Medical Journal     Hybrid Journal   (Followers: 3)
Aircraft Engineering and Aerospace Technology     Hybrid Journal   (Followers: 91)
American Journal of Space Science     Open Access   (Followers: 44)
Annual of Navigation     Open Access   (Followers: 3)
Artificial Satellites : The Journal of Space Research Centre of Polish Academy of Sciences     Open Access   (Followers: 14)
ASTRA Proceedings     Open Access  
Aviation     Hybrid Journal   (Followers: 7)
Aviation in Focus - Journal of Aeronautical Sciences     Open Access   (Followers: 6)
Aviation Psychology and Applied Human Factors     Hybrid Journal   (Followers: 12)
Aviation Week     Full-text available via subscription   (Followers: 36)
Aviation, Space, and Environmental Medicine     Full-text available via subscription   (Followers: 6)
Canadian Aeronautics and Space Journal     Full-text available via subscription   (Followers: 23)
CEAS Aeronautical Journal     Hybrid Journal   (Followers: 25)
Chinese Journal of Aeronautics     Open Access   (Followers: 14)
Control Systems     Hybrid Journal   (Followers: 36)
Cosmic Research     Hybrid Journal   (Followers: 2)
COSPAR Colloquia Series     Full-text available via subscription   (Followers: 1)
Egyptian Journal of Remote Sensing and Space Science     Open Access   (Followers: 5)
Elsevier Astrodynamics Series     Full-text available via subscription   (Followers: 1)
Fatigue of Aircraft Structures     Open Access   (Followers: 7)
Frontiers in Aerospace Engineering     Open Access   (Followers: 6)
Frontiers in Astronomy and Space Sciences     Open Access  
Giroskopiya i Navigatsiya     Open Access  
Gyroscopy and Navigation     Hybrid Journal   (Followers: 118)
IEEE Aerospace and Electronic Systems Magazine     Full-text available via subscription   (Followers: 63)
IEEE Transactions on Circuits and Systems I: Regular Papers     Hybrid Journal   (Followers: 16)
International Journal of Aeroacoustics     Full-text available via subscription   (Followers: 25)
International Journal of Aerodynamics     Hybrid Journal   (Followers: 15)
International Journal of Aerospace Engineering     Open Access   (Followers: 48)
International Journal of Aerospace Innovations     Full-text available via subscription   (Followers: 13)
International Journal of Aerospace Sciences     Open Access   (Followers: 18)
International Journal of Applied Geospatial Research     Hybrid Journal   (Followers: 3)
International Journal of Aviation Management     Hybrid Journal   (Followers: 4)
International Journal of Aviation Psychology     Hybrid Journal   (Followers: 12)
International Journal of Aviation Technology, Engineering and Management     Full-text available via subscription   (Followers: 2)
International Journal of Crashworthiness     Hybrid Journal   (Followers: 7)
International Journal of Flow Control     Full-text available via subscription   (Followers: 4)
International Journal of Hypersonics     Full-text available via subscription   (Followers: 4)
International Journal of Micro Air Vehicles     Full-text available via subscription   (Followers: 5)
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: 3)
International Journal of Space Technology Management and Innovation     Full-text available via subscription   (Followers: 3)
International Journal of Sustainable Aviation     Hybrid Journal   (Followers: 1)
International Journal of Turbo & Jet-Engines     Hybrid Journal   (Followers: 2)
Journal of Aeronautical Materials     Open Access   (Followers: 1)
Journal of Aeronautics & Aerospace Engineering     Open Access   (Followers: 3)
Journal of Aerospace Engineering     Full-text available via subscription   (Followers: 44)
Journal of Aerospace Engineering & Technology     Full-text available via subscription   (Followers: 2)
Journal of Aerospace Information Systems     Full-text available via subscription   (Followers: 1)
Journal of Aerospace Technology and Management     Open Access   (Followers: 2)
Journal of Aircraft     Full-text available via subscription   (Followers: 145)
Journal of Airline and Airport Management     Open Access   (Followers: 6)
Journal of Astrobiology & Outreach     Open Access  
Journal of Aviation Technology and Engineering     Open Access   (Followers: 9)
Journal of Guidance, Control, and Dynamics     Full-text available via subscription   (Followers: 94)
Journal of Konbin     Open Access  
Journal of Navigation     Hybrid Journal   (Followers: 116)
Journal of Propulsion and Power     Full-text available via subscription   (Followers: 210)
Journal of Space Weather and Space Climate     Open Access   (Followers: 6)
Journal of Spacecraft and Rockets     Full-text available via subscription   (Followers: 328)
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   (Followers: 3)
Journal of Wind Engineering and Industrial Aerodynamics     Hybrid Journal   (Followers: 6)
Life Sciences in Space Research     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   (Followers: 6)
Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering     Hybrid Journal   (Followers: 35)
Progress in Aerospace Sciences     Full-text available via subscription   (Followers: 56)
Propulsion and Power Research     Open Access   (Followers: 5)
Recent Patents on Space Technology     Full-text available via subscription  
Research & Reviews : Journal of Space Science & Technology     Full-text available via subscription   (Followers: 1)
Russian Aeronautics (Iz VUZ)     Hybrid Journal   (Followers: 21)
Space and Polity     Hybrid Journal   (Followers: 2)
Space Policy     Hybrid Journal   (Followers: 16)
Space Research Today     Full-text available via subscription   (Followers: 30)
Space Safety Magazine     Free   (Followers: 21)
Space Science Reviews     Hybrid Journal   (Followers: 15)
SpaceNews     Free   (Followers: 279)
Transport and Aerospace Engineering     Full-text available via subscription   (Followers: 1)
Transportmetrica A : Transport Science     Hybrid Journal   (Followers: 3)
Unmanned Systems     Hybrid Journal  
Вісник Національного Авіаційного Університету     Open Access   (Followers: 1)
Вестник УГАТУ     Open Access  
Journal Cover CEAS Aeronautical Journal
  [25 followers]  Follow
   Hybrid Journal Hybrid journal (It can contain Open Access articles)
   ISSN (Print) 1869-5582
   Published by Springer-Verlag Homepage  [2280 journals]
  • Thanks to our Reviewers
    • PubDate: 2016-01-29
  • Initial flight tests of an automatic slung load control system for the
    • Abstract: Abstract An automatic slung load control system for the research helicopter ACT/FHS (active control technology/flying helicopter simulator) of the German Aerospace Center (Deutsches Zentrum für Luft- und Raumfahrt e.V.) has been developed and initially tested in flight. The external load is suspended from a rescue hoist which was mounted at the ACT/FHS for flight test purposes. For the load motion detection an optical-inertial sensor system was developed. The sensor system provides estimations of the cable length and cable angle as well as cable angle rates for the slung load control system. Flight testing of the sensor system proved that the optical marker is detected consistently and accurately for cable length up to 50 m. Furthermore, the estimated load motion signals can be used for the control system. To demonstrate the overall system’s functionality, an initial control system for damping of the pendulum load motion was designed and flight tested. The automatic function of the control system was effective in damping the load pendulum motion for a fixed cable length. Under piloted control the slung load damping system showed deficiencies. When actively controlling the helicopter, the pilot acted against the control system resulting in an adverse effect in load damping. Overall, for the first time, a slung load control system for a load suspended from a rescue hoist could be demonstrated successfully.
      PubDate: 2016-01-28
  • 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: 2016-01-16
  • DLR project Digital-X: towards virtual aircraft design and flight testing
           based on high-fidelity methods
    • Abstract: Abstract Numerical simulation is already an important cornerstone for aircraft design, although the application of highly accurate methods is mainly limited to the design point. To meet future technical, economic and social challenges in aviation, it is essential to simulate a real aircraft at an early stage, including all multidisciplinary interactions covering the entire flight envelope, and to have the ability to provide data with guaranteed accuracy required for development and certification. However, despite the considerable progress made there are still significant obstacles to be overcome in the development of numerical methods, physical modeling, and the integration of different aircraft disciplines for multidisciplinary analysis and optimization of realistic aircraft configurations. At DLR, these challenges are being addressed in the framework of the multidisciplinary project Digital-X (4/2012–12/2015). This paper provides an overview of the project objectives and presents first results on enhanced disciplinary methods in aerodynamics and structural analysis, the development of efficient reduced order methods for load analysis, the development of a multidisciplinary optimization process based on a multi-level/variable-fidelity approach, as well as the development and application of multidisciplinary methods for the analysis of maneuver loads.
      PubDate: 2015-12-22
  • Conceptual design studies of vertical takeoff and landing remotely piloted
           aircraft systems for hybrid missions
    • Abstract: Abstract Spurred by the rapid progress in sensor performance increase associated with contemporary miniaturization, many companies, organizations, and governments are interested in using new opportunities in civil remotely piloted aircraft system applications. Coupled with an enhancement in propulsion system performance as well as an optimized and well-matched aerodynamic design, flight envelope limits can be enlarged and new mission profiles arise. Due to these ambitions, resulting hybrid missions become more complex and individual with partially contradicting demands, such as vertical takeoff and landing capabilities, fast climb and cruise combined with a long-endurance loiter capability, and a hover capability up to altitudes of 5000 m. In order to fulfill the diverse mission requirements, several configuration concepts are investigated. The focus is laid on different propulsion system concepts where various technologies and energy storage types are considered, as well as their effects on the aerodynamic shape and the controllability of the configuration. The investigated concepts comprise tilt propeller, tilt ducted propeller, and tilt wing configurations with fixed and variable pitch propeller. Based on these studies, a feasible concept in the weight category of MTOW ≤150 kg was identified which accomplishes both the aerodynamic and performance demands and the controllability in all flight segments.
      PubDate: 2015-12-08
  • 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 ( 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
  • nxControl instead of pitch-and-power
    • 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
  • 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
    • 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
  • 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
  • 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
    • 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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