Subjects -> AERONAUTICS AND SPACE FLIGHT (Total: 123 journals)
 Showing 1 - 30 of 30 Journals sorted alphabetically Acta Astronautica       (Followers: 496) Advances in Aerospace Engineering       (Followers: 70) Advances in Aerospace Science and Technology       (Followers: 8) Advances in Astronautics Science and Technology       (Followers: 1) Advances in Space Research       (Followers: 458) Aeronautical Journal, The       (Followers: 13) Aerospace       (Followers: 60) Aerospace Medicine and Human Performance       (Followers: 19) Aerospace Science and Technology       (Followers: 430) Aerospace Scientific Journal       (Followers: 18) Aerospace Systems       (Followers: 6) Aerospace technic and technology       (Followers: 3) Aerotecnica Missili & Spazio : Journal of Aerospace Science, Technologies & Systems       (Followers: 4) AIAA Journal       (Followers: 1196) Air Force Magazine       (Followers: 10) Air Medical Journal       (Followers: 8) Aircraft Engineering and Aerospace Technology       (Followers: 264) Annual of Navigation       (Followers: 22) Artificial Satellites       (Followers: 23) ASTRA Proceedings       (Followers: 3) Astrodynamics       (Followers: 4) Aviation       (Followers: 17) Aviation Advances & Maintenance       (Followers: 5) Aviation in Focus - Journal of Aeronautical Sciences       (Followers: 10) Aviation Psychology and Applied Human Factors       (Followers: 27) Aviation Week       (Followers: 438) Canadian Aeronautics and Space Journal       (Followers: 34) CEAS Aeronautical Journal       (Followers: 30) Chinese Journal of Aeronautics       (Followers: 21) Ciencia y Poder Aéreo       (Followers: 2) Civil Aviation High Technologies       (Followers: 5) Control Systems       (Followers: 315) Cosmic Research       (Followers: 5) COSPAR Colloquia Series       (Followers: 11) Egyptian Journal of Remote Sensing and Space Science       (Followers: 24) Elsevier Astrodynamics Series       (Followers: 12) Fatigue of Aircraft Structures       (Followers: 15) Frontiers in Astronomy and Space Sciences       (Followers: 12) Gravitational and Space Research Gyroscopy and Navigation       (Followers: 260) IEEE Aerospace and Electronic Systems Magazine       (Followers: 279) IEEE Journal on Miniaturization for Air and Space Systems       (Followers: 2) IEEE Transactions on Aerospace and Electronic Systems       (Followers: 385) IEEE Transactions on Circuits and Systems I: Regular Papers       (Followers: 39) International Journal of Aeroacoustics       (Followers: 41) International Journal of Aerodynamics       (Followers: 37) International Journal of Aeronautical and Space Sciences       (Followers: 2) International Journal of Aerospace Engineering       (Followers: 82) International Journal of Aerospace Psychology       (Followers: 23) International Journal of Aerospace Sciences       (Followers: 32) International Journal of Applied Geospatial Research       (Followers: 7) International Journal of Aviation Management       (Followers: 9) International Journal of Aviation Technology, Engineering and Management       (Followers: 7) International Journal of Aviation, Aeronautics, and Aerospace       (Followers: 5) International Journal of Crashworthiness       (Followers: 12) International Journal of Micro Air Vehicles       (Followers: 11) International Journal of Satellite Communications Policy and Management       (Followers: 13) International Journal of Space Science and Engineering       (Followers: 11) International Journal of Space Structures       (Followers: 17) International Journal of Space Technology Management and Innovation       (Followers: 10) International Journal of Sustainable Aviation       (Followers: 5) International Journal of Turbo and Jet-Engines       (Followers: 6) Investigación Pecuaria       (Followers: 3) Journal of Aerodynamics       (Followers: 18) Journal of Aeronautical Materials       (Followers: 9) Journal of Aeronautics & Aerospace Engineering       (Followers: 31) Journal of Aerospace Engineering       (Followers: 69) Journal of Aerospace Engineering & Technology       (Followers: 18) Journal of Aerospace Information Systems       (Followers: 22) Journal of Aerospace Information Systems       (Followers: 34) Journal of Aerospace Technology and Management       (Followers: 7) Journal of Aircraft       (Followers: 337) Journal of Aircraft and Spacecraft Technology       (Followers: 9) Journal of Airline and Airport Management       (Followers: 12) Journal of Astrobiology & Outreach       (Followers: 3) Journal of Aviation Technology and Engineering       (Followers: 11) Journal of Aviation/Aerospace Education & Research       (Followers: 2) Journal of Engineering and Technological Sciences       (Followers: 1) Journal of Guidance, Control, and Dynamics       (Followers: 205) Journal of KONBiN       (Followers: 3) Journal of Navigation       (Followers: 280) Journal of Propulsion and Power       (Followers: 615) Journal of Space Safety Engineering       (Followers: 8) Journal of Space Weather and Space Climate       (Followers: 27) Journal of Spacecraft and Rockets       (Followers: 773) Journal of Spatial Science       (Followers: 3) Journal of the American Helicopter Society       (Followers: 8) Journal of the Astronautical Sciences       (Followers: 9) Journal of the Australasian Society of Aerospace Medicine       (Followers: 1) Journal of Wind Engineering and Industrial Aerodynamics       (Followers: 17) Life Sciences in Space Research       (Followers: 4) MAD - Magazine of Aviation Development       (Followers: 2) Mekanika : Jurnal Teknik Mesin i       (Followers: 1) Microgravity Science and Technology       (Followers: 2) New Space       (Followers: 6) Nonlinear Dynamics       (Followers: 20) npj Microgravity       (Followers: 3) Open Aerospace Engineering Journal       (Followers: 1) Perspectives of Earth and Space Scientists i Population Space and Place       (Followers: 9) Problemy Mechatroniki. Uzbrojenie, lotnictwo, inżynieria bezpieczeństwa / Problems of Mechatronics. Armament, Aviation, Safety Engineering       (Followers: 3) Proceedings of the Human Factors and Ergonomics Society Annual Meeting       (Followers: 16) Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering       (Followers: 46) Progress in Aerospace Sciences       (Followers: 81) Propulsion and Power Research       (Followers: 68) REACH - Reviews in Human Space Exploration       (Followers: 5) Research & Reviews : Journal of Space Science & Technology       (Followers: 17) RocketSTEM       (Followers: 6) Russian Aeronautics (Iz VUZ)       (Followers: 24) Science and Education : Scientific Publication of BMSTU       (Followers: 1) Space and Polity       (Followers: 4) Space Policy       (Followers: 29) Space Research Today       (Followers: 48) Space Safety Magazine       (Followers: 51) Space Science International       (Followers: 202) Space Science Reviews       (Followers: 97) SpaceNews       (Followers: 825) Spatial Information Research       (Followers: 1) Technical Soaring       (Followers: 1) Transport and Aerospace Engineering       (Followers: 1) Transportmetrica A : Transport Science       (Followers: 9) Unmanned Systems       (Followers: 5) Вісник Національного Авіаційного Університету       (Followers: 2)
Similar Journals
 CEAS Aeronautical JournalJournal Prestige (SJR): 0.248 Citation Impact (citeScore): 1Number of Followers: 30      Hybrid journal (It can contain Open Access articles) ISSN (Print) 1869-5582 - ISSN (Online) 1869-5590 Published by Springer-Verlag  [2656 journals]
• Development of a hardware-in-the-loop demonstrator for the validation of
fault-tolerant control methods for a hybrid UAV
• Abstract: Abstract Many aircraft are inherently over-actuated with regard to their input variables. This can be particularly advantageous in the context of unmanned aerial vehicles (UAV), where actuator functions can fail in critical situations. In such cases, the redundant actuators can be used to further fulfil the control strategies used and thus increase the operational safety. Within such an active fault-tolerant control system, a fault detection and isolation (FDI) module is required. To evaluate such safety–critical systems, hardware-in-the-loop simulations (HIL) are a necessary step prior to real flight tests. These simulations can verify the correct implementation of the flight controller on the target hardware as well as the real-time capability of the algorithms used. Particularly in the context of active fault-tolerant control, investigations concerning the robustness of the used FDI module with regard to real, noisy sensor signals, which can be generated by a HIL demonstrator, are of utter importance. This paper presents the development of a HIL demonstrator for the validation of fault-tolerant control methods for a hybrid UAV. This includes a detailed description of the demonstrator’s design, control and interfacing between the integrated subsystems. As an application example, a hybrid UAV model will be shortly presented, which, in addition to the primary aerodynamic control surfaces, can also use four lift rotors to control the aircraft during cruise and is therefore inherently over-actuated. Finally, a closed-loop real-time simulation of the UAV model on the HIL demonstrator is presented on the basis of the exemplary simulation of an actuator failure and subsequent reconfiguration by the fault-tolerant flight control law.
PubDate: 2021-05-05

• Turbulence load prediction for manned and unmanned aircraft by means of
anticipating differential pressure measurements
• Abstract: Abstract This paper focuses on the prediction of disturbance effects of the vertical acceleration of an aircraft flying in atmospheric turbulence. To this end, 5-hole probes with high-dynamic differential pressure sensors are installed in front of a fixed-wing unmanned aircraft system (UAS) and a manned experimental aircraft to measure the local airspeed and angle of attack of the airflow. Test flights are performed in light, moderate and severe turbulence to assess the anticipating character and the accuracy of the predicted acceleration. Thereby, depending on the flown airspeed, anticipation times up to 0.1 s are observed. For the UAS the prediction accuracy is assessed to be 71.19% for moderate turbulence and 71.05% for severe turbulence, where vertical acceleration disturbances higher than 30 m/s2 are measured. The first manned test flight revealed a prediction accuracy of 61.97%.
PubDate: 2021-04-30

• Analytic solution of in-plane vortex–rotor interactions with arbitrary
orientation and its impact on rotor trim
• Abstract: Abstract The general aerodynamic problem of arbitrarily oriented in-plane vortex-rotor interaction was investigated in the past only by numerical simulation. Just one special case of in-plane vortex-rotor interaction with the vortex axis in flight direction was recently solved analytically. In this article, the analytical solution for arbitrary in-plane vortex orientation and position relative to the rotor is given for the first time. The solution of the integrals involved as derived here encompasses and simplifies the previous derivation of the special case significantly. Results provide the vortex impact on rotor trim (thrust, aerodynamic rolling and pitching moments about the hub) and the rotor controls required to mitigate these disturbances. For the special case with the vortex axis in flight direction, the results are identical to the former solution and results for the other in-plane vortex orientations and positions agree with the numerical results obtained so far.
PubDate: 2021-04-27

• Sound quality assessment of a medium-range aircraft with enhanced
fan-noise shielding design
• Abstract: Abstract The investigation of technologies that can improve the sustainability of the air transport system requires not only the development of alternative fuel concepts and novel vehicle technologies but also the definition of appropriate assessment strategies. Regarding noise, the assessment should reflect the situation of communities living near airports, i.e., not only addressing sound levels but also accounting for the annoyance caused by aircraft noise. For this purpose, conventional A-weighted sound pressure level metrics provide initial but limited information as the level- and frequency-dependency of the human hearing is accounted for in a simplified manner. Ideally, subjective evaluations are required to adequately quantify the perceived short-term annoyance associated with aircraft noise. However, listening tests are time-consuming and not suitable to be applied during the conceptual aircraft design stage, where a large solution space needs to be explored. Aiming at bridging this gap, this work presents a methodology for the sound quality assessment of computational aircraft noise predictions, which is hereby conducted in terms of objective psychoacoustic metrics. The proposed methodology is applied to a novel medium-range vehicle with fan noise shielding architecture during take-off and landing procedures. The relevance of individual sound sources, i.e., airframe and engine noise contributions, and their dependencies on the aircraft architecture and flight procedures are assessed in terms of loudness, sharpness, and tonality. Moreover, the methodology is steered towards community noise assessment, where the impacts on short-term annoyance brought by the novel aircraft design are analysed. The assessment is based on the modified psychoacoustic annoyance, a metric that provides a quantitative description of human annoyance as a combination of different hearing sensations. The present work is understood as an essential step towards low-annoyance aircraft design.
PubDate: 2021-04-21

• Quieter and Greener rotorcraft: concurrent aerodynamic and acoustic
optimization
• Abstract: Abstract Within the DLR project VicToria an aerodynamic and aero-acoustic optimization of helicopter rotor blades is performed. During the optimization, three independent flight conditions are considered: hover, cruise and descent flight. The first two flight conditions drive the power requirements of the helicopter rotor, while the descent flight is the loudest flight condition for current helicopter generations. To drive down the required power and the emitted noise, a multi-objective design approach coupled with surrogate models is utilized to find a Pareto optimal set of rotors. This approach allows to identify the trade-offs to be made when laying emphasis on either goal function. The underlying CFD simulations utilize fourth-order accurate spatial schemes to capture the vortex dominated flow of helicopter rotor blades. The paper presents the validation of the setups, the optimization results and the off-design analysis of a chosen set of blades from the Pareto front. The conclusion is that the utilization of the Pareto front approach is necessary to find good rotor designs, while the utilization of high-order methods allows for efficient CFD setups.
PubDate: 2021-04-21

• Structural concept of an adaptive shock control bump spoiler
PubDate: 2021-04-21

• Structural design process and subsequent flight mechanical evaluation in
preliminary aircraft design: demonstrated on passenger ride comfort
assessment
PubDate: 2021-04-19

• HLFC-optimized retrofit aircraft design of a medium-range reference
configuration within the AVACON project
• Abstract: Abstract This paper presents an approach for the design of a retrofit aircraft with integrated, optimized hybrid laminar flow control (HLFC). The basis for this research is a medium-range reference configuration derived within the German LuFo project “Advanced Aircraft Concepts” (AVACON). For the aerodynamics, an in-house-developed process chain for flow analysis is used, which requires airfoil shapes at specific sections of a known wing geometry. To improve the accuracy, pressure distributions from the 2D flow solver MSES are first aligned to high-fidelity 3D results from DLR’s TAU code for extracted airfoils. This is done by varying parameters of the transformation methods used. Subsequently, the required suction distributions are optimized based on pre-defined criteria; these include not only the aerodynamic effects but also the needed mass flows. After optimizing the HLFC system architecture concerning mass and power offtakes, a retrofit aircraft is designed with the in-house “Multidisciplinary Integrated Aircraft Design and Optimization” (MICADO) environment. Compared to the turbulent baseline, the promising potential of the HLFC technology is demonstrated. In addition, the actual benefit of the optimization approach is evaluated in the context of overall preliminary aircraft design. This is done by redesigning the aircraft with other suction distributions and HLFC system architectures. Although it is shown that the approach leads to an overall optimum, the optimization benefit remains small. This indicates the limits of the HLFC technology as a pure add-on for initially turbulent aircraft and the need for the application of new laminar wing design methods to tap the full potential of HLFC.
PubDate: 2021-04-18

• Identification and assessment of a nonlinear dynamic actuator model for
controlling an experimental flexible wing
• Abstract: Abstract In this paper, the effect of nonlinear actuator dynamics on the performance of an active load alleviation system for an experimental flexible wing is studied. Common nonlinearities such as backlash or rate limits are considered for the control surface actuator. An aeroelastic simulation model of a flexible wing with control surface is being used. With this, a parameter study is carried out to quantify the impact of the individual nonlinearities on the overall closed-loop performance by means of describing functions. Finally, the nonlinear actuator model with parameters identified from dedicated tests is experimentally validated allowing for an accurate prediction of the expected gust load alleviation performance.
PubDate: 2021-04-16

• A numerical study of vibration-induced instrument reading capability
PubDate: 2021-04-16

• A multi-channel $$\varvec{H}_\infty$$ H ∞ preview control approach to
load alleviation design for flexible aircraft
• Abstract: Abstract Gust load alleviation functions are mainly designed for two objectives: first, alleviating the structural loads resulting from turbulence or gust encounter, and hence reducing the structural fatigue and/or weight; and second, enhancing the ride qualities, and hence the passengers’ comfort. Whilst load alleviation functions can improve both aspects, the designer will still need to make design trade-offs between these two objectives and also between various types and locations of the structural loads. The possible emergence of affordable and reliable remote wind sensor techniques (e.g., Doppler LIDAR) in the future leads to considering new types of load alleviation functions as these sensors would permit anticipating the near future gusts and other types of turbulence. In this paper, we propose a preview control design methodology for the design of a load alleviation function with such anticipation capabilities, based on recent advancements on discrete-time reduced-order multi-channel $$H_\infty$$ techniques. The methodology is illustrated on the DLR Discus-2c flexible sailplane model.
PubDate: 2021-04-12

• Fluid–structure coupling in time domain for dynamic stall using purely
Lagrangian vortex method
• Abstract: Abstract This paper presents the purely fast Lagrangian vortex method (FLVM) for the simulation of the external incompressible flows past heaving and pitching bodies with high-frequency oscillation. The Nascent vortex element is introduced to the flow field to retain the Lagrangian characteristics of the solver. The viscous effect is modeled using a core spreading method coupled with the splitting and merging spatial adaptation scheme. The particle’s velocity is calculated using Biot–Savart formulation. To accelerate computation, a fast multipole method (FMM) is employed. The validity of FLVM solver is verified by temporal and spatial convergence studies for the case of flows past an impulsively started cylinder at the Reynolds numbers ranging from 50 to 9500. The accuracy of FLVM is then confirmed for the simulation of flows around the pitching flat plate and oscillating airfoil. The time history of drag and lift coefficients and the vorticity contours show a good agreement with those reported in literature. Furthermore, the FLVM is employed to determine the flutter derivatives and flutter speed of an oscillating flat plate. Results are compared with theoretical solutions based on Theodorsen’s function. In general, the results agree well with those obtained by the inviscid theory.
PubDate: 2021-04-11

• Business model options for passenger urban air mobility
PubDate: 2021-04-09

• In memoriam Christophe Hermans
• PubDate: 2021-04-05

• Direct numerical simulation of TS-waves over suction panel steps from
manufacturing tolerances
• Abstract: Abstract To determine allowable tolerances between successive suction panels at hybrid laminar wings with suction surfaces, direct numerical simulations of Tollmien–Schlichting waves over different steps are carried out for realistic suction rates on a wind tunnel configuration. Simulations at given suction panel positions over forward and backward facing steps are carried out by the use of a high-order method for the direct simulation of Tollmien–Schlichting wave growth. Comparisons between high-fidelity direct numerical simulations and quick linear stability calculations have shown capabilities and limits of the well-validated linear stability theory design approach.
PubDate: 2021-04-01

• Loads analysis and structural optimization of a high aspect ratio,
composite wing aircraft
• Abstract: Abstract Composite structures have shown a prominent impact in the aircraft structural design. With an increasing shift towards incorporating more composite materials in the primary aircraft structure it is imperative to have corresponding design tools to simplify the design process. In the present work, a simplified implementation for composite optimization has been developed within the DLR-AE (German Aerospace Centre, Institute of Aeroelasticity) automated aeroelastic structural design framework cpacs-MONA. This paper presents the results of structural optimization of a high aspect ratio composite wing aircraft model developed in the DLR project ATLAs. The generation of almost all involved simulation models for this study is done using the in-house DLR tool ModGen. An aeroelastic trim analysis is conducted for various manoeuvre and gust conditions. A load selection process is used to determine the most relevant sizing load cases. A comparison is made between the optimization results of a composite wing and an aluminium wing to demonstrate the more favourable strength to weight ratio of the composite wing. A manoeuvre load alleviation procedure has been introduced in the load calculation process. The results show further weight savings in the design process when load alleviation is utilized due to reduction in the span wise bending moment.
PubDate: 2021-04-01

• Investigation of biogenic materials and ferroelectrets for energy
harvesting on vibrating aircraft structures
• Abstract: Abstract In this publication the application of novel piezoelectric materials for energy harvesting on vibrating aircraft structures is investigated. These materials have significant advantages over conventional piezoelectric transducer materials like piezoceramics. In particular, biogenic materials in the form of wood-based materials and ferroelectrets in the form of irradiation cross-linked polypropylene are the subject of the investigation. The material characterization in terms of mechanical and electromechanical properties is shown for both material types. For the wood materials a compression test is used as the material has load-bearing properties. The ferroelectrets provide high compliances and are therefore investigated in a tensile test for material characterisation as well as in a four-point flexural test regarding its behaviour when glued to a dynamically bending surface. Additionally an FE-model of the material model for ferroelectrets is presented, which is validated by experimental results. An estimation of the power output is given for different concepts with both kinds of materials.
PubDate: 2021-03-27

• Rotorcraft fuselage mass assessment in early design stages
• Abstract: Abstract Like the design of fixed-wing aircraft the design of rotorcraft is generally divided into the three consecutive phases of conceptual, preliminary and detailed design. During each phase the acquired results in turn serve as input for new calculations, thus increasing the detail level and information about the new concept, while uncertainties about the new design are reduced. An important aspect of the overall design process is the mass estimation in early design stages. The weight of the rotorcraft drives the design of many important components, such as the rotor(s), the propulsion system and, therefore, the required fuel. The fuselage is considered as the central structural part, since it connects all other components to each other and serves as protection of the occupants but in the past it often turned out to also be the heaviest part of all rotorcraft components. This paper shows an approach to estimate rotorcraft component masses using statistical methods based on existing rotorcraft but also an approach to use finite element methods that determine the structural airframe mass based on mission profiles, respectively, bearable load cases.
PubDate: 2021-03-25

• Method for designing multi-input system identification signals using a
compact time-frequency representation
• Abstract: Abstract A flight test campaign for system identification is a costly and time-consuming task. Models derived from wind tunnel experiments and CFD calculations must be validated and/or updated with flight data to match the real aircraft stability and control characteristics. Classical maneuvers for system identification are mostly one-surface-at-a-time inputs and need to be performed several times at each flight condition. Various methods for defining very rich multi-axis maneuvers, for instance based on multisine/sum of sines signals, already exist. A new design method based on the wavelet transform allowing the definition of multi-axis inputs in the time-frequency domain has been developed. The compact representation chosen allows the user to define fairly complex maneuvers with very few parameters. This method is demonstrated using simulated flight test data from a high-quality Airbus A320 dynamic model. System identification is then performed with this data, and the results show that aerodynamic parameters can still be accurately estimated from these fairly simple multi-axis maneuvers.
PubDate: 2021-03-12

• Analysis of rotorcraft wind turbine wake encounters using piloted
simulation
• Abstract: Abstract The use of offshore wind farms in Europe to provide a sustainable alternative energy source is now considered normal. Particularly in the North Sea, a large number of wind farms exist with a significant distance from the coast. This is becoming standard practice as larger areas are required to support operations. Efficient transport and monitoring of these wind farms can only be conducted using helicopters. As wind turbines continue to grow in size, there is a need to continuously update operational requirements for these helicopters, to ensure safe operations. This study assesses German regulations for flight corridors within offshore wind farms. A semi-empirical wind turbine wake model is used to generate velocity data for the research flight simulator AVES. The reference offshore wind turbine NREL 5 MW has been used and scaled to represent wind turbine of different sizes. This paper reports result from a simulation study concerning vortex wake encounter during offshore operations. The results have been obtained through piloted simulation for a transport case through a wind farm. Both subjective and objective measures are used to assess the severity of vortex wake encounters.
PubDate: 2021-03-09
DOI: 10.1007/s13272-021-00495-w

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