Relevant bibliographies by topics / Simulating Aircraft

Academic literature on the topic 'Simulating Aircraft'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Simulating Aircraft"

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Das, Sayantan, and Udaya Kumar. "Modeling of Bi-Polar Leader Inception and Propagation from Flying Aircraft Prior to a Lightning Strike." Atmosphere 13, no. 6 (June 9, 2022): 943. http://dx.doi.org/10.3390/atmos13060943.

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Lightning is one of the major environmental threats to aircraft. The lightning strikes during flying are mostly attributed to aircraft-triggered lightning. The first step toward designing suitable protective measures against lightning is identifying the attachment locations. For this purpose, oversimplified approaches are currently employed, which do not represent the associated discharge phenomena. Therefore, in this work, a suitable model is developed for simulating the inception and propagation of bi-polar leader discharge from the aircraft. Modeling of leader discharges requires field computation around the aircraft, which is carried out employing the Surface Charge Simulation Method (SCSM) combined with sub-modeling, which ensures the best accuracy of field computations near nosecone, wingtips, etc. A DC10 aircraft model is considered for the simulation. Simulations are performed for different pairs of leader inception points on aircraft using the developed model. Subsequently, corresponding ambient fields required for stable bi-polar discharge from aircraft are determined. These values are in the range of measured ambient fields reported in the literature. In summary, the present work has come up with a suitable model for simulating the bi-polar leader inception and propagation from the flying aircraft. Using the same, a detailed quantitative description of the discharge phenomena from the aircraft is provided.
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Correia, Diogo, and Adelino Ferreira. "Aircrafts On-Ground Dynamics Models and Simulation Software: State-of-the-Art." Sustainability 13, no. 16 (August 16, 2021): 9147. http://dx.doi.org/10.3390/su13169147.

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The aircraft is a means of transportation that operates mainly in the air; however, it starts and ends its journey on the ground. Due to the aircraft’s structural complexity, simulation tools are used to understand and to predict its behavior in its movements on the ground. Simulation tools allow adjusting the observation parameters to gather a greater amount of data than real tests and explore interactions of the aircraft and their individual components with external objects such as pavement imperfections. This review aims to collect information on how to simulate the aircraft interaction with traffic-dependent energy harvesting systems. The specifications and framework to be met by a conceptual design are explored. The different configurations for simulating the aircraft configuration result in the selection of the two-mass-spring-damper model. For the components, especially the landing gear, a deployable element for on-ground movements, several existing models capable of translating the tire are also presented, resulting in a selection of point-contact, Fiala and Unified semi-empirical models. It is verified which software can address the proposed simulation, such as GearSim from SDI-Engineering and Matlab/Simulink/Simscape Multibody from MathWorks.
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Piccone, Ashley. "Simulating lightning strikes to improve aircraft safety." Scilight 2022, no. 1 (January 7, 2022): 011111. http://dx.doi.org/10.1063/10.0009253.

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Norman, P. J., S. J. Galloway, and J. R. McDonald. "Simulating electrical faults within future aircraft networks." IEEE Transactions on Aerospace and Electronic Systems 44, no. 1 (January 2008): 99–110. http://dx.doi.org/10.1109/taes.2008.4516992.

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Lü, Zhi, Zhan Gao, and Yi Lü. "A Flight Simulator that Grouping Aircrafts Simultaneously Take off and Land in Open Grid Computing Environment." Applied Mechanics and Materials 182-183 (June 2012): 1292–97. http://dx.doi.org/10.4028/www.scientific.net/amm.182-183.1292.

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The performance of airplane in commercial airline environment is determined by, and therefore an indicator of performance measure of, the thermodynamic properties of airplane. The aim of this study was to establish the use of simulators to determine aircraft accident for a flight of airplanes and evaluate the potential of new airspace structure and airport’s runway. This indicates that there is a possibility of obtaining airplane performance from analysis and verification simulating airplane. As compared with AIRBUS Full Flight Simulator, a multiple aircrafts flight simulator that grouping aircrafts simultaneously take off and land was presented, which is basis on a parallel distributed computing in Open Grid Computing Environment (OGCE), and service oriented architecture (SOA) of software in multiple aircraft simulator, the performance of collaborative flight of multiple aircrafts is evaluated.
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Cooper, Michael, Craig Lawson, and Amir Zare Shahneh. "Simulating actuator energy consumption for trajectory optimisation." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 11 (June 13, 2017): 2178–92. http://dx.doi.org/10.1177/0954410017710271.

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This work aims to construct a high-speed simulation tool which is used to quantify the dynamic actuator power consumption of an aircraft in flight, for use within trajectory optimisation packages. The purpose is to evaluate the energy penalties of the flight control actuation system as an aircraft manoeuvre along any arbitrary trajectory. The advantage is that the approximations include major transient properties which previous steady state techniques could not capture. The output can be used to provide feedback to a trajectory optimisation process to help it compute the aircraft level optimality of any given flight path. The tool features a six degree of freedom dynamic model of an aircraft which is combined with low frequency functional electro-mechanical actuator models in order to estimate the major transient power demands. The actuator models interact with the aircraft using an aerodynamic load estimator which generates load forces on the actuators that vary as a function of flight condition and control surface demands. A total energy control system is applied for longitudinal control and a total heading control system is implemented to manage the lateral motion. The outer loop is closed using a simple waypoint following guidance system with turn anticipation and variable turn radius control. To test the model, a simple trajectory analysis is undertaken which quantifies a heading change executed with four different turn rates. The tool shows that the actuation system requires 12.8 times more electrical energy when performing a 90° turn with a radius of 400 m compared to 1000 m. A second test is performed to verify the model’s ability to track a longer trajectory under windy conditions.
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Konovalchik, A. P., M. Y. Konopelkin, M. A. Kudrov, N. M. Grevtsov, and I. A. Martynov. "Vector method in generating trajectory parameters in the air raid simulation task." Journal of «Almaz – Antey» Air and Space Defence Corporation, no. 2 (June 30, 2019): 83–91. http://dx.doi.org/10.38013/2542-0542-2019-2-83-91.

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The paper focuses on the problems of mathematical model development that allow simulating the motion of airborne objects of aircraft, missile and helicopter types. The simulation results of various spatial maneuvers are given
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Silvestrov, P. V., and S. T. Surzhikov. "Numerical Simulation of the HIFiRE-1 Ground Test." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 3 (132) (June 2020): 29–46. http://dx.doi.org/10.18698/0236-3941-2020-3-29-46.

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The paper considers the problem of simulating the HIFiRE-1 ground test numerically. The aircraft geometry is represented by either a pointed or a blunted cone combined with a flared cylinder. Our digital simulation investigated the aerodynamics of two aircraft configurations: one featuring a pointed nose, another featuring a blunted nose with a radius of 2.5 mm. We used the UST3D software developed in the Ishlinsky Institute for Problems in Mechanics RAS, to perform our aerodynamic calculations. The software is specifically designed for numerical simulations of aerodynamics and thermodynamics in high-velocity aircraft. It implements a model of viscous compressible thermally conductive gas described by a non-steady-state spatial system of Navier --- Stokes equations solved over unstructured three-dimensional tetrahedral meshes. We compared the numerical simulation results in the form of pressure distribution in the tail segment of the aircraft to the empirical data obtained via ground tests in a wind tunnel. We analysed result convergence as a function of the mesh density used. We used methods of computational aerodynamics to investigate the turbulent flow field over the computation region from the leading shock wave to the far wake for various Mach numbers and attack angles
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Sun, Ke Yan, Xiao Ying Zhao, Hong Ming Zang, and Gong Lei Zhang. "Numerical Simulation for Lightning Zoning on an Aircraft." Advanced Materials Research 850-851 (December 2013): 328–31. http://dx.doi.org/10.4028/www.scientific.net/amr.850-851.328.

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In this paper, a numerical simulation method based on fractal theory is presented to simulate lightning attachment points on airplane. The dielectric breakdown model is used to simulate the fractal growth of the lightning leaders, which meets physical mechanisms and geometric characteristics of nature lightning. The process of the airplane struck by lightning is simulated according to the relevant provisions about aircraft lightning attachment points test in standard SAE-ARP5416. The distribution of aircraft lightning attachment points are obtained through substantial repeated simulation. Because the probability distribution of lightning attachment obtained through the simulating is almost in line with those obtained through actual aircraft flight test, the validity of the proposed method is verified.
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Tovstonog, V. A., V. I. Tomak, Az A. Aliev, and A. S. Burkov. "Simulating Thermal State of High-Temperature Ceramic Samples." Herald of the Bauman Moscow State Technical University. Series Natural Sciences, no. 2 (95) (April 2021): 85–101. http://dx.doi.org/10.18698/1812-3368-2021-2-85-101.

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Developing high-velocity atmospheric aircraft equipped with ramjet engines, which use atmospheric air as the oxidizer, is an important component of aerospace technology prospects. These craft may be employed to quickly deliver payloads over intercontinental distances and as boosters for spacecraft injection into orbit. A characteristic feature of high-velocity atmospheric aircraft is a presence of sharp aerofoil edges subjected to highly oxidative airflow. This means that actual implementation of numerous hypersonic atmospheric aircraft projects largely depends on whether it is possible to develop materials that could remain stable in an oxidative atmosphere at temperatures of 2000--2500 °C. We estimated the thermal state of a structural component in the shape of a blunted wedge made out of promising refractory ceramics under flight conditions at an altitude of 22 km and a velocity of Mach 7
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Dissertations / Theses on the topic "Simulating Aircraft"

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Ericsson, Max. "Simulating Bird Strike on Aircraft Composite Wing Leading Edge." Thesis, KTH, Hållfasthetslära (Inst.), 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-103783.

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In this master thesis project the possibility to model the response of a wing when subjected to bird strike using finite elements is analyzed. Since this transient event lasts only a few milliseconds the used solution method is explicit time integration. The wing is manufactured using carbon fiber laminate. Carbon fiber laminates have orthotropic material properties with different stiffness in different directions. Accordingly, there are damage mechanisms not considered when using metal that have to be modeled when using composites. One of these damage mechanisms is delamination which occurs when cured layers inside a component become separated. To simulate this phenomenon, multiple layers of shell elements with contact in between are used as a representation of the interface where a component is likely to delaminate. By comparing experimental and simulated results the model of delamination is verified and the influence of different parameters on the results is investigated. Furthermore, studies show that modeling delamination layers in each possible layer of a composite stack is not optimal due to the fact that the global stiffness of the laminate is decreased as more layers are modeled. However, multiple layers are needed in order to mitigate the spreading of delamination and obtain realistic delaminated zones. As the laminates are comprised of carbon fiber and epoxy sheets it is of importance to include damage mechanisms inside each individual sheet. Accordingly, a composite material model built into the software is used which considers tensile and compressive stress in fiber and epoxy. The strength limits are then set according to experimental test data. The bird is modeled using a mesh free technique called Smooth Particle Hydrodynamics using a material model with properties similar to a fluid. The internal pressure of the bird model is linked to the change in volume with an Equation of State. By examining the bird models behavior compared to experimental results it is determined to have a realistic impact on structures. A model of the leading edge is then subjected to bird strike according to European standards. The wing skin is penetrated indicating that reinforcements might be needed in order to protect valuable components inside the wing structure such as the fuel tank. However, the results are not completely accurate due to the fact that there is little experimental data available regarding soft body penetration of composite laminates. As a consequence, the simulation cannot be confirmed against real experimental results and further investigations are required in order to have confidence in modeling such events. Furthermore, the delamination due to the bird strike essentially spreads across the whole model. Since only one layer of delamination is included the spread is most likely overestimated.
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Cooper, Michael Anthony. "Simulating actuator energy demands of an aircraft in flight." Thesis, Cranfield University, 2014. http://dspace.lib.cranfield.ac.uk/handle/1826/8502.

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This thesis contributes towards the discipline of whole aircraft simula- tion; modelling ight dynamics and airframe systems simultaneously. The objective is to produce estimates of the dynamic power consumption char- acteristics of the primary ight control actuation system when executing manoeuvres. Three technologies are studied; the classic hydraulic actuators and the electromechanical and electro-hydrostatic types that are commonly associated with the more electric aircraft. Models are produced which represent the ight dynamics of an aircraft; these are then combined with low frequency dynamic functional models of the three actuator technologies and ight controllers. The result is a model, capable of faster than real time simulation, which produces estimates of ac- tuator power consumption as the aircraft follows prede ned trajectories. The model is used to quantify the energy consumption as a result of di erent manoeuvre rates when executing banked turns. The result from an actuation system point of view alone is that the lower the turn rate, the lower the overall energy used. The tradeo is that the turn radius becomes larger. The use of the model can be extended to assist with additional design challenges such as actuator design and speci cation. Using methods to size actuators based on stall force and no load speed properties leads to oversizing of the control system. Performing dynamic analyses is usually a combined task of laboratory based actuator test rigs stimulated by input data gathered during ight tests. The model in this work provides a method of generating data for preliminary design; therefore reducing the amount of ight testing required in a design and certi cation programme. The major results discovered using the tools developed in this thesis are that a hydraulically powered aileron uses 4.23% more energy to achieve a turn at a heading rate of 0.03 rad/s compared to a 0.005 rad/s manoeuvre in the same conditions. The electromechanical actuator (EMA) uses 1.67% more and the electrohydrostatic actuator (EHA) uses 1.54% more to achieve the same turns. It implies reduced turn rate turns would have the largest bene t for reducing energy consumption in current hydraulically powered actuation systems, compared to electrical actuators.
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Covarrubias, Gillin Daniel, Gustav Arneving, Joel Alexandersson, Persson Leon Li, Lukas Olsson, Martin Banck, and Max Björkander. "Simulera beteende av stridsflygplan med hjälp av AI : Simulating behavior of combat aircraft with AI." Thesis, Linköpings universitet, Institutionen för datavetenskap, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-177689.

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I denna rapport beskrivs ett kandidatarbete som utfördes på beställning av Saab. Det kunden var intresserad av var att simulera beteende av stridsflygplan med hjälp av AI-tekniker. Projektgruppen använde maskininlärningsalgoritmen Q-inlärning för att försöka uppnå detta. Utöver detta utvecklade gruppen en egen simulator som en miljö för kurvstrider mellan simulerade stridsflygplan. Projektet utfördes av sju studenter på programmen civilingenjör inom datateknik och civilingenjör inom mjukvaruteknik vid Linköpings universitet. Resultatet av projektet blev att ett tillfredsställande beteende för det AI-styrda stridsflygplanet ej kunde uppnås, dock kunde ett förbättrat beteende observeras. Mer forskning på området behövs dock för att åstadkomma mer tillfredsställande resultat. Förstärkningsinlärning visar sig vara lovande som metod för att lösa problemet inför framtiden. Diskussioner och insikter om vad som kan göras för att vidareutveckla AI:n för en bättre prestation hos det simulerade planet dokumenterades. I slutet av rapporten finns även individuella bidrag skrivna av var och en av medlemmarna i projektgruppen. De ämnena som valdes berörde projektet, antingen som en del av utvecklingsprocessen eller som en del av temat till projektet.
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Shah, Harshil Dipen. "An Assessment of the CFD Effectiveness for Simulating Wing Propeller Aerodynamics." Thesis, Virginia Tech, 2020. http://hdl.handle.net/10919/98668.

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Today, we see a renewed interest in aircraft with multiple propellers. To support conceptual design of these vehicles, one of the major needs is a fast and accurate method for estimating wing aerodynamic characteristics in the presence of multiple propellers. For the method to be effective, it must be easy to use, have rapid turnaround time and should be able to capture major wing–propeller interaction effects with sufficient accuracy. This research is primarily motivated by the need to assess the effectiveness of computational fluid dynamics (CFD) for simulating aerodynamic characteristics of wings with multiple propellers. The scope of the present research is limited to investigating the interaction between a single tractor propeller and a wing. This research aims to compare computational results from a Reynolds-Averaged Navier-Stokes (RANS) method, StarCCM+, and a vortex lattice method (VLM), VSP Aero. Two configurations that are analysed are 1) WIPP Configuration (Workshop for Integrated Propeller Prediction) 2) APROPOS Configuration. For WIPP, computational results are compared with measured lift and drag data for several angles of attack and Mach numbers. StarCCM+ results of wake flow field are compared with WIPP's wake survey data. For APROPOS, computed data for lift-to-drag ratio of the wing are compared with test data for multiple vertical and spanwise locations of the propeller. The results of the simulations are used to assess the effectiveness of the two CFD methods used in this research.
Master of Science
Today, we see a renewed interest in aircraft with multiple propellers due to an increasing demand for vehicles which fly short distances at low altitudes, be it flying taxis, delivery drones or small passenger aircrafts. To support conceptual design of vehicles, one of the major needs is a fast and accurate method for estimating wing aerodynamic characteristics in the presence of multiple propellers. For the method to be effective, it must be easy to use, have rapid turnaround time and should be able to capture major wing–propeller inter- action effects with sufficient accuracy. This research is primarily motivated by the need to assess the effectiveness of computational fluid dynamics (CFD) for simulating aerodynamic characteristics of wings with multiple propellers. Then only can we can take full advantage of the capabilities of the CFD methods and support design of emerging propeller driven air vehicles with an appropriate level of confidence. This research aims to compare high level methods with increasingly complex geometries and realistic models of physics like Reynolds Averaged Navier Stokes (RANS) and low level methods that rely on simplified geometry and simplified physics models like Vortex Lattice Methods (VLM). We will analyse multiple configurations and validate them against experi- mental data and thus assessing the effectiveness of the CFD models. This research investigates two configurations, 1) WIPP configuration 2) APROPOS config- uration, for which experimental data is available. The results of the simulations are used to assess the effectiveness of the two CFD methods used in this research.
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Chevrolat, Sofia. "Automatic Fusion of Fidelity sources ofAerodynamic Data : Simulating Aircraft Stability And Control Characteristics for Use in Conceptual Design." Thesis, KTH, Aeroakustik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-30614.

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CFD use has increased signi cantly in airplane conception, and the industry demands more andmore precise and reliable tools. This was the goal of the SimSAC project. The result is CEASIOM,a computerized environment made of several modules for the design and prediction of the aircraft'scharacteristics. It constructs aerodynamic tables used in the prediction of the characteristics of anaircraft. In simple ight conditions, simple computation methods are used, whereas in complex ightconditions,involving turbulences, more advanced methods are used. This reduces the computationalcost, but the tables resulting from di erent delity sources must be fused to obtain a coherent tablecovering the whole ight envelope.The goal of this project was to realize the fusion. Additionally, a lter and a custom-made mapping toenhance the accuracy of the results from the fusion were required. The addition of helpful visualizationtools was suggested. The whole should be integrated in the CEASIOM interface as a Fusion module.For this, 6 functions were coded. The rst one loads the data sets. The second, myplot, allows theengineer by plotting the data in a coherent way, to spot any big mistakes or incompatibility in thedata sets. The third, myvisual, displays the elements spotted as outliers or potentially out of pattern.This is used by the next function, my ltermap, to lter out the erroneous data. This function alsorealizes the custom-made mapping.The fth function, myfusion, fuses the data and saves it in a .xmlCEASIOM formatted structure to be used by the next CEASIOM module. The sixth function ltersout, in the same way as my ltermap, the outliers from the fused data, and saves the ltered fused dataset in a .xml CEASIOM formatted structure. Finally, a Matlab GUI was implemented and integratedinto the main CEASIOM interface.The module works perfectly, except for the mapping part, that needs a few readjustments.
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Swift, Adam. "Simulation of aircraft aeroelasticity." Thesis, University of Liverpool, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.569519.

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Aeroelastic phenomena such as flutter can have a detrimental effect on aircraft performance and can lead to severe damage or destruction. Buffet leads to a re- duced fatigue life and therefore higher operating costs and a limited performance envelope. As such the simulation of these aeroelastic phenomena is of utmost importance. Computational aeroelasticity couples computational fluid dynamics and computational structural dynamics solvers through the use of a transforma- tion method. There have been interesting developments over the years towards more efficient methods for predicting the flutter boundaries based upon the sta- bility of the system of equations. This thesis investigates the influence of transformation methods on the flutter boundary predition and considers the simulation of shock-induced buffet of a transport wing. This involves testing a number of transformation methods for their effect on flutter boundaries for two test cases and verifying the flow solver for shock-induced buffet over an aerofoil. This will be followed by static aeroelastic calculations of an aeroelastic wing. It is shown that the transformation methods have a significant effect on the predicted flutter boundary. Multiple transformation methods should be used to build confidence in the results obtained, and extrapolation should be avoided. CFD predictions are verified for buffet calculations and the mechanism behind shock-oscillation of the BGK No. 1 aerofoil is investigated. The use of steady calculations to assess if a case may be unsteady is considered. Finally the static aeroelastic response of the ARW-2 wing is calculated and compared against ex- perimental results.
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Zurheide, Frank Thomas. "Numerical simulation of aircraft vortices." Aachen Shaker, 2009. http://d-nb.info/998626899/04.

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Hogg, C. R. "Simulation of ground handling of taxiing aircraft." Thesis, University of Brighton, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.334354.

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Li, Bo Lim Alvin S. "Multiple UAV simulation with multiresolution multistage models and decision support." Auburn, Ala., 2008. http://hdl.handle.net/10415/1547.

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Ismail, Ibrahim H. "Simulation of aircraft gas turbine engine." Thesis, University of Hertfordshire, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.303465.

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Books on the topic "Simulating Aircraft"

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Anderson, David N. Scaling methods for simulating aircraft in-flight icing encounters. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1997.

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Healey, J. Val. Simulating the helicopter-ship interface as an alternative to current methods of determining the safe operating envelopes. Monterey, Calif: Naval Postgraduate School, 1986.

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L, Lewis Frank, ed. Aircraft control and simulation. New York: Wiley, 1992.

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L, Lewis Frank, ed. Aircraft control and simulation. 2nd ed. Hoboken, N.J: J. Wiley, 2003.

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Karkas, George. The simulation of flexible aircraft. [Downsview, Ont.]: University of Toronto, Institute for Aerospace Studies, 2003.

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Napolitano, Marcello R. Aircraft dynamics: From modeling to simulation. Hoboken, NJ: Wiley, 2012.

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Holmes, K. P. ACSL simulation for aircraft control design THESIS. Manchester: UMIST, 1988.

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Oliva, A. P. A simulation of the Boeing B-747 aircraft. Cranfield, Bedford, England: Cranfield College of Technology, College of Aeronautics, 1992.

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Development, North Atlantic Treaty Organization Advisory Group for Aerospace Research and. Aircraft and sub-system certification by piloted simulation. Neuilly sur Seine, France: AGARD, 1994.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Aircraft and sub-system certification by piloted simulation. Neuilly-sur-Seine: AGARD, 1994.

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Book chapters on the topic "Simulating Aircraft"

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Schmidt, William F., and Otto H. Zinke. "Improved Measurements of Samples Simulating Corrosion in Lap-Seams of Aluminum Aircraft." In Review of Progress in Quantitative Nondestructive Evaluation, 1733–39. Boston, MA: Springer US, 1996. http://dx.doi.org/10.1007/978-1-4613-0383-1_226.

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Zinke, Otto H., and William F. Schmidt. "Modified AC Magnetic Bridge Scanning Patterns of Samples Simulating Flaws in Aircraft Seams." In Review of Progress in Quantitative Nondestructive Evaluation, 2011–19. Boston, MA: Springer US, 1993. http://dx.doi.org/10.1007/978-1-4615-2848-7_258.

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Mathaisel, Dennis F. X., and Husni Idris. "Aircraft Ground Movement Simulation." In Operations Research in the Airline Industry, 189–227. Boston, MA: Springer US, 1998. http://dx.doi.org/10.1007/978-1-4615-5501-8_7.

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Murray-Smith, D. J. "Case Study II — An Aircraft Automatic Landing System." In Continuous System Simulation, 163–73. Boston, MA: Springer US, 1995. http://dx.doi.org/10.1007/978-1-4615-2504-2_11.

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Buethe, Inka, Nicolas Dominguez, Henning Jung, Claus-Peter Fritzen, Damien Ségur, and Frédéric Reverdy. "Path-Based MAPOD Using Numerical Simulations." In Smart Intelligent Aircraft Structures (SARISTU), 631–42. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_29.

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Schütte, Andreas, Gunnar Einarsson, Britta Schöning, Axel Raichle, Thomas Alrutz, Wulf Mönnich, Jens Neumann, and Jörg Heinecke. "Numerical simulation of maneuvering combat aircraft." In New Results in Numerical and Experimental Fluid Mechanics V, 103–11. Berlin, Heidelberg: Springer Berlin Heidelberg, 2006. http://dx.doi.org/10.1007/978-3-540-33287-9_13.

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Zhanjun, Chen, Fu Zhichao, Lv Jinan, and Liu Ziqiang. "Nonlinear Flight Dynamics of Very Flexible Aircraft." In Computational and Experimental Simulations in Engineering, 119–23. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-27053-7_12.

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Colombo, Paolo. "Designing the Next Generation of Aircraft with Simulation." In Flexible Engineering Toward Green Aircraft, 1–7. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-36514-1_1.

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Lal, Ratan, Aaron McKinnis, Dustin Hauptman, Shawn Keshmiri, and Pavithra Prabhakar. "Formally Verified Switching Logic for Recoverability of Aircraft Controller." In Computer Aided Verification, 566–79. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-81685-8_27.

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AbstractIn this paper, we investigate the design of a safe hybrid controller for an aircraft that switches between a classical linear quadratic regulator (LQR) controller and a more intelligent artificial neural network (ANN) controller. Our objective is to switch safely between the controllers, such that the aircraft is always recoverable within a fixed amount of time while allowing the maximum time of operation for the ANN controller. There is a priori known safety zone for the LQR controller operation in which the aircraft never stalls, over accelerates, or exceeds maximum structural loading, and hence, by switching to the LQR controller just before exiting this zone, one can guarantee safety. However, this priori known safety zone is conservative, and therefore, limits the time of operation for the ANN controller. We apply reachability analysis to expand the known safety zone, such that the LQR controller will always be able to drive the aircraft back to the safe zone from the expanded zone (“recoverable zone") within a fixed duration. The “recoverable zone" extends the time of operation of the ANN controller. We perform simulations using the hybrid controller corresponding to the recoverable zone and observe that the design is indeed safe.
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Sacharny, David, and Thomas Henderson. "Agent Based Modeling and Simulation." In Lane-Based Unmanned Aircraft Systems Traffic Management, 121–34. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-98574-5_8.

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Conference papers on the topic "Simulating Aircraft"

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Totah, Joseph, and David Kinney. "Simulating conceptual and developmental aircraft." In AIAA Modeling and Simulation Technologies Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-4161.

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Schauerhamer, Daniel G., and Stephen K. Robinson. "Simulating Aircraft Wake Vortices with OVERFLOW." In 33rd AIAA Applied Aerodynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-3301.

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Hess, Robert. "Simulating aircraft subsystems using non-homogeneous automata networks." In Modeling and Simulation Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-4499.

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Kenney, P. Sean, and Mark Croom. "Simulating The ARES Aircraft In The Mars Environment." In 2nd AIAA "Unmanned Unlimited" Conf. and Workshop & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-6579.

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Rizzi, Arthur. "Modeling & Simulating Aircraft Stability & Control - SimSAC Project." In AIAA Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-8238.

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Singh, Arnav Deo, and Fernando Vanegas Alvarez. "Simulating GPS-denied Autonomous UAV Navigation for Detection of Surface Water Bodies." In 2020 International Conference on Unmanned Aircraft Systems (ICUAS). IEEE, 2020. http://dx.doi.org/10.1109/icuas48674.2020.9213927.

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Warncke, Katharina, Amsini Sadiki, Max Staufer, Christian Hasse, and Johannes Janicka. "Towards Primary Breakup Simulation of a Complete Aircraft Nozzle at Realistic Aircraft Conditions." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14597.

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Abstract Predicting details of aircraft engine combustion by means of numerical simulations requires reliable information about spray characteristics from liquid fuel injection. However, details of liquid fuel injection are not well documented. Indeed, standard droplet distributions are usually utilized in Euler-Lagrange simulations of combustion. Typically, airblast injectors are employed to atomize the liquid fuel by feeding a thin liquid film in the shear zone between two swirled air flows. Unfortunately, droplet data for the wide range of operating conditions during a flight is not available. Focusing on numerical simulations, Direct Numerical simulations (DNS) of full nozzle designs are nowadays out of scope. Reducing numerical costs, but still considering the full nozzle flow, the embedded DNS methodology (eDNS) has been introduced within a Volume of Fluid framework (Sauer et al., Atomization and Sprays, vol. 26, pp. 187–215, 2016). Thereby, DNS domain is kept as small as possible by reducing it to the primary breakup zone. It is then embedded in a Large Eddy Simulation (LES) of the turbulent nozzle flow. This way, realistic turbulent scales of the nozzle flow are included, when simulating primary breakup. Previous studies of a generic atomizer configuration proved that turbulence in the gaseous flow has significant impact on liquid disintegration and should be included in primary breakup simulations (Warncke et al., ILASS Europe, Paris, 2019). In this contribution, an industrial airblast atomizer is numerically investigated for the first time using the eDNS approach. The complete nozzle geometry is simulated, considering all relevant features of the flow. Three steps are necessary: 1. LES of the gaseous nozzle flow until a statistically stationary flow is reached. 2. Position and refinement of the DNS domain. Due to the annular nozzle design the DNS domain is chosen as a ring. It comprises the atomizing edge, where the liquid is brought between inner and outer air flow, and the downstream primary breakup zone. 3. Start of liquid fuel injection and primary breakup simulation. Since the simulation of the two-phase DNS and the LES of the surrounding nozzle flow are conducted at the same time, turbulent scales of the gas flow are directly transferred to the DNS domain. The applicability of eDNS to full nozzle designs is demonstrated and details of primary breakup at the nozzle outlet are presented. In particular a discussion of the phenomenological breakup process and spray characteristics is provided.
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Zhonghua Li and Yan Chen. "Design of aircraft Air Data acquisition and control simulating system." In 2011 2nd International Conference on Artificial Intelligence, Management Science and Electronic Commerce (AIMSEC). IEEE, 2011. http://dx.doi.org/10.1109/aimsec.2011.6010163.

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Schauerhamer, Daniel G., and Stephen Robinson. "Towards Simulating the Evolution of Aircraft Wake Vortices with OVERFLOW." In 55th AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-0956.

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Glass, Robert, Waleed Said, and James Thom. "EXEPS: An Expert System for Simulating Aircraft Electric Power Systems." In International Pacific Air & Space Technolgy Conference. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1991. http://dx.doi.org/10.4271/912049.

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Reports on the topic "Simulating Aircraft"

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Fernandez, Ruben, Hernando Lugo, and Georfe Dulikravich. Aerodynamic Shape Multi-Objective Optimization for SAE Aero Design Competition Aircraft. Florida International University, October 2021. http://dx.doi.org/10.25148/mmeurs.009778.

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The SAE Regular Class Aero Design Competition requires students to design a radio-controlled aircraft with limits to the aircraft power consumption, take-off distance, and wingspan, while maximizing the amount of payload it can carry. As a result, the aircraft should be designed subject to these simultaneous and contradicting objectives: 1) minimize the aerodynamic drag force, 2) minimize the aerodynamic pitching moment, and 3) maximize the aerodynamic lift force. In this study, we optimized the geometric design variables of a biplane configuration using 3D aerodynamic analysis using the ANSYS Fluent. Coefficients of lift, drag, and pitching moment were determined from the completed 3D CFD simulations. Extracted coefficients were used in modeFRONTIER multi-objective optimization software to find a set of non-dominated (Pareto-optimal or best trade-off) optimized 3D aircraft shapes from which the winner was selected based to the desired plane performance.
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Carico, Dean, and Singli Garcia-Otero. Tilt Rotor Aircraft Modeling Using a Generic Simulation Structure,. Fort Belvoir, VA: Defense Technical Information Center, December 1995. http://dx.doi.org/10.21236/ada305253.

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Jordan, J. K., S. A. Bayyuk, and S. D. Habchi. Coupled VSTOL Aircraft and Ship Airwake Turbulent Flow Simulation Model. Fort Belvoir, VA: Defense Technical Information Center, June 2002. http://dx.doi.org/10.21236/ada402936.

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Branson, Roger, Robert Anschuetz, Karen Bourgeois, and Paul Kelly. Advanced Distributed Simulation Technology Advanced Rotary Wing Aircraft. Software Reusability Report. Fort Belvoir, VA: Defense Technical Information Center, April 1994. http://dx.doi.org/10.21236/ada280434.

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Imhof, Greg, and Bill Schork. Using Simulation to Optimize Ski Jump Ramp Profiles for STOVL Aircraft. Fort Belvoir, VA: Defense Technical Information Center, December 1999. http://dx.doi.org/10.21236/ada378145.

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Biezad, Daniel J. Investigation of Dynamic Structural Models Suitable for the Simulation of Large Aircraft. Fort Belvoir, VA: Defense Technical Information Center, November 1999. http://dx.doi.org/10.21236/ada383217.

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Branson, Roger, and Robert Anschuetz. Advanced Distributed Simulation Technology Advanced Rotary Wing Aircraft. System/Segment Specification. Volume 5. Simulation System Module AH-64D Kit. Fort Belvoir, VA: Defense Technical Information Center, March 1994. http://dx.doi.org/10.21236/ada280433.

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Anschuetz, Robert R., and II. Advanced Distributed Simulation Technology Advanced Rotary Wing Aircraft. Software Programmer's Manual Visual System Module. Fort Belvoir, VA: Defense Technical Information Center, April 1994. http://dx.doi.org/10.21236/ada280260.

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Gann, Richard G., and Richard G. Gann. Fire suppression system performance of alternative agents in aircraft engine and dry bay laboratory simulations. Gaithersburg, MD: National Institute of Standards and Technology, 1995. http://dx.doi.org/10.6028/nist.sp.890v1.

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Gann, Richard G., and Richard G. Gann. Fire suppression system performance of alternative agents in aircraft engine and dry bay laboratory simulations. Gaithersburg, MD: National Institute of Standards and Technology, 1995. http://dx.doi.org/10.6028/nist.sp.890v2.

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