Relevant bibliographies by topics / Aerospace engineering – Simulation methods

Academic literature on the topic 'Aerospace engineering – Simulation methods'

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Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Aerospace engineering – Simulation methods"

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Dai, Honghua, and Xiaokui Yue. "Preface: Nonlinear Computational and Control Methods in Aerospace Engineering." Computer Modeling in Engineering & Sciences 122, no. 1 (2020): 1–4. http://dx.doi.org/10.32604/cmes.2020.09126.

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Heinz, Stefan, Joachim Peinke, and Bernhard Stoevesandt. "Cutting-Edge Turbulence Simulation Methods for Wind Energy and Aerospace Problems." Fluids 6, no. 8 (August 16, 2021): 288. http://dx.doi.org/10.3390/fluids6080288.

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The availability of reliable and efficient turbulent flow simulation methods is highly beneficial for wind energy and aerospace developments. However, existing simulation methods suffer from significant shortcomings. In particular, the most promising methods (hybrid RANS-LES methods) face divergent developments over decades, there is a significant waste of resources and opportunities. It is very likely that this development will continue as long as there is little awareness of conceptional differences of hybrid methods and their implications. The main purpose of this paper is to contribute to such clarification by identifying a basic requirement for the proper functioning of hybrid RANS-LES methods: a physically correct communication of RANS and LES modes. The state of the art of continuous eddy simulations (CES) methods (which include the required mode communication) is described and requirements for further developments are presented.
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Perfect, P., M. D. White, G. D. Padfield, and A. W. Gubbels. "Rotorcraft simulation fidelity: new methods for quantification and assessment." Aeronautical Journal 117, no. 1189 (March 2013): 235–82. http://dx.doi.org/10.1017/s0001924000007983.

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AbstractFlight simulators are integral to the design/development, testing/qualification, training and research communities and their utilisation is ever expanding. The use of flight simulation to provide a safe environment for pilot training, and in research and development, must be underpinned by quantification of simulator fidelity. While regulatory simulator standards exist for flight training simulators and new standards are in development, previous research has shown that current standards do not provide a fully quantitative approach for assessing simulation fidelity, especially in a research environment. This paper reports on progress made in a research project at the University of Liverpool (Lifting Standards), in which new predicted and perceptual measures of simulator fidelity have been developed. The new metrics have been derived from handling qualities engineering practice. Results from flight tests on the National Research Council (Canada) Bell 412 ASRA research aircraft and piloted simulation trials using the HELIFLIGHT-R simulator at Liverpool are presented to show the efficacy of adopting a handling qualities approach for fidelity assessment. Analysis of the new metrics has shown an appropriate degree of sensitivity to differences between flight and simulation.
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Shi, Renhe, Teng Long, Nianhui Ye, Yufei Wu, Zhao Wei, and Zhenyu Liu. "Metamodel-based multidisciplinary design optimization methods for aerospace system." Astrodynamics 5, no. 3 (September 2021): 185–215. http://dx.doi.org/10.1007/s42064-021-0109-x.

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AbstractThe design of complex aerospace systems is a multidisciplinary design optimization (MDO) problem involving the interaction of multiple disciplines. However, because of the necessity of evaluating expensive black-box simulations, the enormous computational cost of solving MDO problems in aerospace systems has also become a problem in practice. To resolve this, metamodel-based design optimization techniques have been applied to MDO. With these methods, system models can be rapidly predicted using approximate metamodels to improve the optimization efficiency. This paper presents an overall survey of metamodel-based MDO for aerospace systems. From the perspective of aerospace system design, this paper introduces the fundamental methodology and technology of metamodel-based MDO, including aerospace system MDO problem formulation, metamodeling techniques, state-of-the-art metamodel-based multidisciplinary optimization strategies, and expensive black-box constraint-handling mechanisms. Moreover, various aerospace system examples are presented to illustrate the application of metamodel-based MDOs to practical engineering. The conclusions derived from this work are summarized in the final section of the paper. The survey results are expected to serve as guide and reference for designers involved in metamodel-based MDO in the field of aerospace engineering.
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Bieniek, D., R. Luckner, I. De Visscher, and G. Winckelmans. "Simulation Methods for Aircraft Encounters with Deformed Wake Vortices." Journal of Aircraft 53, no. 6 (November 2016): 1581–96. http://dx.doi.org/10.2514/1.c033790.

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Sun, Fuyu, Hua Wang, and Jianping Zhou. "Research and development techniques for early-warning satellite systems using concurrent engineering." Concurrent Engineering 26, no. 3 (April 23, 2018): 215–30. http://dx.doi.org/10.1177/1063293x18768668.

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An early-warning satellite system is a complex project that requires the participation of many aerospace academies and scientific institutions. In terms of software programming, this study proposes a new simulation integrated management platform for the analysis of parallel and distributed systems. The platform facilitates the design and testing of both applications and architectures. To improve the efficiency of project development, new early-warning satellite systems are designed based on the simulation integrated management platform. In terms of project management, this study applies concurrent engineering theory to aerospace engineering and presents a method of collaborative project management. Finally, through a series of experiments, this study validates the simulation integrated management platform, models, and project management method. Furthermore, the causes of deviation and prevention methods are explained in detail. The proposed simulation platform, models, and project management method provide a foundation for further validations of autonomous technology in space attack–defense architecture research.
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Albinsson, Anton, Fredrik Bruzelius, Bengt Jacobson, and Shenhai Ran. "Validation of vehicle-based tyre testing methods." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 233, no. 1 (June 20, 2018): 18–27. http://dx.doi.org/10.1177/0954407018777581.

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The development process for passenger cars is both time- and resource-consuming. Full vehicle testing is an extensive part of the development process that consumes large amount of resources, especially within the field of vehicle dynamics and active safety. By replacing physical testing with complete vehicle simulations, both the development time and cost can potentially be reduced. This requires accurate simulation models that represent the real vehicle. One major challenge with full vehicle simulation models is the representation of tyres in terms of force and moment generation. The force and moment generation of the tyres is affected by both operating conditions and road surface. Vehicle-based tyre testing offers a fast and efficient way to rescale force and moment tyre models to different road surfaces, in this study the Pacejka 2002 model. The resulting tyre model is sensitive to both the operating conditions during testing and the road surface used. This study investigates the influence of the slip angle sweep rate and road surface on the lateral tyre force characteristics of the fitted tyre model. Tyre models fitted to different manoeuvres are compared and the influence on the full vehicle behaviour is investigated in IPG Carmaker. The results show that by using the wrong road surface, the resulting tyre model can end up outside the tolerances specified by the ISO standard for vehicle simulation model verification in steady-state cornering. The use of Pacejka 2002 models parameterized in a steady-state manoeuvre to simulate the vehicle behaviour in sine-with-dwell manoeuvres is also discussed.
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Huang, Shizhuo, Qian Chen, Yuwei Cheng, Jinyu Xian, and Zhengqi Tai. "Supersonic Combustion Modeling and Simulation on General Platforms." Aerospace 9, no. 7 (July 7, 2022): 366. http://dx.doi.org/10.3390/aerospace9070366.

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Supersonic combustion is an advanced technology for the next generation of aerospace vehicles. In the last two decades, numerical simulation has been widely used for the investigation on supersonic combustion. In this paper, the modeling and simulation of supersonic combustion on general platforms are thoroughly reviewed, with emphasis placed on turbulence modeling and turbulence–chemistry interactions treatment which are both essential for engineering computation of supersonic combustion. It is found that the Reynolds-averaged Navier–Stokes methods on the general platforms have provided useful experience for the numerical simulation in engineering design of supersonic combustion, while the large eddy simulation methods need to be widely utilized and further developed on these platforms. Meanwhile, the species transport models as a kind of reasonable combustion model accounting for the turbulence–chemistry interactions in supersonic combustion have achieved good results. With the development of new combustion models, especially those designed in recent years for high-speed combustion, the turbulence–chemistry interactions treatment for numerical simulation of supersonic combustion based on general platforms is expected to be further mature in the future.
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Cao, Yihua, Kungang Yuan, and Xiaoyong Li. "Computational Methods for Simulation of Flow Around Helicopter Engine Inlet." Journal of Aircraft 43, no. 1 (January 2006): 141–46. http://dx.doi.org/10.2514/1.14679.

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Yoh, Jack J., and Xiaolin Zhong. "New Hybrid Runge-Kutta Methods for Unsteady Reactive Flow Simulation." AIAA Journal 42, no. 8 (August 2004): 1593–600. http://dx.doi.org/10.2514/1.3843.

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Dissertations / Theses on the topic "Aerospace engineering – Simulation methods"

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Boles, John Arthur. "Hybrid Large-Eddy Simulation/Reynolds-Averaged Navier-Stokes Methods and Predictions for Various High-Speed Flows." NCSU, 2009. http://www.lib.ncsu.edu/theses/available/etd-08122009-170842/.

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Hybrid Large Eddy Simulation/Reynolds-Averaged Navier-Stokes (LES/RANS) simulations of several high-speed flows are presented in this work. The solver blends a Menter BSL two-equation model for the RANS part of the closure with a Smagorisnky sub-grid model for the LES component. The solver uses a flow-dependent blending function based on wall distance and a modeled form of the Taylor micro-scale to transition from RANS to LES. Turbulent fluctuations are initiated and are sustained in the inflow region using a recycling/rescaling technique. A new multi-wall recycling/rescaling technique is described and tested. A spanwise-shifting method is introduced that is intended to alleviate unphysical streamwise streaks of high- and low-momentum fluid that appear in the time-averaged solution due to the recycling procedure. Simulations of sonic injection of air, helium and ethylene into a Mach 2 cross-flow of air are performed. Also, simulations of Mach 5 flow in a subscale inlet/isolator configuration with and without back-pressuring are performed. Finally, a Mach 3.9 flow through a square duct is used as an initial test case for the new multi-wall recycling and rescaling method as well as a multi-wall shifting procedure. A discussion of the methods, implementation and results of these simulations is included.
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Butler, William M. "The Impact of Simulation-Based Learning in Aircraft Design on Aerospace Student Preparedness for Engineering Practice: A Mixed Methods Approach." Diss., Virginia Tech, 2012. http://hdl.handle.net/10919/27601.

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It has been said that engineers create that which never was. The university experience is a key component in preparing engineers who support the creation of products and systems that improve the world we live in. The way in which engineers have been trained in universities has changed throughout history in America, moving from an apprentice-like approach to the still-used engineer scientist. Some in industry and academia feel that this model of engineer preparation needs to change in order to better address the complexities of engineering in the 21st century, and help fill a perceived gap between academic preparation and 21st century industrial necessity. A new model for student preparation centering on engineering design called the Live Simulation Based Learning (LSBL) approach is proposed based upon the theories of situated learning, game-based learning, epistemic frames, and accidental competencies. This dissertation discusses the results of a study of the application of LSBL in a two term capstone design class in aerospace engineering aircraft design at Virginia Tech. It includes LSBLâ s impact on student professional and technical skills in relation to aerospace engineering design practice. Results indicate that the participants found the LSBL experience to be more engaging than the traditional lecture approach and does help students respond and think more like aerospace engineering practicing professionals and thus begin to address the â gapâ between academia and industry.
Ph. D.
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Adams, Ryan, and s200866s@student rmit edu au. "Evaluation of computerised methods of design optimisation and its application to engineering practice." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2006. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20070130.122013.

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The ongoing drive for lighter and more efficient structural components by the commercial engineering industry has resulted in the rapid adoption of the finite element method (FE) for design analysis. Satisfied with the success of finite elements in reducing prototyping costs and overall production times, the industry has begun to look at other areas where the finite element method can save time, and in particular, improve designs. First, the mathematical methods of optimisation, on which the methods of structural design improvement are based, are presented. This includes the methods of: topology, influence functions, basis vectors, geometric splines and direct sensitivity methods. Each method is demonstrated with the solution of a sample structural improvement problem for various objectives (frequency, stress and weight reduction, for example). The practical application of the individual methods has been tested by solving three structural engineering problems sourced from the automotive engineering industry: the redesign of two different front suspension control arms, and the cost-reduction of an automatic brake tubing system. All three problems were solved successfully, resulting in improved designs. Each method has been evaluated with respect the practical application, popularity of the method and also any problems using the method. The solutions presented in each section were all solved using the FE design improvement software ReSHAPE from Advea Engineering Pty. Ltd.
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Taha, Wael. "Simulation of unsteady 3-D viscous compressible propeller flow by finite element method." Thesis, McGill University, 2004. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=80145.

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The flow produced by a rotating propeller is inherently unsteady and three-dimensional. Conventional design of propellers uses blade-element theory but becomes inaccurate in capturing three-dimensional vortical and compressible effects at the tips, as well as the effect on downstream bodies. A propeller is always attached to a fixed component that affects its performance, thus the need arises to couple a fixed domain to a rotating domain in an unsteady aerodynamic simulation. A finite element formulation for the simulation of propellers is presented in terms of the Reynolds-averaged Navier-Stokes equations for unsteady, three-dimensional, viscous, compressible flows. The first step consists of preparing a mesh containing two separate domains interfacing at a virtual surface. Then, simulation is run to obtain an initial solution. This step highlights the live/dead interfacing scheme between the fixed and rotating domains without mesh movement. Finally the unsteady simulation performs interpolations at each time step with node movement until a periodic steady state is reached. Mesh movement can be treated by either an ALE formulation or a rotating frame of reference correction. Two test cases are used to validate the code: a two-dimensional pitching airfoil in transonic flow and a 3-bladed 5868-9 propeller with a liquid cooled nacelle.
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Senneberg, Sofia. "Methods for validating a flight mechanical simulation model for dynamic maneuvering." Thesis, KTH, Flygdynamik, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-299412.

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Flight mechanical simulators play an important role in the design steps during development of a new aircraft. To be able to simulate and evaluate flight mechanical characteristics during development it is important to minimize development time and cost while keeping flight safety high during early flights. The aim of the project presented in this thesis is to develop a method for validating a flight mechanical simulator against flight test data from dynamic maneuvering. An important part in this thesis is about how deviations in the result data can be found and analyzed, for example deviations between aircraft individuals or store configurations. The work presented here results in a good model for comparison of a big amount of data where it is easy to backtrace where the deviation occurs.
Flygmekaniska simulatorer är av stor betydelse under utvecklingen av ett nytt stridsflygplan. Möjligheten att simulera och utvärdera under tidens gång har stor betydelse både ur tid- och kostnadsbesparings perspektiv men även ur flygsäkerhetsperspektiv när det är dags för första flygning. Syftet med det här projektet är att utveckla en metod för jämförelse mellan simulering och flygprov för att validera hur bra den flygmekaniska simulatorn kan förutspå flygplansbeteende. En viktig del i projektet syftar till hur skillnader i resultaten kan hittas och analyseras, till exempel skillnader mellan olika flygplansindivider eller lastkonfigurationer. Arbetet presenterat här har resulterat i en modell som är bra för jämförelse av en stor mängd data där det är enkelt att spåra var skillnaderna har uppstått.
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Papp, John Laszlo. "SIMULATION OF TURBULENT SUPERSONIC SEPARATED BASE FLOWS USING ENHANCED TURBULENCE MODELING TECHNIQUES WITH APPLICATION TO AN X-33 AEROSPIKE ROCKET NOZZLE SYSTEM." University of Cincinnati / OhioLINK, 2000. http://rave.ohiolink.edu/etdc/view?acc_num=ucin962118912.

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Suksila, Thada. "The cathode plasma simulation." Thesis, University of Southern California, 2015. http://pqdtopen.proquest.com/#viewpdf?dispub=3704256.

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Since its invention at the University of Stuttgart, Germany in the mid-1960, scientists have been trying to understand and explain the mechanism of the plasma interaction inside the magnetoplasmadynamics (MPD) thruster. Because this thruster creates a larger level of efficiency than combustion thrusters, this MPD thruster is the primary cadidate thruster for a long duration (planetary) spacecraft. However, the complexity of this thruster make it difficult to fully understand the plasma interaction in an MPD thruster while operating the device. That is, there is a great deal of physics involved: the fluid dynamics, the electromagnetics, the plasma dynamics, and the thermodynamics. All of these physics must be included when an MPD thruster operates.

In recent years, a computer simulation helped scientists to simulate the experiments by programing the physics theories and comparing the simulation results with the experimental data. Many MPD thruster simulations have been conducted: E. Niewood et al.[5], C. K. J. Hulston et al.[6], K. D. Goodfellow[3], J Rossignol et al.[7]. All of these MPD computer simulations helped the scientists to see how quickly the system responds to the new design parameters.

For this work, a 1D MPD thruster simulation was developed to find the voltage drop between the cathode and the plasma regions. Also, the properties such as thermal conductivity, electrical conductivity and heat capacity are temperature and pressure dependent. These two conductivity and heat capacity are usually definded as constant values in many other models. However, this 1D and 2D cylindrical symmetry MPD thruster simulations include both temperature and pressure effects to the electrical, thermal conductivities and heat capacity values interpolated from W. F. Ahtye [4]. Eventhough, the pressure effect is also significant; however, in this study the pressure at 66 Pa was set as a baseline.

The 1D MPD thruster simulation includes the sheath region, which is the interface between the plasma and the cathode regions. This sheath model [3] has been fully combined in the 1D simulation. That is, the sheath model calculates the heat flux and the sheath voltage by giving the temperature and the current density. This sheath model must be included in the simulation, as the sheath region is treated differently from the main plasma region.

For our 2D cylindrical symmetry simulation, the dimensions of the cathode, the anode, the total current, the pressure, the type of gases, the work function can be changed in the input process as needed for particular interested. Also, the sheath model is still included and fully integrated in this 2D cylindrical symmetry simulation at the cathode surface grids. In addition, the focus of the 2D cylindrical symmetry simulation is to connect the properties on the plasma and the cathode regions on the cathode surface until the MPD thruster reach steady state and estimate the plasma arc attachement edge, electroarc edge, on the cathode surface. Finally, we can understand more about the behavior of an MPD thruster under many different conditions of 2D cylindrical symmetry MPD thruster simulations.

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Kalaver, Satchidanand Anil. "Management of reference frames in simulation and its application to error reduction in numerical integration." Thesis, Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12406.

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Li, Yuwen. "Dynamics modeling and simulation of flexible airships." Thesis, McGill University, 2008. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=18756.

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The resurgence of airships has created a need for dynamics models and simulation capabilities of these lighter-than-air vehicles. The focus of this thesis is a theoretical framework that integrates the flight dynamics, structural dynamics, aerostatics and aerodynamics of flexible airships. The study begins with a dynamics model based on a rigid-body assumption. A comprehensive computation of aerodynamic effects is presented, where the aerodynamic forces and moments are categorized into various terms based on different physical effects. A series of prediction approaches for different aerodynamic effects are unified and applied to airships. The numerical results of aerodynamic derivatives and the simulated responses to control surface deflection inputs are verified by comparing to existing wind-tunnel and flight test data. With the validated aerodynamics and rigid-body modeling, the equations of motion of an elastic airship are derived by the Lagrangian formulation. The airship is modeled as a free-free Euler-Bernoulli beam and the bending deformations are represented by shape functions chosen as the free-free normal modes. In order to capture the coupling between the aerodynamic forces and the structural elasticity, local velocity on the deformed vehicle is used in the computation of aerodynamic forces. Finally, with the inertial, gravity, aerostatic and control forces incorporated, the dynamics model of a flexible airship is represented by a single set of nonlinear ordinary differential equations. The proposed model is implemented as a dynamics simulation program to analyze the dynamics characteristics of the Skyship-500 airship. Simulation results are presented to demonstrate the influence of structural deformation on the aerodynamic forces and the dynamics behavior of the airship. The nonlinear equations of motion are linearized numerically for the purpose of frequency domain analysis and for aeroelastic stability analysis. The results from the latter for
L'intérêt renouvelé envers les dirigeables a créé un besoin de modèles dynamique et de simulations de ces véhicules plus légers que l'air. Cette thèse traite d'un cadre théorique qui intègre la dynamique de vol, la dynamique structurale, l'aérostatique et l'aérodynamique des dirigeables flexibles. La recherche débute par une étude d'un modèle dynamique fondé sur l'hypothèse d'un corps rigide. Une approche de calcul d'aérodynamique complète est présentée, où les forces et les moments aérodynamiques sont classés par catégories basées sur différents effets physiques. Une série d'approches de prédiction des différents effets aérodynamiques est unifiée et appliqué aux dirigeables. Les résultats numériques des dérivés aérodynamiques et des réponses simulées à des commandes spécifiés sont comparés à des résultats d'essais provenant d'autre œuvres. Une fois l'aérodynamique et le modèle de corps rigide validés, les équations de mouvement d'un dirigeable élastique sont dérivées avec une formulation Lagrangienne. Le dirigeable est modélisé comme poutre Euler-Bernoulli et les déformations sont représentées par des fonctions de forme choisies. Afin de prendre en considération la dépendance entre les forces aérodynamiques et l'élasticité structurale, la vitesse locale sur le véhicule déformé est employée dans le calcul des forces aérodynamiques. En conclusion, avec les forces d'inertie, de gravité, d'aérodynamique et de commande incorporées, le modèle dynamique d'un dirigeable flexible est exprimé sous la forme d'un ensemble d'équations différentielles ordinaires non-linéaires. Le modèle proposé est mis en pratique sous forme de simulation dynamique afin d'analyser les caractéristiques dynamiques du dirigeable Skyship-500. Des résultats de simulation sont présentés pour démontrer l'influence de la déformation structurale sur les forces aérodynamiques et le comportement dynamique du di
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Buettner, Robert W. "Dynamic Modeling and Simulation of a Variable Cycle Turbofan Engine with Controls." Wright State University / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=wright1496179248257409.

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Books on the topic "Aerospace engineering – Simulation methods"

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service), SpringerLink (Online, ed. Simulating Spacecraft Systems. Berlin, Heidelberg: Springer-Verlag Berlin Heidelberg, 2009.

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K, Remple Robert, ed. Aircraft and rotorcraft system identification: Engineering methods with flight-test examples aircraft and rotorcraft system identification engineering methods with flight-test examples. Reston, VA: American Institute of Aeronautics and Astronautics, 2006.

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International Mechanical Engineering Congress and Exposition (2008 Boston, Mass.). Proceedings of the ASME International Mechanical Engineering Congress and Exposition--2008: Presented at 2008 ASME International Mechanical Engineering Congress and Exposition, October 31-November 6, 2008, Boston, Massachusetts, USA. New York: ASME, 2009.

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International Mechanical Engineering Congress and Exposition (2008 Boston, Mass.). Proceedings of the ASME International Mechanical Engineering Congress and Exposition--2008: Presented at 2008 ASME International Mechanical Engineering Congress and Exposition, October 31-November 6, 2008, Boston, Massachusetts, USA. New York: ASME, 2009.

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Colo.) International Mechanical Engineering Congress and Exposition (2011 Denver. Proceedings of the ASME International Mechanical Engineering Congress and Exposition--2011: Presented at ASME 2011 International Mechanical Engineering Congress and Exposition, November 11-17, 2011, Denver, Colorado. New York, N.Y: ASME, 2012.

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International, Mechanical Engineering Congress and Exposition (2008 Boston Mass ). Proceedings of the ASME International Mechanical Engineering Congress and Exposition--2008: Presented at 2008 ASME International Mechanical Engineering Congress and Exposition, October 31-November 6, 2008, Boston, Massachusetts, USA. New York: ASME, 2009.

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International Mechanical Engineering Congress and Exposition (2008 Boston, Mass.). Proceedings of the ASME International Mechanical Engineering Congress and Exposition--2008: Presented at 2008 ASME International Mechanical Engineering Congress and Exposition, October 31-November 6, 2008, Boston, Massachusetts, USA. New York: ASME, 2009.

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International Mechanical Engineering Congress and Exposition (2008 Boston, Mass.). Proceedings of the ASME International Mechanical Engineering Congress and Exposition--2008: Presented at 2008 ASME International Mechanical Engineering Congress and Exposition, October 31-November 6, 2008, Boston, Massachusetts, USA. New York: ASME, 2009.

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International, Mechanical Engineering Congress and Exposition (2008 Boston Mass ). Proceedings of the ASME International Mechanical Engineering Congress and Exposition--2008: Presented at 2008 ASME International Mechanical Engineering Congress and Exposition, October 31-November 6, 2008, Boston, Massachusetts, USA. New York: ASME, 2009.

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International Mechanical Engineering Congress and Exposition (2008 Boston, Mass.). Proceedings of the ASME International Mechanical Engineering Congress and Exposition--2008: Presented at 2008 ASME International Mechanical Engineering Congress and Exposition, October 31-November 6, 2008, Boston, Massachusetts, USA. New York: ASME, 2009.

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Book chapters on the topic "Aerospace engineering – Simulation methods"

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Shan, Chen, and Sun Ji-yin. "Simulation Method Research of Ground Target IR Scene Based on Aerospace Information." In Lecture Notes in Electrical Engineering, 101–9. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14350-2_13.

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Tao, Qitian, Hailiang Jin, and Xiaohua Liu. "Computational Method in the Throughflow Simulation of Aeroengine Compressor." In Proceedings of the International Conference on Aerospace System Science and Engineering 2020, 345–58. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-33-6060-0_24.

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Müller, Mark, and Dietmar Pfahl. "Simulation Methods." In Guide to Advanced Empirical Software Engineering, 117–52. London: Springer London, 2008. http://dx.doi.org/10.1007/978-1-84800-044-5_5.

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Cipolla, Vittorio, and Fabrizio Oliviero. "HyPSim: A Simulation Tool for Hybrid Aircraft Performance Analysis." In Variational Analysis and Aerospace Engineering, 95–116. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-45680-5_4.

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Rauh, Andreas, and Eberhard P. Hofer. "Interval Methods for Optimal Control." In Variational Analysis and Aerospace Engineering, 397–418. New York, NY: Springer New York, 2009. http://dx.doi.org/10.1007/978-0-387-95857-6_22.

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Cakmakci, Melih, Gullu Kiziltas Sendur, and Umut Durak. "Simulation-Based Engineering." In Simulation Foundations, Methods and Applications, 39–73. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-61264-5_3.

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Teofilatto, Paolo, and Mauro Pontani. "Numerical and Analytical Methods for Global Optimization." In Variational Analysis and Aerospace Engineering, 461–75. New York, NY: Springer New York, 2009. http://dx.doi.org/10.1007/978-0-387-95857-6_25.

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Formaggia, Luca, Edie Miglio, Andrea Mola, and Anna Scotti. "Numerical simulation of the dynamics of boats by a variational inequality approach." In Variational Analysis and Aerospace Engineering, 213–27. New York, NY: Springer New York, 2009. http://dx.doi.org/10.1007/978-0-387-95857-6_12.

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Rozier, Kristin Yvonne. "On Teaching Applied Formal Methods in Aerospace Engineering." In Formal Methods Teaching, 111–31. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-32441-4_8.

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Putcha, Chandrasekhar, Subhrajit Dutta, and Sanjay K. Gupta. "Probabilistic Simulation Methods." In Reliability and Risk Analysis in Engineering and Medicine, 67–84. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-80454-1_5.

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Conference papers on the topic "Aerospace engineering – Simulation methods"

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LaMont, Douglas V., Jack J. Rodden, and William E. Nelson. "High-technology multibody spacecraft dynamics simulation methods." In Optical Engineering and Photonics in Aerospace Sensing, edited by Michael K. Masten and Larry A. Stockum. SPIE, 1993. http://dx.doi.org/10.1117/12.156602.

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Zheng, Yao, Lijun Xie, Jianfeng Zou, Jianjun Chen, Jifa Zhang, Jane W. Z. Lu, Andrew Y. T. Leung, Vai Pan Iu, and Kai Meng Mok. "Aerospace Numerical Simulation and Digital Prototyping Technologies." In PROCEEDINGS OF THE 2ND INTERNATIONAL SYMPOSIUM ON COMPUTATIONAL MECHANICS AND THE 12TH INTERNATIONAL CONFERENCE ON THE ENHANCEMENT AND PROMOTION OF COMPUTATIONAL METHODS IN ENGINEERING AND SCIENCE. AIP, 2010. http://dx.doi.org/10.1063/1.3452141.

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LaMont, Douglas V., Jack J. Rodden, and William E. Nelson. "High-TEC multibody spacecraft dynamics simulation methods extended." In SPIE's International Symposium on Optical Engineering and Photonics in Aerospace Sensing, edited by Michael K. Masten, Larry A. Stockum, Morris M. Birnbaum, and George E. Sevaston. SPIE, 1994. http://dx.doi.org/10.1117/12.178947.

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Chamis, Christos C. "Aerospace Composite Structures: Applications/Design/Analysis." In ASME 1998 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/imece1998-0386.

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Abstract Fiber composites are an emerging material with tailoring potential to achieve substantially “better-cheaper-faster” and even “greener” products. The lecture provides an overview on the advantages of composites design/analysis methods and applications. The review will synoptically cover analysis methods that span all composites scales from constituents (fiber, matrix) and fabrication process to structural optimization. Several typical composites applications to aerospace structures are presented to demonstrate specific advantages of composites in these structures. Recent application to space station, advanced satellites and X-33 are included as are potential applications of smart composite structural concepts for aerospace applications. Emerging simulation methods to evaluate the reliability and risk of aerospace composite structures are summarized. The presentation provides a broad perspective of what can be done with composites and the state of the composites technology readiness to meet even greater application challenges in aerospace structures.
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Somov, Sergey, and Tatyana Somova. "Methods for nonlinear analysis, simulation and animation of land-survey spacecraft guidance." In 10TH INTERNATIONAL CONFERENCE ON MATHEMATICAL PROBLEMS IN ENGINEERING, AEROSPACE AND SCIENCES: ICNPAA 2014. AIP Publishing LLC, 2014. http://dx.doi.org/10.1063/1.4904678.

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Braccesi, Claudio, Filippo Cianetti, and Luca Landi. "Random Loads Fatigue: The Use of Spectral Methods Within Multibody Simulation." In ASME 2005 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/detc2005-84453.

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The evaluation of the fatigue damage performed by using the Power Spectral Density function (PSD) of stress and strain state is proving to be extremely accurate for a family of random processes characterized by the property of being stationary. The present work’s original contribution is the definition of a methodology which extracts stress and strain PSD matrices from components modelled using a modal approach (starting from a finite element modelling and analysis) within mechanical systems modelled using multibody dynamic simulation and subject to a generic random load (i.e. multiple-input, with partially correlated inputs). This capability extends the actual stress evaluation scenario (principally characterised by the use of finite element analysis approach) to the multibody dynamic simulation environment, more powerful and useful to simulate complex mechanical systems (i.e. railway, automotive, aircraft and aerospace systems). As regards the fatigue damage evaluation, a synthesis approach to evaluate an equivalent stress state expressed in terms of the PSD function of Preumont’s “equivalent von Mises stress (EVMS)”, starting from the complete stress state representation expressed in terms of PSD stress matrix and easily usable in the consolidated spectral methods, is proposed. This approach allows and has allowed the use of the above methods such as the Dirlik formula as a damage evaluation method. An additional result is the conception and implementation of a frequency domain method for the component’s most probable state of stress, allowing quickly identification of the most stressed and damageble locations. The described methodologies were developed and embedded into commercial simulation codes and verified by using as a test case a simple reference multibody model with a simple flexible component.
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Nielsen, Eric J. "Adjoint-Based Aerodynamic Design of Complex Aerospace Configurations." In ASME 2016 Fluids Engineering Division Summer Meeting collocated with the ASME 2016 Heat Transfer Summer Conference and the ASME 2016 14th International Conference on Nanochannels, Microchannels, and Minichannels. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/fedsm2016-7573.

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An overview of twenty years of adjoint-based aerodynamic design research at NASA Langley Research Center is presented. Adjoint-based algorithms provide a powerful tool for efficient sensitivity analysis of complex large-scale computational fluid dynamics (CFD) simulations. Unlike alternative approaches for which computational expense generally scales with the number of design parameters, adjoint techniques yield sensitivity derivatives of a simulation output with respect to all input parameters at the cost of a single additional simulation. With modern large-scale CFD applications often requiring millions of compute hours for a single analysis, the efficiency afforded by adjoint methods is critical in realizing a computationally tractable design optimization capability for such applications.
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Bowkett, Joseph, and Rudranarayan Mukherjee. "Comparison of Control Methods for Two-Link Planar Flexible Manipulator." In ASME 2017 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/detc2017-67937.

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While the majority of terrestrial multi-link manipulators can be considered in a purely kinematic sense due to their high stiffness, the launch mass restrictions of aerospace applications such as in-orbit assembly of large space structures result in low stiffness links being employed, meaning dynamics can no longer be ignored. This paper seeks to investigate the suitability of several different open and closed loop control techniques for application to the problem of end effector position control with minimal vibration for a low stiffness space based manipulator. Simulations of a representative planar problem with two flexible links are used to measure performance and sensitivity to parameter variation of: model predictive control, command shaping, and command shaping with linear quadratic regulator (LQR) feedback. An experimental testbed is then used to validate simulation results for the recommended command shaped controller.
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Kourdali, Houda Kerkoub, and Lance Sherry. "A systems engineering method for analysis and simulation of standard operating procedures." In HCI-Aero '16: International Conference on Human-Computer Interaction in Aerospace 2016. New York, NY, USA: ACM, 2016. http://dx.doi.org/10.1145/2950112.2964580.

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Mufti, Abdullah, Romana Basit, and M. Abdul Basit. "Numerical simulation of thermal incompressible fluid flow using Lattice Boltzmann's method." In 2013 International Conference on Aerospace Science & Engineering (ICASE). IEEE, 2013. http://dx.doi.org/10.1109/icase.2013.6785545.

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Reports on the topic "Aerospace engineering – Simulation methods"

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Markova, Oksana, Serhiy Semerikov, and Maiia Popel. СoCalc as a Learning Tool for Neural Network Simulation in the Special Course “Foundations of Mathematic Informatics”. Sun SITE Central Europe, May 2018. http://dx.doi.org/10.31812/0564/2250.

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The role of neural network modeling in the learning сontent of special course “Foundations of Mathematic Informatics” was discussed. The course was developed for the students of technical universities – future IT-specialists and directed to breaking the gap between theoretic computer science and it’s applied applications: software, system and computing engineering. CoCalc was justified as a learning tool of mathematical informatics in general and neural network modeling in particular. The elements of technique of using CoCalc at studying topic “Neural network and pattern recognition” of the special course “Foundations of Mathematic Informatics” are shown. The program code was presented in a CofeeScript language, which implements the basic components of artificial neural network: neurons, synaptic connections, functions of activations (tangential, sigmoid, stepped) and their derivatives, methods of calculating the network`s weights, etc. The features of the Kolmogorov–Arnold representation theorem application were discussed for determination the architecture of multilayer neural networks. The implementation of the disjunctive logical element and approximation of an arbitrary function using a three-layer neural network were given as an examples. According to the simulation results, a conclusion was made as for the limits of the use of constructed networks, in which they retain their adequacy. The framework topics of individual research of the artificial neural networks is proposed.
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Duque, Earl, Steve Legensky, Brad Whitlock, David Rogers, Andrew Bauer, Scott Imlay, David Thompson, and Seiji Tsutsumi. Summary of the SciTech 2020 Technical Panel on In Situ/In Transit Computational Environments for Visualization and Data Analysis. Engineer Research and Development Center (U.S.), June 2021. http://dx.doi.org/10.21079/11681/40887.

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At the AIAA SciTech 2020 conference, the Meshing, Visualization and Computational Environments Technical Committee hosted a special technical panel on In Situ/In Transit Computational Environments for Visualization and Data Analytics. The panel brought together leading experts from industry, software vendors, Department of Energy, Department of Defense and the Japan Aerospace Exploration Agency (JAXA). In situ and in transit methodologies enable Computational Fluid Dynamic (CFD) simulations to avoid the excessive overhead associated with data I/O at large scales especially as simulations scale to millions of processors. These methods either share the data analysis/visualization pipelines with the memory space of the solver or efficiently off load the workload to alternate processors. Using these methods, simulations can scale and have the promise of enabling the community to satisfy the Knowledge Extraction milestones as envisioned by the CFD Vision 2030 study for "on demand analysis/visualization of a 100 Billion point unsteady CFD simulation". This paper summarizes the presentations providing a discussion point of how the community can achieve the goals set forth in the CFD Vision 2030.
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Bidier, S., U. Khristenko, R. Tosi, R. Rossi, and C. Soriano. D7.3 Report on UQ results and overall user experience. Scipedia, 2021. http://dx.doi.org/10.23967/exaqute.2021.9.002.

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This deliverable report focuses on the main Uncertainty Quanti cation (UQ) results obtained within the EXAscale Quanti cation of Uncertainties for Technology and Science Simulation (ExaQUte) project. Details on the turbulent wind inlet generator, that enables the supply of random, yet steady, wind velocity boundary conditions during run-time, are given in section 2. This enables the developed UQ workflow, whose results are presented on the basis of the Commonwealth Advisory Aeronautical Council (CAARC) as described in Deliverable 7.1. Finally, the completed UQ workflow and the results are evaluated from an application-driven wind engineering point of view. Thereby, the significance of the developed methods and the obtained results are discussed and their applicability in practical wind-engineering applications is tested through a complete test-run of the UQ workflow.
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Bidier, S., U. Khristenko, A. Kodakkal, C. Soriano, and R. Rossi. D7.4 Final report on Stochastic Optimization results. Scipedia, 2022. http://dx.doi.org/10.23967/exaqute.2022.3.02.

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This deliverable report focuses on the final stochastic optimization results obtained within the EXAscale Quantification of Uncertainties for Technology and Science Simulation (ExaQUte) project. Details on a novel wind inlet generator that is able to incorporate local wind-field data through a deep-learned rapid distortion model and generates the turbulent wind data during run-time is presented in section 2. Section 3 presents the results of the overall stochastic optimization procedure applied to a twisted tapered tower with multiple design parameters within an uncertain synthetic wind field. Thereby, the significance of the developed methods and the obtained results are discussed and their integration in industrial wind-engineering workflows is outlined in section 4.
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Diahyleva, Olena S., Igor V. Gritsuk, Olena Y. Kononova, and Alona Y. Yurzhenko. Computerized adaptive testing in educational electronic environment of maritime higher education institutions. [б. в.], June 2021. http://dx.doi.org/10.31812/123456789/4448.

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The article is devoted to the organization of modern learning process, namely the use of innovative technologies – computerized adaptive testing in educational electronic environment of maritime higher education institutions. The example of educational electronic environment is presented in the article on LMS Moodle. The provided new technological and methodological opportunities are a priority in the developed methods of control and testing of knowledge, skills and abilities of students. Comparative characteristic of using computerized adaptive testing in educational electronic environment is given in the article according to different criteria: the role of tests in the learning process; methods of training; equipment; presence of the problems in educational process; level of its control and learning outcomes. The paper also presents examples of activities to form communicative competency of future maritime professionals. Types of adaptive tests are listed in the paper. The research activities were done by second year cadets of ship engineering department of Maritime College of Kherson State Maritime Academy. The experiment was devoted to the formation of communicative competence with the help of electronic environment of maritime higher education institution. The results of experiment proved positive impact of computerized adaptive testing on communicative competence of future ship engineers. Further investigation of adaptive testing can also be done for learning system of maritime education establishments using simulation technologies of virtual, augmented and mixed realities.
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Roye, Thorsten. Unsettled Technology Areas in Deterministic Assembly Approaches for Industry 4.0. SAE International, August 2021. http://dx.doi.org/10.4271/epr2021018.

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Increased production rates and cost reduction are affecting manufacturing in all sectors of the mobility industry. One enabling methodology that could achieve these goals in the burgeoning “Industry 4.0” environment is the deterministic assembly (DA) approach. The DA approach is defined as an optimized assembly process; it always forms the same final structure and has a strong link to design-for-assembly and design-for-automation methodologies. It also looks at the whole supply chain, enabling drastic savings at the original equipment manufacturer (OEM) level by reducing recurring costs and lead time. Within Industry 4.0, DA will be required mainly for the aerospace and the space industry, but serves as an interesting approach for other industries assembling large and/or complex components. In its entirety, the DA approach connects an entire supply chain—from part manufacturing at an elementary level to an OEM’s final assembly line level. Addressing the whole process of aircraft design and manufacturing is necessary to develop further collaboration models between OEMs and the supply chain, including addressing the most pressing technology challenges. Since all parts aggregate at the OEM level, the OEM—as an integrator of all these single parts—needs special end-to-end methodologies to drastically decrease cost and lead time. This holistic approach can be considered in part design as well (in the design-for-automation and design-for-assembly philosophy). This allows for quicker assembly at the OEM level, such as “part-to-part” or “hole-to-hole” approaches, versus traditional, classical assembly methods like manual measurement or measurement-assisted assembly. In addition, it can increase flexibility regarding rate changes in production (such as those due to pandemic- or climate-related environmental challenges). The standardization and harmonization of these areas would help all industries and designers to have a deterministic approach with an end-to-end concept. Simulations can easily compare possible production and assembly steps with different impacts on local and global tolerances. Global measurement feedback needs high-accuracy turnkey solutions, which are very costly and inflexible. The goal of standardization would be to use Industry 4.0 feedback and features, as well as to define several building blocks of the DA approach as a one-way assembly (also known as one-up assembly, or “OUA”), false one-way assembly, “Jig-as-Master,” etc., up to the hole-to-hole assembly approach. The evolution of these assembly principles and the link to simulation approaches are undefined and unsolved domains; they are discussed in this report. They must be discussed in greater depth with aims of (first) clarifying the scope of the industry-wide alignment needs and (second) prioritizing the issues requiring standardization. NOTE: SAE EDGE™ Research Reports are intended to identify and illuminate key issues in emerging, but still unsettled, technologies of interest to the mobility industry. The goal of SAE EDGE™ Research Reports is to stimulate discussion and work in the hope of promoting and speeding resolution of identified issues. SAE EDGE™ Research Reports are not intended to resolve the challenges they identify or close any topic to further scrutiny.
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Malej, Matt, and Fengyan Shi. Suppressing the pressure-source instability in modeling deep-draft vessels with low under-keel clearance in FUNWAVE-TVD. Engineer Research and Development Center (U.S.), May 2021. http://dx.doi.org/10.21079/11681/40639.

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This Coastal and Hydraulics Engineering Technical Note (CHETN) documents the development through verification and validation of three instability-suppressing mechanisms in FUNWAVE-TVD, a Boussinesq-type numerical wave model, when modeling deep-draft vessels with a low under-keel clearance (UKC). Many large commercial ports and channels (e.g., Houston Ship Channel, Galveston, US Army Corps of Engineers [USACE]) are traveled and affected by tens of thousands of commercial vessel passages per year. In a series of recent projects undertaken for the Galveston District (USACE), it was discovered that when deep-draft vessels are modeled using pressure-source mechanisms, they can suffer from model instabilities when low UKC is employed (e.g., vessel draft of 12 m¹ in a channel of 15 m or less of depth), rendering a simulation unstable and obsolete. As an increasingly large number of deep-draft vessels are put into service, this problem is becoming more severe. This presents an operational challenge when modeling large container-type vessels in busy shipping channels, as these often will come as close as 1 m to the bottom of the channel, or even touch the bottom. This behavior would subsequently exhibit a numerical discontinuity in a given model and could severely limit the sample size of modeled vessels. This CHETN outlines a robust approach to suppressing such instability without compromising the integrity of the far-field vessel wave/wake solution. The three methods developed in this study aim to suppress high-frequency spikes generated nearfield of a vessel. They are a shock-capturing method, a friction method, and a viscosity method, respectively. The tests show that the combined shock-capturing and friction method is the most effective method to suppress the local high-frequency noises, while not affecting the far-field solution. A strong test, in which the target draft is larger than the channel depth, shows that there are no high-frequency noises generated in the case of ship squat as long as the shock-capturing method is used.
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