Journal articles: '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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Красноруцький, А. О., О. В. Федоровський, and В. Ж. Ященок. "Method of description for the dynamics of the signal delay change in discrete time with changing aircraft position in space." Системи обробки інформації, no. 3(166) (September 24, 2021): 41–45. http://dx.doi.org/10.30748/soi.2021.166.04.

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The article presents an innovative approach to the description of the aircraft range parameter in discrete time when simulating the process of its repositioning in space. A method of describing the dynamics of changes in signal delay in discrete time when the aircraft is changing its spatial position is proposed. Such a model adequately describes the change in signal delay in discrete time. The direction of estimation for the adequacy of radio signal delay change simulation in algorithms of optimum filtration is defined in accordance with the aerodynamic properties of the aircraft. Simulation of the signal delay dynamic change is carried out (it is completely described by the dynamics of change in the distance to the aircraft). The transformation stages of simulation data for the initial model in continuous time with realization of the standard Gaussian random numbers are justified. Information on the simulation data transformation taking into account the correlation matrix of discrete white noise is provided. A method of calculating the transition matrix through the Laplace transform is proposed. The scientific-applied direction of research is determined – it lies in the development of a method for the legitimate representation for the mathematical model of aircraft’s changing range in discrete time within one-dimensional space: the longitudinal and the transverse dimensions. This approach takes into account the continuous description for a system of stochastic differential equations. A comprehensive algorithm for modeling the values of discrete white noise on modern computer equipment and calculating the dynamics of the aircraft range parameter changes is proposed. This algorithm allows to correctly form the a priori information about the change of the vector parameters of the aircraft spatial position at discrete moments of time. As a result, it was shown that the use of the obtained information in the optimal filtering algorithms minimizes the error when determining distance to the aircraft and, accordingly, allows to increase the accuracy and adequacy of the signal delay simulation in discrete time. The results of this research can be used in modernization of the existing models and development of promising on-board radar stations, integrated rangefinders, systems of radio technical reconnaissance and electronic warfare systems, as well as in technical implementation of aircraft flight simulation systems.

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Smetankina, Natalia, Alyona Malykhina, and Dmytro Merkulov. "Simulating of Bird Strike on Aircraft Laminated Glazing." MATEC Web of Conferences 304 (2019): 01010. http://dx.doi.org/10.1051/matecconf/201930401010.

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A bird strike is a critical problem in the context of safety in the aviation industry. All modern aircraft structures are designed with account of likely collision with birds. Thus, aviation standards in force require that the aircraft construction would allow the crew to conclude the flight safely after collision with a 1.81-kg bird. A method for analysing the stress-strained state of laminated airplane glazing at different operational factors is presented. The method includes a technique for strength analysis of the laminated airplane glazing at bird impact, and a technique for analysis of excess pressure. The model of laminated glazing is based on the refined first-order theory accounting for transverse shear strains, thickness reduction and normal element rotation inertia in each layer. The mathematical model of the pressure impulse authentically reproducing the bird impact is based on experimental research. Theoretical results are in good agreement with experimental data, thus allowing to recommend the method to develop new airplane glazing elements.

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Luo, Yongliang, Yingnian Wu, Yuanhui Qin, Lin Zhang, and Yuanming Wang. "Modeling method for integration of air command and security process." International Journal of Modeling, Simulation, and Scientific Computing 07, no. 01 (March 2016): 1641004. http://dx.doi.org/10.1142/s179396231641004x.

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Air command and security (ACS) process is a kind of typical complex operation process. Its modeling issue has become a hot spot and challenge in the research field of complex operation process. Combining the demand on the application of air command and support, this paper proposes a simulation-based modeling method of integrating air command and support process, emphatically describing such aspects as the meta-model of the concept of aviation support process, work flow service modeling and arrangement of multi-aircraft process, etc. Finally, based on actual cases of application, this paper unfolds simulating verification and assessment on the whole process of control and support operation process of a flight task involving multiple aircrafts.

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Sasongko, Rianto A., Yorgi A. Ndaomanu, Yazdi I. Jenie, M. Luthfi I. Nurhakin, M. Rafi Hadytama, and Yusuf K. Asalani. "DEVELOPMENT OF NUMERICAL PLATFORM FOR AIRCRAFT SYSTEMS SIMULATION." INSIST 2, no. 2 (January 25, 2019): 97. http://dx.doi.org/10.23960/ins.v2i2.89.

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This paper discusses the development of a numerical simulation platform that can be used for representing the principal works of aircraft systems. The platform consists of some parts each of which is intended to replicate the operation of a system implemented in a modern aircraft, such as hydraulic line, electrical system, landing gear system, control system, etc. The platform is intended to be a tool for modeling and analyzing the operation and performance of certain systems configuration. To some extend the platform can be viewed as a virtual Iron Bird System. Iron Bird is a term representing a platform for simulating the works of aircraft systems using real components, which is very important for aircraft system development. At this stage, the numerical platform will only involve some sub-systems, namely main hydraulic line, control surface actuation, landing gear, and control system. These sub-systems are chosen to be the basis for further development where other sub-systems will be added and integrated to the platform.Keywords—Aircraft System, Numerical Simulation, System Analysis

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Wang, Li Feng. "A Practical Tool for Multiple Simulation Tasks of Gas Engine." Advanced Materials Research 403-408 (November 2011): 3071–76. http://dx.doi.org/10.4028/www.scientific.net/amr.403-408.3071.

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A practical tool for multiple simulation tasks of gas engine has been developed in order to meet the needs coming from factory, institute and academic for research & develop platform. In the tool, not only can aircraft engine and ship engine be visually modeled and all of data can be setup in the window, but also different simulating tasks can be completed, such as flight performance, linear state space model, transient & fault simulating and gas path analysis. The objective of this paper is to provide the comprehensive overview of multiple simulation tasks of gas engine.

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Pan, Zhong Jian, Qing Hua He, Yong Guo, Yu Ming Zhao, and Jing Yang. "Research on the Turbocharger Technology of Piston Aircraft Engine." Applied Mechanics and Materials 457-458 (October 2013): 531–35. http://dx.doi.org/10.4028/www.scientific.net/amm.457-458.531.

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The supercharger technology of piston aviation engine determines its flight capabilities, and then establishes a turbocharger simulation model of an aviation piston engine. After simulating the engine ground features and 5000-meter altitude characteristics, and comparing the efficiency of compressor and turbocharger in different environments, after the installation of mechanical supercharger, gas flow has been improved, the cylinder pressure decreased about 10% compared with ground condition and engine altitude state power is restored, even 20,000 feet Power restored to 80%, which can meet the needs of high-altitude flight.

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Arntzen, Michael, Stephen A. Rizzi, Hendrikus G. Visser, and Dick G. Simons. "Framework for Simulating Aircraft Flyover Noise Through Nonstandard Atmospheres." Journal of Aircraft 51, no. 3 (May 2014): 956–66. http://dx.doi.org/10.2514/1.c032049.

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Luo, Hong. "Lightning Protection Design of Transceiver Based on Radio Altimeter." Architecture Engineering and Science 3, no. 2 (July 5, 2022): 151. http://dx.doi.org/10.32629/aes.v3i2.899.

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Lightning is a great threat to aircraft flight safety. The lightning protection test of aircraft and the ability of aircraft and its parts to withstand direct and indirect effects are investigated and verified by simulating the real lightning environment in the laboratory. According to the requirements of GJB lightning test, this paper analyzes the lightning grade and introduces several lightning protection designs commonly used in engineer practice.

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Li, Xin Sheng, Gang Li, Cao Xiao, and Shi Yong Lan. "A Simplified Method of Simulation for Aircraft Performance Parameters in Air Traffic Control." Applied Mechanics and Materials 235 (November 2012): 198–203. http://dx.doi.org/10.4028/www.scientific.net/amm.235.198.

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In order to simplify the traditional methods for simulating aircraft performance in ATC, a method is proposed in this paper by the flight aerodynamics theories, normal and maximal climb rate in steady climb motion and acceleration/deceleration of Straight-and-Level Flight of performance computation. This method can be used to simulate acceleration, deceleration, and climb/descent rate of usual civil aircraft types. It is convenient and useable compared with the traditional complex methods which need input many parameters manually in air traffic control (ATC) simulation. The experimental result listed in this paper coincides with the basic flying rules of aircraft types such as 737-300, A310-300, B747F, Y-7. The application of this method in the real ATC simulator for controller training proved its function and effect.

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Jasztal, Michał. "Testing the Process of Evacuation from the Passenger Aircraft with the Use of Computer Simulation." Safety & Fire Technology 56, no. 2 (2020): 22–39. http://dx.doi.org/10.12845/sft.56.2.2020.2.

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Aim: The main aim of the study was to investigate the possibility to use the Pathfinder simulation software to determine the duration of an evacuation and to plan its course for various scenarios of evacuation organisation, for specific profiles and behaviours of passengers and on-board personnel, and for a specific geometrical arrangement of the passenger cabin of a selected passenger aircraft. In addition, the paper discusses selected factors that affect the evacuation from the passenger aircraft. Project and methods: The Pathfinder software used in the research has the graphical interface to create an evacuation simulation model (2D and 3D) as well as tools to visualise the results. Pathfinder is based on artificial intelligence algorithms, in which each passenger has a number of individual features that can influence his/her movements and decisions during the simulation. The simulation of people's movement is determined by their profiles and behaviours, the parameters of which can be entered by means of probability distributions, which makes it possible to take into account the stochastic nature of the evacuation process. Results: The Boeing 787 Dreamliner was selected for the study, for which six options for simulating the evacuation of 252 passengers and eight members of on-board personnel were conducted. The shortest evacuation time was achieved by changing the even distribution of the number of passengers to the individual emergency exits, thus avoiding congestions in sensitive areas of the passenger cabin. The increase in passengers' maximum speed has paradoxically increased evacuation times, as it has increased the intensity of passenger collisions. It was found that one of the key issues affecting the timing of an evacuation is the proper organisation of the evacuation by on-board personnel, who, by guiding passengers through the geometrically most advantageous passageways, results in the fastest possible evacuation. The simulations in variants five and six have achieved satisfactory evacuation times, which are within the emergency aircraft evacuation time limit required in a certification process. Conclusions: The presented simulation models, the results obtained, and the wide range of possibilities of three-dimensional visualisation of research results give a rational basis for the use of Pathfinder software for testing the evacuation process and thus: for the usage in the aircraft design process, for preparing aircrafts for tests, for shaping evacuation procedures, for on-board personnel training and for air accident investigation.

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Huang, Zhao Dong, Wen Bing Chang, Yi Yong Xiao, and Rui Liu. "An Extended Monte Carlo Method on Simulating the Development Cost Uncertainties of Aircraft." Advanced Materials Research 118-120 (June 2010): 810–14. http://dx.doi.org/10.4028/www.scientific.net/amr.118-120.810.

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Monte Carlo Simulation is a general method for evaluating a deterministic model by iteratively generating inputs so as to get the natural distribution of outputs, which has often been employed for risk analysis of development cost estimation under uncertain environment. However, the traditional way of implementing Monte Carlo Simulation on cost risk analysis is always based on deterministic Cost Estimation Relation (CER) model and does not take the uncertainty of history cost data used to build CER into account, which will considerably affect the cost risk analysis. In this paper, we extend Monte Carlo Simulation model to make its simulating process cover the stage of building model so that not only the inputs are iteratively generated but also the model is iteratively rebuilt. An example is carried out to compare the extended model to the traditional one on analyzing aircraft development cost risk, which shows that the risk distribution gotten by Extended Monte Carlo Simulation is considerably different to that gotten by traditional one.

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Robbins, C. R., and S. McKee. "Simulating the evacuation of a commercial airliner." Aeronautical Journal 105, no. 1048 (June 2001): 323–28. http://dx.doi.org/10.1017/s0001924000012203.

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Abstract The discrete element method is modified so as to simulate the movement of passengers evacuating an aircraft. The results display reasonable agreement with timed trials. However, by focusing on the 1985 Manchester air disaster where only some of the exits could be opened and only then a considerable time after landing, it is argued that the certification procedures are inadequate.

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Keltner, N., W. Gill, and L. Kent. "Simulating Fuel Spill Fires Under The Wing Of An Aircraft." Fire Safety Science 4 (1994): 1017–28. http://dx.doi.org/10.3801/iafss.fss.4-1017.

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Sausen, R., and I. Köhler. "Simulating the global transport of nitrogen oxides emissions from aircraft." Annales Geophysicae 12, no. 5 (April 30, 1994): 394–402. http://dx.doi.org/10.1007/s00585-994-0394-8.

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Abstract. With the atmosphere general circulation model ECHAM the passive transport of NOx emitted from global subsonic air traffic and the NOx concentration change due to these emissions are investigated. The source of NOx is prescribed according to an aircraft emission data base. The sink of NOx is parameterized as an exponential decay process with globally constant lifetime. Simulations in perpetual January and July modes are performed. Both the resulting mean and the standard deviation of the NOx mass mixing ratio are analysed. In January horizontal dispersion is more pronounced and vertical mixing is smaller than in July. In both cases the resulting quasi-stationary fields of the mass mixing ratio display a pronounced zonal asymmetry. The variability accounts up to 30% of the mean field.

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Rizzi, Arthur. "Modeling and simulating aircraft stability and control—The SimSAC project." Progress in Aerospace Sciences 47, no. 8 (November 2011): 573–88. http://dx.doi.org/10.1016/j.paerosci.2011.08.004.

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Zhou, Hong Cheng, and Dao Bao Wang. "Aircraft Controller Flight Control System Design." Applied Mechanics and Materials 602-605 (August 2014): 1291–94. http://dx.doi.org/10.4028/www.scientific.net/amm.602-605.1291.

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The servo control methods of motion configuration are researched. Based on analysis for characteristic of the motion configuration, the control strategy and control law used on the motion control system are presented. The controllers are respectively designed by frequency correcting method and normal control method which belongs to classical control theory. Sliding mode variable structure control method is presented for location control law designing, so that the problem of location control loop low velocity creeping is solved, and a simulating experimentation demonstrate the effectiveness of the proposed approach.

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Benini, M., M. Bonfè, P. Castaldi, W. Geri, and S. Simani. "Design and Analysis of Robust Fault Diagnosis Schemes for a Simulated Aircraft Model." Journal of Control Science and Engineering 2008 (2008): 1–18. http://dx.doi.org/10.1155/2008/274313.

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Several procedures for sensor fault detection and isolation (FDI) applied to a simulated model of a commercial aircraft are presented. The main contributions of the paper are related to the design and the optimisation of two FDI schemes based on a linear polynomial method (PM) and the nonlinear geometric approach (NLGA). The FDI strategies are applied to the aircraft model, characterised by tight-coupled longitudinal and lateral dynamics. The robustness and the reliability properties of the residual generators related to the considered FDI techniques are investigated and verified by simulating a general aircraft reference trajectory. Extensive simulations exploiting the Monte Carlo analysis tool are also used for assessing the overall performance capabilities of the developed FDI schemes, in the presence of turbulence, measurement, and model errors. Comparisons with other disturbance-decoupling methods for FDI based on neural networks (NNs) and unknown input kalman filter (UIKF) are finally reported.

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Pecora, Rosario. "A Rational Numerical Method for Simulation of Drop-Impact Dynamics of Oleo-Pneumatic Landing Gear." Applied Sciences 11, no. 9 (April 30, 2021): 4136. http://dx.doi.org/10.3390/app11094136.

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Oleo-pneumatic landing gear is a complex mechanical system conceived to efficiently absorb and dissipate an aircraft’s kinetic energy at touchdown, thus reducing the impact load and acceleration transmitted to the airframe. Due to its significant influence on ground loads, this system is generally designed in parallel with the main structural components of the aircraft, such as the fuselage and wings. Robust numerical models for simulating landing gear impact dynamics are essential from the preliminary design stage in order to properly assess aircraft configuration and structural arrangements. Finite element (FE) analysis is a viable solution for supporting the design. However, regarding the oleo-pneumatic struts, FE-based simulation may become unpractical, since detailed models are required to obtain reliable results. Moreover, FE models could not be very versatile for accommodating the many design updates that usually occur at the beginning of the landing gear project or during the layout optimization process. In this work, a numerical method for simulating oleo-pneumatic landing gear drop dynamics is presented. To effectively support both the preliminary and advanced design of landing gear units, the proposed simulation approach rationally balances the level of sophistication of the adopted model with the need for accurate results. Although based on a formulation assuming only four state variables for the description of landing gear dynamics, the approach successfully accounts for all the relevant forces that arise during the drop and their influence on landing gear motion. A set of intercommunicating routines was implemented in MATLAB® environment to integrate the dynamic impact equations, starting from user-defined initial conditions and general parameters related to the geometric and structural configuration of the landing gear. The tool was then used to simulate a drop test of a reference landing gear, and the obtained results were successfully validated against available experimental data.

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Silvestrov, P. V., and S. T. Surzhikov. "Computational Analysis of Aerodynamics and Thermodynamics for the X-51 High-Velocity Aircraft." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 5 (134) (October 2020): 41–57. http://dx.doi.org/10.18698/0236-3941-2020-5-41-57.

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The paper presents a numerical investigation of aero-dynamic coefficients for a model of an X-51-type high-velocity aircraft moving at Mach 6. The simulation made use of the original and modified versions of our custom hydrocodes (UST3D and UST3D-AUSMPW) designed for numerical simulation of aerodynamics and thermodynamics in high-velocity aircraft of arbitrary shapes. Such hydrocodes implement 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. The paper considers the theoretical aspects of simulating the aerodynamics and thermodynamics of high-velocity aircraft numerically. We describe the method for computing mass flow through mesh cell boundaries implemented in the modified custom hydrocode version. We performed cross-validation of the results obtained using our custom hydrocodes and compared our hydrocodes in terms of result convergence time. We show that these custom hydrocodes ensure adequately accurate distribution patterns concerning the fields of the values sought, and provide high-precision computation of aerodynamic characteristics as compared to each other

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Cooke, Joseph M., Michael J. Zyda, David R. Pratt, and Robert B. McGhee. "NPSNET: Flight Simulation Dynamic Modeling Using Quaternions." Presence: Teleoperators and Virtual Environments 1, no. 4 (January 1992): 404–20. http://dx.doi.org/10.1162/pres.1992.1.4.404.

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The Naval Postgraduate School (NPS) has actively explored the design and implementation of networked, real time, three-dimensional battlefield simulations on low-cost, commercially available graphics workstations. The most recent system, NPSNET, has improved in functionality to such an extent that it is considered a low-cost version of the Defense Advanced Research Project Agency's (DARPA) SIMNET system. To reach that level, it was necessary to economize in certain areas of the code so that real time performance occurred at an acceptable level. One of those areas was in aircraft dynamics. However, with “off-the-shelf” computers becoming faster and cheaper, real-time and realistic dynamics are no longer an expensive option. Realistic behavior can now be enhanced through the incorporation of an aerodynamic model. To accomplish this task, a prototype flight simulator was built that is capable of simulating numerous types of aircraft simultaneously within a virtual world. Besides being easily incorporated into NPSNET, such a simulator also provides the base functionality for the creation of a general purpose aerodynamic simulator that is particularly useful to aerodynamics students for graphically analyzing differing aircraft's stability and control characteristics. This system is designed for use on a Silicon Graphics workstation and uses the GL libraries. A key feature of the simulator is the use of quaternions for aircraft orientation representation to avoid singularities and high data rates associated with the more common Euler angle representation of orientation.

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Kondor, Máté, and Gergely Dezső. "Unmanned Aerial Vehichle Wing Fuselage Junction Optimalisation with Finite Element Method." Műszaki Tudományos Közlemények 11, no. 1 (October 1, 2019): 113–16. http://dx.doi.org/10.33894/mtk-2019.11.24.

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Abstract Nowadays one of the main lines of development in aerial craft is the design and construction of unmanned aerial vehicles (UAV’s). Within this wide topic, development of ultralight (UL) aircrafts is especially popular because of their versatility and relative low cost. My task was to design the shape of an airplane wing-fuselage junction, which will be classified as an ultralight and unmanned aerial vehicle. The most optimal wing-fuselage junction is made with the Ansys simulating program, including model calculations. Based on the calculations and results, solutions can be recommended. With CAD geometry models, first stage of testing of the aircraft with 3D printed models, is prepared.

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32

Magill, S. A. N. "On The Vertical Speeds Of Airways Traffic." Journal of Navigation 49, no. 1 (January 1996): 58–71. http://dx.doi.org/10.1017/s0373463300013102.

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Knowledge of the statistics of aircraft vertical speeds is important both for the construction of realistic traffic simulators and for the development of trajectory prediction tools for use in future air traffic control (ATC) systems. This paper reports on the analysis of radar data recordings for nearly 10000 civil flights on airways. Results are presented for the means and spreads of vertical speeds as functions of altitude. Evidence is presented that roughly half of the observed spreads arise from fluctuations within each aircraft's trajectory, as opposed to variation from one aircraft to another. A simple procedure is proposed for simulating vertical speed data which has statistics similar to those obtained from the radar recordings. Some consequences of the results for the development of trajectory prediction tools for use in future ATC systems are discussed. The results suggest that the provision of accurate trajectory prediction tools is not as straightforward as it might at first appear to be.

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Nöding, Michel, and Lothar Bertsch. "Application of Noise Certification Regulations within Conceptual Aircraft Design." Aerospace 8, no. 8 (August 3, 2021): 210. http://dx.doi.org/10.3390/aerospace8080210.

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ICAO Annex 16 regulations are used to certify the acoustic performance of subsonic transport aircraft. Each aircraft is classified according to the measured EPNL levels at specific certification locations along the approach and departure. By simulating this certification process, it becomes possible to identify all relevant parameters and assess promising measures to reduce the noise certification levels in compliance with the underlying ICAO regulations, i.e., allowable operating conditions of the aircraft. Furthermore, simulation is the only way to enable an assessment of novel technology and non-existing vehicle concepts, which is the main motivation behind the presented research activities. Consequently, the ICAO Annex 16 regulations are integrated into an existing noise simulation framework at DLR, and the virtual noise certification of novel aircraft concepts is realized at the conceptual design phase. The predicted certification levels can be directly selected as design objectives in order to realize an advantageous ICAO noise category for a new aircraft design, i.e., simultaneously accounting for the design and the resulting flight performance. A detailed assessment and identification of operational limits and allowable flight procedures for each conceptual aircraft design under consideration is enabled. Sensitivity studies can be performed for the relevant input parameters that influence the predicted noise certification levels. Specific noise sources with a dominating impact on the certification noise levels can be identified, and promising additional low-noise measures can be applied within the conceptual design phase. The overall simulation process is applied to existing vehicles in order to assess the validity of the simulation resultsfcompared to published data. Thereafter, the process is applied to some DLR low-noise aircraft concepts to evaluate their noise certification levels. These results can then be compared to other standard noise metrics that are typically applied in order to describe aircraft noise, e.g., SEL isocontour areas. It can be demonstrated that certain technologies can significantly reduce the noise impact along most of an approach or departure flight track but have only a limited influence on the noise certification levels and vice versa. Finally, an outlook of the ongoing developments is provided, in order to apply the new simulation process to supersonic aircraft. Newly proposed regulations for such concepts are implemented into the process in order to evaluate these new regulations and enable direct comparison with existing regulations.

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Liu, Wendi, Omar Ahmed Mahfoze, Stephen M. Longshaw, Alex Skillen, and David R. Emerson. "Simulating Slosh Induced Damping, with Application to Aircraft Wing-like Structures." Applied Sciences 12, no. 17 (August 25, 2022): 8481. http://dx.doi.org/10.3390/app12178481.

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The added damping generated by liquid sloshing in a tank has been utilized in a number of civil applications, including aviation, to reduce the vibration of the system. As part of a wider EU H2020 project called SLOWD (Sloshing Wing Dynamics), the presented study performed numerical simulations on the slosh-induced damping of liquid in tanks that were under free decay oscillations and embedded in an aircraft wing-like structure. A new open-source partitioned fluid–structure interaction software framework is presented and employed for the numerical simulations. Periodic sloshing waves and violent vertical fluid motions are observed in the study. These demonstrate the effects of slosh-induced damping under different excitation amplitudes of the structure and a varying number of baffled regions within the tank. Various sloshing patterns caused by different combinations of the excitation amplitude and compartment numbers lead to different induced dampings of the free decay motion. We observed a distinctly non-monotonic function on the slosh damping when the initial excitation amplitude is small (i.e., 0.25), with a 59% reduction when we increase the number of baffled compartments from one to four, and a 153% increase when moving from one to eight compartments. This is due to the change in the sloshing wave frequency, resulting in a significant change in the impact of the fluid between the tank ceiling and the wave crests. When the initial excitation amplitude is large (i.e., 1.0), there is no significant change in the slosh-induced damping when changing the number of compartments in the tank, for the range of parameters considered, due to the highly turbulent fluid motion. This work is expected to form the basis of further, more detailed studies within the context of the SLOWD project and its ever-expanding experimental data output.

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LIN, Mengda, Guixiang CUI, and Zhaoshun ZHANG. "A new vortex sheet model for simulating aircraft wake vortex evolution." Chinese Journal of Aeronautics 30, no. 4 (August 2017): 1315–26. http://dx.doi.org/10.1016/j.cja.2017.04.015.

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Wu, Wei Guo, Zhen Tao Wang, and Teng Jia. "Nonlinear Dynamic Response Analysis of Aircraft Landing Gear with Finite Element Modeling." Applied Mechanics and Materials 826 (February 2016): 23–27. http://dx.doi.org/10.4028/www.scientific.net/amm.826.23.

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The precise model and the analysis of nonlinear response are important for the landing gear research. In this paper, the FEM model of landing gear was established. The shock absorber is modeled with the nonlinear spring and damper. Random displacements were applied for simulating runway unevenness at aircraft taxiing. Through the simulation, the nonlinear FEM dynamic response of landing gear was acquired. The results show that: the stress of landing gear is large in the landing progress, especially for the random displacements; the weakness of landing gear is the axle sleeve. So the material and technology of the axle sleeve are important in the design of landing gear.

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BOUGHARI, Yamina, Ruxandra Mihaela BOTEZ, Amir BANIAMERIAN, Ehsan SOBHANI TEHRANI, and Armineh GARABEDIAN. "Validation of Aero-Load Estimator for Convair 880 Aircraft Flight Simulator Benchmark with Electro-Hydrostatic Actuators." INCAS BULLETIN 13, no. 3 (September 4, 2021): 13–27. http://dx.doi.org/10.13111/2066-8201.2021.13.3.2.

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Simulating an aircraft model using of high fidelity models of subsystems for its primary and secondary flight control actuators requires measuring or estimating aero-load data acting on flight control surfaces. One solution would be to incorporate the data recorded from flight tests, which is a time-consuming and costly process. This paper proposes another solution based on the validation of an aero-loads estimator or on the hinge moments predictor for fully electrical aircraft simulator benchmark. This estimator is based on an aerodynamic coefficient calculation methodology, inspired by Roskam’s method that uses the geometrical data of the wing and control surfaces airfoils. The hinge moment values are found from two-dimensional lookup tables where the deflections of the control surfaces, aircraft altitude, and aircraft angles of attack are the input vectors of the tables; and the resulting hinge moment coefficients are the output vectors. The resulting hinge moment coefficients of the Convair 880 primary flight control surfaces are compared to those of its recorded flight test data; the results from the new software solution were found to be very accurate. Hinge moment lookup tables are integrated in the Convair 880 high fidelity flight simulation benchmark using mathematical models of energy-efficient Electro-Hydrostatic Actuators (EHA). Autopilot controls are designed for the roll, pitch, attitude and yaw damper motions using Proportional Integral (PI) controller scheduled for different flight conditions. Several different aircraft simulation scenarios are evaluated to demonstrate the efficacy and accuracy of the predicted hinge moment results.

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Khalili, S. M. R., M. Assar, R. Eslami Farsani, and I. Hajiyousefi. "Numerical Study on Impact Response of Aircraft Sandwich Wing Made of Fiber-Metal Laminate Face-Sheets Subjected to Bird Strike." Advanced Materials Research 488-489 (March 2012): 8–13. http://dx.doi.org/10.4028/www.scientific.net/amr.488-489.8.

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Aircraft structures are frequently subjected to impacts from objects such as runway debris and birds. In new aircraft structural design, Fiber Metal Laminates (FMLs) play a significant role due to their excellent mechanical properties, particularly the impact properties. In this study, the aircraft sandwich wing with FML face-sheets are analyzed by finite element model for simulating the bird strike. The numerical simulations of bird strike impact are performed adopting a lagrangian approach to design the wing by MSC/PATRAN FE code. The numerical obtained results are compared with the results in the literature for validation of the model. The effect of fiber orientations, fiber types, metal types in FML face sheets in sandwich wing on impact responses are investigated. The impact responses are illustrated by displacement history, contact force history and energy absorption. According to these results, the sandwich panel with FML skin is suitable structure for energy absorption (that is the most important factor in impact phenomena). The lay-ups with titanium metal layer with aramid fibers are the best.

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Karunakaran, Sreedhar. "Innovative application of LSS in aircraft maintenance environment." International Journal of Lean Six Sigma 7, no. 1 (March 7, 2016): 85–108. http://dx.doi.org/10.1108/ijlss-01-2015-0001.

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Purpose – The purpose of this paper is to eliminate the wastes and inefficient procedures in the maintenance organization of aircraft so as to reduce its downtime and increase mission availability. Design/methodology/approach – Customized lean Six Sigma (LSS) was applied at the task level and servicing cycle level to reduce the task content, cycle length and resources in servicing. The loading of the servicing facility was simulated through a simulation program developed from a statistical analysis of historical data for validating/simulating/determining optimum loading of servicing facility with refined tasks, reduced cycle length and resources. In simulation, the optimum combination of manpower, resources and infrastructure at the facility level was determined through sensitive analysis and design of experiments (DoE). Findings – Optimization at the task level and its re-organization at the servicing cycle level reduced the cycle length by 55-68 per cent and manpower resources by 26 per cent. This further reduced facility-level manpower by 25 to 40 per cent, capacity requirements by more than 33 per cent and annual aircraft downtime by 78 per cent. The approach reduced the average number of aircraft undergoing servicing at each airbase at any time from 2.35 to just 0.76 and increased the mission availability to 20 per cent. Originality/value – The hallmark of the paper has been the design of LSS approach from structured historical data and its validation through innovative simulation. The multi-pronged bottom-up approach practically bundles all wastes resident in the maintenance organization. The paper provides cursory approach to lean practitioners in the elimination of wastes in the maintenance of capital assets like aircraft.

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Mardanpour, Pezhman, and Dewey H. Hodges. "On the Importance of Nonlinear Aeroelasticity and Energy Efficiency in Design of Flying Wing Aircraft." Advances in Aerospace Engineering 2015 (January 18, 2015): 1–11. http://dx.doi.org/10.1155/2015/613962.

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Energy efficiency plays important role in aeroelastic design of flying wing aircraft and may be attained by use of lightweight structures as well as solar energy. NATASHA (Nonlinear Aeroelastic Trim And Stability of HALE Aircraft) is a newly developed computer program which uses a nonlinear composite beam theory that eliminates the difficulties in aeroelastic simulations of flexible high-aspect-ratio wings which undergoes large deformation, as well as the singularities due to finite rotations. NATASHA has shown that proper engine placement could significantly increase the aeroelastic flight envelope which typically leads to more flexible and lighter aircraft. The areas of minimum kinetic energy for the lower frequency modes are in accordance with the zones with maximum flutter speed and have the potential to save computational effort. Another aspect of energy efficiency for High Altitude, Long Endurance (HALE) drones stems from needing to minimize energy consumption because of limitations on the source of energy, that is, solar power. NATASHA is capable of simulating the aeroelastic passive morphing maneuver (i.e., morphing without relying on actuators) and at as near zero energy cost as possible of the aircraft so as the solar panels installed on the wing are in maximum exposure to sun during different time of the day.

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41

Nasir, Rizal E. M., Wahyu Kuntjoro, and Wirachman Wisnoe. "Investigation on the Effect of Airspeed and Altitude to Phugoid Mode of a Small Unmanned Blended Wing-Body Aircraft with Canard as a Longitudinal Control Surface." Applied Mechanics and Materials 225 (November 2012): 375–84. http://dx.doi.org/10.4028/www.scientific.net/amm.225.375.

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Phugoid mode is a lowly damped, low-frequency oscillatory motion representing vertical translation usually related to kinetic and potential energy interchange. MIL-F-8785C standard has ruled out qualitative specification requirements on measurement of flying and handling qualities of piloted aircraft. For phugoid mode, these requirements lie in the value of its damping ratio. Small aircraft is sensitive to atmospheric conditions and poor phugoid mode performance is observed in many unmanned aircraft. This paper discusses the effect of airspeed and altitude to phugoid mode of small, unmanned blended wing-body (BWB) aircraft named Baseline-II E-2. Baseline-II is a low subsonic, remotely-piloted UAV used to study the behaviour of a BWB-type aircraft. The case presented here is an E-2 version in which a specifically-designed canard is incorporated as its longitudinal control surface. Five Category B flight cases (airspeeds) per altitude-case, and three altitude cases (low, medium and high) are studied. Model-N dynamic model is introduced here to become the basis of flight simulation. The model is compared to models derived by other authors and approximation equations. The mean of simulating phugoid behaviour is using state-space representation of the aircraft using Matlab SIMULINK. The computations show that Baseline-II E-2 undamped natural frequency of phugoid mode is inversely-proportional to airspeed and reduces as altitude increases. These have adverse effect on its damping ratio that increases near parabolically when the aircraft flies faster, and reduces when it climbs up. The cause of these trends is looked into in detail and issues concerning Baseline-II E-2’s unsatisfactory and unstable phugoid mode oscillation at low speed are addressed.

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42

Chen, Jinhe, Zhengzhong Wang, and Hongyuan Tian. "Hurdle-Hop Simulation of Tilt-Rotor Aircraft Based on Optimal Control Theory." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 38, no. 6 (December 2020): 1266–74. http://dx.doi.org/10.1051/jnwpu/20203861266.

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Aiming at simulating the hurdle-hop of tilt-rotor aircraft in forward flight near the ground, two models of numerical simulation and analysis based on optimal control theory were proposed. Firstly, Longitudinal flight dynamic model for tilt-rotor was modified considering the influence of ground effect. Secondly, the first model is combined with predicted trajectory from inverse simulation method, the inverse model of hurdle-hop of tilt-rotor is established based on optimal trajectory, and the second model is the optimal control model of unpredicted trajectory, which is formulated from the reasonable function of objective, path and boundary constraints for hurdle-hop with detailed analysis, solved two models by direct multiple shooting method and nonlinear programming algorithm. Finally, XV-15 as the sample vehicle. Two models for hurdle-hop based on optimal control theory was calculated, the history of optimal flight trajectory and control are given.

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Xing, Zhi Wei, and Bing Jun Ding. "Intelligent Control Method for Aircraft Deicing Fluidtemperature Based on a New Adaptive Smith Predictor." Advanced Materials Research 424-425 (January 2012): 936–40. http://dx.doi.org/10.4028/www.scientific.net/amr.424-425.936.

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During the course of industry control, pure hysteresis, time-varying，non- linear complex systems often occur. It is ineffective to solve the issues above with the traditional fuzzy control and PID control methods. Against the pure hysteresis, time-varying, non- linear characteristics of Aircraft Deicing Fluid rapid heating system, on the basis of Smith Predictor and traditional PID, a Fuzzy-PID control method is proposed based on an adaptive Smith predictor. In this way, pure hysteresis of the system will be compensated, to reduce the overshoot and enhance the stability of the system. By establishing the mathematical model of Aircraft Deicing Fluid rapid heating system and simulating for the model obtain the simulation results, which have shown that the method is effective, can improve the qualities of control and enhance the stability of temperature control system significantly

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44

Hendricks, J., B. Kärcher, A. Döpelheuer, J. Feichter, U. Lohmann, and D. Baumgardner. "Simulating the global atmospheric black carbon cycle: a revisit to the contribution of aircraft emissions." Atmospheric Chemistry and Physics Discussions 4, no. 3 (June 22, 2004): 3485–533. http://dx.doi.org/10.5194/acpd-4-3485-2004.

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Abstract. The black carbon (BC) burden of the upper troposphere and lowermost stratosphere (UTLS) is investigated with the general circulation model (GCM) ECHAM4. The special focus is the contribution of aircraft emissions to the UTLS BC loading. Previous studies on the role of aircraft emissions in the global BC cycle either neglect BC sources located at the Earth's surface or simplify the BC cycle by assuming pre-defined BC residence times. Here, the global BC cycle including emissions, transport, and removal is explicitly simulated. The BC emissions considered include surface sources as well as BC from aviation. This enables a consistent calculation of the relative contribution of aviation to the global atmospheric BC cycle. As a further extension to the previous studies, the aviation-induced perturbation of the UTLS BC particle number concentration is investigated. Several sensitivity studies were performed to evaluate the uncertainties associated with the model predictions. The simulated UTLS BC concentrations are compared to in-situ observations. The simulations suggest that the large-scale contribution of aviation to the UTLS BC mass budget typically amounts to only a few percent, even in the most frequented flight regions. The aviation impact far away from these regions is negligible. The simulated aircraft contributions to the UTLS BC particle number concentration are much larger compared to the corresponding mass perturbations. The simulations suggest that aviation can cause large-scale increases in the UTLS BC particle number concentration of more than 30% in regions highly frequented by aircraft. The relative effect shows a pronounced annual variation with the largest relative aviation impact occurring during winter.

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45

Hale, Alan, Milt Davis, and Jim Sirbaugh. "A Numerical Simulation Capability for Analysis of Aircraft Inlet-Engine Compatibility." Journal of Engineering for Gas Turbines and Power 128, no. 3 (March 1, 2004): 473–81. http://dx.doi.org/10.1115/1.1925649.

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Two primary aircraft propulsion subsystems are the inlet and the engine. Traditionally these subsystems have been designed, analyzed, and tested as isolated systems. The interaction between the subsystems is modeled primarily through evaluating inlet distortion in an inlet test and then simulating this distortion in engine tests via screens or similar devices. Recently, it has been recognized that significant improvements in both performance and operability can be realized when both the inlet and the engine are designed with full knowledge of the other. In this paper, a computational tool called Turbine Engine Analysis Compressor Code is used to evaluate the effect of inlet distortion on a three-stage military fan. This three-stage military fan is further connected to an F-16 inlet and forebody operating at an angle of attack and sideslip to demonstrate the effect of inlet distortion generated by flight maneuvers. The computational approach of simulating an integrated inlet-engine system is expected to provide additional insight over evaluating the components separately.

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46

Miller, R. A. "Progress Toward Life Modeling of Thermal Barrier Coatings for Aircraft Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 109, no. 4 (October 1, 1987): 448–51. http://dx.doi.org/10.1115/1.3240062.

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Progress toward developing life models for simulating the behavior of thermal barrier coatings in aircraft gas turbine engines is discussed. A preliminary laboratory model is described as are current efforts to develop engine-capable models. Current understanding into failure mechanisms is also summarized.

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47

Hendricks, J., B. Kärcher, A. Döpelheuer, J. Feichter, U. Lohmann, and D. Baumgardner. "Simulating the global atmospheric black carbon cycle: a revisit to the contribution of aircraft emissions." Atmospheric Chemistry and Physics 4, no. 11/12 (December 10, 2004): 2521–41. http://dx.doi.org/10.5194/acp-4-2521-2004.

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Abstract. The black carbon (BC) burden of the upper troposphere and lowermost stratosphere (UTLS) is investigated with the general circulation model (GCM) ECHAM4. The special focus is the contribution of aircraft emissions to the UTLS BC loading. Previous studies on the role of aircraft emissions in the global BC cycle either neglect BC sources located at the Earth's surface or simplify the BC cycle by assuming pre-defined BC residence times. Here, the global BC cycle including emissions, transport, and removal is explicitly simulated. The BC emissions considered include surface sources as well as BC from aviation. This enables a consistent calculation of the relative contribution of aviation to the global atmospheric BC cycle. As a further extension to the previous studies, the aviation-induced perturbation of the UTLS BC particle number concentration is investigated. The uncertainties associated with the model predictions are evaluated by means of several sensitivity studies. Especially, the sensitivity of the results to different assumptions on the BC hygroscopic properties is analysed. The simulated UTLS BC concentrations are compared to in-situ observations. The simulations suggest that the large-scale contribution of aviation to the UTLS BC mass budget typically amounts to only a few percent, even in the most frequented flight regions. The aviation impact far away from these regions is negligible. The simulated aircraft contributions to the UTLS BC particle number concentration are much larger compared to the corresponding mass perturbations. The simulations suggest that aviation can cause large-scale increases in the UTLS BC particle number concentration of more than 30% in regions highly frequented by aircraft. The relative effect shows a pronounced annual variation with the largest relative aviation impact occurring during winter.

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48

Giitsidis, Themistoklis, Nikolaos I. Dourvas, and Georgios Ch Sirakoulis. "Parallel implementation of aircraft disembarking and emergency evacuation based on cellular automata." International Journal of High Performance Computing Applications 31, no. 2 (July 28, 2016): 134–51. http://dx.doi.org/10.1177/1094342015584533.

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In this paper we present a model based on the parallel computational tool of cellular automata (CA) capable of simulating the process of disembarking in a small airplane seat layout, corresponding to Airbus A320/ Boeing 737 layout, in search of ways to make it faster and safer under normal evacuation conditions, as well as emergency scenarios. The proposed model is highly customizable, with the number of exits, the walking speed of passengers, depending on their sex, age and height, and the effects of retrieving and carrying luggage. Additionally, the presence of obstacles in the aisles as well as the emergence of panic being parameters whose values can be varied in order to enlighten the disembarking and emergency evacuation processes are considered in detail. The simulation results were compared to existing aircraft disembarking and evacuation times and indicate the efficacy of the proposed model in investigating and revealing passenger attributes during these processes in all the examined cases. Moreover, we parallelized our code in order to run on a graphics processing unit (GPU) using the CUDA programming language, speeding up the simulation process. Finally, in order to present a fully dynamical anticipative real-time system helpful for decision-making we implemented the proposed CA model in a field programmable gate array (FPGA) device, and recreated the results given by the software simulations in a fraction of the time. We then compared and exported the performance results among a sequential software implementation, the implementation running on a GPU, and a hardware implementation, proving the consequent acceleration that results from the parallel CA implementation in specific hardware.

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Ratvasky, Thomas P., Billy P. Barnhart, and Sam Lee. "Current Methods Modeling and Simulating Icing Effects on Aircraft Performance, Stability, Control." Journal of Aircraft 47, no. 1 (January 2010): 201–11. http://dx.doi.org/10.2514/1.44650.

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50

Sharma, S., Y. Sun, and L. Udpa. "Finite element modeling for simulating remote field flaw detection in aircraft frame." IEEE Transactions on Magnetics 35, no. 3 (May 1999): 1750–53. http://dx.doi.org/10.1109/20.767368.

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Journal articles on the topic 'Simulating Aircraft'

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