Relevant bibliographies by topics / Aircraft modelling

Academic literature on the topic 'Aircraft modelling'

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

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Journal articles on the topic "Aircraft modelling"

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Al-Ahmed, S., and J. P. Fielding. "Vulnerability prediction method for use in aircraft conceptual design." Aeronautical Journal 103, no. 1024 (June 1999): 309–15. http://dx.doi.org/10.1017/s0001924000064903.

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Abstract A methodology has been developed to integrate the vulnerability discipline into the conceptual/preliminary design process of combat aircraft. An interactive and programmable solid modelling Computer Aided Design (CAD) system is used to generate a CAD solid model of the aircraft’s critical components. The aircraft’s components’ sizes and shapes are pre-defined by a conceptual/preliminary design synthesis computer model. A systematic Child-Parent assembly process is used to model the aircraft vulnerability, by defining the criticality degree of each component in the aircraft assembly. Solid Modelling CAD techniques have been modified to develop techniques to perform the two main standard vulnerability assessments, namely the shotline and vulnerable area methods.
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Döpelheuer, Andreas. "Aircraft emission parameter modelling." Air & Space Europe 2, no. 3 (May 2000): 34–37. http://dx.doi.org/10.1016/s1290-0958(00)80060-x.

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Zhaohui, Ming, Zhang Ming, Tang Xinmin, and Han Song-Chen. "Structural Modelling and Deceleration Algorithm for a Follow Aircraft on Performance-Based Navigation Airway Based on Multi-Agent Technique." Cybernetics and Information Technologies 15, no. 6 (December 1, 2015): 46–56. http://dx.doi.org/10.1515/cait-2015-0066.

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Abstract Considering the operation characteristics of the high-speed PBN airway, we propose an aircraft agent structural model and a basic algorithm flow of decision-making by Multi-agent technique. According to the constraint of safe separation and speed with the aircrafts, making use of the car-following theory, the deceleration constraint model is built for a flight management system. When the front aircraft decelerates, the model can offer a speed adjustment proposal for the following aircraft. The model is built based on the minimal safe separation and speed interval constraint; each variable, influencing the deceleration of the following aircraft can be analyzed. Simulation analysis is carried out for different combinations of aircraft types, initial speed, safe separation and deceleration. The follow aircraft deceleration was calculated under different conditions and the results coincided with reality. It is proved that the model can provide safe separation between the two aircrafts.
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Galea, E., and N. Markatos. "Modelling Of Aircraft Cabin Fires." Fire Safety Science 2 (1989): 801–10. http://dx.doi.org/10.3801/iafss.fss.2-801.

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Dongsheng, Chen, He Yan, and Zhou Mengqian. "Research on operation scenario based aircraft power system architecture analysis and modelling." E3S Web of Conferences 271 (2021): 01017. http://dx.doi.org/10.1051/e3sconf/202127101017.

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Aircraft power system is a complex system consisting of the power generation system, the power management and distribution system, and the power consumption system, which accounts for the aircraft's major fuel consumption and emissions. This paper proposes a scenario-based comprehensive power requirement analysis and system architecture methodology in order to alleviate the risk of systems over-design and discoordination caused by traditional bottom-up load collection and individual system design. Starting from the operation scenario, system functions are identified and corresponding physical architecture and power loads are analysed. Given the complexity of operation scenarios and aircraft power system, model-based system engineering methodology is applied to the top-down aircraft power system architecture design. SysML tool is used to carry out to analyse the aircraft power system architecture during taxi scenario, which provides great advantages on model tracing and reuse.
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Albagory, Yasser. "Modelling, Investigation, and Feasibility of Stratospheric Broadband mm-Wave 5G and beyond Networks for Aviation." Electronics 9, no. 11 (November 7, 2020): 1872. http://dx.doi.org/10.3390/electronics9111872.

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Recent advances in communication systems provide an enabling technology for aircraft connection and safety. A promising communication system that uses stratospheric platforms provides an efficient and improved communication performance and can be an efficient solution for establishing communication networks for aviation. Therefore, in this paper, a novel communication network based on stratospheric basestation (SB) is proposed to provide fifth-generation (5G) and beyond services for civil aviation aircrafts to improve global flight connectivity, control, and safety. The proposed aircraft–SB network is demonstrated, and its coverage geometry is modelled and investigated. As the 5G and beyond networks use millimeter wave frequency bands (mm-wave), the performance of different atmospheric losses including gaseous absorption, rain, and fog/cloud is analyzed to investigate the system’s practical feasibility at different 5G proposed frequencies ranging from 3.5 to 66 GHz through a flight model including three distinct stages which are takeoff/landing, climbing/descending, and cruise stages. Also, handover scenarios in the proposed aircraft–SB network are investigated and analyzed at the proposed 5G frequencies. In addition, the aircraft–SB 5G network is compared to the most recent low-Earth orbit (LEO) Internet satellites where the proposed system is expected to provide low latency, less atmospheric attenuation, longer aircraft–SB link duration, and very low handover rate.
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Levinski, O. "Aeroelastic modelling of aircraft empennage buffet." ANZIAM Journal 45 (September 6, 2004): 981. http://dx.doi.org/10.21914/anziamj.v45i0.936.

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Scanlan, Jim, Terry Hill, Rob Marsh, Christophe Bru, Martin Dunkley, and Paul Cleevely. "Cost modelling for aircraft design optimization." Journal of Engineering Design 13, no. 3 (September 2002): 261–69. http://dx.doi.org/10.1080/09544820110108962.

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Mengall, G. "Fuzzy modelling for aircraft dynamics identification." Aeronautical Journal 105, no. 1051 (September 2001): 551–55. http://dx.doi.org/10.1017/s0001924000018029.

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A new methodology is described to identify aircraft dynamics and extract the corresponding aerodynamic coefficients. The proposed approach makes use of fuzzy modelling for the identification process where input/output data are first classified by means of the concept of fuzzy clustering and then the linguistic rules are extracted from the fuzzy clusters. The fuzzy rule-based models are in the form of affine Takagi-Sugeno models, that are able to approximate a large class of nonlinear systems. A comparative study is performed with existing techniques based on the employment of neural networks, showing interesting advantages of the proposed methodology both for the physical insight of the identified model and the simplicity to obtain accurate results with fewer parameters to be properly tuned.
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Kachel, Stanisław. "Control Curves Method of Airframe Geometry Modeling." Solid State Phenomena 199 (March 2013): 279–84. http://dx.doi.org/10.4028/www.scientific.net/ssp.199.279.

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The paper presents the methodological approach to development of curves by selection of driving parameters with the application of the method to designing and reproduction of aircraft surfaces on the examples of both newly designed aircrafts and the ones that are already in service. The major assumptions are outlined that are necessary to develop the mathematical model of driving curves and surfaces, these assumptions served as the basis to draw up the relevant algorithms and to convert them to routines of the GRIP (Graphics Interactive Programming) language that is a part of the CAD/CAM/CAE Unigraphics system. These algorithms include the newly developed tool dedicated to design aircraft components and provided with inputs to the multi-criteria synthesis of the aerodynamic profiles of aircrafts. The study comprises also the assumptions to the newly developed algorithms dedicated to modelling of components incorporated into aircraft structures, these algorithms have been successfully implemented by the author.
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Dissertations / Theses on the topic "Aircraft modelling"

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Rubin, Felix. "Modelling & Analysis of a TiltWing Aircraft." Thesis, KTH, Flygdynamik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-244832.

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The aim of this report is the investigation of a hybrid vertical take-off and landing (VTOL) tilt wing aircraft which is in development at the company Dufour Aerospace. Using a model, programmed in MATLAB® different stages of flight can be simulated and investigated. Maininvestigation area of this report is the transition between cruise and hover conditions of the aircraft.The simulation is based on the six-degree-of-freedom nonlinear equations of motion for aircraft modified for tilt wing operation. The model characteristics have been determined using various CFD programs, wind tunnel data, as well as numerical and handbook methods.The main focus of modeling lies on the static longitudinal aerodynamic coefficients, the propeller and engine coefficients as well as a propeller slipstream model. Furthermore lateral directional aerodynamic coefficients and dynamic effects and a tail blower (Notar) system are modeled.As results, aerodynamic characteristics of the wing in the propeller slipstream are shown and discussed and the transition conditions are investigated by ’trimming’ the model at equilibrium points over its speed range and analyzing the resulting power requirements.
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Harasani, W. "Aircraft conceptual design decision through operational modelling." Thesis, Cranfield University, 2005. http://dspace.lib.cranfield.ac.uk/handle/1826/11093.

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Aircraft manufacturing is not only a difficult business but also a very competitive one, the consequences of any drop in sales would cost billions, loss of jobs, and maybe an economical failure. Therefore, concentrating on just flight performance and adding new technologies just because they exit is not enough to win the airlines attention, especially the flow cost carriers. Manufactures must be able to convince operators that the application of a new design or technology will produce a favourable change in the bottom line of their balance sheets and not just a reduction in fuel burn. Aircraft designers must put more emphasis on what happens to the aircraft after it leaves the assembly line, through the designed life operation cycle of the aircraft with the airline customer, quality should be built in to the aircraft. Knowing what are the airline's concerns, how the aircraft with a given design behaves, and the issues that the airline has, is vital. Firstly, it is important to know what are the issues that the airline has, the costumer (airlines) needs are identified, and, since fleet planning is the top level decision making department in the airline in which a decision is made to buy one aircraft over the other, it is important to understand the process and the elements that are involved in fleet planning. So fleet planning was studied. Second different technologies for the design have been looked at and selected. Then the aircraft, airline, airport, and air traffic control are studied, as well as the interaction between them. A key element of the research is a simulation program DEBOS that has been built to see the impact of the different design technologies and concepts through the operation of a simulation fleet size of 23 aircraft. The Boeing777 aircraft has been chosen to be the base line of the study. Finally, it was found that a given technology with improved performance, or a new concept, would improve the aircraft attractiveness only if it has better life cycle behaviour characteristics.
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Poudel, Minesh. "Aircraft emergency evacuation : analysis, modelling and simulation." Toulouse 2, 2008. http://www.theses.fr/2008TOU20026.

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Cette thèse s’intéresse à l’évacuation d’urgence des avions et plus particulièrement à la conception d’un simulateur numérique capable de représenter de façon réaliste ce processus afin de contribuer à la certification de configurations et de procédures d’évacuation d’urgence pour les avions gros porteurs. Cette thèse est composée de deux grandes parties. Dans la première partie, il s’est agi d’identifier le problème, de réaliser un état de l’art et de caractériser le comportement des passagers pendant l’évacuation. Dans la deuxième partie de la thèse il s’est agi de concevoir les élément constitutifs d’un simulateur d’évacuation d’urgence des aéronefs. Après avoir analysé les modèles existants et revu les méthodes de modélisation des systèmes dynamiques cellulaires, le schéma conceptuel d’un tel simulateur a été développé. Le simulateur d’évacuation d’urgence a été conçu via UML en langage Java. En conclusion, les perspectives concernant la poursuite de cette étude sont présentées
This thesis is about aircraft emergency evacuation and its principal objective is to establish a computational model able to simulate realistically it. This will contribute to the certification process of new aircraft emergency evacuation layouts and egress procedures for large capacity airliners. This thesis is composed of two main parts. In the first one, the main problem issues are identified, a state of the art in emergency evacuation from aircraft is realized and human behaviours during such an event are described. In the second part of this work, the elements of the emergency evacuation model are identified. After analysing existing models and different models of dynamic cellular systems, the conceptual model of this simulator is proposed. Its framework has been designed using UML and the routines are written in Java. Finally future research directions are given
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Shao, Liang. "GNSS performance modelling for high interrity aircraft applications." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7442.

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Till recently, no significant attempts have been made of developing Aircraft Based Augmentation System (ABAS) architectures capable of generating integrity signals suitable for safety-critical GNSS applications and no commercial ABAS products are available at present. The aim of this research is to support the design a system that generates integrity signals suitable for GNSS application. The conceptual design and key mathematical models were recently developed by the Italian Air Force Experimental Flight Test Centre (CSV-RSV) [1, 2]. Such a system, would be able to provide steering information to the pilot, allowing for real-time and continuous integrity monitoring, avoidance of safety/mission-critical flight conditions and fast recovery of the required navigation performance in case of GNSS data losses. The key elements addressed in this thesis are the development of a CATIA model for military and civil aircraft, supporting antenna obscuration and multipath analysis. This is to allow the ABAS system to generate suitable integrity flags when satellites signals are lost. In order to analyse the GNSS signal loss causes, the GNSS constellation models, the flight dynamics models, fading models, multipath models, Doppler shift models, and GNSS receiver tracking technology previously developed by CSV-RSV, are considered in this research.
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Wu, Tao. "Integrative system modelling of aircraft electrical power systems." Thesis, University of Nottingham, 2010. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.537690.

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Areerak, Kongpan. "Modelling and stability analysis of aircraft power systems." Thesis, University of Nottingham, 2009. http://eprints.nottingham.ac.uk/12944/.

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The more-electric aircraft concept is a major trend in aircraft electrical power system engineering and results in an increase in electrical loads based on power electronic converters and motor drive systems. Unfortunately, power electronic driven loads often behave as constant power loads having the small-signal negative impedance that can significantly degrade the power system stability margin. Therefore, the stability issue of aircraft power systems is of great importance. The research of the thesis deals with the modelling and stability analysis of an aircraft power system. The aircraft power system architecture considered in the thesis is based on the More Open Electrical Technologies (MOET) aircraft power system with one generator as only a single generator can be connected to a system at any one time. The small-signal stability analysis is used with the system dynamic model derived from the dq modelling method under the assumption that the aircraft power system operating point does not change rapidly during normal operation mode. The linearization technique using the first order terms of a Taylor expansion is used so as to achieve a set of linear models around an equilibrium point for a small-signal stability study. The thesis presents the development of effective models capable of representing the electrical power system dynamic behaviour for stability studies. The proposed model can be used to predict the instability point for variations in operating points and/or system parameters. Agreement between the theoretical estimation, simulation, and experimental results for a simple system are achieved that ranges from acceptable to very good. Finally, the subsystem models described in the thesis can be interconnected in an algorithmic way that is representative of a more generalized aircraft power system model. The generalized model is also applied to a more complex and realistic aircraft power system with simulation validations for thorough investigations of aircraft power system stability. This model may be considered as a powerful and flexible stability analysis tool to analyse the complex multi-converter electrical power systems.
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Coetzee, Etienne. "Modelling and nonlinear analysis of aircraft ground manoeuvres." Thesis, University of Bristol, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.541611.

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Hoff, J. C. "Aircraft parameter estimation by estimation - before - modelling technique." Thesis, Cranfield University, 1995. http://dspace.lib.cranfield.ac.uk/handle/1826/10748.

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The use of the estímation-before-modellíng (EBM) two step identification procedure for the determination of aircraft aerodynamic derivatives from flight test data is analysed and illustrated. In the first step of the identification procedure the usual Extended Kalman Filter (EKF) associated with the Modified Bryson-Frazíer (MBF) smoother is compared with a new alterative filtering and smoothing process. The new smoother is simpler and less computationally demanding than the MBF smoother. However, its main advantage is that it enables simultaneous data smoothing with state derivative estimation, thereby avoiding the need for a separate differentiation algorithm. The new smoother differentiator has an important feature that is the determination of the noise characteristics of the measurement signal under analysis prior to the smoothing process. This is done by variance matching between the theoretical and measured autocorrelation of the innovation process generated by a Kalman filter. The new technique is compared with the old one by determining the aerodynamic models for a EMB-312 Tucano dutch roll manoeuvre. It is demonstrated that the new smoother may be used to replace the MBF. Otherwise the new technique is used in the analysis of the Handley Page Jetstream-100 aircraft low speed controls free phugoid trying to identify the contribution of the power Variation observed during the phugoid to the stability of the oscillation. Finally the models obtained from the phugoid analysis are reprocessed using the Total Least Square regression and the results are compared with those from the ordinary Least Square formulation.
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Von, Klemperer Nicholas. "Dual-axis tilting quadrotor aircraft: Dynamic modelling and control of dual-axis tilting quadrotor aircraft." Master's thesis, Faculty of Engineering and the Built Environment, 2018. http://hdl.handle.net/11427/30156.

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This dissertation aims to apply non-zero attitude and position setpoint tracking to a quadrotor aircraft, achieved by solving the problem of a quadrotor’s inherent underactuation. The introduction of extra actuation aims to mechanically accommodate for stable tracking of non-zero state trajectories. The requirement of the project is to design, model, simulate and control a novel quadrotor platform which can articulate all six degrees of rotational and translational freedom (6-DOF) by redirecting and vectoring each propeller’s individually produced thrust. Considering the extended articulation, the proposal is to add an additional two axes (degrees) of actuation to each propeller on a traditional quadrotor frame. Each lift propeller can be independently pitched or rolled relative to the body frame. Such an adaptation, to what is an otherwise well understood aircraft, produces an over-actuated control problem. Being first and foremost a control engineering project, the focus of this work is plant model identification and control solution of the proposed aircraft design. A higher-level setpoint tracking control loop designs a generalized plant input (net forces and torques) to act on the vehicle. An allocation rule then distributes that virtual input in solving for explicit actuator servo positions and rotational propeller speeds. The dissertation is structured as follows: First a schedule of relevant existing works is reviewed in Ch:1 following an introduction to the project. Thereafter the prototype’s design is detailed in Ch:2, however only the final outcome of the design stage is presented. Following that, kinematics associated with generalized rigid body motion are derived in Ch:3 and subsequently expanded to incorporate any aerodynamic and multibody nonlinearities which may arise as a result of the aircraft’s configuration (changes). Higher-level state tracking control design is applied in Ch:4 whilst lower-level control allocation rules are then proposed in Ch:5. Next, a comprehensive simulation is constructed in Ch:6, based on the plant dynamics derived in order to test and compare the proposed controller techniques. Finally a conclusion on the design(s) proposed and results achieved is presented in Ch:7. Throughout the research, physical tests and simulations are used to corroborate proposed models or theorems. It was decided to omit flight tests of the platform due to time constraints, those aspects of the project remain open to further investigation. The subsequent embedded systems design stemming from the proposed control plant is outlined in the latter of Ch:2, Sec:2.4. Such implementations are not investigated here but design proposals are suggested. The primary outcome of the investigation is ascertaining the practicality and feasibility of such a design, most importantly whether or not the complexity of the mechanical design is an acceptable compromise for the additional degrees of control actuation introduced. Control derivations and the prototype design presented here are by no means optimal nor the most exhaustive solutions, focus is placed on the whole system and not just a single aspect of it.
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Linehan, Rory Daniel. "Modelling simulation and control of a remotely piloted vehicle." Thesis, Coventry University, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.363857.

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Books on the topic "Aircraft modelling"

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Aircraft modelling. Oxford: Osprey, 2010.

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Aircraft modelling. Oxford: Osprey, 2010.

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Villalba, J. M. Aircraft: Modelling step by step. Alcobendas (Madrid): T+1, 2002.

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Computational modelling of aircraft and the environment. Chichester, West Sussex, U.K: Wiley, 2009.

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Turk, Thomas Andrew. Aircraft wing anti-icing system: Modelling, integration, and validation. [Downsview, Ont.]: University of Toronto, Institute for Aerospace Studies, 2003.

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Aluminium alloy corrosion of aircraft structures: Modelling and simulation. Southampton: WIT Press, 2013.

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Diston, Dominic J. Computational Modelling and Simulation of Aircraft and the Environment. Chichester, UK: John Wiley & Sons, Ltd, 2009. http://dx.doi.org/10.1002/9780470744130.

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Diston, Dominic J. Computational modelling and simulation of aircraft and the environment. Reston, VA: American Institute of Aeronautics and Astronautics, 2009.

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Plastic model kits: Perfect techniques for modelling cars,ships and aircraft. Hemel Hempstead: Argus Bks., 1993.

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1954-, Lozano R., and Dzul Alejandro E, eds. Modelling and control of mini-flying machines. London: Springer, 2005.

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Book chapters on the topic "Aircraft modelling"

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Raivio, T., H. Ehtamo, and R. P. Hämäläinen. "Aircraft trajectory optimization using nonlinear programming." In System Modelling and Optimization, 435–41. Boston, MA: Springer US, 1996. http://dx.doi.org/10.1007/978-0-387-34897-1_52.

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Bloor, M. I. G., and M. J. Wilson. "The Shape Parametrisation of an Aircraft Engine Nacelle and Pylon." In Geometric Modelling, 39–50. Vienna: Springer Vienna, 1998. http://dx.doi.org/10.1007/978-3-7091-6444-0_4.

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Czyba, Roman, Zbigniew Gorol, Marcin Lemanowicz, Mariusz Pawlak, and Adam Sikora. "Development of Unmanned Cargo VTOL Aircraft." In Modelling in Engineering 2020: Applied Mechanics, 31–42. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-68455-6_3.

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Merlen, A. "From the analytical theory to hypersonic aircraft design." In Asymptotic Modelling in Fluid Mechanics, 221–28. Berlin, Heidelberg: Springer Berlin Heidelberg, 1994. http://dx.doi.org/10.1007/3-540-59414-0_69.

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Sillén, M., E. Amundsson, S. Arvidson, I. Persson, and M. Säterskog. "Flow Modelling in Aircraft Design – An Engineering Perspective." In Progress in Hybrid RANS-LES Modelling, 25–39. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14168-3_3.

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Psarras, Spyridon, Raul Muñoz, Mazdak Ghajari, Paul Robinson, and Domenico Furfari. "Compression After Multiple Impacts: Modelling and Experimental Validation on Composite Coupon Specimens." In Smart Intelligent Aircraft Structures (SARISTU), 667–79. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_31.

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Soykasap, Omer, Sukru Karakaya, Yelda Akcin, and Mehmet Colakoglu. "Finite Element Modelling of CNT-Doped CFRP Plates for Lightning Strike Damage." In Smart Intelligent Aircraft Structures (SARISTU), 825–37. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_44.

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Feng, Weizhi, Cheng-Chao Huang, Andrea Turrini, and Yong Li. "Modelling and Implementation of Unmanned Aircraft Collision Avoidance." In Dependable Software Engineering. Theories, Tools, and Applications, 52–69. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-62822-2_4.

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Smetankina, Natalia, Igor Kravchenko, Vyacheslav Merculov, Dmitry Ivchenko, and Alyona Malykhina. "Modelling of Bird Strike on an Aircraft Glazing." In Integrated Computer Technologies in Mechanical Engineering, 289–97. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-37618-5_25.

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Martinez-Pascual, A., Marco Evangelos Biancolini, and J. Ortega-Casanova. "Fluid Structure Modelling of Ground Excited Vibrations by Mesh Morphing and Modal Superposition." In Flexible Engineering Toward Green Aircraft, 111–27. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-36514-1_7.

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Conference papers on the topic "Aircraft modelling"

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Jones, C. C. R. "Modelling of aircraft skins." In IEE Colloquium on Computer Methods for Material Modelling in Electromagnetics. IEE, 1997. http://dx.doi.org/10.1049/ic:19970361.

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SIMKINS, DAVID, and DANIEL BREYER. "Mission modelling of helicopter combat effectiveness." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2146.

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Tomazic, T., and D. Matko. "A Guide in Design-Oriented Aircraft Modelling: Theory and Practice." In Modelling and Simulation. Calgary,AB,Canada: ACTAPRESS, 2010. http://dx.doi.org/10.2316/p.2010.696-021.

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Grigorie, Teodor Lucian, Ruxandra Mihaela Botez, and Dragos George Sandu. "A Numerical Implemented Method for the Aircraft Attitude Determination." In Applied Simulation and Modelling. Calgary,AB,Canada: ACTAPRESS, 2012. http://dx.doi.org/10.2316/p.2012.776-033.

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Thain, A., G. Peres, J. P. Estienne, G. Sylvand, P. Cailleu, P. Benjamin, I. Terrasse, G. P. Piau, and G. Sabanowski. "Numerical modelling of aircraft antenna installations." In 2nd European Conference on Antennas and Propagation (EuCAP 2007). Institution of Engineering and Technology, 2007. http://dx.doi.org/10.1049/ic.2007.0853.

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Fielding, J., and M. Vaziry-Z. "Avionics reliability modelling for aircraft conceptual design." In Aircraft Engineering, Technology, and Operations Congress. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-3906.

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Melkou, Lamia, Amar Rezoug, and Mustapha Hamerlain. "PID-Terminal Sliding Mode Control of Aircraft UAV." In 2014 European Modelling Symposium (EMS). IEEE, 2014. http://dx.doi.org/10.1109/ems.2014.97.

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Anton, Nicoleta, and Ruxandra M. Botez. "Aircraft X-31 Stability Analysis and Validation with Experimental Data." In Applied Simulation and Modelling. Calgary,AB,Canada: ACTAPRESS, 2012. http://dx.doi.org/10.2316/p.2012.776-020.

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Boughari, Yamina, Ruxandra M. Botez, Florian Theel, and Georges Ghazi. "Optimal Flight Control on Cessna X Aircraft using Differential Evolution." In Modelling, Identification and Control. Calgary,AB,Canada: ACTAPRESS, 2014. http://dx.doi.org/10.2316/p.2014.809-052.

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10

Iyigunlu, Serter, Clinton Fookes, and Prasad Yarlagadda. "Agent-based Modelling of Aircraft Boarding Methods." In 4th International Conference on Simulation and Modeling Methodologies, Technologies and Applications. SCITEPRESS - Science and Technology Publications, 2014. http://dx.doi.org/10.5220/0005033601480154.

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