Relevant bibliographies by topics / Simulating Aircraft / Dissertations / Theses

Dissertations / Theses on the topic 'Simulating Aircraft'

To see the other types of publications on this topic, follow the link: Simulating Aircraft.
Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the top 50 dissertations / theses for your research on the topic 'Simulating Aircraft.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Browse dissertations / theses on a wide variety of disciplines and organise your bibliography correctly.

1

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

Full text
Abstract:
In this master thesis project the possibility to model the response of a wing when subjected to bird strike using finite elements is analyzed. Since this transient event lasts only a few milliseconds the used solution method is explicit time integration. The wing is manufactured using carbon fiber laminate. Carbon fiber laminates have orthotropic material properties with different stiffness in different directions. Accordingly, there are damage mechanisms not considered when using metal that have to be modeled when using composites. One of these damage mechanisms is delamination which occurs when cured layers inside a component become separated. To simulate this phenomenon, multiple layers of shell elements with contact in between are used as a representation of the interface where a component is likely to delaminate. By comparing experimental and simulated results the model of delamination is verified and the influence of different parameters on the results is investigated. Furthermore, studies show that modeling delamination layers in each possible layer of a composite stack is not optimal due to the fact that the global stiffness of the laminate is decreased as more layers are modeled. However, multiple layers are needed in order to mitigate the spreading of delamination and obtain realistic delaminated zones. As the laminates are comprised of carbon fiber and epoxy sheets it is of importance to include damage mechanisms inside each individual sheet. Accordingly, a composite material model built into the software is used which considers tensile and compressive stress in fiber and epoxy. The strength limits are then set according to experimental test data. The bird is modeled using a mesh free technique called Smooth Particle Hydrodynamics using a material model with properties similar to a fluid. The internal pressure of the bird model is linked to the change in volume with an Equation of State. By examining the bird models behavior compared to experimental results it is determined to have a realistic impact on structures. A model of the leading edge is then subjected to bird strike according to European standards. The wing skin is penetrated indicating that reinforcements might be needed in order to protect valuable components inside the wing structure such as the fuel tank. However, the results are not completely accurate due to the fact that there is little experimental data available regarding soft body penetration of composite laminates. As a consequence, the simulation cannot be confirmed against real experimental results and further investigations are required in order to have confidence in modeling such events. Furthermore, the delamination due to the bird strike essentially spreads across the whole model. Since only one layer of delamination is included the spread is most likely overestimated.
APA, Harvard, Vancouver, ISO, and other styles
2

Cooper, Michael Anthony. "Simulating actuator energy demands of an aircraft in flight." Thesis, Cranfield University, 2014. http://dspace.lib.cranfield.ac.uk/handle/1826/8502.

Full text
Abstract:
This thesis contributes towards the discipline of whole aircraft simula- tion; modelling ight dynamics and airframe systems simultaneously. The objective is to produce estimates of the dynamic power consumption char- acteristics of the primary ight control actuation system when executing manoeuvres. Three technologies are studied; the classic hydraulic actuators and the electromechanical and electro-hydrostatic types that are commonly associated with the more electric aircraft. Models are produced which represent the ight dynamics of an aircraft; these are then combined with low frequency dynamic functional models of the three actuator technologies and ight controllers. The result is a model, capable of faster than real time simulation, which produces estimates of ac- tuator power consumption as the aircraft follows prede ned trajectories. The model is used to quantify the energy consumption as a result of di erent manoeuvre rates when executing banked turns. The result from an actuation system point of view alone is that the lower the turn rate, the lower the overall energy used. The tradeo is that the turn radius becomes larger. The use of the model can be extended to assist with additional design challenges such as actuator design and speci cation. Using methods to size actuators based on stall force and no load speed properties leads to oversizing of the control system. Performing dynamic analyses is usually a combined task of laboratory based actuator test rigs stimulated by input data gathered during ight tests. The model in this work provides a method of generating data for preliminary design; therefore reducing the amount of ight testing required in a design and certi cation programme. The major results discovered using the tools developed in this thesis are that a hydraulically powered aileron uses 4.23% more energy to achieve a turn at a heading rate of 0.03 rad/s compared to a 0.005 rad/s manoeuvre in the same conditions. The electromechanical actuator (EMA) uses 1.67% more and the electrohydrostatic actuator (EHA) uses 1.54% more to achieve the same turns. It implies reduced turn rate turns would have the largest bene t for reducing energy consumption in current hydraulically powered actuation systems, compared to electrical actuators.
APA, Harvard, Vancouver, ISO, and other styles
3

Covarrubias, Gillin Daniel, Gustav Arneving, Joel Alexandersson, Persson Leon Li, Lukas Olsson, Martin Banck, and Max Björkander. "Simulera beteende av stridsflygplan med hjälp av AI : Simulating behavior of combat aircraft with AI." Thesis, Linköpings universitet, Institutionen för datavetenskap, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-177689.

Full text
Abstract:
I denna rapport beskrivs ett kandidatarbete som utfördes på beställning av Saab. Det kunden var intresserad av var att simulera beteende av stridsflygplan med hjälp av AI-tekniker. Projektgruppen använde maskininlärningsalgoritmen Q-inlärning för att försöka uppnå detta. Utöver detta utvecklade gruppen en egen simulator som en miljö för kurvstrider mellan simulerade stridsflygplan. Projektet utfördes av sju studenter på programmen civilingenjör inom datateknik och civilingenjör inom mjukvaruteknik vid Linköpings universitet. Resultatet av projektet blev att ett tillfredsställande beteende för det AI-styrda stridsflygplanet ej kunde uppnås, dock kunde ett förbättrat beteende observeras. Mer forskning på området behövs dock för att åstadkomma mer tillfredsställande resultat. Förstärkningsinlärning visar sig vara lovande som metod för att lösa problemet inför framtiden. Diskussioner och insikter om vad som kan göras för att vidareutveckla AI:n för en bättre prestation hos det simulerade planet dokumenterades. I slutet av rapporten finns även individuella bidrag skrivna av var och en av medlemmarna i projektgruppen. De ämnena som valdes berörde projektet, antingen som en del av utvecklingsprocessen eller som en del av temat till projektet.
APA, Harvard, Vancouver, ISO, and other styles
4

Shah, Harshil Dipen. "An Assessment of the CFD Effectiveness for Simulating Wing Propeller Aerodynamics." Thesis, Virginia Tech, 2020. http://hdl.handle.net/10919/98668.

Full text
Abstract:
Today, we see a renewed interest in aircraft with multiple propellers. To support conceptual design of these vehicles, one of the major needs is a fast and accurate method for estimating wing aerodynamic characteristics in the presence of multiple propellers. For the method to be effective, it must be easy to use, have rapid turnaround time and should be able to capture major wing–propeller interaction effects with sufficient accuracy. This research is primarily motivated by the need to assess the effectiveness of computational fluid dynamics (CFD) for simulating aerodynamic characteristics of wings with multiple propellers. The scope of the present research is limited to investigating the interaction between a single tractor propeller and a wing. This research aims to compare computational results from a Reynolds-Averaged Navier-Stokes (RANS) method, StarCCM+, and a vortex lattice method (VLM), VSP Aero. Two configurations that are analysed are 1) WIPP Configuration (Workshop for Integrated Propeller Prediction) 2) APROPOS Configuration. For WIPP, computational results are compared with measured lift and drag data for several angles of attack and Mach numbers. StarCCM+ results of wake flow field are compared with WIPP's wake survey data. For APROPOS, computed data for lift-to-drag ratio of the wing are compared with test data for multiple vertical and spanwise locations of the propeller. The results of the simulations are used to assess the effectiveness of the two CFD methods used in this research.
Master of Science
Today, we see a renewed interest in aircraft with multiple propellers due to an increasing demand for vehicles which fly short distances at low altitudes, be it flying taxis, delivery drones or small passenger aircrafts. To support conceptual design of vehicles, one of the major needs is a fast and accurate method for estimating wing aerodynamic characteristics in the presence of multiple propellers. For the method to be effective, it must be easy to use, have rapid turnaround time and should be able to capture major wing–propeller inter- action effects with sufficient accuracy. This research is primarily motivated by the need to assess the effectiveness of computational fluid dynamics (CFD) for simulating aerodynamic characteristics of wings with multiple propellers. Then only can we can take full advantage of the capabilities of the CFD methods and support design of emerging propeller driven air vehicles with an appropriate level of confidence. This research aims to compare high level methods with increasingly complex geometries and realistic models of physics like Reynolds Averaged Navier Stokes (RANS) and low level methods that rely on simplified geometry and simplified physics models like Vortex Lattice Methods (VLM). We will analyse multiple configurations and validate them against experi- mental data and thus assessing the effectiveness of the CFD models. This research investigates two configurations, 1) WIPP configuration 2) APROPOS config- uration, for which experimental data is available. The results of the simulations are used to assess the effectiveness of the two CFD methods used in this research.
APA, Harvard, Vancouver, ISO, and other styles
5

Chevrolat, Sofia. "Automatic Fusion of Fidelity sources ofAerodynamic Data : Simulating Aircraft Stability And Control Characteristics for Use in Conceptual Design." Thesis, KTH, Aeroakustik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-30614.

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

Swift, Adam. "Simulation of aircraft aeroelasticity." Thesis, University of Liverpool, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.569519.

Full text
Abstract:
Aeroelastic phenomena such as flutter can have a detrimental effect on aircraft performance and can lead to severe damage or destruction. Buffet leads to a re- duced fatigue life and therefore higher operating costs and a limited performance envelope. As such the simulation of these aeroelastic phenomena is of utmost importance. Computational aeroelasticity couples computational fluid dynamics and computational structural dynamics solvers through the use of a transforma- tion method. There have been interesting developments over the years towards more efficient methods for predicting the flutter boundaries based upon the sta- bility of the system of equations. This thesis investigates the influence of transformation methods on the flutter boundary predition and considers the simulation of shock-induced buffet of a transport wing. This involves testing a number of transformation methods for their effect on flutter boundaries for two test cases and verifying the flow solver for shock-induced buffet over an aerofoil. This will be followed by static aeroelastic calculations of an aeroelastic wing. It is shown that the transformation methods have a significant effect on the predicted flutter boundary. Multiple transformation methods should be used to build confidence in the results obtained, and extrapolation should be avoided. CFD predictions are verified for buffet calculations and the mechanism behind shock-oscillation of the BGK No. 1 aerofoil is investigated. The use of steady calculations to assess if a case may be unsteady is considered. Finally the static aeroelastic response of the ARW-2 wing is calculated and compared against ex- perimental results.
APA, Harvard, Vancouver, ISO, and other styles
7

Zurheide, Frank Thomas. "Numerical simulation of aircraft vortices." Aachen Shaker, 2009. http://d-nb.info/998626899/04.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

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

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

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

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

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

Full text
APA, Harvard, Vancouver, ISO, and other styles
11

Bartlett, Brandon. "Simulation of a Configurable Hybrid Aircraft." DigitalCommons@CalPoly, 2021. https://digitalcommons.calpoly.edu/theses/2318.

Full text
Abstract:
As the demand for air transportation is projected to increase, the environmental impacts produced by air travel will also increase. In order to counter the environmental impacts while also meeting the demand for air travel, there are goals and research initiatives that aim to develop more efficient aircraft. An emerging technology that supports these goals is the application of hybrid propulsion to aircraft, but there is a challenge in effectively exploring the performance of hybrid aircraft due to the time and money required for safe flight testing and due to the diverse design space of hybrid architectures and components. Therefore, computational tools that are capable of simulating the performance of a hybrid aircraft are incredibly useful in the design process and research space. Existing work on the simulation of hybrid aircraft focuses on modelling a specific hybrid propulsion system in a particular airframe, but it would be desirable to have a simulation tool that is not specific to one design. In this thesis, a simulation framework that can be easily configured for different types of hybrid structures and components is presented, and the simulator is validated using flight test data which demonstrates that the performance of the simulated aircraft is representative of a real aircraft. A design for a hybrid aircraft is also modelled and simulated over different flight profiles in order to study the performance of the hybrid propulsion system. Results indicate that the hybrid aircraft can be successfully simulated and demonstrate how the simulator can be used as a tool to study the best way to fly and operate a hybrid aircraft.
APA, Harvard, Vancouver, ISO, and other styles
12

Miao, Zhisong. "Aircraft engine performance and integration in a flying wing aircraft conceptual design." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7249.

Full text
Abstract:
The increasing demand of more economical and environmentally friendly aero engines leads to the proposal of a new concept – geared turbofan. In this thesis, the characteristics of this kind of engine and relevant considerations of integration on a flying wing aircraft were studied. The studies can be divided into four levels: GTF-11 engine modelling and performance simulation; aircraft performance calculation; nacelle design and aerodynamic performance evaluation; preliminary engine installation. Firstly, a geared concept engine model was constructed using TURBOMATCH software. Based on parametric analysis and SFC target, the main cycle parameters were selected. Then, the maximum take-off thrust was verified and corrected from 195.56kN to 212kN to meet the requirements of take-off field length and second segment climb. Besides, the engine performance at offdesign points was simulated for aircraft performance calculation. Secondly, an aircraft performance model was developed and the performance of FW-11 was calculated on the basis of GTF-11 simulation results. Then, the effect of GTF-11 characteristics performance on aircraft performance was evaluated. A comparison between GTF-11 and conventional turbofan, RB211- 524B4, indicated that the aircraft can achieve a 13.1% improvement in fuel efficiency by using the new concept engine. Thirdly, a nacelle was designed for GTF-11 based on NACA 1-series and empirical methods while the nacelle dimensions of conventional turbofan RB211-525B4 were obtained by measure approach. Then, the installation thrust losses caused by nacelle drags of the two engines were evaluated using ESDU 81024a. The results showed that the nacelle drags account for about 4.08% and 3.09% of net thrust for GTF-11 and RB211-525B4, respectively. Finally, the considerations of engine installation on a flying wing aircraft were discussed and a preliminary disposition of GTF-11 on FW-11 was presented.
APA, Harvard, Vancouver, ISO, and other styles
13

Aslin, P. P. "Aircraft simulation and robust flight control system design." Thesis, University of York, 1985. http://etheses.whiterose.ac.uk/9821/.

Full text
APA, Harvard, Vancouver, ISO, and other styles
14

Andersson, Henric. "Aircraft Systems Modeling : Model Based Systems Engineering in Avionics Design and Aircraft Simulation." Licentiate thesis, Linköping University, Linköping University, Machine Design, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-17573.

Full text
Abstract:

Aircraft developers like other development and manufacturing companies, are experiencing increasing complexity in their products and growing competition in the global market. One way to confront the challenges is to make the development process more efficient and to shorten time to market for new products/variants by using design and development methods based on models. Model Based Systems Engineering (MBSE) is introduced to, in a structured way, support engineers with aids and rules in order to engineer systems in a new way.

In this thesis, model based strategies for aircraft and avionics development are studied. A background to avionics architectures and in particular Integrated Modular Avionics is described. The integrating discipline Systems Engineering, MBSE and applicable standards are also described. A survey on available and emerging modeling techniques and tools, such as Hosted Simulation, is presented and Modeling Domains are defined in order to analyze the engineering environment with all its vital parts to support an MBSE approach.

Time and money may be saved by using modeling techniques that enable understanding of the engineering problem, state-of-the-art analysis and team communication, with preserved or increased quality and sense of control. Dynamic simulation is an activity increasingly used in aerospace, for several reasons; to prove the product concept, to validate stated requirements, and to verify the final implementation. Simulation is also used for end-user training, with specialized training simulators, but with the same underlying models. As models grow in complexity, and the set of simulation platforms is expanded, new needs for specification, model building and configuration support arise, which requires a modeling framework to be efficient.

APA, Harvard, Vancouver, ISO, and other styles
15

Keyvani, Parvin. "Emergency Evacuation Simulation of Large Civil Aircraft." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020.

Find full text
Abstract:
The safety of passengers using transport aircraft is crucially dependent on the rapid evacuation of the cabin in the event of an emergency, and therefore, when new aircraft types are registered, the manufacturer must prove that the cabin can be evacuated within 90 seconds with the maximum number of passengers and in darkness. Only the doors and emergency exits on one fuselage side are available. Its mandatory verification by a certification test is costly and expensive for the manufacturers. Significant changes to an aircraft model could result in the need to re-test the emergency evacuation before implementation. As this a huge effort a method is necessary to predict the behavior of passengers as accurately as possible. In order to determine reliable evacuation times already during the aircraft preliminary design phase, numerical simulations of emergency evacuations are required. For this purpose, studies on the basis of various simulation algorithms have been carried out at the Chair of Aircraft Design and aerostructures within the framework of various Theses. In particular, it has to be ensured that human behavior can be assessed realistically within the simulation in order to achieve evacuation times as accurate as possible. The aim of this thesis is to examine to what extent the PATHFINDER software is suitable for the evacuation simulation of single-aisle and twin-aisle airliners, which could have an over wing exits. These are typically aircraft of the Airbus A320 or A340 family. Therefore, this thesis shall investigate to what extent numerical simulation methods are suitable for the evacuation simulation of commercial aircraft. This suitability shall be analyzed and evaluated with the help of the PATHFINDER tool with regard to the design of the cabin.
APA, Harvard, Vancouver, ISO, and other styles
16

Kaila, Vivek. "Aeroelastic simulation of aircraft using meshless methods." Diss., Connect to online resource, 2005. http://wwwlib.umi.com/cr/colorado/fullcit?p1430189.

Full text
APA, Harvard, Vancouver, ISO, and other styles
17

Eek, Magnus. "On Credibility Assessment in Aircraft System Simulation." Doctoral thesis, Linköpings universitet, Maskinkonstruktion, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-127380.

Full text
Abstract:
The aeronautical industry is becoming increasingly reliant on Modeling and Simulation (M&S) for use throughout all system development phases, for system verification, and end-user training. To justify and to utilize the full potential of today’s model-based approach, the development of efficient and industrially applicable methods for credibility assessment of M&S efforts is a key challenge. This work addresses methods facilitating credibility assessment of simulation models and simulator applications used in aircraft system development. For models of individual aircraft subsystems, an uncertainty aggregation method is proposed that facilitates early model validation through approximate uncertainty quantification. The central idea is to integrate information obtained during component level validation directly into the component equations, and to utilize this information in model level uncertainty quantification. In addition to methods intended for models of individual subsystems, this work also proposes a method and an associated tool for credibility assessment of large-scale simulator applications. As a complement to traditional document-centric approaches, static and dynamic credibility information is here presented to end-users directly during simulation. This implies a support for detecting test plan deficiencies, or that a simulator configuration is not a suitable platform for the execution of a particular test. The credibility assessment tool has been implemented and evaluated in two large-scale system simulators for the Saab Gripen fighter aircraft. The work presented herein also includes an industrially applicable workflow for development, validation, and export of simulation models.
APA, Harvard, Vancouver, ISO, and other styles
18

Poudel, Minesh. "Aircraft emergency evacuation : analysis, modelling and simulation." Toulouse 2, 2008. http://www.theses.fr/2008TOU20026.

Full text
Abstract:
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
APA, Harvard, Vancouver, ISO, and other styles
19

Mirmohammadsadeghi, Navid. "Development of an Aircraft Landing Database and Models to Estimate Aircraft Runway Occupancy Times." Diss., Virginia Tech, 2020. http://hdl.handle.net/10919/99914.

Full text
Abstract:
This dissertation represents the methodologies used to develop an aircraft landing database and predictive models for estimating arrival flight runway occupancy times. In the second chapter, all the algorithms developed for analyzing the airport surface radar data are explained, and detailed statistical information about various airports in the United States in terms of landing behavior is studied. In the third chapter a novel data-driven approach for modeling aircraft landing behavior is represented. The outputs of the developed approach are runway occupancy time distributions and runway exit utilizations. The represented hybrid approach in the third chapter is a combination of machine learning and Monte Carlo simulation methods. This novel approach was calibrated based on two years of airport radar data. The study's output is a computer application, which is currently being used by the Federal Aviation Administration and various airport consulting firms for analyzing and designing optimum runway exits to optimize runway occupancy times at airports. In the fourth chapter, four real-world case scenarios were analyzed to show the power of the developed model in solving real-world challenges in airport capacity. In the fifth chapter, pilot motivational behaviors were introduced, and three methodologies were used to replicate motivated pilot behaviors on the runway. Finally, in the sixth chapter, a neural network approach was used as an alternative model for estimating runway occupancy time distributions.
Doctor of Philosophy
The federal aviation administration predicts ongoing growth in the aviation industry over the following 20 years. Therefore, the airports will be more crowded, and a higher number of operations will occur at those facilities. An accurate prediction of airports' capacities can help the authorities to improve the airports appropriately. Due to significant reductions in in-trail aircraft separations, runway occupancy times will become more significant in airport arrival procedures. In this study, a landing event database was developed to represent the accurate distributions of runway occupancy times. Also, it is essential to have computer applications capable of replicating runway occupancy time distributions. In this dissertation, a novel approach was developed to replicate aircraft runway occupancy times. A massive amount of airport surface radar data was utilized to create all the mentioned computer applications. The results of the final products were validated against real data. Real-world case scenarios were discussed as part of this study to showcase the strengths of the final developed product in solving challenging problems related to airport capacity. Finally, extreme cases of motivated landing behavior from airline pilots were studied, and multiple methodologies were introduced to replicate pilot motivational behavior while landing on runway.
APA, Harvard, Vancouver, ISO, and other styles
20

M, Venkata Raghu Chaitanya. "Model Based Aircraft Control System Design and Simulation." Thesis, Linköping University, Linköping University, Department of Management and Engineering, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-19264.

Full text
Abstract:

Development of modern aircraft has become more and more expensive and time consuming. In order to minimize the development cost, an improvement of the conceptual design phase is needed. The desired goal of the project is to enhance the functionality of an in house produced framework conducted at the department of machine design, consisting of parametric models representing a large variety of aircraft concepts.

The first part of the work consists of the construction of geometric aircraft control surfaces such as flaps, aileron, rudder and elevator parametrically in CATIA V5.

The second part of the work involves designing and simulating an Inverse dynamic model in Dymola software.

An Excel interface has been developed between CATIA and Dymola. Parameters can be varied in the interface as per user specification; these values are sent to CATIA or Dymola and vice versa. The constructed concept model of control surfaces has been tested for different aircraft shapes and layout. The simulation has been done in Dymola for the control surfaces.

APA, Harvard, Vancouver, ISO, and other styles
21

Braun, Robert. "Hardware-in-the-Loop Simulation of Aircraft Actuator." Thesis, Linköping University, Linköping University, Department of Management and Engineering, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-20466.

Full text
Abstract:

Advanced computer simulations will play a more and more important role in future aircraft development and aeronautic research. Hardware-in-the-loop simulations enable examination of single components without the need of a full-scale model of the system. This project investigates the possibility of conducting hardware-in-the-loop simulations using a hydraulic test rig utilizing modern computer equipment. Controllers and models have been built in Simulink and Hopsan. Most hydraulic and mechanical components used in Hopsan have also been translated from Fortran to C and compiled into shared libraries (.dll). This provides an easy way of importing Hopsan models in LabVIEW, which is used to control the test rig. The results have been compared between Hopsan and LabVIEW, and no major differences in the results could be found. Importing Hopsan components to LabVIEW can potentially enable powerful features not available in Hopsan, such as hardware-in-the-loop simulations, multi-core processing and advanced plotting tools. It does however require fast computer systems to achieve real-time speed. The results of this project can provide interesting starting points in the development of the next generation of Hopsan.

APA, Harvard, Vancouver, ISO, and other styles
22

Zurheide, Frank Th [Verfasser]. "Numerical Simulation of Aircraft Vortices / Frank Th Zurheide." Aachen : Shaker, 2009. http://d-nb.info/1161301038/34.

Full text
APA, Harvard, Vancouver, ISO, and other styles
23

Weekley, Christopher D. "Aircraft simulation validation using an instrumental variable approach." Thesis, Virginia Tech, 1992. http://hdl.handle.net/10919/41517.

Full text
Abstract:
A procedure is developed which offers the potential to validate aircraft simulation models using noisy flight test measurements. The proposed validation procedure is based on the instrumental variable parameter identification method. The instrumental variable method requires a choice of "instruments." For this research, the "instruments" are chosen using the response predicted by an available simulation model. With the “instruments” chosen from the predicted response, it is shown that the parameter estimates are correlated with only the measured input noise vector. In contrast, the generally used least-squares approach is shown to be correlated with both the state and input noise vectors. Several studies are presented to demonstrate the utility of the validation procedure. These studies include input variations and noise variations. The method is demonstrated using longitudinal and lateral/directional axis cases derived from a nonlinear simulation of a high performance fighter aircraft. The results are presented using time response comparisons, eigenvalue comparisons, and identified stability derivative comparisons. The case study results confirm that the instrumental variable method performs better than the least-squares technique when the state noise level is high and the input noise level is relatively low.
Master of Science
APA, Harvard, Vancouver, ISO, and other styles
24

Pala, Fatih. "Frequency and polarization diversity simulations for Urban UAV communication and data links." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2004. http://library.nps.navy.mil/uhtbin/hyperion/04Sep%5FPala.pdf.

Full text
APA, Harvard, Vancouver, ISO, and other styles
25

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.

Full text
APA, Harvard, Vancouver, ISO, and other styles
26

Blackshear, Henry L. "Developing a conceptual unmanned aerial vehicle communications mobile AD Hoc network simulation model." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02Jun%5FBlackshear.pdf.

Full text
APA, Harvard, Vancouver, ISO, and other styles
27

Seaton, M. Scot. "Performance measurements, flow visualization, and numerical simulation of a crossflow fan." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Mar%5FSeaton.pdf.

Full text
Abstract:
Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, March 2003.
Thesis advisor(s): Garth V. Hobson, Raymond P. Shreeve. Includes bibliographical references (p. 69-70). Also available online.
APA, Harvard, Vancouver, ISO, and other styles
28

Eklund, John M. "Aircraft flight control simulation using parallel cascade system identification." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1998. http://www.collectionscanada.ca/obj/s4/f2/dsk2/tape17/PQDD_0004/MQ28194.pdf.

Full text
APA, Harvard, Vancouver, ISO, and other styles
29

Hoefener, Carl E. "DISTRIBUTED INTERACTIVE SIMULATION PROVEN IN FLIGHT TEST AIRCRAFT TRACKING." International Foundation for Telemetering, 1994. http://hdl.handle.net/10150/608558.

Full text
Abstract:
International Telemetering Conference Proceedings / October 17-20, 1994 / Town & Country Hotel and Conference Center, San Diego, California
With the decline in military budgets worldwide, the need for ever more effective training is becoming apparent. The size of the armed forces is being reduced, so the remaining members have to be trained to be more effective and efficient in doing their jobs. To improve effectiveness and efficiency of performance, military training needs will be increased. Our largest training costs will be in pilot training because of the high cost of keeping aircraft in the air. When we look at the cost of training a pilot to operate in a multiplayer scenario against a large number of unfriendly aircraft and a large number of ground threats, the cost of training is tremendous. It requires a large number of personnel, aircraft and ground equipment to train a limited number of pilots. Our current Red Flag exercises can require as many as 75 aircraft in the air simultaneously plus a large number of ground threats and a large number of support personnel. This can amount to a prohibitive cost to train a limited number of pilots.
APA, Harvard, Vancouver, ISO, and other styles
30

Donovan, Adam. "Vehicle Level Transient Aircraft Thermal Management Modeling and Simulation." Wright State University / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=wright1472236965.

Full text
APA, Harvard, Vancouver, ISO, and other styles
31

Hiltner, Dale W. "A nonlinear aircraft simulation of ice contaminated tailplane stall /." The Ohio State University, 1998. http://rave.ohiolink.edu/etdc/view?acc_num=osu1487951595502405.

Full text
APA, Harvard, Vancouver, ISO, and other styles
32

Vembar, Deepak S. "Visuohaptic simulation of a borescope for aircraft engine inspection." Connect to this title online, 2009. http://etd.lib.clemson.edu/documents/1263397699/.

Full text
APA, Harvard, Vancouver, ISO, and other styles
33

Tipton, Austin L. "Simulation, Experimentation, Control and Management of a Novel Fuel Thermal System." Wright State University / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=wright1578320719632833.

Full text
APA, Harvard, Vancouver, ISO, and other styles
34

Rambalakos, Andreas. "Monte Carlo simulation methodology for the reliability of aircraft structures reliability of aircraft structures under damage tolerance requirements." Saarbrücken VDM Verlag Dr. Müller, 2006. http://d-nb.info/988567741/04.

Full text
APA, Harvard, Vancouver, ISO, and other styles
35

Harris, Carl John. "A generic simulation model for analysis of aircraft undercarriage behaviour." Thesis, University of Brighton, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.323405.

Full text
APA, Harvard, Vancouver, ISO, and other styles
36

Kapadoukas, Georgios G. "High fidelity on and near the ground aircraft flight simulation." Thesis, University of Brighton, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.361583.

Full text
APA, Harvard, Vancouver, ISO, and other styles
37

Coates, Tim. "Numerical simulation of unconventional aero-engine exhaust systems for aircraft." Thesis, Loughborough University, 2014. https://dspace.lboro.ac.uk/2134/16365.

Full text
Abstract:
This thesis investigates the impact of upstream duct convolution on the plume development for high speed jets. In particular, investigations are carried out into an unconventional aero-engine exhaust systems comprised of a modified convergent-divergent rectangular nozzle where the converging section of the nozzle includes an S-bend in the duct. The motivation for this work comes from both the military and civilian sectors of the aerospace industry. The growing interest into highly efficient engines in the civilian sector and increasing complexities involved in stealth technologies for military applications has led to new design constraints on aero-engine exhaust systems that require further research into flows through more complex duct geometries. Due to a lack of experimental data into this area in the open literature validation studies are undertaken into flows through an S-bend duct and exhaust plume development from a rectangular convergent-divergent nozzle. The validation work is simulated using RANS CFD with common industrial turbulence models as well as LES with artificial inlet conditions. Subsequently, a CFD investigation into three unconventional aero-engine exhaust systems, with over-expanded conditions, with differing angles of curvature across the converging S-bend is undertaken using both RANS and LES methodologies governed by the validation work. As the curvature of the S-bend was increased it was found that the thrust and effective NPR both decrease. Whilst these changes were within acceptable levels (with some optimisation) for a circumferential extent of up to 53.1 the losses became prohibitive large at extents. For the ducts with a greater circumferential extents separation was seen to occur at the throat of the nozzle; this changes the design parameters of the nozzle leading to a higher Mach number and could potentially be harnessed to improve performance of the engine creating a `variable throat' nozzle. The impact of using different numerical solvers to simulate the flow through an unconventional aero-engine exhaust system has also been considered. The use of LES has shown that the octagonal, hexahedral and trapezoidal shapes initially observed in the development of the plumes of the RANS cases are likely to be an artifact caused by the RANS solver, as would the transverse total pressure gradients observed in the RANS cases at the nozzle exit as they are both absent from all of the LES results. Likewise the implementation of realistic inlet conditions has a significant impact on the development of the plume, particularly in the length of the potential core and the number of shock cells.
APA, Harvard, Vancouver, ISO, and other styles
38

Islam, Md Rubayat Ul. "Utilizing Scenario Based Simulation Modeling to Optimize Aircraft Fleet Scheduling." University of Akron / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=akron1560965666900518.

Full text
APA, Harvard, Vancouver, ISO, and other styles
39

Hällqvist, Robert. "On Standardized Model Integration : Automated Validation in Aircraft System Simulation." Licentiate thesis, Linköpings universitet, Fluida och mekatroniska system, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-162810.

Full text
Abstract:
Designing modern aircraft is not an easy task. Today, it is not enough to optimize aircraft sub-systems at a sub-system level. Instead, a holistic approach is taken whereby the constituent sub-systems need to be designed for the best joint performance. The State-of-the-Art (SotA) in simulating and exchanging simulation models is moving forward at a fast pace. As such, the feasible use of simulation models has increased and additional benefits can be exploited, such as analysing coupled sub-systems in simulators. Furthermore, if aircraft sub-system simulation models are to be utilized to their fullest extent, opensource tooling and the use of open standards, interoperability between domain specific modeling tools, alongside robust and automated processes for model Verification and Validation (V&V) are required. The financial and safety related risks associated with aircraft development and operation require well founded design and operational decisions. If those decisions are to be founded upon information provided by models and simulators, then the credibility of that information needs to be assessed and communicated. Today, the large number of sensors available in modern aircraft enable model validation and credibility assessment on a different scale than what has been possible up to this point. This thesis aims to identify and address challenges to allow for automated, independent, and objective methods of integrating sub-system models into simulators while assessing and conveying the constituent models aggregated credibility. The results of the work include a proposed method for presenting the individual models’ aggregated credibility in a simulator. As the communicated credibility of simulators here relies on the credibility of each included model, the assembly procedure itself cannot introduce unknown discrepancies with respect to the System of Interest (SoI). Available methods for the accurate simulation of coupled models are therefore exploited and tailored to the applications of aircraft development under consideration. Finally, a framework for automated model validation is outlined, supporting on-line simulator credibility assessment according to the presented proposed method.

Ytterligare forskningsfinansiär: Saab Aeronautics


Model Validation – from Concept to Product
Open Cyber-Physical System Model-Driven Certified Development (OpenCPS).
APA, Harvard, Vancouver, ISO, and other styles
40

Meo, Michele. "Application of welding to a large civil aircraft wing." Thesis, Cranfield University, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.323959.

Full text
APA, Harvard, Vancouver, ISO, and other styles
41

Manimala, Binoy James. "Mathematical modelling for the evaluation of a tiltwing aircraft." Thesis, Glasgow Caledonian University, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.287856.

Full text
APA, Harvard, Vancouver, ISO, and other styles
42

Gavel, Hampus. "On aircraft fuel systems : conceptual design and modeling." Doctoral thesis, Linköping : Division of Machine Design, Department of Mechanical Engineering, Linköpings universitet, 2007. http://www.bibl.liu.se/liupubl/disp/disp2007/tek1067s.pdf.

Full text
APA, Harvard, Vancouver, ISO, and other styles
43

Marinus, Benoît. "Multidisciplinary optimization of aircraft propeller blades." Phd thesis, Ecole Centrale de Lyon, 2011. http://tel.archives-ouvertes.fr/tel-00692363.

Full text
Abstract:
Open rotors are known to have significant advantages in terms of propulsive efficiency. These advantages translate directly in reduced fuel burn so that they nowadays benefit from a surge of interest. At the same time, recent advances in numerical simulations make the application of multidisciplinary optimization for the demanding design of transonic propeller blades, an affordable option. Therefore, an optimization method in which the performance objectives of aerodynamics, aeroacoustics and aeroelasticity compete against each other, is developed and applied for the design of high-speed single-rotation propellers. The optimization is based on Multi-Objective Differential Evolution (MODE).This technique is a particular kind of evolutionary algorithm that mimics the natural evolution of populations by relying on the selection, recombination and eventually mutation of blade designs, each of them being represented by a vector of design variables (e.g. chord width, tip sweep, etc). MODE has the advantage of dealing concurrently with all the objectives in the selection of potentially promising designs among a population. In order to keep the computational cost within reasonable margins, the assessment of the performance of proposed designs is done in a two-level approach. A metamodel provides performance estimates for each proposed design at extremely low computational effort while high-fidelity analysis codes provide accurate performance values on some promising designs at much higher cost. To safeguard the accuracy of the estimates, the metamodel is initially trained on a population that is specifically assembled for that purpose. The training is repeated from time to time with the high-fidelity performance values of promising designs. Different high-fidelity tools have been developed and used for the assessment of performance.The CFD-tool performs steady RANS simulations of a single blade passage of the isolated propeller in free air under zero angle of attack. These simulations provide the aerodynamic performance values. The full propeller is modelled thanks to cyclic boundary conditions. The k - ε turbulence model is used in combination with wall treatment. Adiabatic no-slip wall conditions are imposed on the spinner and blade surfaces whereas the test-section radial boundary is reproducing the effects of a pressure far-field. This approach has proven its robustness and, above all, its accuracy as satisfactory agreement with experimental results has been found for different operating conditions over a wide range of blade shapes, as well as sufficient grid independency. In the post-processing of the aerodynamic results, the Sound Pressure Level (SPL)is computed for tonal noise at various observer locations by the aeroacoustic solver(CHA). Formulation 1A from Farassat is used for this purpose. This formulation is related to the inhomogeneous wave equation derived from Lighthill's acoustic analogy by Ffowcs Williams and Hawkings (FW-H). It benefits from the partial decoupling of the acoustic and aerodynamic aspects and is particularly suited to compute the noise from propellers. The thickness noise and loading noise are expressed by separate equations in the time-domain whereas the quadrupole source term is dropped from the original FW-H equation. The blade surface is chosen as integration surface and a newly developed truncation technique is applied to circumvent the mathematical singularity arising when parts of the blade reach sonic conditions in terms of kinematics with respect to the observer. This approach delivers accurate values at acceptable computational cost. Besides, CSM-computations make use of a finite elements solver to compute the total mass of the blade as well as the stresses resulting from the centrifugal and aerodynamic forces. Considering the numerous possibilities to tailor the blade structure so that it properly takes on the stresses, only a simplified blade model is implemented. [...]
APA, Harvard, Vancouver, ISO, and other styles
44

Bernabè, Matteo. "Multi-rotor aircraft flying qualities assessment by means of inverse simulation." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2018. http://amslaurea.unibo.it/15910/.

Full text
Abstract:
This thesis work wants to investigate in how complex the mathematical model of a multi-rotor drone has to be, in order to simulate three different flight conditions: impulsive responses, vertical and horizontal flight. This is done by exploiting a technique called inverse simulation. Also the two autopilot used to control the model has been designed to be as close as possible to the real one. The results obtained with Simulink are then compared with the telemetry data collected during the real flight by the Pixhawk flight controller.
APA, Harvard, Vancouver, ISO, and other styles
45

Arruda, Michael. "Dynamic inverse resiliant control for damaged asymmetric aircraft: Modeling and simulation." Thesis, Wichita State University, 2009. http://hdl.handle.net/10057/2513.

Full text
Abstract:
This paper presents the development and simulation of a dynamic inverse resilient control (DIRC) system that can recover a general aviation aircraft that has sustained damage to a lifting surface in ight, and is now asymmetrical. A new set of di erential equations of motion for the aircraft are derived that account for the asymmetries of the aircraft and for the dynamic e ects of the shift in the center of gravity away from the original body centered axis. The typical symmetric force and moment coe cient buildup is altered to include the inuences of asymmetric lift, drag, and control deection. For the simulation, a Raytheon Bonanaza F-33C y-by-wire testbed is selected since it has been used in both ight and simulation testing for prior Wichita State University research. Geometric, mass, and aerodynamic properties for the damaged aircraft are determined with conceptual design techniques. The DIRC consists of an inverse controller with decoupled ight controls and an adaptive system to correct the command signals for a damaged aircraft. Modeling errors between the inverse control and the actual aircraft are large. Adaptive Bias Correctors, a simpli ed neural network, are applied to adapt the controller to the modeling errors between the undamaged symmetric based inverse controller and damaged asymmetric aircraft. Adaptation happens fast enough to limit the bank angle excursion and bring the aircraft back to wings level ight. Simulations are performed with a MATLAB/Simulink R and a full 6DOF model of the aircraft. Tests show that for losses to the left wing, the DIRC can recover the aircraft until the available control authority is unable to counteract the asymmetric moments.
Thesis (M.S.)--Wichita State University, College of Engineering, Dept. of Aerospace Engineering
APA, Harvard, Vancouver, ISO, and other styles
46

Gelman, Gabriel E. "Comparison of model checking and simulation to examine aircraft system behavior." Thesis, Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/49145.

Full text
Abstract:
Automation surprises are examples of poor Human-Machine Interaction (HMI) where pilots were surprised by actions of the automation, which lead to dangerous situations during which pilots had to counteract the autopilot. To be able to identify problems that may arise between pilots and automation before implementation, methods are needed that can uncover potentially dangerous HMI early in the design process. In this work, two such methods, simulation and model checking, have been combined and compared to leverage the benefits of both. In the past, model checking has been successful at uncovering known automation surprises. Simulation, on the other hand, has been successful in the aviation domain and human factor issues. To be able to compare these two approaches, this work focused on a common case study involving a known automation surprise. The automation surprise that was examined, is linked to the former Airbus speed protection logic that caused aircraft on approach to change the flight mode, resulting in a sudden climb. The results provided by the model checking with SAL (Symbolic Analysis Laboratory) in a previous work, have been used to provide input for simulation. In this work, this automation surprise was simulated with the simulation platform WMC (Work Models that Compute) and compared to the corresponding results from SAL. By using the case study, this work provides a method to examine system behavior, such as automation surprises, using model checking and simulation in conjunction to leverage the benefits of both.
APA, Harvard, Vancouver, ISO, and other styles
47

Woodburn, David. "Modeling and Simulation of All-electric Aircraft Power Generation and Actuation." Doctoral diss., University of Central Florida, 2013. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/6037.

Full text
Abstract:
Modern aircraft, military and commercial, rely extensively on hydraulic systems. However, there is great interest in the avionics community to replace hydraulic systems with electric systems. There are physical challenges to replacing hydraulic actuators with electromechanical actuators (EMAs), especially for flight control surface actuation. These include dynamic heat generation and power management. Simulation is seen as a powerful tool in making the transition to all-electric aircraft by predicting the dynamic heat generated and the power flow in the EMA. Chapter 2 of this dissertation describes the nonlinear, lumped-element, integrated modeling of a permanent magnet (PM) motor used in an EMA. This model is capable of representing transient dynamics of an EMA, mechanically, electrically, and thermally. Inductance is a primary parameter that links the electrical and mechanical domains and, therefore, is of critical importance to the modeling of the whole EMA. In the dynamic mode of operation of an EMA, the inductances are quite nonlinear. Chapter 3 details the careful analysis of the inductances from finite element software and the mathematical modeling of these inductances for use in the overall EMA model. Chapter 4 covers the design and verification of a nonlinear, transient simulation model of a two-step synchronous generator with three-phase rectifiers. Simulation results are shown.
Ph.D.
Doctorate
Electrical Engineering and Computer Science
Engineering and Computer Science
Electrical Engineering
APA, Harvard, Vancouver, ISO, and other styles
48

Reimer, Lars [Verfasser]. "Simulation Environment for CFD-based Aeroelastic Analysis of Aircraft / Lars Reimer." München : Verlag Dr. Hut, 2020. http://d-nb.info/1222352052/34.

Full text
APA, Harvard, Vancouver, ISO, and other styles
49

Mohmad, Rouyan Nurhana. "Model simulation suitable for an aircraft at high angle of attack." Thesis, Cranfield University, 2016. http://dspace.lib.cranfield.ac.uk/handle/1826/9722.

Full text
Abstract:
Simulation of a dynamic system is known to be sensitive to various factors and one of them could be the precision of model parameters. While the sensitivity of flight dynamic simulation to small changes in aerodynamic coefficients is typically not studied, the simulation of aircraft required to operate in nonlinear flight regimes usually at high angles of attack can be very sensitive to such small differences. Determining the significance and impact of the differences in aerodynamic characteristics is critical for understanding the flight dynamics and designing suitable flight control laws. This thesis uses this concept to study the effect of the differences in aerodynamic data for different aerodynamic models provided for a same aircraft which is F-18 HARV combat aircraft. The aircraft was used as a prototype for the high angles of attack technology program. However modeling an aircraft at high angles of attack requires an extensive aerodynamic data which are usually di cult to access. All aerodynamic models were collected from open literature and implemented within a nonlinear six degree of freedom aircraft model. Inspection of aerodynamic data set for these models has shown mismatches for certain aerodynamic derivatives, especially at higher angles of attack where nonlinear dynamics are known to exist. Nonlinear simulations are used to analyse three different types of flight dynamic models that use look-up-tables, arc-tangent formulation and polynomial functions to represent aerodynamic data that are suitable for high angles of attack application. To achieve this, a nonlinear six degree of freedom Simulink model was developed to accommodate these aerodynamic models separately. The trim conditions were obtained for different combinations of angles of attack and airspeed and the models were linearized in each case. Properties of the resulting state matrices such as eigenvalues and eigenvectors were studied to determine the dynamic behaviour of the aircraft at various flight conditions.
APA, Harvard, Vancouver, ISO, and other styles
50

Reel, Brian H. "A FLIGHT SIMULATION STUDY OF THE SIMULTANEOUS NON-INTERFERING AIRCRAFT APPROACH." DigitalCommons@CalPoly, 2009. https://digitalcommons.calpoly.edu/theses/80.

Full text
Abstract:
Using a new implementation of a NASA flight simulation of the Quiet Short-Haul Research Aircraft, autopilots were designed to be capable of flying both straight in (ILS) approaches, and circling (SNI) approaches. A standard glideslope coupler was sufficient for most conditions, but a standard Proportional-Integral-Derivative (PID) based localizer tracker was not sufficient for maintaining a lateral track on the SNI course. To track the SNI course, a feed-forward system, using GPS steering provided much better results. NASA and the FAA embrace the concept of a Simultaneous, Non-Interfering (SNI) approach as a way to increase airport throughput while reducing the noise footprints of aircraft on approach. The NASA concept for the SNI approach for Short Takeoff and Landing (STOL) aircraft involves a straight in segment flown above the flight path of a normal approach, followed by a spiraling descent to the runway. As this is a procedure that would be utilized by regional airliners, it is assumed that it would be conducted under Instrument Flight Rules (IFR). GPS or INS guidance would be required to fly this approach, and it is likely that it would be necessary to fly the approach with a coupled autopilot: a stabilized, curving, instrument approach to decision altitude would be exceedingly difficult to fly. The autopilots in many current commuter and general aviation aircraft, however, were designed before the event of GPS, and do not have provisions for tracking curved paths. This study identifies problem areas in implementing the SNI circling approach on aircraft and avionics as they stand today and also gives examples of what can be done for the SNI approach to be successful.
APA, Harvard, Vancouver, ISO, and other styles
You might also be interested in the bibliographies on the topic 'Simulating Aircraft' for other source types:
Journal articles Books
We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!

To the bibliography