Development of a dynamic flight model of a jet trainer aircraft

Download

index.pdf

Date

2007

Author

Gilani, Muhaned

Metadata

Show full item record

Item Usage Stats

344
views

391
downloads

A dynamic flight model of a jet trainer aircraft is developed in MATLAB-SIMULINK. Using a six degree of freedom mathematical model, non-linear simulation is used to observe the longitudinal and lateral-directional motions of the aircraft following a pilot input. The mathematical model is in state-space form and uses aircraft stability and control derivatives calculated from the aircraft geometric and aerodynamic characteristics. The simulation takes the changes in speed and altitude into consideration due to pilot input and demonstrates the non-linearity of the aircraft motion. The results from the simulation are compared with the results from flight characteristics manual of the actual aircraft to validate the mathematical model used. The simulation is carried out for a number of airspeed and altitude combinations to examine the effect of changing speed and altitude on the aircraft dynamic response.

Subject Keywords

Aeronautics., Aeronautical Engineering.

URI

http://etd.lib.metu.edu.tr/upload/2/12608298/index.pdf
https://hdl.handle.net/11511/16646

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Structural optimization of a composite wing Sökmen, Özlem; Akgün, Mehmet A.; Department of Aerospace Engineering (2006) In this study, the structural optimization of a cruise missile wing is accomplished for the aerodynamic loads for four different flight conditions. The flight conditions correspond to the corner points of the V-n diagram. The structural analysis and optimization is performed using the ANSYS finite element program. In order to construct the flight envelope and to find the pressure distribution in each flight condition, FASTRAN Computational Fluid Dynamics program is used. The structural optimization is perfo...
Nonlinear modeling and flight control system design of an unmanned aerial vehicle Karakaş, Deniz; Balkan, Raif Tuna; Department of Mechanical Engineering (2007) The nonlinear simulation model of an unmanned aerial vehicle (UAV) in MATLAB®/Simulink® environment is developed by taking into consideration all the possible major system components such as actuators, gravity, engine, atmosphere, wind-turbulence models, as well as the aerodynamics components in the 6 DOF equations of motion. Trim and linearization of the developed nonlinear model are accomplished and various related analyses are carried out. The model is validated by comparing with a similar UAV data in te...
Multidisciplinary design of an unmanned aerial vehicle wing Sakarya, Arzu; Yaman, Yavuz; Department of Aerospace Engineering (2011) In this thesis, the structural design, structural analysis and producibility analysis of an unmanned aerial vehicle wing were performed. Three different wing models, made of different materials, were designed. The wings were aluminum wing model and composite wing models; made of prepreg and wet lay-up. All wings have the same aerodynamic geometry and structural configuration under the same flight conditions. The structural designs of three wings were done by using Unigraphics NX. The finite element modeling...
Robust controller design for a fixed wing uav Prach, Anna; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2009) This study describes the design and implementation of the pitch and roll autopilots for a fixed wing unmanned vehicle. A Tactical Unmanned Aerial Vehicle (TUAV), which is designed at the Middle East Technical University (METU), is used as a platform. This work combines development of the classical and robust controllers, which are used for the pitch and roll autopilots. One of the important steps in the thesis is development of the non-linear dynamic model of the UAV, which is developed in MATLAB/Simulink e...
Design and analysis of a mode-switching micro unmanned aerial vehicle Cakici, Ferit; Leblebicioğlu, Mehmet Kemal (SAGE Publications, 2016-12-01) In this study, design and analysis of a mode-switching vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) with level flight capability is considered. The design of the platform includes both multirotor and fixed-wing (FW) conventional airplane structures; therefore named as VTOL-FW. The aircraft is modeled using aerodynamical principles including post-stall conditions. Trim conditions are obtained by solving constrained optimization problems. Linear analysis techniques are utilized for trim ...

Citation Formats

M. Gilani, “Development of a dynamic flight model of a jet trainer aircraft,” M.S. - Master of Science, Middle East Technical University, 2007.