Structural design and analysis of the mission adaptive wings of an unmanned aerial vehicle

Download

index.pdf

Date

2010

Author

Ünlüsoy, Levent

Metadata

Show full item record

Item Usage Stats

383
views

246
downloads

In this study, the structural design and analysis of a wing having mission-adaptive control surfaces were conducted. The wing structure was designed in order to withstand a maximum aerodynamic loading of 5 g due to maneuver. The structural model of the wing was developed by using MSC/PATRAN package program and that structural model was analyzed by using MSC/NASTRAN package program. The designed wing was then manufactured by Turkish Aerospace Industries Inc. (TUSAŞ-TAI). The finite element analysis results were verified by conducting ground vibration tests on the manufactured wing. The comparative results were used to tune the finite element model and the results obtained showed that the modeling was very successful.

Subject Keywords

Aerospace engineering., Finite Element Analysis.

URI

http://etd.lib.metu.edu.tr/upload/12611515/index.pdf
https://hdl.handle.net/11511/19160

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Design and analysis of a structural component of a heavy transport aircraft Çıkrıkcı, Davut; Yaman, Yavuz; Department of Aerospace Engineering (2010) This thesis aims to present the design and analysis of a structural component of a heavy transport aircraft. The designed component is the “coupling“ which is the interface member connecting two frames or two stringers in the fuselage assembly. The “frames”, which are the circumferential stiffeners, are joined together by the “frame couplings”. The “stringers”, which are the longitudinal stiffeners, are joined together by the “stringer couplings”. At the preliminary design phase; the structural design princ...
Analysis and design of helicopter rotor blades for reduced vibrational level Tamer, Aykut; Yaman, Yavuz; Department of Aerospace Engineering (2011) In this thesis analysis and design of helicopter rotor blades were discussed for reduced vibrational level. For this purpose an optimization procedure was developed which involves coupling of the comprehensive rotorcraft analysis tool CAMRAD JA and the gradient based optimization algorithm. The main goal was to achieve favorable blade structural dynamics characteristics that would lead to reduction in vibrational level. For this purpose blade stiffness and mass distributions were considered as the design va...
Investigation of rotor wake interactions in helicopters using 3d unsteady free vortex wake methodology Yemenici, Öznur; Uzol, Oğuz; Department of Aerospace Engineering (2010) This thesis focuses on developing and examining the capabilities of a new in-house aerodynamic analysis tool, AeroSIM+, and investigating rotor-rotor aerodynamic interactions for two helicopters, one behind the other in forward flight. AeroSIM+ is a 3-D unsteady vortex panel method potential flow solver based on a free vortex wake methodology. Validation of the results with the experimental data is performed using the Caradonna-Tung hovering rotor test case. AeroSIM+ code is improved for forward flight cond...
Design and analysis of an equipment rack structure of a medium transport aircraft Yalçın, Mehmet Efruz; Yaman, Yavuz; Department of Aerospace Engineering (2009) In this study, equipment rack structure for a medium transport aircraft was designed and finite element analysis of this design was performed. The equipment rack structure, which was designed for a modernization project, was positioned and dimensions were determined by regarding the geometry of primary structures of the aircraft. The structure was designed such that it satisfies the pre-defined margin of safety values. Design of the structure was prepared in Unigraphics, and the finite element modeling and ...
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...

Citation Formats

L. Ünlüsoy, “Structural design and analysis of the mission adaptive wings of an unmanned aerial vehicle,” M.S. - Master of Science, Middle East Technical University, 2010.