Aeroelastic behaviour of UAV wings due to morphing

Download
index.pdf
2017-01-01
Unlusoy, Levent
Yaman, Yavuz
Show full item record
Creative Commons License
This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.
169
views
0
downloads
Purpose - The purpose of this paper is to analyse the effects of morphing on the aeroelastic behaviour of unmanned aerial vehicle (UAV) wings to make an emphasis on the required aeroelastic tailoring starting from the conceptual design of the morphing mechanisms.
Flutter prediction, Morphing wings, Pk-method, State-space solution, Thodorsen aerodynamics, Typical section model
https://hdl.handle.net/11511/36561
AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY
Department of Aerospace Engineering, Article

Suggestions

Aerodynamic parameter estimation using flight test data
Kutluay, Ümit; Platin, Bülent Emre; Mahmutyazıcıoğlu, Gökmen; Department of Mechanical Engineering (2011)
This doctoral study aims to develop a methodology for use in determining aerodynamic models and parameters from actual flight test data for different types of autonomous flight vehicles. The stepwise regression method and equation error method are utilized for the aerodynamic model identification and parameter estimation. A closed loop aerodynamic parameter estimation approach is also applied in this study which can be used to fine tune the model parameters. Genetic algorithm is used as the optimization ker...
Aero-structural analysis of the morphing trailing edge control surface of a fully morphing unmanned aerial vehicle wing
Kalkan, Uğur; Şahin, Melin; Department of Aerospace Engineering (2017)
This thesis investigates the aero-structural analysis of the morphing trailing edge control surface of a fully morphing unmanned aerial vehicle wing for some camber morphing missions. Designed control surface was structurally analyzed with Finite Element Method using ANSYS Workbench v14.0 Static Structural module. Open Cell, Closed Cell designs with some material and thickness changes were studied in order to find the optimum design in terms of minimum weight and structural relevance. Analyses were both per...
Three dimensional aerodynamic analysis of missiles by a panel method
Başoğlu, Osman; Özyörük, Yusuf; Department of Aeronautical Engineering (2002)
Panel methods are extensively used in aerodynamic analysis of missiles in early stages of their development. An existing TUBİTAK-SAGE panel code is modified and improved for routine and more efficient calculation of the aerodynamic coefficients of various missile configurations at subsonic and supersonic flight conditions. Particularly, the poor convergence, user unfriendliness and poor output characters of this code have been improved by modifying and adding new routines to it. Now the code with an incorpo...
Aeroelastic analysis of an unmanned aerial vehicle
Susuz, Umut; Yaman, Yavuz; Department of Aerospace Engineering (2008)
In this thesis aeroelastic analysis of a typical Unmanned Aerial Vehicle (UAV) using MSC®FlightLoads and Dynamics module and MSC®NASTRAN Aero 1 solver was performed. The analyses were carried out at sea level, 1000m, 2000m and 4000m altitudes for Mach Numbers M=0.2, 0.4 and 0.6 for the full model of the UAV. The flutter characteristics of the UAV for different flight conditions were obtained and presented. The effect of altitude on flutter characteristics has been examined and compared with the theoretical ...
Aerodynamic parameter estimation of a supersonic missile with rapid speed variation by using kalman filtering
Bayoğlu, Tuğba; Kutay, Ali Türker; Department of Aerospace Engineering (2016)
This study aims to develop an approach for the aerodynamic parameter estimation problem for supersonic air to air missile with rapid speed variation, as well as large variation of aerodynamic parameters with respect to Mach number. In literature, most of the estimation techniques require that estimator is time independent. Therefore, most of the aerodynamic parameter estimation methods are applied for air vehicles which have control over their speed or which can operate at relatively constant Mach number so...
Citation Formats
L. Unlusoy and Y. Yaman, “Aeroelastic behaviour of UAV wings due to morphing,” AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY, pp. 30–38, 2017, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/36561.
METU IIS - Integrated Information Service open@metu.edu.tr