VERIFICATION OF A FINITE ELEMENT MODEL OF AN UNMANNED AERIAL VEHICLE WING TORQUE BOX VIA EXPERIMENTAL MODAL TESTING

Date

2012-07-04

Author

Unlusoy, Levent
Şahin, Melin
Yaman, Yavuz

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

236
views

0
downloads

In this study, the detailed finite element model (FEM) of an unmanned aerial vehicle wing torque box was verified by the experimental modal testing. During the computational studies the free-free boundary conditions were used and the natural frequencies and mode-shapes of the structure were obtained by using the MSC Software. The results were then compared with the experimentally obtained resonance frequencies and mode-shapes. It was observed that the frequencies were in close agreement having an error within the range of 1.5-3.6%.

Subject Keywords

Finite Element Modeling, Ground Vibration Tests, Unmanned Aerial Vehicle Wing

URI

https://hdl.handle.net/11511/55441

Conference Name

11th ASME Biennial Conference on Engineering Systems Design and Analysis, (ESDA 2012)

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Modelling of an articulated flying body and control system design Güzelcan, Burçin Tutku; Yazıcıoğlu, Yiğit; Özgören, Mustafa Kemal; Department of Mechanical Engineering (2022-12-5) This study presents the conceptual design of an articulated coaxial rotor Unmanned Air Vehicle (UAV) with three-dimensional dynamical models and a control strategy. Conventional rotary-wing aircrafts operate maneuvers via swashplates which is a complex mechanism adding bulky elements to the aircrafts. While designing light weight UAVs, there appears a need for less complex and compact mechanisms for maneuverability rather than swashplates. There are different methods and mechanisms to acquire maneuvering wi...
An Approach for System Identification in Unmanned Surface Vehicles Erunsal, Izzet Kagan; Ahiska, Kenan; Kumru, Murat; Leblebicioğlu, Mehmet Kemal (2017-10-21) In this study, a system identification methodology is introduced to determine the model parameters of unmanned surface vehicles. The proposed identification scheme is based on sequencing the experiments according to their capabilities to identify the model parameters. In each experiment, the parameters to be found are updated and the results are validated before ascertaining the final value. A procedure to complete the identification work in an experiment, namely the required post-processing, the optimizati...
Improvement of finite element model by using sine vibration test results of acommunication satellite Çekiç, Abdulkadir; Yaman, Yavuz; Department of Aerospace Engineering (2021-2-15) In this thesis, the vibration analysis of a communication satellite is performed,and the improvementof the finite element model by using vibration test results is presented. First, the satellite finite element model isgenerated using MSC/PATRAN and MSC/NASTRAN commercial software. With the natural frequency and frequency response analysis, the expected frequency values and response amplitudes in accelerometers arecalculated in vibration tests. The results obtained in the vib...
Aerodynamic design and control of tandem wing unmanned aerial vehicle Kaya, Taşkın; Özgen, Serkan; Department of Aerospace Engineering (2019) This thesis presents an approach towards the design methodology of electrical propulsion, tandem wing unmanned aerial vehicle. Due to its possible rewarding features, tandem wing design is investigated as the main subject of this study. The stability and control characteristics of tandem wing aircraft are critical since the interference between the two wings may result in nonlinear aerodynamic characteristics for varying angles of attack. Thus, the design of the controller system requires careful handling, ...
Design and aerodynamic analysis of a VTOL tilt-wing UAV Cakir, Hasan; Kurtuluş, Dilek Funda (2022-01-01) The aerodynamic design and analysis of an Unmanned Air Vehicle, capable of vertical take-off and landing by employing fixed four rotors on the tilt-wing and two rotors on the tilt-tail, will be presented in this study. Both main wing and the horizontal tail can be tilted 90 degrees. During VTOL, transition and forward flight, aerodynamic and thrust forces have been employed. Different flight conditions, including the effects of angle of attack, side slip, wing tilt angle and control surfaces deflection angl...

Citation Formats

L. Unlusoy, M. Şahin, and Y. Yaman, “VERIFICATION OF A FINITE ELEMENT MODEL OF AN UNMANNED AERIAL VEHICLE WING TORQUE BOX VIA EXPERIMENTAL MODAL TESTING,” presented at the 11th ASME Biennial Conference on Engineering Systems Design and Analysis, (ESDA 2012), Nantes, FRANCE, 2012, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/55441.