Multi-objective morphing wing optimization for an Unmanned Air Vehicle

Date

2017-07-03

Author

Körpe, Durmuş Sinan
Özgen, Serkan

Metadata

Show full item record

Item Usage Stats

152
views

0
downloads

This work describes the optimization process of a morphing wing for an unmanned air vehicle (UAV) by using multi-objective gradient based optimization algorithmin which maximizationof lift to dragratioand minimization of bending moment at wing rootchord planearedefined asthe objective functions. Six different optimization problems are solved by changing weighted sum coefficients of the objective functions in order to observe the morphing wing planform and the airfoil shape change.According to the results, 15.2% lift to drag ratioincreaseis obtainedwhile the increase in the bending moment is 2%

URI

https://hdl.handle.net/11511/83473

DOI

https://doi.org/0.13009/EUCASS2017-184

Conference Name

7th European Conference for Aeronautics and Spaice Sciences (3 - 06 Juyl 2017)

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Multidisciplinary and multiobjective design optimization of an unmanned combat aerial vehicle (UCAV) Çavuş, Nesrin; Tekinalp, Ozan; Department of Aerospace Engineering (2009) The Multiple Cooling Multi-Objective Simulated Annealing Algorithm is used for the conceptual design optimization of a supersonic Unmanned Combat Aerial Vehicle (UCAV). Single and multiobjective optimization problems are addressed while limiting performance requirements between desired bounds to obtain viable aircraft configurations. A conceptual aircraft design code was prepared for planned but flexible combat missions. The results demonstrate that the optimization technique employed is an effective tool f...
Multistage launch vehicle design with thrust profile and trajectory optimization / Civek Coşkun, Ezgi; Özgören, Mustafa Kemal; Department of Mechanical Engineering (2014) In the frame of this thesis, a Matlab® based design tool utilizing a general purpose optimal control solver GPOPS-II® was developed for the optimization of ascent trajectories of multistage launch vehicles. This tool can be utilized both for preliminary mission design of an existing launch vehicle and conceptual design of a new launch vehicle. In the preliminary mission design of an existing launch vehicle, maximizing payload mass is a very common performance measure. Therefore, a trajectory optimization co...
Flow Visualization around a Flapping-Wing Micro Air Vehicle in Free Flight Using Large-Scale PIV Herrero, Alejandro del Estal; Perçin, Mustafa; Karasek, Matej; van Oudheusden, Bas (2018-12-01) Flow visualizations have been performed on a free flying, flapping-wing micro air vehicle (MAV), using a large-scale particle image velocimetry (PIV) approach. The PIV method involves the use of helium-filled soap bubbles (HFSB) as tracer particles. HFSB scatter light with much higher intensity than regular seeding particles, comparable to that reflected off the flexible flapping wings. This enables flow field visualization to be achieved close to the flapping wings, in contrast to previous PIV experiments ...
Flow visualization around a flapping-wing micro air vehicle in free flight Del Estal Herrero, Alejandro; Perçin, Mustafa; Karasek, Matej; Van Oudheusden, Bas W. (null; 2018-10-05) Flow visualizations have been performed on a free flying flapping-wing Micro Air Vehicle (MAV), using a large-scale particle image velocimetry (PIV) approach. The PIV method involves the use of helium filled soap bubbles (HFSB) as tracer particles. HFSB scatter light with much higher intensity than regular seeding particles and comparable to that reflected off the flexible flapping wings. This enables flow field visualization to be achieved also close to the flapping wings, in contrast to previous PIV exper...
Vortex Formation and Force Generation Mechanisms of the DelFly II in Hovering Flight Tenaglia, A; Perçin, Mustafa; Van Oudheusden, Bas W.; Deng, Shuanghou; Remes, Bart (2014-08-12) This paper addresses the unsteady aerodynamic mechanisms in the hovering flight of the DelFly II flapping-wing Micro Aerial Vehicle (MAV). Stereoscopic Particle Image Velocimetry (Stereo-PIV) were carried out around the wings at a high framing rate. Thrust-force was measured to investigate the relation between the vortex dynamics and the aerodynamic force generation. The results reveal that the Leading-Edge-Vortex (LEV), as well as the high flexibility of the wings, have a major effect on thrust generation....

Citation Formats

D. S. Körpe and S. Özgen, “Multi-objective morphing wing optimization for an Unmanned Air Vehicle,” presented at the 7th European Conference for Aeronautics and Spaice Sciences (3 - 06 Juyl 2017), Milan, Italy, 2017, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/83473.