Boşta Hareket Doğrusalsızlığı Bulunan Göreve Uyumlu Kontrol Yüzeylerinin Çırpma Yönünden İncelenmesi

Date

2013-09-12

Author

Ünlüsoy, Levent
Yaman, Yavuz

Metadata

Show full item record

Item Usage Stats

142
views

0
downloads

Bu çalışmada kontrol yüzeyleri göreve uyumlu olarak şekil değiştirebilen bir kanadın, açık kesitli kontrol yüzeylerine ait bağlantılardan kaynaklı olarak ortaya çıkan boşta hareket davranışının (freeplay), kontrol yüzeyi ve kanadın çırpma özellikleri (flutter) üzerindeki etkileri incelenecektir. Çalışma kapsamında sonlu elemanlar yöntemi kullanılarak kanadın eş-direngenlik ve eş-ağırlık özellikleri hesaplanacak ve bu özellikler kullanılarak üç serbestlik dereceli bir çırpma modeli oluşturulacaktır. Model içerisinde yer alan aerodinamik yükler, Theodorsen tarafından geliştirilen durağan olmayan aerodinamik çözüm kullanılarak hesaplanacaktır. Öncelikle Fortran programlama dili kullanılarak geliştirilen bir çırpma çözücüsü kullanılarak, oluşturulan çırpma modelinin doğrusal çırpma sonuçları elde edilecektir. Bunu takiben modele boşta hareket doğrusalsızlığı eklenecek ve armonik dengeleme yöntemi (Harmonic Balance Method) temeliyle geliştirilen çözücü yardımıyla doğrusal almayan çırpma sonuçları hesaplanacaktır. Çalışmada doğrusal ve doğrusal olmayan çırpma sonuçları karşılaştırılarak boşta hareket doğrusalsızlığının göreve uyumlu kontrol yüzeylerinin ve onlara sahip kanatların çırpma hızları üzerindeki etkileri değerlendirilecektir.

Subject Keywords

Flutter, Nonlinear Structural Dynamics, Morphing Aircraft, Harmonic Balance Method

URI

https://hdl.handle.net/11511/71248
http://ae.metu.edu.tr/~yyaman/Publications/National/63.pdf

Conference Name

UMTS2013, 16. Ulusal Makina Teorisi Sempozyumu, 12 - 13 Eylül 2013

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Nonlinear aeroservoelastic modelling and analysis of aircraft with control surface freeplay Yurtsever, Utku; Şahin, Melin; Kayran, Altan; Department of Aerospace Engineering (2022-11-24) In this study, nonlinear aeroservoelastic analysis of aircraft with control surface freeplay is performed using the fictitious mass approach. For the demonstration of the nonlinear aeroservoelastic analysis methodology, an available very light aircraft (VLA) design configuration is selected. The aeroelastic model of the aircraft is obtained by combining the structural and aerodynamic models of the aircraft, which are prepared by the finite element modelling and analysis tool MSC.Patran/MSC.Nastran and the a...
Investigation of effect of mass distribution on wing flutter by fluid-structure interaction analysis Celen, Furkan; Darendeliler, Haluk; Oktay, Erdal; Department of Mechanical Engineering (2022-8) In this study, a closely coupled fluid-structure interaction analysis is carried out in order to investigate the effect of mass distribution on wing flutter. A commercial software is used to carry out and couple the structural and computational fluid dynamics analyses. The validation of the analysis procedure is realized by simulating the AGARD 445.6 wing flutter experiment and comparing the simulation results with the experimental ones. The simulation results agreed well with the experimental results. The ...
ESTIMATION OF WEAR IN DRY FRICTION DAMPERS AND ITS EFFECT ON VIBRATION REDUCTION Çardak, Aykut; Ciğeroğlu, Ender; Department of Mechanical Engineering (2022-8-31) Although friction is mostly considered an undesirable phenomenon due to its energy dissipation characteristic, specially designed dry friction dampers utilize this feature to reduce the dynamic response of the system at the resonant frequencies. However, fretting wear due to dry friction during the operational life of the structure may drastically shift the performance from the initial design point and eventually cause drastic failures. Hence, it is important to establish a sophisticated algorithm that coup...
Nonlinear vibration analysis of L-shaped beams and their use in vibration reduction Ekici, Yiğitcan; Ciğeroğlu, Ender; Yazıcıoğlu, Yiğit; Department of Mechanical Engineering (2022-9) In this thesis, nonlinear vibration analysis of both fixed L-shaped beam and L-shaped beam attached to a single degree of freedom (SDOF) system is performed for several cases with different structural parameters to observe the effect of these parameters. Then these beams are proposed to reduce the vibration amplitudes of certain structures, and the nonlinear effects on the dynamic responses of these structures are investigated. The nonlinear dynamic model of the L-shaped beam is obtained by using Euler-Bern...
Data-Driven Model Discovery and Control of Lateral-Directional Fighter Aircraft Dynamics Öznurlu, Can; Uğur, Ömür; Çimen, Tayfun; Department of Scientific Computing (2022-8-26) The focus of this thesis is to control the lateral-directional motion of the fighter aircraft by using integral action based Model Predictive Control (MPC) where the model is obtained by data-driven model discovery method. Dynamic Mode Decomposition with Control (DMDc) is used as a model discovery technique based only on measurement data with no modeling assumptions. The model created using this technique is used for MPC and tested against noisy conditions. In addition, performance comparison of MPC with Cl...

Citation Formats

L. Ünlüsoy and Y. Yaman, “Boşta Hareket Doğrusalsızlığı Bulunan Göreve Uyumlu Kontrol Yüzeylerinin Çırpma Yönünden İncelenmesi,” presented at the UMTS2013, 16. Ulusal Makina Teorisi Sempozyumu, 12 - 13 Eylül 2013, Erzurum, Türkiye, 2013, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/71248.