Volume 19, Issue 10 (October 2019)                   Modares Mechanical Engineering 2019, 19(10): 2511-2521 | Back to browse issues page

‎ 20.1001.1.10275940.1398.19.10.24.6

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Borhanpanah M, Dehghani Firouz-Abadi R. Developing an Aero-Elastic Model of a Full Aircraft to Study the Effect of Flexibility on its Flight Dynamics Derivatives. Modares Mechanical Engineering 2019; 19 (10) :2511-2521
URL: http://mme.modares.ac.ir/article-15-28593-en.html
Developing an Aero-Elastic Model of a Full Aircraft to Study the Effect of Flexibility on its Flight Dynamics Derivatives
M. Borhanpanah1 , R. Dehghani Firouz-Abadi * 2
1- Department of Aerospace Engineering, Sharif University of Technology, Tehran, Iran
2- Department of Aerospace Engineering, Sharif University of Technology, Tehran, Iran , firouzabadi@sharif.ir
Abstract:   (5294 Views)
Flexible and lightweight unmanned aerial vehicles (UAVs) have shown their widespread applications in recent years and hence attracted so much attention of various aerospace communities. Due to their high flexibility, the interactions of aerodynamic loading and structure deformations are the dominant factor in their design process. Aerodynamic causes a set of deformations in the structure which consequently alters aerodynamic coefficients. In the current study, the effect of UAV flexibility on aerodynamic derivatives and lateral stability of the vehicle was investigated and an efficient method is proposed to provide an accurate estimation of the aerodynamic coefficients. This method is based on fast aerodynamic calculations as well as the formulation of elastic beams and is given for a full free-free airplane. Vehicle analysis is conducted by using the Modal beam formulation (through finite element mode shapes) and aerodynamic calculations based upon the 3D panel method (source–doublet combination). The final aero-elastic coupled formulation the whole system is also given in terms of matrix operators. Verification studies are conducted for a special type of UAV and flexibility effects on derivatives are evaluated in the two states. In a first evaluation, the lift load factor is altered and after trimming the airplane, various aerodynamic derivatives are computed while in the second evaluation, with varying the wingspan length, the aerodynamic derivatives are obtained at each aspect ratio of the wing. Results show that flexibility can enhance some of the stability derivatives of the UAV up to several times.
 
Keywords: Aero-Elasticity, Stability, HALE UAV, Aerodynamic Derivatives, Flexible Airplane
Full-Text [PDF 1567 kb]   (2436 Downloads)    
Article Type: Original Research | Subject: Sonic Flow
Received: 2018/12/25 | Accepted: 2019/02/23 | Published: 2019/10/22
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