Aeroelastic Modelling and Testing of a Thin Laminated Composite Missile Fin/Wing

Aslan, Göktuğ
Kırımlıoğlu, Serdar
Kurtuluş, Dilek Funda
Missile fins or wings exposed to different coupled aerodynamic loads during the mission or flight at subsonic and supersonic velocity profile. Aerodynamic loads varying with the angle of attack and the velocity profile may cause some structural fatigue and failure problems. In order to achieve such problems, high strength materials such as composites are required. In this work, a laminated composite missile fin was investigated in terms of the strength varying with the aerodynamic profile. The fiber orientation of the laminated fin/wing will be optimized to obtain a high strength configuration. The double wedge airfoil profile was used in Computational Fluid Dynamics (CFD) and structural analysis. A set of computational fluid dynamic and structural finite element analysis had been done in order to optimize the composite configuration. During the analyses, fluid structure interactions were observed for the different boundary conditions. © 2017 American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
8th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, 2017


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...
Aeroservoelastic Modelling and Analysis of a Missile Control Surface with a Nonlinear Electromechanical Actuator
Mehmet Ozan, Nalcı; Kayran, Altan (null; 2014-06-16)
In this study, aeroservoelastic modeling and analysis of a missile control surface which is operated and controlled by a power limited, nonlinear electromechanical actuator is performed. Linear models of the control fin structure and aerodynamics together with the nonlinear servo-actuation system are built and integrated. The resulting aeroservoelastic system is analyzed both in time and frequency domain. Structural model of the control fin is based on the finite element model of the fin. Aerodynamic model ...
Aeroservoelastic analysis and robust controller synthesis for flutter suppression of air vehicle control actuation systems
Akmeşe, Alper; Platin, Bülent Emre; Department of Mechanical Engineering (2006)
Flutter is one of the most important phenomena in which aerodynamic surfaces become unstable in certain flight conditions. Since the 1930’s many studies were conducted in the areas of flutter prediction in design stage, research of design methods for flutter prevention, derivation and confirmation of flutter flight envelopes via tests, and in similar subjects for aircraft wings. With the use of controllers in 1960’s, studies on the active flutter suppression began. First the classical controllers were used....
Yutük, Kaan; Tuncer, İsmail Hakkı; Department of Aerospace Engineering (2021-11-8)
Modern fighter aircraft compulsorily demand high maneuverability capability, which is mainly provided by an improved aerodynamic performance at high angles of attack. This is achieved by mostly employing strakes and canards. In this study, adjoint-based configuration and leading edge shape optimizations of a strake on a double-delta wing configuration are performed. SU2 is employed for flow and adjoint solutions. SU2 flow solutions are first verified on solutions for adaptive grids. In the configuration opt...
Numerical and experimantal analysis of flapping motion
Sarıgöl, Ebru; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2007)
The aerodynamics of two-dimensional and three-dimensional flapping motion in hover is analyzed in incompressible, laminar flow at low Reynolds number regime. The aim of this study is to understand the physics and the underlying mechanisms of the flapping motion using both numerical tools (Direct Numerical Simulation) and experimental tools (Particle Image Velocimetry PIV technique). Numerical analyses cover both two-dimensional and three-dimensional configurations for different parameters using two differen...
Citation Formats
G. Aslan, S. Kırımlıoğlu, and D. F. Kurtuluş, “Aeroelastic Modelling and Testing of a Thin Laminated Composite Missile Fin/Wing,” presented at the 8th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, 2017, Denver; United States, 2017, Accessed: 00, 2021. [Online]. Available: