Static aeroelastic modeling and parametric study of stacking sequence for laminated composite missile fins

Aslan, Göktuğ Murat
In this thesis, a surface-to-surface missile model with laminated composite fins is examined with respect to one-way static aeroelastic response under constant supersonic flight conditions. Two different modified double wedge fins or control surfaces using for control actuation system of a missile are investigated and compared in terms of aerodynamic and linear structural characteristics in order to minimize tip deflection. A serial set of steady-state supersonic Computational Fluid Dynamics (CFD) analyses at different angles of attack are conducted in order to obtain pressure distribution causing the structural deflection or failure on fins having modified double-wedge cross-sections. Grid refinement study is also performed for CFD analysis part. Control surface models are manufactured and tested in supersonic wind tunnel at a certain angle of attack and Mach number in order to observe shock waves on control surfaces during the flight. By using aerodynamic loads due to pressure distribution on fins, linear structural analyses with an algorithm written in Matlab® are executed in Nastran®. This algorithm examines the different stacking sequence of the laminated composite control surfaces in order to reduce tip deflection by considering four different failure criteria. Three structures with different stacking sequences not failing under maximum aerodynamic loads in structural analyses are manufactured and tested for both control surface models in order to compare and verify the maximum tip deflection results of Finite Element Method.


Investigation of missiles with strake fins and reduction of aerodynamic cross coupling effects by optimization
Usta, Engin; Tuncer, İsmail Hakkı; Department of Aerospace Engineering (2015)
Missiles with very low aspect ratio fins (also called strakes) are generally difficult to model by using engineering level aerodynamic methods and linear theories break due to complex nature of the flow adjacent to the mutual interference of the body and fin. Since fast prediction methods cannot accurately model vortex development along and downstream of very low aspect ratio fins, they have limited success for application to missiles with strake fins. Moreover, there is limited number of CFD studies for in...
Nonlinear Static Aeroelastic Behaviour of Composite Missile Fin with Interlaminar Damage
Özkaya, Özge; Kayran, Altan (2017-09-22)
Nonlinear static aeroelastic behavior of a basic composite missile fin is analyzed by means of two-way coupled FSI simulation and the effects of composite damages are presented. The configuration has been simulated by coupling the two commercial solvers ANSYS CFX for the fluid mechanical simulation with ANSYS Mechanical for the structural simulation. 3D composite fin geometry is constructed using ANSYS ACP tool. Interlaminar damage cases were investigated and the influence of the damage locations on the sta...
Nonlinear Static Aeroelastic Behavior of Composite Missile Fin with Interlaminar and Intralaminar Damage
ÖZKAYA, ÖZGE; Kayran, Altan (2018-01-12)
Nonlinear static aeroelastic behavior of the damaged composite missile fins is investigated. For this purpose, two-way coupled fluid structure interaction (FSI) analyses are performed to study the effect of different failure modes on the static aeroelastic behaviour of composite missile fins.The FSI analysis is done with two separate solvers, ANSYS CFX for the fluid (CFD) and ANSYS Mechanical for the structure (FEM) which runs in sequential order and exchange information at the interface of the fluid and st...
Dynamic modeling, guidance, and control of homing missiles
Özkan, Bülent; Özgören, Mustafa Kemal; Department of Mechanical Engineering (2005)
In this study, the dynamic modeling, guidance, and control of a missile with two relatively rotating parts are dealt with. The two parts of the missile are connected to each other by means of a roller bearing. In the first part of the study, the governing differential equations of motion of the mentioned missile are derived. Then, regarding the relative rotation between the bodies, the aerodynamic model of the missile is constructed by means of the Missile Datcom software available in TÜBİTAK-SAGE. After ob...
Thermal radiation from solid propellant rocket motor plume
Özen, Güzide; Selçuk, Nevin; Department of Chemical Engineering (2015)
Radiation emitted from rocket plumes plays a significant role in quantifying infrared (IR) radiative signature which is essential for identification and tracking of rockets. Prediction of plume radiation necessitates simultaneous solution of conservation equations for mass, momentum, energy, chemical species and radiant energy to provide input data for the radiation code. This is carried out by a Computational Fluid Dynamics (CFD) solver. As CFD solvers are CPU time expensive, an accurate and CPU efficient ...
Citation Formats
G. M. Aslan, “Static aeroelastic modeling and parametric study of stacking sequence for laminated composite missile fins,” M.S. - Master of Science, Middle East Technical University, 2018.