Aerodynamic optimization of missile external configurations

Download
index.pdf
2014
Arslan, Kıvanç
Show full item record
853
views
450
downloads
In this thesis, design optimization methods capable of optimizing aerodynamic performances of missiles and rockets are developed. Sequential Quadratic Programming (SQP) and Random Search (RS) methods are used for optimization, whereas Missile DATCOM, which is a semi-empirical aerodynamic analysis tool, is used to calculate aerodynamic coefficients of missile configurations. As the first part of the work, capabilities and limitations of SQP and RS optimization methods are investigated on a complex test function. In addition to that, a validation for aerodynamic analysis tool is done. Then, using reverse engineering approach, aerodynamic performance parameters of “NASA Tandem Control Missile” (TCM) configuration are defined as objectives to the developed design optimization method with the aim of reaching TCM configuration at the end of aerodynamic performance optimization process. Geometric properties and aerodynamic performance parameters of the optimum configurations obtained using the developed design method are compared to the ones of the TCM configuration. Moreover, an optimization case study for a generic air-to-ground missile is carried out. It is concluded that the developed design optimization method is able to determine missile external configurations for pre-defined aerodynamic performance parameters.
Guided missiles, Mathematical optimization., Quadratic programming., Rockets (Aeronautics.
http://etd.lib.metu.edu.tr/upload/12618026/index.pdf
https://hdl.handle.net/11511/24019
Graduate School of Natural and Applied Sciences, Thesis

Suggestions

Missile autopilot design by projective control theory
Doruk, Reşat Özgür; Kocaoğlan, Erol; Department of Electrical and Electronics Engineering (2003)
In this thesis, autopilots are developed for missiles with moderate dynamics and stationary targets. The aim is to use the designs in real applications. Since the real missile model is nonlinear, a linearization process is required to get use of systematic linear controller design techniques. In the scope of this thesis, the linear quadratic full state feedback approach is applied for developing missile autopilots. However, the limitations of measurement systems on the missiles restrict the availability of ...
Numerical investigation of characteristics of pitch and roll damping coefficients for missile models
Kayabaşı, İskander; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2012)
In this thesis the characteristics of pitch and roll damping coefficients of missile models are investigated by using Computational Fluid Dynamics (CFD) techniques. Experimental data of NACA0012 airfoil, Basic Finner (BF) and Modified Basic Finner (MBF) models are used for validation and verification studies. Numerical computations are performed from subsonic to supersonic flow regimes. Grid refinement and turbulence model selection studies are conducted before starting the dynamic motion simulations. Numer...
Numerical investigations of lateral jets for missile aerodynamics
Ağsarlıoğlu, Ekin; Albayrak, Kahraman; Department of Mechanical Engineering (2011)
In this thesis, effects of sonic lateral jets on aerodynamics of missiles and missilelike geometries are investigated numerically by commercial Computational Fluid Dynamics (CFD) software FLUENT. The study consists of two parts. In the first part, two generic missile-like geometries with lateral jets, of which experimental data are available in literature, are analyzed by the software for validation studies. As the result of this study, experimental data and CFD results are in good agreement with each other...
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...
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...
Citation Formats
K. Arslan, “Aerodynamic optimization of missile external configurations,” M.S. - Master of Science, Middle East Technical University, 2014.
METU IIS - Integrated Information Service open@metu.edu.tr