Three dimensional aerodynamic analysis of missiles by a panel method

Başoğlu, Osman
Panel methods are extensively used in aerodynamic analysis of missiles in early stages of their development. An existing TUBİTAK-SAGE panel code is modified and improved for routine and more efficient calculation of the aerodynamic coefficients of various missile configurations at subsonic and supersonic flight conditions. Particularly, the poor convergence, user unfriendliness and poor output characters of this code have been improved by modifying and adding new routines to it. Now the code with an incorporated graphical user interface converges faster, gives more useful aerodynamic information, including the hinge moments of the control surfaces and surface pressure distribution, and produces ready-to-visualize outputs. The modified 111and improved code is called the TÜBİTAK SAGE Vortex Lattice Method (TS- VLM). Previously unstudied capabilities and applicability range of this code are also explored in this thesis by carrying out extensive benchmarking studies of the code by solving various missile configurations, such as Sparrow, Sidewinder, NASA TM X -3310, and the generic wrap-around finned missiles. Comparisons of the results with available experimental data indicate that the code can generally compute the lift and normal force coefficients accurately at small to moderate angles of attack (0 to 15 degrees), and the pitching moment coefficient accurately at only small angles of attack (0 to 5 degrees), but Ms to compute these at higher angles. It is also proved that some aerodynamic coefficients related to the rotational motions of the missiles such as Magnus moment, roll and pitch damping coefficients can be computed accurately for supersonic Mach numbers.


Aeroservoelastic modeling of a missile control
Nalcı, Mehmet Ozan; Kayran, Altan; Department of Aerospace Engineering (2013)
In this thesis, aeroservoelastic modeling of a typical Missile Control Fin was performed. MSC®PATRAN, MSC®NASTRAN, MSC®FlightLoads and Dynamics, MATLAB® and MATLAB®Simulink were used for technical computing, modeling and simulation throughout the study. Linear models of the control fin structure, aerodynamics and servo-actuator system were developed, so as to be able to analyze the aeroservoelastic system in frequency and time domains. The flutter characteristics of the missile control fin for different fli...
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...
Adaptive control of guided missiles
Tiryaki Kutluay, Kadriye; Yavrucuk, İlkay; Department of Aerospace Engineering (2011)
This thesis presents applications and an analysis of various adaptive control augmentation schemes to various baseline flight control systems of an air to ground guided missile. The missile model used in this research has aerodynamic control surfaces on its tail section. The missile is desired to make skid to turn maneuvers by following acceleration commands in the pitch and yaw axis, and by keeping zero roll attitude. First, a linear quadratic regulator baseline autopilot is designed for the control of the...
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 ...
Aeroelastic behaviour of UAV wings due to morphing
Unlusoy, Levent; Yaman, Yavuz (2017-01-01)
Purpose - The purpose of this paper is to analyse the effects of morphing on the aeroelastic behaviour of unmanned aerial vehicle (UAV) wings to make an emphasis on the required aeroelastic tailoring starting from the conceptual design of the morphing mechanisms.
Citation Formats
O. Başoğlu, “Three dimensional aerodynamic analysis of missiles by a panel method,” Middle East Technical University, 2002.