Design of a grid fin aerodynamic control device for transonic flight regime

Download
index.pdf
2015
Dikbaş, Erdem
Show full item record
712
views
371
downloads
Grid fins is unconventional control devices and they are used for aerodynamic control of various types of missiles. Low hinge moment requirement and superior packaging possibilities make grid fins attractive when compared to conventional planar fins. However, design of grid fins is more involved when transonic flight regime is considered. The reason for this is high drag force encountered by the grid fin. The purpose of the thesis is to overcome this drawback and to define a proper design methodology for transonic flight regime. Computational Fluid Dynamics (CFD) is utilized as main tool in calculation of aerodynamic force and moments. Computational efforts are significantly easified by utilization of `unit grid fin' concept, which is introduced in this thesis study. At the end, an equivalent control performance is accomplished with a more efficient design when compared to a conventional planar fin example.
Aerofoils., Aerodynamics., Aerodynamics, Transonic., Guided missiles, Computational fluid Dynamics., Fluid Dynamics.
http://etd.lib.metu.edu.tr/upload/12618820/index.pdf
https://hdl.handle.net/11511/24701
Graduate School of Natural and Applied Sciences, Thesis

Suggestions

Simplified Numerical Approach for the Prediction of Aerodynamic Forces on Grid Fins
DIKBAS, Erdem; Baran, Özgür Uğraş; Sert, Cüneyt (2018-07-01)
Grid fins are unconventional control devices used for aerodynamic control of various types of missiles. Low hinge moment requirement and superior packaging potential make grid fins attractive alternatives to conventional planar fins. Unlike missiles with planar fins, widely accepted preliminary design tools for missiles with grid fins are not available. As an alternative, aerodynamic forces and moments are obtained through full computational fluid dynamics solutions. However, generating an aerodynamic force...
Optimization of aeroelastic flapping motion of thin airfoils in a biplane configuration for maximum thrust
Kaya, Mustafa; Tuncer, İsmail Hakkı; Jones, Kevin D.; Platzer, Max F. (2007-01-01)
An aeroelastic flapping motion of thin airfoils in a biplane configuration is optimized for maximum thrust. Airfoils are attached to swing arms by an elastic joint, which is model led by a torsional spring. A spring-mass system is employed for the aeroelastic coupling. The stiffness coefficient and the mass moment of inertia of the airfoil are optimized for maximum thrust. A gradient based optimization method is employed in a parallel computing environment. Unsteady, low speed flows are computed in parallel...
Parametric investigation of hull shaped fuselage for amphibious UAV
Sazak, Emre; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2017)
Performance of amphibious unmanned aerial vehicles (UAV’s) that take off from and land on water, like seaplanes, greatly depend on hydrodynamic effects as well as aerodynamic effects, therefore their geometries need to be optimized for both. This study mainly investigates the effect of geometric parameters of a generic, hull-shaped fuselage that are constrained by hydrodynamic drivers, such as the step height needed to reduce hydrodynamic drag, sternpost angle and deadrise angle needed for safe landing; on ...
Experimental and numerical investigation of a jet vane of thrust vector control system
Söğütcü, Burak.; Perçin, Mustafa; Department of Aerospace Engineering (2019)
Thrust vectoring is generally used in tactical missile systems when attitude control with conventional control systems is inadequate. One of the most widely used thrust vectoring method is to employ jet vanes in the divergent section of the rocket motor nozzle to have the desired thrust vectoring. In the present study, the flow over the jet vane of a thrust vector control system is investigated using both numerical and experimental techniques. Three dimensional, unsteady and viscous flow over the jet vane i...
Parametric investigation of hull shaped fuselage for an amphibious UAV
Sazak, Emre; Kurtuluş, Dilek Funda (null; 2016-07-15)
Performance of amphibious UAV’s (Unmanned Aerial Vehicles) that take off from and land on water, like seaplanes, greatly depend on hydrodynamic effects as well as aerodynamic effects, therefore their geometries need to be optimized. This study mainly investigates the effect of geometric parameters of a generic, hull-shaped fuselage that are constrained by hydrodynamic drivers, such as the step height needed to reduce hydrodynamic drag, and deadrise and sternpost angles needed for safe landing, on aerodynami...
Citation Formats
E. Dikbaş, “Design of a grid fin aerodynamic control device for transonic flight regime,” M.S. - Master of Science, Middle East Technical University, 2015.
METU IIS - Integrated Information Service open@metu.edu.tr