Experimental and numerical investigation of a jet vane of thrust vector control system

Söğütcü, Burak.
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 is solved numerically, in which the interaction of high temperature and high speed combustion gas flow with the jet vane located in the exit plane of the solid rocket motor nozzle is examined in detail. In addition, static firing tests of a rocket motor, which contains jet vanes at the nozzle exit plane, are conducted in the static rocket motor stand of TÜB˙ITAK-SAGE. The thrust and the side forces due to the jet vane are measured for different angles of attack values of jet vanes. The nozzle shock pattern in the presence of the jet vane is also visualized by using the Schlieren technique.


Design of a grid fin aerodynamic control device for transonic flight regime
Dikbaş, Erdem; Sert, Cüneyt; Baran, Özgür Uğraş; Department of Mechanical Engineering (2015)
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 tr...
The Effects of geometric design parameters on the flow behavior of a dual pulse solid rocket motor during secondary firing
Ertuğrul, Suat Erdem; Kurtuluş, Dilek Funda; Ulaş, Abdullah; Department of Aerospace Engineering (2012)
The ability of a propulsion system is very crucial for the capability of a missile or a rocket system. Unlike liquid propellant rocket motors, the only control mechanism of the thrust value is the propellant geometry in solid propellant rocket motors. When the operation of solid propellant rocket motor has started, it cannot be stopped anymore. For this main reason the advance of dual pulse motor technology has started. The aim of this study is to investigate the geometrical effects of design parameters on ...
Performance prediction of nozzleless solid propellant rocket motors
Özer, Ali Can; Özyörük, Yusuf; Department of Aerospace Engineering (2015)
Integral rocket ramjet (IRR) type propulsion systems have many advantages over conventional solid rocket motors when used in tactical missile systems. Nozzleless boosters are one of the applicable concept choices for the system [1]. During the design and development phase of solid propellant rocket motors, simulation and prediction of behavior of a given motor by numerical tools is important in terms of decreasing the development duration and costs. The present approach includes performance prediction of no...
Yerlikaya, Umit; Balkan, Raif Tuna (2017-10-13)
Electromechanical actuators are widely used in miscellaneous applications in engineering such as aircrafts, missiles, etc. due to their momentary overdrive capability, long-term storability, and low quiescent power/low maintenance characteristics. This work focuses on electromechanical control actuation systems (CAS) that are composed of a brushless direct current motor, ball screw, and lever mechanism. In this type of CAS, nonlinearity and asymmetry occur due to the lever mechanism itself, saturation limit...
Conceptual aerodynamic design of ramjet missiles
Demiral, Ertan; Eyi, Sinan; Department of Aerospace Engineering (2017)
The prediction of aerodynamic coefficients of missiles that have air-breathing components is a challenging task during the preliminary design phase. It is considerably important to estimate missile aerodynamic coefficients accurately at the beginning of design phase to avoid poor designs which could lead to redesign at later stages of the design process. In this study, firstly an improved method is developed to predict the aerodynamic coefficients of missile configurations with air-breathing components more...
Citation Formats
B. Söğütcü, “Experimental and numerical investigation of a jet vane of thrust vector control system,” Thesis (M.S.) -- Graduate School of Natural and Applied Sciences. Aerospace Engineering., Middle East Technical University, 2019.