Akademik Veri Yönetim Sistemi
AIAA Atmospheric Flight Mechanics Conference 2010, Toronto, Kanada, 2 - 05 Ağustos 2010
The recent interests in the necessity of high maneuverability and vertical launching triggered namely the unconventional control design techniques that are effective at high angle of attack flight regimes. For most of missile configurations, considering the offensive mission requirements, an efficient approach to the mentioned interest become the application of thrust vector control together with conventional aerodynamic control. In this study, nonlinear modeling and vertical launch analysis of a surface to air missile with both aerodynamic and thrust vector control is investigated. Aerodynamic force and moment modeling of the presented missile includes the challenging high angle of attack aerodynamics behavior and the so called hybrid control, which utilizes both tail fins and jet vanes as control surfaces. Six degree of freedom (6 DoF) flight dynamics modeling is examined by simulation analysis to test the accuracy and validity of the nonlinear missile model, in vertical launch, transition to free fall and maneuvering phases of the missile. Consecutively, linearization of the nonlinear model is presented. Linearization study is conducted in two different approaches for flight phases of the missile. The key results are presented numerically with graphs and discussions are made on the results to provide contribution to the current literature. © 2010 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.