**Thesis Type:** Post Graduate

**Institution Of The Thesis:** Orta Doğu Teknik Üniversitesi, Faculty of Engineering, Department of Aerospace Engineering, Turkey

**Approval Date:** 2018

**Student:** NEŞE BAŞAK BİNGÖL TAŞTANKAYA

**Consultant: **OZAN TEKİNALP

In this thesis, a guidance algorithm is proposed which aims to control impact time via polynomial shaping of the missile trajectory and missile flight path angle. The main motivation of the trajectory design, which is convenient for impact time control, is its application to multiple missile engagement situations. In the first part of the study, a planar engagement geometry is considered. The trajectory of the missile is defined as a third order polynomial function of downrange. The coefficients of the polynomial function are obtained by solving a set of parametric equations to control impact time and impact angle. The guidance command required for the missile to follow the designed trajectory is defined as the acceleration command applied in the direction that is normal to the missile velocity vector. Nonlinear equations of motion in planar geometry are used to obtain the acceleration command. vi By defining the missile flight path angle in terms of polynomial function coefficients, the acceleration command is derived analytically. In the existence of disturbance effects during flight, the use of this acceleration command will cause the missile to deviate from the reference trajectory. For this reason, in order to obtain the guidance commands in feedback form, a virtual target approach is proposed. After the trajectory design is completed, it has been studied on the application of the proposed guidance method in 3D space. A maneuver-plane approach is used for the application of the trajectory defined in the planar geometry to 3D space. A reference frame is defined so that its