Nonlinear Model for Micro-Launcher Attitude Control

The paper presents aspects regarding six degree of freedom (6DOF) model used for attitude control of the three-stage micro-launcher (ML) with a payload of up to 50 kg. This work uses two separate attitude control models dedicated for different flight phases. In the ascending phases, we will control the attitude angles related to the start frame, and in injection phases, we will control the attitude angles related to the geographical frame. The results analyzed will be the flight parameters in longitudinal, in lateral, and in roll movement. Using this model, the attitude control of the launcher can be evaluated. The novelty of the paper consists in alternative attitude angles used for control and in description of guidance signal.