ADCS Design for a Sounding Rocket with Thrust Vectoring

Abstract This paper addresses the development of an attitude determination and control system (ADCS) for a sounding rocket using thrust vector (TVC). To design ADCS, non-linear 6 degrees-of-freedom (DoF) model dynamics kinematics is deduced implemented in simulation environment. An optimal controller designed linear quadratic regulator (LQR) with additional integral action (LQI), relying on derived linear, time-varying, state-space representation rocket. The tested environment, demonstrating satisfactory tracking performance, robustness to uncertainties. A navigation designed, based measurements available on-board, provide accurate real-time estimates rocket’s state aerodynamic forces moments acting vehicle. These are used by adaptive version that computes gains real time after correcting model. Finally, ADCS result integration systems, complete being simulation, performance.