Undesirable rolling minimization on the EDF missiles flight based on LQR methods

Abstract

Missile is a flying vehicle or Unmanned Aerial Vehicle (UAV) with a bullet-like shape equipped with wings or tails. An electric missile can use an electric ducted fan (EDF) as the rocket driving force. EDF motor is a small electric motor with many blades that are in the cylinder protector. As a vehicle that still needs much development, EDF missiles require good flying control before it can be used for various needs. One of the main disadvantage in EDF missiles is the occurrence of rotary missile caused by the use of EDF motors EDF motor provides a moment on the missile when taking off so that the missile becomes uncontrollable rolling. Therefore we need a control method that can minimize unwanted rolling that occurs so we can achieve the stability in a missile flight. LQR is a modern control method that has the advantage of maintaining a state. LQR has excellent performance and robustness so it can optimize the control system. Due to the advantages of the LQR method, using this method is expected to improve the flying stability of EDF missiles in the face of unwanted rolling.