FLIGHT GUIDANCE AND CONTROL SYSTEMS OF CRUISE MISSILE FOR CRUISE AND TERMINAL PHASE

• Main Author: Fariz, Ahmad
• Format: Theses
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/35146
• Institution: Institut Teknologi Bandung

Cruise missiles are one type of unmanned weapon used to attack a long-range target with a precise angle of impact. The flight in the cruise phase is carried out at low altitudes with the terrain following guidance system. In the terminal phase, the missile aims a specific point on the target. The cruise phase guidance system is supported by a stabilization system and a normal acceleration and an altitude tracking system. The guidance system for terminal phase is supported by the same tracking system but without altitude tracking system. The guidance and control systems design is carried out in stages. The terrain following system works with 2 algorithms, i.e. weighting equation and moving average, to produce guides in the form of flying heights. The impact angle guidance system works with proportional navigation guidance law. Control gains of the stability augmentation system are designed using linear quadratic regulator method. The control augmentation system gains are designed using a PID controller. The missile that have been equipped with guidance and control systemsis tested in cases. The case in cruise phase is done by the missile facing 2 types of obstacles. Flight in the terminal phase tested to impact the target from 2 directions. The results of the cruise phase test show that the missile can pass the obstacle properly if the obstacle characteristics fulfill the maneuver restrictions. Meanwhile, the test results in the terminal phase indicate that missile maneuvers is not fast enough to follow the guidance, resulting in miss distances. Several methods to restore the problem are proposed.