GUIDANCE AND FLIGHT CONTROL SYSTEM OF SURFACE-TO-AIR MISSILE(SAM) BASED 122 MM CALIBER ROCKET

• Main Author: Ardiansyah, Alvin
• Format: Final Project
• Language: Indonesia
• Subjects: Teknik (Rekayasa, enjinering dan kegiatan berkaitan)
• Online Access: https://digilib.itb.ac.id/gdl/view/75174
• Institution: Institut Teknologi Bandung

SAM is a surface-to-air missile and is the most effective air defense weapon against fighter aircraft. Indonesia itself needs a lot of air defense due to its large and strategic area. Therefore, the development of SAM in Indonesia is needed to reduce the dependences on missile needs from other countries. The R-Han 122B rocket is a rocket made in Indonesia which has the potential to be developed into a SAM. In this undergraduate assignment, a study was conducted on the development of the 122 mm caliber rocket flight control and guidance system. The study was carried out by modeling missile dynamics, guidance systems and control systems. The missile dynamics model is based on the 6 DOF (Degrees of Freedom) equation of a rigid body. In modeling missile dynamics, missile aerodynamic data is needed, this data can be obtained from the Missile Datcom program. The guidance system model is based on proportional navigation guidance law. The control system model is based on the LQR (Linear Quadratic Regulator) method. The modeling is done in Simulink software. The simulation is run with several variations of scenarios. The analysis is carried out by looking at the missile trajectory, the missile acceleration command, the missile acceleration, the deflection of the control plane, the missile's distance to the target or CPA (closest point approach) when it reaches the target, and the time it takes to hit the target. The simulation results show that the missile is capable of intercepting targets under many conditions. However, in some target conditions, the missile is unable to intercept the target.