Optimal Design of Integrated Missile Guidance and Control
Tactical ballistic missiles (TBM) target may experience severe spiral maneuvers as they reenter the earth's atmosphere due to a configurational asymmetry. To hit these targets, the interceptor must possess extremely fast maneuver response characteristics. Before 10 secs to go optimal integrated guidance and control (OIGC) is slightly better than a conventional autopilot. From 2 to 10 secs OIGC is much better than a conventional autopilot in closing up trajectories. However, with 2 secs to go, OIGC uses up full authority and with the aerodynamic surfaces alone may not catch the tactical ballistic missile target. Therefore, there is a need for thrusters. In this paper, a blending mechanism of optimal integrated guidance and control (OIGC) and fuzzy logic controlled thruster is developed for a skid-to-turn missile to improve the missile interception performance. OIGC is an innovative approach to designing guidance and control laws.