AN IMPROVED GUIDANCE ALGORITHM FOR SOLID PROPELLENT BALLISTIC MISSILES

Due to production tolerences and off-nominal environmental conditions, the thrust time profile of solid propellant rocket motors suffers from high uncertainties in both magnitude and burn-out time. This behaviour leads to higher uncertainties in the motion parameters of the missile at the shut-off (burn-out) point. Accordingly, the impact point is highly erroneous.This paper develops a guidance and control strategy for compensating the effects of the above-mentioned uncertainties insuch a way as to minimize impact errors.