Optimal Stochastic Guidance Laws for Tactical Missiles
ANALYTIC SCIENCES CORP READING MA
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Guidance laws are developed for tactical missiles which take into account the following important dynamic and random effects random target motion, homing sensor measurement noise, bounded control level, bounded acceleration level, and missile autopilot dynamics. Several different guidance laws are derived using optimal stochastic control theory and evaluated by computer simulation. An important conclusion of this work is that when intercept accuracy is appreciably limited by missile maneuvering capability, a control policy obtained by taking control saturation into account can yeild significantly better performance than control policies derived assuming that control levels are unconstrained.
- Guided Missile Dynamics, Configurations and Control Surfaces