This document provides a detailed description of the optimal control theory employed to establish the lower bound performance accuracy limits for air-to-surface missile systems. Techniques from optimal control theory are used to separate the contribution of sensor error to mean square miss distance from the total missile system mean square miss distance. The guidance sensor measurements are operated on by a Kalman filter which provides optimal estimates of the measured state variables. Employing these optimal estimates to steer an ideal missile, the lower bound performance accuracy is established. Two general types of guidance measurements are considered; Line of Sight Angle Tracking and Direct Distance Measurement.
Lower Bound Accuracy Estimate for Air-to-Surface Missile Systems
1969
38 pages
Report
No indication
English
Missile Trajectories & Reentry Dynamics , Air & Space-Launched Missiles , Guided missile trajectories , Air to surface missiles , Accuracy , Impact prediction , Errors , Direction finding , Proportional navigation , Equations of motion , Position finding , Guided missile targets , Guided missile tracking systems , Miss distance , Automatic pilots , Pursuit courses , Target position indicators , Detectors , Optimization , Stabilized platforms , Velocity , Kalman filters , S/L change 8309
Missile deployment module accuracy verification
AIAA | 1984
|Submarine launched ballistic missile - Improved accuracy
AIAA | 1981
|Time-to-Go Estimate for Missile Guidance
AIAA | 2005
|A Probabilistic Method to Estimate a Missile Target
British Library Conference Proceedings | 1999
|