Optimal guidance law for linearized equations of missile is constructed which is based on information supplied from inertial platform and noisy TV tracker; mean-square miss distance of missiles respectively, using optimal guidance law, pursuit guidance, or proportional guidance are compared; comparison is made for typical initial position and velocity errors, and variety of system parameter variations, and nominal terminal trajectories; mean-square miss distance in each case was obtained from computer solution of matrix Riccati equation for covariance matrix of state vector of linearized missile equations.
Optimal terminal guidance of air-to-surface missile
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 5 , n 6
1968
6 pages
Article (Journal)
English
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Optimal terminal guidance of an air-to-surface missile.
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