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.


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    Title :

    Optimal terminal guidance of air-to-surface missile


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1968


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English






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