Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1982-09-22
1985-03-05
Jordan, Charles T.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
F41G 722
Patent
active
045026505
ABSTRACT:
A method for augmenting a noise-adaptive predictive proportional navigation terminal guidance scheme. In a third order configuration with noise adaptive varying gain parameters calculated as a function of time-to-go, this system implements an optimal control law to augment proportional navigation with a target acceleration feed forward term and a navigation ratio which is a function of time-to-go and the control effort weighting factor. This third order system may also implement another optimal control law to even greater advantage, taking into account not only target acceleration but also missile acceleration in a feedback loop which, together with the navigation ratio, are both functions of time-to-go and autopilot dynamics, whereby first order autopilot time lag is accounted for. This system is particularly useful for high and medium altitude targets and results in significant miss distance improvement for terminal guidance against small maneuvering targets.
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General Dynamics Pomona Division
Johnson Edward B.
Jordan Charles T.
Martin Neil F.
Maxham Lawrence A.
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