Optimum control theory is applied to develop a guidance law for homing missiles for which the airframe dynamics is not neglected. This work extends the applicability of the laws derived in a previous report to systems characterized by two time constants. The effectiveness of the optimum controller thus derived is evaluated in an example by comparing it with classical proportional navigation. Additionally, extensive quantitative plots of the controller parameters are provided as an aid in specific designs. (Author)
Optimal Controllers for Homing Missiles With Two Time Constants
1969
62 pages
Report
Keine Angabe
Englisch
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