Optimal Controllers for Homing Missiles With Two Time Constants
ARMY MISSILE COMMAND REDSTONE ARSENAL AL ADVANCED SENSORS DIRECTORATE
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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.
- Air Navigation and Guidance