| Abstract |
A class of weighted control-effort minimizing guidance laws are derived for missiles of varying velocity. As a practical weighting function, we consider a function of air density and missile velocity parameterized by positive real numbers. The resulting optimal guidance problem can be interpreted as the drag minimization problem for subsonic or supersonic missiles, depending on what parameters are used. This approach is extended easily to solve the drag minimizationof a typical antiaircraft missile system with an arbitrary velocity pro le and arbitrary drag characteristics, as demonstrated by a simulation study. We also present analytical results on how the guidance gain of the optimal law varies according to the values of the parameters. Because the optimal guidance laws make use of the future missile velocity pro le, one critical issue is how to implement the laws. To avoid the dif culty that an inaccurately predicted missile velocity pro le causes the guidance command to blow up in the last part of the engagement, we suggest two simple on-line velocity-pro le updatingschemes, which considerably alleviatethe |
Implementation of Optimal Guidance Laws Using Predicted Missile Velocity Profiles.pdf (379.0K) [14] DATE : 2015-10-01 13:47:51
