This paper examines the problem of guiding a missile to a target using minimal energy. First, an optimal controller is developed for a missile that has arbitrary control over its acceleration vector. Next, an optimal controller is sought for a missile that has a directional control constraint, which is intended to model the actual constraint present in aerodynamically controlled missiles. The optimal guidance law is shown to have a very convenient form that is directly related to the optimal guidance law without the control constraint. Simulation results are conducted to completely characterize the new guidance law.
Minimum Energy Guidance for Aerodynamically Controlled Missiles
IEEE Transactions on Automatic Control ; 56 , 9 ; 2026-2037
2011
12 Seiten, 18 Quellen
Article (Journal)
English