A linear quadratic based missile guidance law is presented that imposes a predetermined terminal body angle. Solutions are provided for arbitrary order autopilot dynamics, with explicit analytical expressions given for first-order and zero-lag dynamics. Performance is demonstrated through simulation in a planar interception scenario.
Missile guidance with constrained intercept body angle
IEEE Transactions on Aerospace and Electronic Systems ; 50 , 2 ; 1445-1453
2014-04-01
736431 byte
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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