This thesis deals with a simulation of a missile versus target engagement scenario. After driving simplified transfer functions for the missile seeker head, missile autopilot, missile dynamics, and target dynamics, a three dimensional simulation is developed using classical proportional navigation. The scenario is simulated using state variable design. A forward time solution of the two dimensional problem is developed which is converted to an adjoint model. The adjoint model is used to determine the optimal time to initiate simplified and tactical evasion maneuvers in order to maximize the final miss distance.
Target/Missile Engagement Scenario Using Classical Proportional Navigation
1990
122 pages
Report
Keine Angabe
Englisch
Missile Tracking Systems , Missile Trajectories & Reentry Dynamics , Evasion , Proportional navigation , Automatic pilots , Dynamics , Forward areas , Guided missile components , Guided missile warheads , Guided missiles , Homing devices , Maneuvers , Miss distance , Optimization , Simplification , Simulation , Solutions(General) , Targets , Theses , Three dimensional , Time , Transfer functions , Two dimensional , Variables , Guided missile trajectories , Guided missile targets , Flight maneuvers , Intercept trajectories , Antiaircraft missiles , Aircraft defense systems , Adjoint models , Survivability , Barrel roll maneuver , Split S maneuver , Scenarios , Computer programs
Missile Acceleration in Proportional Navigation
IEEE | 1973
|Application to Missile Guidance: Proportional Navigation
AIAA | 2010
|Root-Mean-Square Miss Distance of Proportional Navigation Missile Against Sinusoidal Target
Online Contents | 1996
|Root-Mean-Square Miss Distance of Proportional Navigation Missile Against Sinusoidal Target
British Library Conference Proceedings | 1996
|