Terminal guidance of the missile against an evasive target is explored. The two main types of guidance laws employed in the majority of missiles, namely proportional navigation and command to line-of-sight are modeled using Matlab(registered) Simulink(Trademark). The two-dimensioned missile-target intercept geometry is simulated for a point mass missile and target. Missile velocity due to its drag also factored. The engagement results for different scenarios with target doing a 9-g evasive maneuver are then compared to analyze the performance of hybrid proportional navigation guidance with bang-bang control.
Missile Terminal Guidance and Control Against Evasive Targets
2000
94 pages
Report
Keine Angabe
Englisch
Missile Trajectories & Reentry Dynamics , Surface Launched Missiles , Maneuverability , Surface to air missiles , Guided missile simulators , Line of sight , Military strategy , Performance(Engineering) , Theses , Air navigation , Flight maneuvers , Intercept trajectories , Proportional navigation , Technology assessment , Guidance laws , Bang bang control
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