The problem of minimizing the maximum terminal miss of a planar case, proportional navigation missile attacking a high performance aircraft by optimally selecting missile launch angle is studied. System models are developed for both the aircraft and the missile; constraints are introduced to preserve physical realism. An algorithm based upon a worst-case error analysis is applied to find the optimum missile launch angle. Recurring patterns have been found for target and missile control over the area of interest. Effects of variations in missile velocity, missile time constant, and proportional navigation constant have been observed. (Author)
A Minmax Study of AIM Angle for Proportional Navigation Missile (the Planar Case)
1970
188 pages
Report
Keine Angabe
Englisch
Missile Trajectories & Reentry Dynamics , Aerial warfare , Guided missiles(Air-to-air) , Interception probabilities , Proportional navigation , Minimax technique , Optimization , Miss distance , Time-lag theory , Hamiltonian , Boundary value problems , Iterative methods , Mathematical models , Computer logic , Computer programs , Theses
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