Optimal intercept trajectories in one and two-dimensional situations are investigated. Target evasive maneuvers are not considered. Aerodynamic drag on the rocket is a function of rocket velocity and an exponential atmosphere. Trajectories, often including singular thrusting, are calculated for the one-dimensional case by digital computer using the final rocket velocity as a parameter. Newton-Raphson techniques are used, and prove sensitive to estimates of initial values. The boundary-value problem for the the two-dimensional situation is formulated, but the numerical solution diverged. The difficulty is apparently due to the of Newton-Raphson methods. (Author)
Optimal Intercept Trajectories of a Ground-Launched Rocket
1970
90 pages
Report
Keine Angabe
Englisch
Missile Trajectories & Reentry Dynamics , Passive Defense Systems , Antiaircraft defense systems , Guided missile trajectories , Surface to air missiles , Kill probabilities , Intercept trajectories , Optimization , Time , Drag , Numerical analysis , Computer programs , Theses , Optimal control theory
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