An application of time-optimal control theory to launch vehicle regulation
National Aeronautics and Space Administration, 1963 - Science - 22 pages
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000 trajectories 13th-order vehicle actuator Aeronautics and Space analog simulation angle of attack APPLICATION OF TIME-OPTIMAL Attitude Regulation Bending Mode closed-loop control law collection of open-loop containing the primary control law properly criterion is applied D-1895 National Aeronautics define a closed-loop F. B. Smith flexible launch vehicle flexible vehicle results flexure modes Honeywell Regulator Company J. A. Lovingood LAUNCH VEHICLE REGULATION law properly applied logic of Eq maximum principle methods of Reference minimum response Minneapolis-Honeywell Regulator Company Minneapolis1 mode feedback NASA NASA TN NASA TECHNICAL NOTE open-loop optimal trajectories Optimal Control optimum order model containing OTS price pitch rate pitch-attitude controller presented which show primary dynamics response time criterion Rigid-body pitch SEC Figure SEC I SEC secondary dynamics shown in Figure simulation are presented Space Administration synthesis procedure target set TECHNICAL NOTE D-1895 THEORY TO LAUNCH TIME-OPTIMAL CONTROL THEORY time-optimal regulation TN D-1895 National transfer function truncated model