Steepest-ascent optimization technique involving control variables and control parameters is reviewed with emphasis on influence coefficients for booster staging times; operational computer program to solve optimization problems for boosters having from two to five stages is described; combinations of launching azimuth, lift-off weight, pitchover rate, and cutoff and ignition times of each stage may be used as control variables; problems are defined by choosing payoff quantity and desired terminal conditions from library of 22 terminal functions; two example problems are solved.
Optimization of thrust direction histories and vehicle parameters for three-dimensional ascent trajectories
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 3 , n 5
1966
9 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Optimization of three-dimensional range and ascent trajectories of a two-stage hypersonic vehicle
Online Contents | 1996
|Optimization of three-dimensional range and ascent trajectories of a two-stage hypersonic vehicle
Online Contents | 1996
|British Library Conference Proceedings | 1993
|