Results show effects on performance boundaries of variations in initial entry conditions and vehicle characteristics and of constraints on such trajectory variables as altitude and acceleration; effect of earth's rotation on optimal performance is also included; typical trajectories are presented to illustrate and contrast basic nature of various optimal entry missions; results also show that there are numerous trade-offs possible between maximum maneuver capability and optimal entry heating; factors for trade-off are initial entry conditions, trajectory constraints, and physical characteristics of vehicle; results also show that, although radiative effects can account for significant portion of total entry heating, trajectories for optimal heat entries are largely determined by convective inputs.
Trajectory optimization for apollo-type vehicle under entry conditions encountered during lunar return
NASA -- Tech Report
1967
39 pages
Report
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Coupled Shape and Reentry Trajectory Optimization of Entry Vehicle for Lunar Return
Tema Archive | 2012
|Coupled Entry Heat Shield/Trajectory Optimization for Lunar Return
British Library Conference Proceedings | 2008
|