NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Application of the steepest ascent optimization method to a reentry trajectory problemThe direct optimization method is presented in detail. Nominal values of the control variables are input parameters. Perturbations are introduced into the control variables and the resulting first order predictions of changes in the payoff, and constraint functions are then determined. Through a sequence of prescribed cycles, a trajectory is eventually obtained which is reasonably close to the optimum. The method is successfully applied to an Apollo three-dimensional reentry problem. The study of this Apollo application problem has resulted in the development of a highly flexible computer program that can be modified to consider other trajectory optimization problems.
Document ID
19720010255
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Junkin, B. G. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 2, 2013
Publication Date
December 10, 1971
Subject Category
Space Sciences
Report/Patent Number
NASA-TM-X-64636
Accession Number
72N17905
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available