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Ascent control analysis for S-II derivative launch vehicles, digital computer programModel is used for analysis of the six degrees-of-freedom dynamics of general launch vehicle during atmospheric boost. Equations of motion are developed for rigid body and flat earth. Case may be started at any time beginning with ignition of stage and may be ended upon, or prior to, stage burnout. End of case may be at a specified time or based on propellant expended.
Document ID
19730000120
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Andrews, P. D. (Rockwell International Corp.)
Date Acquired
August 7, 2013
Publication Date
May 1, 1973
Subject Category
Mathematics And Information Sciences
Report/Patent Number
MFS-24324
Accession Number
73B10120
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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