NASA NTRS · 19730000120
Ascent control analysis for S-II derivative launch vehicles, digital computer program
Abstract
Model 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.
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Andrews, P. D.. 1973-05-01. Ascent control analysis for S-II derivative launch vehicles, digital computer program. https://ntrs.nasa.gov/citations/19730000120
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