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Return-to-launch-site trajectory shapingThe results are presented of a study to show the effect on flyback trajectories of constant inertial attitude during the fuel dissipation phase of a return-to-launch-site abort. It is shown that the value of the constant inertial attitude can be chosen to shape the flyback trajectory.
Document ID
19760026147
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Bown, R. L. (McDonnell-Douglas Technical Services Co., Inc. Houston, TX, United States)
Date Acquired
September 3, 2013
Publication Date
October 17, 1975
Subject Category
Astrodynamics
Report/Patent Number
DN-1.4-4-14
NASA-CR-151009
Report Number: DN-1.4-4-14
Report Number: NASA-CR-151009
Accession Number
76N33235
Funding Number(s)
CONTRACT_GRANT: NAS9-13970
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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