The effects of liquid propellant motion on the attitude stability of spin stabilized space-craft

An analysis of the effects of liquid motion on the attitude stability of spin stabilized spacecraft is presented. The effects of varying the fuel load and the asymmetry of the platform are emphasized. The energy sink stability criteria are compared to the results of a computer simulation. Based on this comparison the limitations of the energy sink stability criteria are identified.

Department dc:contributor.department

Department of Aeronautics and Astronautics

Grantor dc:publisher

Monterey, California. Naval Postgraduate School

Year dc:date.issued

1990

Author dc:creator

• Myers, Jack W. Jr.

Advisor dc:contributor.advisor

• Agrawal, Brij N.

Statement dc:rights

• This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.

Language dc:language.iso

en_US

Handle dc:identifier.uri

https://hdl.handle.net/10945/37548

OAI identifier oai:identifier

oai:calhoun.nps.edu:10945/37548