Galileo spin rate controlThis paper presents the analysis and design of the spin rate control flight algorithm for the dual-spin Galileo spacecraft. Because of thruster plume contamination constraints, only one poorly located thruster is available for spin rate correction in each spin direction. Hence, firing of any of the spin thrusters has a deleterious effect on spacecraft pointing. A control strategy was developed for achieving the desired spin rate correction while keeping disturbances at acceptable levels. This involved symmetrically distributed multiple thruster burns. Results of extensive tests of the adopted scheme on a computer simulation of the spacecraft are also presented.
Document ID
19820055353
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Eke, F. O. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Man, G. K. (California Institute of Technology, Jet Propulsion Laboratory, Pasadena CA, United States)
Date Acquired
August 10, 2013
Publication Date
August 1, 1982
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 82-1461
Meeting Information
Meeting: Astrodynamics Conference
Location: San Diego, CA
Start Date: August 9, 1982
End Date: August 11, 1982
Sponsors: American Institute of Aeronautics and Astronautics and American Astronautical Society