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Attitude and articulation control of the CRAF/Cassini spacecraft in the presence of structural flexibilities and propellant sloshPreliminary attitude and articulation controller designs for the CRAF/Cassini spacecraft have prompted a consideration of potential interactions with structural dynamics and propellant motion. The two algorithms significantly affected are attitude control during main engine burns, and articulation control of the high-precision scan platform (HPSP). For main engine burns, the primary concerns are the sloshing of the bipropellant, which constitutes 70 percent of initial spacecraft mass, and the vibration of the three large appendages, especially the HPSP, on which the gyros are mounted. For the HPSP pointing algorithm, the main concern is the fairly large offset of the HPSP center-of-mass from the gimbals, which is motivated by other system and subsystem considerations. This offset results in significant coupling between HPSP articulation and HPSP boom structural dynamics. This paper surveys the operational scenarios of these algorithms, and the impacts of nonrigid dynamics on controller design and performance.
Document ID
19930066603
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Enright, Paul J.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Macala, Glenn A.
(JPL Pasadena, CA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1992
Publication Information
Publication: In: Guidance and control 1992; Proceedings of the 15th Annual AAS Rocky Mountain Conference, Keystone, CO, Feb. 8-12, 1992 (A93-50576 21-18)
Publisher: Univelt, Inc.
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AAS PAPER 92-063
Accession Number
93A50600
Distribution Limits
Public
Copyright
Other

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