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Stability Of Large Damped Flexible Spacecraft With Stored Angular Momentum

Maharana, Prashanta K. and Shrivastava, Shashi K. (1985) Stability Of Large Damped Flexible Spacecraft With Stored Angular Momentum. In: ACTA Astronautica, 12 (11). pp. 889-898.

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Vibrational stability of large flexible structurally damped spacecraft carrying internal angular momentum and undergoing large rigid body rotations is analysed modeling the systems as elastic continua. Initially, analytical solutions to the motion of rigid gyrostats under torque-free conditions are developed. The solutions to the gyrostats modeled as axisymmetric and triaxial spacecraft carrying three and two constant speed momentum wheels, respectively, with spin axes aligned with body principal axes are shown to be complicated. These represent extensions of solutions for simpler cases existing in the literature. Using these solutions and modal analysis, the vibrational equations are reduced to linear ordinary differential equations. Equations with periodically varying coefficients are analysed applying Floquet theory. Study of a few typical beam- and plate-like spacecraft configurations indicate that the introduction of a single reaction wheel into an axisymmetric satellite does not alter the stability criterion. However, introduction of constant speed rotors deteriorates vibrational stability. Effects of structural damping and vehicle inertia ratio are also studied.

Item Type: Journal Article
Publication: ACTA Astronautica
Publisher: Elsevier Science
Additional Information: The copyright of this article belongs to Elsevier Science
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 12 Nov 2009 10:52
Last Modified: 12 Oct 2020 11:07
URI: http://eprints.iisc.ac.in/id/eprint/20137

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