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Stability of large flexible damped spacecraft modeled as elastic continua

Maharana, Prashant K and Shrivastava, Shashi K (1984) Stability of large flexible damped spacecraft modeled as elastic continua. In: Acta Astronautica, 11 (2). pp. 103-109.

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Vibrational stability of a large flexible, structurally damped spacecraft subject to large rigid body rotations is analysed modelling the system as an elastic continuum. Using solution of rigid body attitude motion under torque free conditions and modal analysis, the vibrational equations are reduced to ordinary differential equations with time-varying coefficients. Stability analysis is carried out using Floquet theory and Sonin-Polya theorem. The cases of spinning and non-spinning spacecraft idealized as a flexible beam plate undergoing simple structural vibration are analysed in detail. The critical damping required for stabilization is shown to be a function of the spacecraft's inertia ratio and the level of disturbance.

Item Type: Journal Article
Publication: Acta Astronautica
Publisher: Elsevier science
Additional Information: Copyright for this article belongs to Elsevier science.
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 15 Jan 2010 09:37
Last Modified: 19 Sep 2010 05:48
URI: http://eprints.iisc.ac.in/id/eprint/23980

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