NDLI: The dynamics and optimal control of spinning spacecraft with movable telescoping appendages. part c: effect of flexibility during boom deployment

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The dynamics and optimal control of spinning spacecraft with movable telescoping appendages. part c: effect of flexibility during boom deployment

Content Provider	NASA Technical Reports Server (NTRS)
Author	Bainum, P. M. James, P. K.
Copyright Year	1977
Description	The dynamics of a spinning symmetrical spacecraft system during the deployment (or retraction) of flexible boom-type appendages were investigated. The effect of flexibility during boom deployment is treated by modelling the deployable members as compound spherical pendula of varying length (according to a control law). The orientation of the flexible booms with respect to the hub, is described by a sequence of two Euler angles. The boom members contain a flexural stiffness which can be related to an assumed effective restoring linear spring constant, and structural damping which effects the entire system. Linearized equations of motion for this system, when the boom length is constant, involve periodic coefficients with the frequency of the hub spin. A bounded transformation is found which converts this system into a kinematically equivalent one involving only constant coefficients.
File Size	3519656
Page Count	52
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19770017219
Archival Resource Key	ark:/13960/t7sn50530
Language	English
Publisher Date	1977-05-01
Access Restriction	Open
Subject Keyword	Launch Vehicles And Space Vehicles Spin Dynamics Liapunov Functions Flexible Bodies Dynamic Stability Booms Equipment Rotating Bodies Elastic Damping Mathematical Models Equations of Motion Spacecraft Motion Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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