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Optimal control of spin-stabilized spacecraft with telescoping appendagesThe control of a spin-stabilized spacecraft consisting of a rigid central hub and one or two movable offset telescoping booms (with end masses) is considered. The equations of rotational motion are linearized about either of two desired final states. A control law for the boom end mass position is sought such that a quadratic cost functional involving the weighted components of angular velocity plus the control is minimized when the final time is unspecified and involves the solution of the matrix Riccati algebraic equation. For three axis control more than one offset boom (orthogonal to each other) is required. For two-axis control with a single boom offset from a symmetrical hub, an analytic solution is obtained; when this system is used for nutation decay the time constant is one order of magnitude smaller than previously achieved using nonoptimal control logic. For the general case results are obtained numerically.
Document ID
19770044772
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Bainum, P. M.
(Howard Univ. Washington, DC, United States)
Sellappan, R.
(Howard University Washington, D.C., United States)
Date Acquired
August 8, 2013
Publication Date
December 1, 1976
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
77A27624
Funding Number(s)
CONTRACT_GRANT: NSG-1181
Distribution Limits
Public
Copyright
Other

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