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The dynamics and control of large flexible space structures - 13The optimal control of three-dimensional large angle maneuvers and vibrations of a Shuttle-mast-reflector system is considered. The nonlinear equations of motion are formulated by using Lagrange's formula, with the mast modeled as a continuous beam subject to three-dimensional deformations. Pontryagin's Maximum Principle is applied to the slewing problem, to derive the necessary conditions for the optimal controls, which are bounded by given saturation levels. The resulting two point boundary value problem is then solved by using the quasilinearization algorithm and the method of particular solutions. The study of the large angle maneuvering of the Shuttle-beam-reflector spacecraft in the plane of a circular earth orbit is extended to consider the effects of the structural offset connection, the axial shortening, and the gravitational torque on the slewing motion. Finally the effect of additional design parameters (such as related to additional payload requirement) on the linear quadratic regulator based design of an orbiting control/structural system is examined.
Document ID
19900019275
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Bainum, Peter M. (Howard Univ. Washington, DC, United States)
Li, Feiyue (Howard Univ. Washington, DC, United States)
Xu, Jianke (Howard Univ. Washington, DC, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1990
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA-CR-186930
NAS 1.26:186930
Accession Number
90N28591
Funding Number(s)
CONTRACT_GRANT: NSG-1414
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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