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Dynamic analysis of satellites with deployable hinged appendagesThe nonlinear equations of motion determining the planar dynamical behavior of an orbiting satellite deploying both one and two rigid appendages have been formulated using Lagrange's equations. The analysis accounts for large angle rotations, Coriolis effects, and the gravitational gradient, and the resulting coupled governing equations are integrated numerically. The analysis is applied to the Space Shuttle based deployment of rigid truss-like members, and results show that spacecraft inertia parameters, appendage mass and length, deployment velocity, and initial conditions all influence the system response. It is found that the resulting librational movement is related to the size of the deployment payload, and that gravitational forces lead to vehicle stabilization.
Document ID
19870035090
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Oakes, Kevin F.
(Flight Mechanics and Control, Inc. Hampton, VA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1987
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 87-0020
Accession Number
87A22364
Funding Number(s)
CONTRACT_GRANT: NGR-47-003-052
Distribution Limits
Public
Copyright
Other

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