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An analytical investigation of shape control of large space structures by applied temperaturesAn analytical procedure for the static shape control of flexible space structures subjected to thermal distortions is developed which is based on prescribing temperatures in control elements having much higher coefficients of thermal expansion than the main structure. The temperatures at the control elements are defined so as to minimize the overall thermal distortion of the structure from its ideal shape, and a matrix equation is obtained which can be solved for the set of optimum control temperatures. A formulation of the procedure for continuous structures governed by differential equations and a formulation for discrete (finite element modeled) structures governed by matrix equations are presented. The equations from the continuous formulation are employed for the shape control of a simple beam distorted by nonuniform heating, and the discrete formulation is applied in a general purpose finite-element structural analysis computer program for the shape control of a 750 m radiometer antenna reflector dish subjected to orbital heating. A reduction in thermal distortion by a factor of nearly 50 was obtained with the use of only seven control elements. Results for four different sets of control locations for the antenna are presented in which reductions in distortion of up to a factor of four were obtained.
Document ID
19830062673
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Haftka, R. T.
(Virginia Polytechnic Institute and State University Blacksburg, VA, United States)
Adelman, H. M.
(NASA Langley Research Center Loads and Aeroelasticity Div., Hampton, VA, United States)
Date Acquired
August 11, 2013
Publication Date
June 1, 1983
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
83A43891
Distribution Limits
Public
Copyright
Other

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