Solar Dynamic Modules for Space Station Freedom: The Relationship Between Fine-Pointing Control and Thermal Loading of the Aperture Plate: Part II—Results

[+] Author and Article Information
T. W. Kerslake

NASA Lewis Research Center, Cleveland, OH 44135

R. D. Quinn

Department of Mechanical and Aerospace Engineering, Case Western Reserve University, Cleveland, OH 44106

J. Sol. Energy Eng 115(4), 195-199 (Nov 01, 1993) (5 pages) doi:10.1115/1.2930049 History: Received July 01, 1991; Revised March 01, 1993; Online June 06, 2008


The analytical approaches developed in a companion paper (Part I) were used to quantify the relationship between fine-pointing control and thermal loading of the aperture plate. Dynamic simulations of Space Station Freedom configured with solar dynamic (SD) power modules were performed. The structure was subjected to shuttle docking disturbances, while being controlled with a “natural” vibration and tracking control approach. Three control cases were investigated for the purpose of investigating the relationship between actuator effort, SD pointing, and thermal loading on the receiver aperture plate. Transient one-dimensional heat transfer analyses were performed to conservatively predict temperatures of the multilayered receiver aperture plate assembly and thermal stresses in its shield layer. Results indicate that the proposed aperture plate is tolerant of concentrated flux impingement during short-lived structural disturbances. Pointing requirements may be loosened and the required control torques lessened from that previously specified. Downsizing and simplifying the joint drive system should result in a considerable savings in mass.

Copyright © 1993 by The American Society of Mechanical Engineers
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