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

[+] Author and Article Information
R. D. Quinn

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

T. W. Kerslake

NASA Lewis Research Center, Cleveland, OH 44135

J. Sol. Energy Eng 115(4), 189-194 (Nov 01, 1993) (6 pages) doi:10.1115/1.2930048 History: Received July 01, 1991; Revised March 01, 1993; Online June 06, 2008


The dynamic equations for the simulation of Space Station Freedom configured with solar dynamic (SD) power modules are developed. The formulation permits the structure to be subjected to shuttle docking disturbances while being controlled with a “natural” vibration and tracking control approach. Multiple control cases can be performed 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 equations are formulated to conservatively predict temperatures of the multilayered receiver aperture plate assembly and thermal stresses in its shield layer. Numerical results from these analyses are presented in a companion paper (Part II).

Copyright © 1993 by The American Society of Mechanical Engineers
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