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.

This content is only available via PDF.
You do not currently have access to this content.