SD power module components. These dimensions are 8.4 X 2.6 X 0.6 m3(27.6 X 8.7 X 2.1 ft3). The second constraint is associated with the growth option of the Space Station Freedom, in which additional pairs of SDPM, on opposite sides of the transverse boom and at both ends of the space station, would be added to meet the growing power demands. These additional SDPMs will be located adjacent to the original SDPMs on the opposite side of the same truss bay or in pairs, separated by a distance equivalent to 6 truss bay lengths (30 m, 98.4 ft). The second physical constraint requires the design of the SDR to support the SDPM requirement to avoid physical interference between adjacent modules in case of a beta gimbal malfunction. No problem of this nature was found for the modified baseline vertical configuration. For the ‘bow-tie' configuration, a limit in panel size was found which does not allow for eight full-size panels. In the case of the ‘butterfly' option, the ability to meet this constraint is a function of the angle theta determined by both radiative surfaces' normal vectors, as shown in Fig. 3. Table I summarizes the SDR sizing constraints for all three configurations. Two additional cases were studied for the ‘bow-tie' and ‘butterfly' configurations, the offset and no-offset cases which correspond to the location of the SDR relative to the interface structure base plate (see Fig. 1). In the no-offset configuration, the SDR deploys from the center of the SDPM interface structure base plate, whereas, in the offset configuration, the deployment occurs on one side of it. Panel area was maximized within the constraints of the space shuttle packing and on orbit SDPM interference. Results are shown in Table I. Thermal Performance For the growth configurations of the Space Station Freedom, two SDPMs will be located at each end of the station, on opposite sides of the transverse boom. For the ‘bow-tie' and ‘butterfly' options, this arrangement results in radiative surfaces of adjacent modules facing each other and thus restricting the view factor to the space environment. Consequently, thermal performance degrades and the radiative area must
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