SPS Feasability Study SD76SA0239-2

Figure 3.6-5. Assembly Schedule - Nth Satellite The first method appeared to be the more conservative approach. Also, the structure fabricating facility can be used to provide the reactive forces required to move the blanket facilities and uniformly disperse residual forces into the SPS structure. After the facility's transfer is complete the structural fabrication and blanket installation proceeds along the second wing of the SPS. Microwave antenna installations, interrupted by the facility transfer operations, are also continued. The remaining microwave assembly procedures follow. 3.7 INSTALLATION OF ELECTRONIC ELEMENTS AND PHASED-ARRAY ANTENNA The microwave antenna assembly utilizes subcomponent modules integrated and tested on earth and transported to geosynchronous orbit for final assembly. The process is based on manufacture of 10-meter by 30-meter panels complete with amplitrons and waveguide elements and assembled on earth. In geosynchronous orbit these subassemblies would be assembled into the required 30- meter by 30-meter subarray sections. An in-line assembly facility (Figure 3.7-1) is required to maintain on- orbit schedules. This facility has orbit maneuvering capability. When the blanket layer completes the first bay of the second wing, this facility is located over the first frame of the second SPS wing to complete the antenna assembly. The second antenna assembly procedure is fully described below.