Figure 14-12(a) is a conceptual drawing of the elements requiring assembly in Mission 8. The antenna (Mission 6) is interfaced to the rotary joint (Mission 7). The interface structure can be assembled using the rotary joint as an assembly base and mating the antenna to the interface structure’s five points via a docking maneuver. Figure 14- 12(b) is a schedule of Mission 8 flights which assemble the interface structure (Flight 1) and mates the antenna and rotary joint to the interface structure. Interface wiring and electronics integration is performed on Flight 3. Mission 9 - Central Mast Assembly and Integrated Test The objective of Mission 9 is to assemble the middle section (roughly 210 meters) of the orbital test facility satellite central mast and interface the mast to the rotary joint. After assembly, an integration test is performed to demonstrate system operation. Figure 14-13(a) is a conceptual drawing of the integration test proposed for Mission 9* After assembly and mating of the central mast to the rotary joint, an interface to the Shuttle power supply could be used to perform limited tests of the antenna by "lighting-up" individual amplitrons. To provide sufficient power, a solar array and additional heat rejection has been added to the Shuttle cargo manifest. Holding tanks for fuel-cell water are added in an effort to minimize contaminants. As summarized in Figure 14-13(b), the first flight in Mission 9 will assemble the 213m conducting central mast and mate it to the rotary joint. The test objectives can be accomplished by using the indicated options during assembly on different segments of the mast. The second flight is designed to test the integrated microwave subassembly at lower than operational power levels. Mission 10 - Solar Array Assembly The objective of Mission 10 is to demonstrate assembly of a large solar array and establish methods for achieving required assembly rates. The details of assembly include: construction of the support structure, installation of the solar blanket, with the required tension spring interface and the support structure to minimize the impact of large temperature variations expected in low earth orbit. The installation of the aluminized Kapton mirrors and power distribution systems
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