Structure is characterized as being thin wall, low deployed density, high surface-to-mass ratio, metallic or possibly composite elements assembled into open space frame structural elements which in turn are assembled into yet larger space frames forming very large (approx. 1 km) antenna and even larger solar arrays. After materials technology development & selection, the new problems associated with low thermal inertia large dimension structures traversing the sunlight/shadow terminator at orbital velocities must be resolved. The resulting basic design^recognizing high launch packaging density limitations^ must be fabricated on orbit to achieve the final low density deployed configuration. How this should be done is not known and development risk rating should be considered as a firm 4. The specific technology for manufacturing modules is not known at this time, but should be relatively straightforward to develop once the basic design & materials have been established for the items to be manufactured in space. The major items are structural elements (open space frame structures) and slotted waveguides for the subarrays. Materials technology must be understood first and then engineering effort for relatively automated manufacture must begin. Several iterations are probably required so the development must be paced to assure a reliable economic process. Development risk rating should be a firm 4. The specific technology for remote manipulation modules is not known at this time. However, some investigations have been conducted in associated control systems. The development of these ' particular remote manipulators should begin after the hardware to be maneuvered and joined has been defined. The control links will probably be through TDRS so capabilities and limitations may begin earlier. Development risk rating should be a firm 4.
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