9.41 kilogram of structural mass. Non-flight structures, such as the TLA, the living quarters on the lunar surface and at L-5, and the construction shacks at L-5, are costed at an order of magnitude less, or $2400 per kilogram for R&D. The sole exception to this is the transport linear accelerator, which has a 100% risk surcharge applied due to the high development technologies required, bringing its R&D cost to $4800 per kilogram. Procurement costs for all aerospace structures, flight vehicle or not, were costed at a single rate of $1000 per kilogram, as explained earlier. This covers all the systems mentioned so far in this section, except for the procurement costs of additional orbiters necessary, since these production costs are computed on an 80% learning curve from the cost of the first shuttle orbiter. Construction machinery, such as rolling mills, welding heads, and refinery parts, differ little from their counterparts on the surface of the Earth, and therefore are priced at a typical cost for heavy machinery of $11 per kilogram (9.18). This cost was also used for the crane and frame assembly used in final colony assembly. Power systems were assumed to be in all cases off-the-shelf hardware; solar cells where possible, and a nuclear reactor for the lunar surface application, where the 14-day lunar night would leave the TLA and base without power if solar cells were the only energy source. The charge for procurement of these energy sources is here assumed to be the "break-even" cost widely used for new power pl~nt construction: $1000 per kilowatt. Probably the most difficult price to pin down was the research and development necessary for the space colony itself. As designed, the colony consists of a large number of pieces covering a wide range of technologies and tolerances. It was felt that a uniform pricing scheme,such as the $2400 per kilogram for non-flight aerospace hardware, was not an adequate approach. Therefore the colony R&D was priced on the basis of each type of component part, and the assumption was made that the parts within each type were simi.lar enough to allow a common design procedure.
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