Since the asteroid is brought to a high earth orbit the same AV from geosynchronous orbit as L2, the same number of large mass driver reaction engines per solar power satellite is required as in the extended S S L plans. The large mass driver reaction engines used in the asteroid return are used to transport the solar power satellites, and since 13 large mass driver reaction engines per solar power satellite are required, the number of sets of 13 large mass driver reaction engines that are in use simultaneously is 205/13 = 15.8 = 15. Since the round trip takes 6 months, the time from beginning of solar power satellite transport to return of the large mass driver reaction engines after delivery of all 271 solar power satellites is (Here the rounding has been done to the lowest appropriate multiple of six months.) Since the travel time during return from geosynchronous orbit is one month, the last solar power satellite is delivered one month earlier. The first group of 15 solar power satellites leave the asteroid one month after it arrives in high earth orbit, simultaneously, to prevent collision between reaction mass exhaust and other solar power satellites. This group reaches geosynchronous orbit at month 54+ 51 + 1 + 5 = 111 = 9 yr., 3 mo., and the last group arrives at geosynchronous orbit at month 54 + 51 + 1 + 113 = 219 mo. = 18 yr., 3 mo. The only objects which require research are
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