Value chain · CLM-0973
In plain terms
Apply that same measured pace to the whole satellite rather than just its framework, and the 1978 design would have needed several thousand people, not a few hundred, to finish in six months. The design assumed something made people two to fourteen times more productive and never said what.
The claim as recorded
Applying the same 6 to 12 kg per man-hour rate to the whole 1978 Reference System satellite - 34.2 to 51.0 million kg including contingency - requires 1,561 to 7,764 crew for a six-month build, against the published 555 to 715. The published figure therefore implies a productivity multiplier of about 2x to 14x over Skylab-calibrated manual rates, equivalent to 54 to 93 per cent of assembly labour being automated, and DOE/ER-0023 states neither the multiplier nor its basis. At the published crew and manual rates one satellite takes 13 to 84 months.
Evidence behind this: T0-derivation; the multiplier is an inference from two sources three years apart, stated in neither.
Scope and limits
THE MULTIPLIER IS AN INFERENCE FROM TWO SOURCES THREE YEARS APART, NOT A STATEMENT IN EITHER. The 1975 study intended a fabrication "factory" (p.175); that automates structure, which CLM-0972 shows was within manual reach, and says nothing about the mass that dominates. The published crew includes non-assembling LEO staff; the p.14 versus Figure 37 discrepancy (CLM-0963) moves the silicon multiplier between 3.3x and 14x. The rate itself is terrestrial steelwork calibrated to one Skylab pole. Two per year with six months each is not tested here.
What it assumes
Hours per crew-day 6 to 10, ASSUMED. That blanket, klystron and subarray installation proceeds at the structural mass rate, which is an order-of-magnitude device and not a claim about those operations.
Where it comes from
This is the project's own working, shown in full:
Table 1 printed p.48: "SUB TOTAL 27.327 40.787 CONTINGENCY (25%) 6.832 10.197 TOTAL 34.159 50.984", millions of kg, GaAlAs then silicon. SRC-085 printed pp.11 and 14: "construction time being six months. The initial estimates of construction crew size are 555 for the silicon option ... and 715 for the GaAlAs option". SRC-451 Vol III p.175: "a rate of assembly of 420 lb/hr for the MPTS structural elements. At this rate, eight manufacturing modules would be required to meet assembly time tables." Arithmetic in CALC-113 sections 4 and 5: 50.984e6 / 12 / (182.4 x 10) = 2,329; 50.984e6 / 6 / (182.4 x 6) = 7,764; 2,329 / 555 = 4.2; 7,764 / 555 = 14.0.
Basis: productivity multiplier over manual assembly; months at published crew
Related records
- Answers question
- QST-015 not published in this release
Cite this
energyaperture.com/c/clm-0973
CLM-0973, Energy Aperture, as of 2026-09-17.
Connected records
Other published records linked to this one. A list, not a judgement.
- Also from SRC-085
- CLM-0013The paper that modern UK studies rely on for the beam figure calls anything below 1 kilowatt per square metre safe, with 230 watts per...CLM-0020The original 1978 design set the beam at 230 watts per square metre in the middle of the receiving site, about one twenty-third of that at...CLM-0023In the 1978 reference design, two limits set the size of the transmitter and the receiving site: how much heat the transmitter can shed...CLM-0039The 1978 report set the figure to protect radio and navigation systems from a disturbed ionosphere, called the number theoretical and...CLM-0045The apparent conflict between 12 and 23 was not an error. The underlying study gave a range, and the figure adopted sits near the top of it.CLM-0101The 1978 contract required the researchers to report fixes if ionospheric disturbance pushed the pilot-beam phase error past 2 to 3...CLM-0137In four major space solar power studies from 1978 to 2007, none put a number on how much of the beam's energy would be lost if the beam...CLM-0138The original 1978 government design for beaming power down from space adds up all the expected energy losses to get 63% overall efficiency...More on the source page.
- Also from SRC-451
- CLM-0954The 1975 designers worked out how much their kilometre-wide antenna would bend, precisely so they could decide how good the beam-steering...CLM-0959The original 1975 calculation found the satellite's radio noise would be fine for ordinary and troposcatter radio links and a problem only...CLM-0960The 1975 study found the satellite's harmonics - the multiples of its transmit frequency - would trouble radio astronomy at the second and...CLM-0961Everything in the 1975 interference analysis is for one satellite. The study itself says that a hundred of them would raise the noise and...CLM-0965In 1973 an astronaut on Skylab put together two long poles from short sections in just over two hours, about six minutes per join. A 1975...CLM-0966In 1975 the antenna alone was expected to take one to two years to assemble in orbit with about fifty people, and robot arms were judged...CLM-0968The 1975 antenna study worked out how hot the middle of the transmitter gets depending on how efficient the tubes are and how tightly they...CLM-0969If the tubes are only 70 per cent efficient, the transmitter's own face is not big enough to get rid of the heat they make, even spread...More on the source page.