Value chain · CLM-1468
In plain terms
The basic idea, a solar power satellite climbing to its final orbit on electric engines run by solar panels it carries, with no separate fuel tanker, is real: it has flown on communications satellites, though not at the scale of a power station. A 2013 design does it with a separate, smaller set of panels. The stronger version, where the satellite's own main panels run the engines, has been proposed, for example by a 1977 US study, which found the panels used for the trip would be badly damaged on the way, and by a 2021 UK study for the last part of the climb only, after chemical stages carry the parts past the inner radiation belt. None of these designs has flown.
The claim as recorded
The hypothesis that an SBSP can power its own electric orbit-raising from the hardware it is delivering holds in a weak form (no propellant depot, no tanker fleet, power drawn from photovoltaic hardware the mission carries): all-electric transfer to GEO has flown at communications-satellite scale, electric transfer was modelled at SBSP mass scale in 1980, and Leitgab's 2013 SBSP-scale design powers each unit's transfer from a separate, smaller auxiliary array, giving no reason for that choice beyond following the author's earlier design. The strong form, in which the satellite's own power-generating array runs the thrusters, is proposed in held designs and flown by none, among them these two: Boeing's 1977 system definition study for NASA sizes a self-powered transfer from low Earth orbit to GEO for a satellite built in low Earth orbit, with thruster panels on each photovoltaic module powered by a deployed share of that module's solar cells, and reports the transfer blankets severely degraded on the way; and the 2021 Frazer-Nash study for the UK states, in an input-data annex, that the assembled satellite would raise itself to its final orbit on its own arrays from about 5,900 km, after chemical tugs carry the payload above the inner Van Allen belt.
Evidence behind this: T0-ANALYSIS, so no CALC is owed: this record DERIVES NO NUMBER. It is a hypothesis test result: the self-powered-orbit-raising hypothesis holds in a weak form, and the strong form is proposed in held designs, including the two named in src, and flown by none. Method, stated here so a reader can dispute it: the judgement is made over the claims and pages named in src, and rests on no quantity this record computes.
Scope and limits
This is this document's own synthesis across several individually tiered sources, not a single citable result; each component claim carries its own limits. No source tested the strong form and found that it fails. Boeing's 1977 sizing is a contractor study of a different, much larger satellite, built in low Earth orbit and moved in modules, and it powers the trip from a deployed share of the array rather than the whole finished array. The Frazer-Nash statement is a design intent with no transfer figures, and the same consultancy's later studies plan the trip differently (CLM-0714). None of these is a flown or measured result at SBSP scale.
What it assumes
No assumptions are recorded against this claim.
Where it comes from
CLM-0702 (all-electric transfers to GEO, flown at comsat scale in about 4 to 6 months, within a 4 to 7 month span of flown and modelled cases), CLM-0700 (electric transfer modelled at SBSP mass scale, JPL 1980), CLM-1459 (low confidence) and CLM-0682 (Leitgab's SBSP-scale design, its auxiliary array, the delta-v it states and the reasons the paper gives). CLM-0714 and SRC-019 PDF p.11 (the Frazer-Nash self-powered final raise from about 5,900 km, after chemical tugs). SRC-475 PDF p.15 (printed 9), in paraphrase: the self-powered option assumed construction in low Earth orbit. SRC-475 PDF p.117 (printed 112), section 3.2.4.5, power distribution and controls for self-powered LEO-GEO transportation, in paraphrase: a thruster panel on corners of each photovoltaic module, the input power each panel needs, and the share of the solar cells that must be deployed to provide it. CLM-1117 (for LEO assembly with self-powered transfer, the transfer blankets about 50 per cent degraded, depending on coverglass thickness and transfer time).
Related records
- Answers question
- QST-002 not published in this release
- Supersedes
- CLM-0685 not published in this release
Cite this
energyaperture.com/c/clm-1468
CLM-1468, Energy Aperture, as of 2026-10.
Connected records
Other published records linked to this one. A list, not a judgement.
- Also from SRC-019
- CLM-0172The study uses a high assumed rate of return (20%) to work out the headline cost-per-unit-of-electricity figure, but uses a much lower...CLM-0176The launch-cost range that drives most of this study's cost uncertainty is not based on any launch that has actually happened - for...CLM-0177The cost model assumes the satellite gets cheaper to build the more of them are made, using a range that runs from the faster cost-learning...CLM-0522The UK study used a 20% return requirement, based on what institutional investors are expected to want. The US study used 3%, on a one-line...CLM-0531Neither the UK nor the US figure for what it costs to get a kilogram of hardware into the power station's real orbit is based on an actual...CLM-0539A UK consultancy, working for the European Space Agency and using the same design as its reference point, actually published a full weight...CLM-0714The 2021 UK study by Frazer-Nash Consultancy proposed that the satellite fly itself to its final orbit, using its own solar panels to run...CLM-0715The 2021 UK study assumed one extra fuel launch for every payload launch; NASA's 2024 study assumed twelve. The reason, which neither study...More on the source page.
- Also from SRC-475
- CLM-1114The 1977 silicon design assumed an 18 per cent cell that did not yet exist, doubled the sunlight on it with cheap plastic mirrors, and got...CLM-1115Mirrors that doubled the light only added 40 per cent to the output, because the cells ran hot and the mirrors were not flat; after thirty...CLM-1116Thirty years of radiation behind a hair-thin glass cover was expected to take a third of the cell's power; a cover three times thicker...CLM-1117The 1977 study found the cheapest way to keep a silicon satellite at full power was to heal the radiation damage in place rather than build...CLM-1118In 1977 five radiation-damaged cells were healed with a laser or an electron gun, getting back between a fifth and a half of what they had...CLM-1120In 1977 the gallium arsenide option rested on a 20 per cent cell nobody had made, an assumption that it would still be near 20 per cent...CLM-1121Half a kilogram per square metre for the working blanket, about half of it the silicon itself; per kilowatt delivered on the ground the...