Energy Aperture

Value chain · CLM-0702

In plain terms

Electric trips from a low orbit to a high one took four to seven months on real flights and in most models held here, and NASA's four-month figure is at the fast end of that. One European study expects at least 20 months for its modules, because the time depends on how much thrust each tonne gets.

The claim as recorded

All-electric LEO or GTO to GEO transfer durations in the flown and modelled cases listed below span roughly 4 to 7 months, and NASA OTPS's "about 4 months" sits inside that span rather than below it; one held SBSP study models a much longer transfer, 620 days as an ideal figure for 50 t modules on Falcon Heavy (SRC-206), so the span is not universal and depends on the thrust-to-mass ratio assumed. Measured: Boeing 702SP family "in the order of 6 months"; Eutelsat 172B about 4 months. Modelled: Lozinski et al. about 200 days; JPL 1980 at 2 x 10^6 kg gives 160 to 213 days depending on thruster.

Evidence behind this: T3 (SRC-190, SRC-012); T4/T5 (comsat mission reporting)

Scope and limits

The Eutelsat 172B figure comes from mission reporting, not from a primary technical post-flight paper, and none is held. Spacecraft masses differ by three orders of magnitude across these cases, so the span is not a like-for-like comparison - see CLM-0701 on why specific power, not mass, is the controlling variable.

What it assumes

that "transfer duration" means the powered orbit-raising phase in each case.

Where it comes from

SRC-190 The Applicability of MPD Thrusters to Satellite Power Systems, 1980
SRC-012 Space Based Solar Power., 2024
SRC-206 TN 03 System breakdown, costs and technical feasibility of a SPS. Issue 01, 14.07.2022, 59 pp,...
Figure 2, image-read: 205, 213 and 160 days for three thruster options at 2 x 10^6 kg. SRC-012 PDF p.91: "about 4 months". eoPortal, Boeing 702SP: "in the order of 6 months". Eutelsat 172B: about 4 months, all-electric, reported in the corroboration pass. SRC-206 PDF p.22: "the ideal transfer time to GEO will be 620 days. In reality it will take longer"; PDF p.20: EP "elongates the transport time to target orbit from LEO to GEO to years (depending on the thrust-to-mass-ratio installed)".
Related records
Answers question
QST-040 not published in this release
Contradicts
CLM-0674 not published in this release
Supersedes
CLM-0674 not published in this release

Cite this

energyaperture.com/c/clm-0702

CLM-0702, Energy Aperture, as of 2026-09.

Connected records

Other published records linked to this one. A list, not a judgement.

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More on the source page.
Also from SRC-190
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Also from SRC-206
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