Value chain · CLM-0687
In plain terms
The Chinese design says how it gets to orbit. Rockets carry the parts to a low orbit. A reusable space tug then moves each part up to the high orbit, where they are put together. The paper says that assembling it high up lowers the risk of hitting space debris, because there is much less debris there. The tug comes back down to be refuelled and to have its solar panels swapped. The design does not say whether the tug burns fuel or uses electric thrusters.
The claim as recorded
CAST's modular multi-rotary-joint SPS (MMR-SPS) states its transfer architecture directly: heavy-lift rockets launch the modules to low Earth orbit, then "the upper stage of the rocket or an interorbit transporter is employed to transport all the SPS modules to GEO, where assembly takes place". All assembly happens at GEO, which the paper says significantly reduces the risk of collision with space debris, because debris concentration is substantially lower there than in lower orbits. The interorbit transporter is designed for reuse "through propellant refueling and the solar array replacement in LEO". The propulsion TYPE of the transporter is not stated.
Scope and limits
The propulsion type is NOT stated, so this does not settle whether CAST assumes chemical or electric transfer. "Propellant refueling" is consistent with either. No delta-v figure is given. No transfer duration is given. Assembly robot counts are given only as "a minimum of several dozen".
What it assumes
that the arXiv version records the same architecture as the journal version.
Where it comes from
PDF p.10 (index 9), Section IV, verbatim: "MMR-SPS adopts the GEO assembly and transportation mode. The process involves utilizing heavy-lift rockets to launch the SPS modules into low Earth orbit (LEO). Then, the upper stage of the rocket or an interorbit transporter is employed to transport all the SPS modules to GEO, where assembly takes place". Also verbatim: "the interorbit transporter can achieve long-term reusability through propellant refueling and the solar array replacement in LEO". Figure 14 on the same page schematises the sequence Ground - LEO - GTO - GEO. Same page (printed p.116), verbatim: "Key features of this approach include conducting all assembly processes in GEO, which significantly reduces the risk of collisions with space debris. This is due to the substantially lower concentration of debris present in GEO compared with lower orbits".
Related records
- Answers question
- QST-040 not published in this release
Cite this
energyaperture.com/c/clm-0687
CLM-0687, Energy Aperture, as of 2025.
Connected records
Other published records linked to this one. A list, not a judgement.
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