Value chain · CLM-0675
In plain terms
Some real satellites use a mixed approach: a normal rocket engine does most of the work of reaching high orbit, and small electric thrusters only fine-tune the final position. This is much faster than doing the whole trip electrically: 4 to 74 days on the eleven flights reported.
The claim as recorded
A distinct, real, pre-2015 hybrid transfer architecture exists: chemical propellant places a satellite into a 24-hour synchronous elliptical transfer orbit, and XIPS ion thrusters then circularise and position it in its final orbit; across 11 flown Boeing programmes, this hybrid approach took 4 to 74 days - much shorter than full-electric transfer, because only the final circularisation, not the whole LEO-to-GEO delta-v, is delivered electrically.
Evidence behind this: NTRS gives the venue as a 2007 symposium proceedings, STI type CONFERENCE_PAPER, so not peer-reviewed, and the paper states no uncertainty - both T1 conditions fail. Not T3 either: Boeing employees on Boeing's own product, with NTRS the cataloguing venue and not the author, per the Glaser T4 ruling. Supports ranges only: all eleven flights are anonymised Program 1 to Program 11.
Scope and limits
This is a different, and by design much less propellant-saving, transfer profile than full-electric (CLM-0674) or NASA OTPS's modelled all-electric case; it should not be conflated with either.
What it assumes
No assumptions are recorded against this claim.
Where it comes from
"Chemical propellant is used to place the satellite into a 24-hour synchronous elliptical transfer orbit, and XIPS maneuvers are used to circularize the orbit and position the satellite in its final orbit." Mission table across 11 flown programmes: ascent durations of 4 to 74 days.
Basis: days
Related records
- Answers question
- QST-002 not published in this release
Cite this
energyaperture.com/c/clm-0675
CLM-0675, Energy Aperture, as of 2008.