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The following is a closed discussion of a requested move. Please do not modify it. Subsequent comments should be made in a new section on the talk page. Editors desiring to contest the closing decision should consider a move review after discussing it on the closer's talk page. No further edits should be made to this discussion.
Oppose for now, will keep track of the discussion. The page indicates that the system was Space Shuttle specific, so using the present name seems a more accurate encyclopedic descriptor. Randy Kryn (talk) 03:42, 23 January 2020 (UTC)[reply]
The above discussion is preserved as an archive of a requested move. Please do not modify it. Subsequent comments should be made in a new section on this talk page or in a move review. No further edits should be made to this section.
Data mismatch dv/isp/mass
The figures, despite from seemingly reliable sources, don't add up.
Isp of 316 s
ve of 3100 m/s
ve = Isp*g0
dv
300 m/s
Orbiter dry mass
78,000 kg
Orbiter wet mass, or gross take-off weight
100-110,000 kg
depending on source
OMS fuel capacity
21,660 kg
Payload
29,500 kg
This means:
wet mass
129,000 kg
dry mass + payload + fuel
dry mass
59,000 kg
wet mass - payload - fuel
dv
565-750 m/s
dv = Isp * g0 * ln(m0/(m0-fuel)), for m0=129 and 100 tons, respectively
I feel this article should answer the question of why there was even a need to fit a separate OMS instead of using the main engines to perform its functions.--Cancun (talk) 11:50, 9 August 2020 (UTC)[reply]