Skip to main content
12 events
when toggle format what by license comment
Jul 10, 2015 at 2:55 history edited geoffc
edited tags
Feb 26, 2015 at 17:41 answer added xxyxyx timeline score: 5
Feb 25, 2015 at 19:02 comment added Deer Hunter This is one of the most important fundamental questions I've ever seen on this site.
Feb 25, 2015 at 11:42 history tweeted twitter.com/#!/StackSpaceExp/status/570549515243159553
Feb 25, 2015 at 7:37 comment added neelsg I would imagine that it might also be easier to make the first stage reusable if it reaches a lower maximum velocity
Feb 25, 2015 at 6:15 comment added Adam Wuerl The Saturn V is a poor comparison because it’s a 3-stage rocket and had a much higher ideal delta-V, since it’s mission was the moon, not LEO. Rocket design is exceedingly complex, and for an actual vehicle determining the ideal delta-V split depends on the specifics of almost all aspects of the design: propellant, staging, engines, aerodynamics, etc.
Feb 25, 2015 at 0:13 comment added Russell Borogove Falcon 9, using the same fuel (and almost the same engine) on both stages, would have different optimization considerations.
Feb 25, 2015 at 0:03 comment added Russell Borogove The Saturn V upper stages were hydrogen fueled; at first blush one would assume you wanted as much of the delta-v as possible delivered on hydrogen/LOX instead of kerosene/LOX because of its ISP advantage. However, hydrogen stages are vastly larger in volume than equivalent delta-v of kerosene/LOX, so one possible explanation could be that the S-II stage was as big as was practical for a hydrogen stage and the rest had to be done in kerosene.
Feb 24, 2015 at 23:50 history edited geoffc
edited tags
Feb 24, 2015 at 23:39 comment added Deer Hunter Obligatory (assuming no Wertz/Larson at hand): projectrho.com/public_html/rocket/multistage.php
Feb 24, 2015 at 22:20 review First posts
Feb 24, 2015 at 22:32
Feb 24, 2015 at 22:20 history asked xxyxyx CC BY-SA 3.0