The delta-V number itself doesn't tell the whole story though. Rocket is much more effective in vacuum than in atmosphere. That 9.4km/s delta V cost a whole lot more to achieve than that 8.67km/s in vacuum. You're right about NASA built their biggest rocket ever to go to the moon, here I assume you you mean the Saturn V rocket. To put it in perespective:pjknibbs wrote: ↑Tue, 11. Dec 18, 06:10Peanuts? The delta-V required to achieve LEO (at around the level of the ISS) is 9.4km/s. To get from there to the Moon's surface requires 5.93km/s, and to then get from the Moon's surface back to LEO is another 2.74km/s*, for a total of 8.67km/s--near enough exactly the same as it took to get into space in the first place. There's a reason NASA had to build the biggest rocket ever made in order to deliver a comparatively tiny payload to the Moon and get it back again!Mightysword wrote: ↑Tue, 11. Dec 18, 02:39Which mainly come down to one bottleneck: getting from earth to space. Because going from space to the moon, moon to space and back to earth cost peanuts in comparison.
- The first two stages are used sorely for the purpose of escaping Earth Gravity.
- About a third of the third stage is used to put the craft in a low orbit with the remaining fuel use for the moon orbit transfer. And this is a bit of a cheating because it's not a stable orbit, hang around here long enough and it''ll be dragged back to earth. To get to a stable LEO like the ISS probably gonna use at least half of the third stage.
- And those 3 stages took up most of the space and weight of the rocket. If we say that complete half of the journey, then you can see the other half is completed by just the small sections on the top of the rocket with the command module and the lunar module that handling orbiting the moon, land, go back from the surface, and tail back to Earth.
The fuel break down is like this:
First stage: 21212800L.
Second stage: 1331000L.
Third stage: 344550L.
CMS+LM: 18600L.
Factoring the fact it cost a lot more to build the engines for the first 3 stages (due to structure integrity demand, and the need of much bigger size) comparing to the much smaller size rockets that's used exclusive in space on the CMS and you get the idea why I said it's peanuts. Even when you're not talking about fuel, that's why SpaceX is already saving pretty penny by simply able to reuse the in-atmosphere rockets of the launch vehicle, after all 75% of the cost of their rocket lies in the first stage alone.