# Was the Space Shuttle the most efficient orbital launcher, based on the launch/LEO mass ratio?

It seems that the mass of the Space Shuttle at launch was around 2,000 tons, and it could deliver a total payload of around 122 tons to LEO. This would give it a launch/LEO mass ratio of around 16.4. Is this the lowest ratio among all orbital launchers in history?

• According to Wikipedia the LEO payload capacity was "just" 27.5 tons. Where did you get your number from? That's almost as high as Saturn V. Jul 20, 2017 at 10:46
• @DarkDust I think the OP is using the combined mass to orbit, so the shuttle plus the payload plus the external tank (which practically makes orbit). Since an empty shuttle has a mass around 68t, and the empty ET about 26t, the total mass to orbit including payload is around 122t as a rough calculation. Jul 20, 2017 at 11:38
• You can make a case that the orbiter is useful payload; you cannot make that case for the ET. In addition, the ET doesn't reach a stable orbit, and some payload compromise would be needed to make it so. Jul 20, 2017 at 14:26
• I got the 122 tons number from the STS-93 wiki page, and assumed it didn't include the external tank. en.wikipedia.org/wiki/STS-93 Jul 20, 2017 at 19:50

The shuttle was certainly one of the more mass-efficient orbital launchers, but it's a more complicated question than it might seem at first.

The shuttle orbiter is ambiguously part of the launcher and part of the payload, so it's simply not possible to compare it apples-to-apples against other launchers.

For "pure" payload that's going to stay in orbit after the flight, the ratio is very poor, as it delivers about 25-27.5 tons. This considers the orbiter and crew to be dead weight.

If the crew are going to be doing useful science then it's reasonable to consider the 68-ton orbiter as payload, bringing the delivered payload to 93-95.5 tons.

The ET isn't useful and doesn't reach stable orbit, so it's not reasonable to count it as delivered payload. Building space stations or fuel depots out of ETs has been proposed, but these plans were never developed.

This gives us a practical payload ratio of about 21.2:1. This is just about on par with Saturn V's demonstrated 21.7:1 (Apollo 11; later flights may have performed slightly better).

Falcon 9 Full Thrust has a ratio of about 26; Atlas V 401 has a ratio of about 32.

I will also take this opportunity to note that defining efficiency by the ratio of liftoff mass to LEO mass is only of academic interest; liftoff cost to LEO mass is a much more significant figure of merit.