Since the main engines can't be used after external tank separation, what's the reason for having the engines on the orbiter rather than just building a third rocket on the stack instead of the external tank?

It seems that not having to deal with attached main engines would make for a less complicated orbiter, while leaving some extra mass behind to make it easier to maneuver in orbit.

Did this design decision have to do with the optimal way of balancing the stack? Or, perhaps a cost issue to keep that external tank cheap so it didn't have to be refurbished? Or... some other reason?

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    $\begingroup$ different but related: 1, 2, 3 $\endgroup$
    – uhoh
    Feb 6, 2020 at 6:50
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    $\begingroup$ physics related - to not introduce unnecessary angles between propulsion system and steering system $\endgroup$
    – eagle275
    Feb 6, 2020 at 13:01
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    $\begingroup$ @eagle275 note that the Orbiter mounting resulted in a large built-in angle (~10-16 deg) space.stackexchange.com/a/23139/6944 so I think you have it backwards. $\endgroup$ Feb 6, 2020 at 14:21
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    $\begingroup$ I thought that's how it did the de-orbit burn, but the 90 m/s required is done by the, 300 m/s capable, OMS system. $\endgroup$
    – Mazura
    Feb 7, 2020 at 2:58
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    $\begingroup$ FWIW, despite all similarities, the Soviet Energia/Buran stack did expend the main engines with the rocket, the orbiter did not carry them. $\endgroup$ Feb 7, 2020 at 8:14

2 Answers 2


The quick answer--so they could get the engines back--has already been provided, but I'd like to offer some more historical context to that design decision.

Note that the shuttle as originally conceived didn't always drag useless engines into space. In fact, many of the original proposals were developed to be fully reusable, which meant there was no expendable ET, and the engines remained connected to their fuel tanks the whole time.

enter image description here

enter image description here

Some early shuttle proposals.

However, there's a fundamental problem here. The efficiency of hydrolox (this is when you burn HYDROgen with Liquid OXygen) on the orbital stage was virtually required if you wanted to have any meaningful payload (read: military satellites) on a reusable orbiter. However, the low density of hydrogen meant that the volume of tankage required would be very large. That by itself isn't a problem, except you've got to shield all that tankage during reentry.

The mass cost of the thermal protection system was quickly realized to balloon for a fully reusable shuttle. There were two ways around this: build a bigger booster, or not try to reuse your tankage. Pretty quickly, designers clued into the fact that this second route was the more affordable one...

For both companies, the point of departure lay in partially-reusable configurations that would carry their propellant in expendable tanks. This offered a route to lower development cost because the orbiter could shrink in size by carrying its propellant externally. The tanks could take form as simple aluminum shells, while the orbiter would have much less volume to enclose within its hot structures, and much less surface area to protect thermally. [...] Why was this approach so promising? Liquid hydrogen is bulky, having only one-fourteenth the density of water. Thus, although it makes up only about one-seventh of a shuttle's propellant load by weight, with six-sevenths being liquid oxygen, liquid hydrogen accounts for nearly three-fourths of the volume. Being low in density and hence light in weight, this fuel could be carried in external tanks of similar light weight. Being bulky, its removal would bring a welcome reduction in the vehicle size and surface area.

The developmental cost savings of this route were aggressively pushed by Northrup Grumman...

The use of external tankage cut the dry or unfueled weight of the complete two-stage shuttle by nearly one-third, from 1.02 million pounds to 692,000 pounds. In the words of the report, this weight saving "means structure we eliminate from design, do not provide tooling for, nor build, maintain, refurbish or otherwise pay for." [...] The peak funding level, \$1.85 billion, was a long way from the OMB requirement of \$1 billion. Nevertheless, it was \$350 million closer to this goal than the fully-reusable design. Moreover, in a brilliant example of having one's cake and eating it, Grumman proposed that the expendable tankage [341] would actually reduce the cost per flight. The tanks per se would cost \$740,000 per flight. Other savings, however, would more than offset this, with the largest of them stemming from a substantial cut in the amount of propellants for a flight, and from eliminating the need to refurbish the thermal protection of the now-simpler booster.

Eventually, people starting thinking about moving the LOX to external tankage also...

The next step was to lengthen this single external tank to allow it to carry liquid oxygen as well. This would reduce the size of the orbiter to a bare minimum. The tank, attached to the orbiter's belly, would demand structural strengthening, for its store of liquid oxygen would be quite heavy. With all propellant removed from the orbiter, that vehicle could achieve a standard design, independent of the tank. The tank could grow to a particularly large size, further lowering the staging velocity of the booster. In turn, this lower staging velocity would further reduce the size of the booster, cutting the cost of the Shuttle program anew.

After all this iteration, the shuttle we know was pretty much designed.

enter image description here

The new shuttle, sans boosters.

Source (and a very very good read): https://history.nasa.gov/SP-4221/contents.htm

All emphasis mine.

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    $\begingroup$ That's a great book indeed. $\endgroup$ Feb 6, 2020 at 14:04
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    $\begingroup$ Seems odd that internal-LOX and external-LH was ever considered, i.e. before "the next step" moved all propellant to external. Maybe still driven by the expectation that, aside from bulky LH, reusable tanks would be cheaper? $\endgroup$ Feb 6, 2020 at 21:16
  • $\begingroup$ I wonder if it would have had an effect on Challenger, if only LH was in the main tank and there was TPS between it and the O2. $\endgroup$ Feb 6, 2020 at 22:18
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    $\begingroup$ @Harper-ReinstateMonica It would have made no significant difference. Challenger was destroyed by aerodynamic forces, not by the hydrogen-oxygen fireball. As soon as the SRB mount failed and the booster tilted out of alignment, the orbiter's fate was sealed. $\endgroup$ Feb 7, 2020 at 0:47
  • $\begingroup$ On the other hand, empty fuel tanks are big and light, so they would be able to slow down more higher in the atmosphere than the dense orbiter (especially if the tanks had wings with which to generate lift), reducing the peak heating flux experienced during booster reentry and simplifying the design of its TPS. $\endgroup$
    – Vikki
    Feb 9, 2020 at 3:31

So that the reusable engines could be reused.

If they were mounted on the expendable external tank, they would have been thrown away each mission.

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    $\begingroup$ In one of life's great ironies, the SLS is literally an external tank with shuttle engines attached. And the engines are thrown away with the tank. $\endgroup$
    – Machavity
    Feb 6, 2020 at 14:16
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    $\begingroup$ @Machavity I know, it kills me that they are dumping those magnificent machines into the ocean. $\endgroup$ Feb 6, 2020 at 14:17
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    $\begingroup$ @Machavity To be fair, the reusability of the main shuttle engines sucked - the heavy strain on the high-tech technology meant they needed much refurbishing after each flight. Really, in general, the idea of the reusable shuttle didn't quite work out. We could probably do better today, but I wouldn't be too surprised if ditching the concept proved to be the more economical choice, at least right now, especially under the pressure from competing "cheap" launchers. $\endgroup$
    – Luaan
    Feb 7, 2020 at 9:30
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    $\begingroup$ @Luaan makes one wonder if SpaceX will actually manage to do better with their methalox engines. At least it's a vertical stack. $\endgroup$
    – ikrase
    Feb 8, 2020 at 3:06

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