There do not appear to be a definite number of stages to launch a craft. Amongst others entries under the 'launch', 'spacecraft-development' tags mention as many as 4 stages. Engines and fuel vary too.

Are payload and impulse the sole criteria to decide the launch engines, and each stage engine? What factors are relevant to this decision?


3 Answers 3


A rocket has different needs at different times.

At liftoff, there is a need for a level of thrust that exceeds the weight of the vehicle, or it ain't going anywhere. Solids are very good at high thrust, but usually have a kind of sucky $I_{sp}$ (specific impulse). For example, the SRBs from the shuttle produce 2.8 million lbs of thrust each which is an awe inspiring amount of thrust, but $I_{sp}$ is 269 seconds, really lousy. In contrast the F-1 engine (the largest liquid fueled single chamber (Yes RD-170 I am ignoring you!) ever flown) is only 1.5 million lbs thrust, but an $I_{sp}$ of 263? (What? I thought it was in the 300's.) Regardless the point is high thrust is key for a first stage.

Once out of the atmosphere, performance changes, so using a single rocket from ground level to orbit has its own penalties. (Thus the aerospike, where air pressure (and then lack thereof) acts as a nozzle extension for performance reasons).

Also, once you are out of the atmosphere and working towards orbit, you want the highest $I_{sp}$ at that point. Nozzle design is different for in atmosphere vs out of atmosphere. Usually want higher expansion ratio as the ambient pressure gets lower.

Additionally, denser propellants mean less tankage, which reduces size of the stage. Hydrogen (the fluffiest of them all) is the least dense of the common propellants and thus needs huge tanks in comparison to RP-1 which is pretty dense and can get by with smaller tanks.

  • $\begingroup$ Could you explain what ISP is? I have a bad one, but I bet that's not what you are talking about. $\endgroup$
    – Undo
    Aug 21, 2013 at 21:11
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    $\begingroup$ Another factor--the highest energy fuels are cryogenic. That's fine for blasting away from the Earth but keeping your fuel cold in space is another matter. An engine that's going to be used long after launch is going to use different fuel and thus have to be a different engine than the one that blasted it into space in the first place. $\endgroup$ Aug 21, 2013 at 22:20
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    $\begingroup$ And yet another factor--while you're blasting away from Earth you're losing energy to gravity and want to do it as fast as possible. Once you're in orbit or beyond that's no longer a factor, there's no need to carry a big engine. A pound of engine or a pound of payload, they cost the same amount of fuel to push. $\endgroup$ Aug 21, 2013 at 22:21
  • $\begingroup$ @LorenPechtel Cryogenic storage is a good point! Will edit it in. (LH is the hardest, but LOX is not terrible). Also, I did not want to address gravity losses, since they are fairly complicated in this example. $\endgroup$
    – geoffc
    Aug 21, 2013 at 22:50
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    $\begingroup$ @Undo ISP is Specific Impulse (I sub sp). This is measured, oddly in seconds. Thus the 268s of the SRB's is low. For a Kerosene/LOX engine, Merlin 1-D is one of the best at 310s I think. The SSME is one of the best LOX/LOH engines at 453s. It is a measure of efficiency, and the units of distance and mass all cancel out (thus the remaining unit of seconds). $\endgroup$
    – geoffc
    Aug 21, 2013 at 22:52

Aside from the delta V requirements, there are a number of other things that are used to decide how to make a rocket. A few of the key things:

  1. How flexible do you want the profile of the rocket to be? If you don't care, solid rockets are a great choice. If you do care, then maybe you need a liquid fuel.
  2. Where are you launching from? If you are forced to launch near other people, you will make choices based on the environment near where you are. For example, ICBMs and other large rockets launched from ships commonly have a small first stage using a "safe" rocket propellant to get it away from the ship.
  3. Availability of the fuel.

As far as which engine to use, essentially you want to make a good engine that will work with your desired fuel, and at your desired attitude, be easy to make and test, and meet your weight requirements. More than that is probably beyond the scope of this answer.


No, but ISP and thrust are two of the most important.

Also considered are environmental concerns, fuel handling requirements, drive mass, fuel mass, and price of drives, fuel, and supporting structure. A few types of drive, namely ORION and NTR, are not used despite fairly high thrust and ISP, for reasons of politics, namely, extant treaties.

The ESA won't use certain types of power system (fission and/or radiothermal generator) due to the environmental risks in case of launch failure; this also makes the needed drives for maneuver more restricted, since ion drives require rather high power that cannot be provided in the far reaches of the solar system.

  • $\begingroup$ Maturity of the technology would presumably also be a factor relative to cost of losing the payload (though that might fall under the asker's use of "payload" [my first reading of the question translated that as "size/mass"]). $\endgroup$
    – user56
    Aug 21, 2013 at 22:25

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