First, a clarification: I understand the aerodynamic reasons that interstages are used, and I understand that the shockwaves that would be generated without an interstage would wreck the rocket. My question is if there are any non-aerodynamic reasons an interstage is required.

My contradictory thoughts:

  1. The engine bell(s) already support the entire compressional stress generated by the weight of the stages above it when the engine is firing, and does so in a controlled manner--the gimbals don't fail to keep the firing stage pointing in the right direction.

  2. However, the burnout Gs of the upper stage might be fewer than that of the lower stage, so the nozzle will not support as much weight as the interstage has to.

  3. Also, the aero forces might cause the compressional stress upon the interstage to exceed that which the nozzle can support in low atmosphere.

  4. However, max-Q is usually well before burnout, so total stress even with drag considered is likely still less than it'd be at max-Gs.

  5. Replacing load-bearing interstages with much thinner ones that serve only as an aerodynamic surface would save a lot of mass.

  6. Or even allowing the nozzle bell to take part of the load seems like it'd allow you to save a lot of mass.

  7. But it clearly hasn't been done yet (I think, related question here), so there's some "nail-in-the-coffin" reason that interstages must be entirely load-bearing.

Finally to the question: Why aren't nozzles used to bear the stress of accelerating upper stages? Why are interstages used (required?)?

Am I misunderstanding the stresses involved? Do the stresses during engine burn differ substantially from those endured when being accelerated by the stages below? Or is it an orthogonal issue to the stresses of launch--maybe it's difficulty designing an effective nozzle which can be reliably decoupled from the stage below it?

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    $\begingroup$ If the nozzle structure is enhanced to bear the the stress of accelerating upper stages, the additional weight adds to the upper stage after separation. But the additonal weight for a load bearing interstage does not add to the upper stage after separation. $\endgroup$
    – Uwe
    Commented Jun 22, 2020 at 17:25
  • $\begingroup$ Great point, hadn't considered that. $\endgroup$ Commented Jun 22, 2020 at 17:29
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    $\begingroup$ The nozzle is very weak around the edges. Also you want your support structure to be around the outside so that you have better resistance to bending. $\endgroup$ Commented Jun 22, 2020 at 17:36
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    $\begingroup$ To counter the second example: an RCS jet is not firing through the center of mass, and even if it were, it's only accelerating the Orbiter at a tiny fraction of a G. That's not a lot of weight to support. $\endgroup$ Commented Jun 22, 2020 at 17:56
  • $\begingroup$ An aerodynamically clean interstage is common, but not necessary: spaceinfo.jaxa.jp/ja/m3s2.html $\endgroup$
    – John Doty
    Commented Jun 23, 2020 at 21:13

3 Answers 3


The answer is a bit more nuanced than Organic Marble presents it. It makes sense to make a force balance to see what bits of engine can take which amount of force.

First, let's look at the chamber. It has a static pressure $p_1$ which is balanced everywhere by the walls, except at the throat where there is a large gap. This results in a net force of magnitude $p_1A_{throat}$. I plugged in some values of the Raptor rocket engine, and found that this contribution is about half of the total thrust.

The other half is then created by the diverging nozzle/bell. Again by force balance, this means that just after the throat, there is indeed a 'compressive force' equal to around half the total thrust. So one could think that you can at least support half the rocket's weight on the engine bell. However, we find that the load case from firing the rocket and just 'standing' on the bell is different. In case of firing the rocket, this 'compressive force' is due to a distributed load of the nozzle pressure, whereas a 'standing' rocket has all the force concentrated at the nozzle edge. This means that in the first case, the end of the bell almost only sees hoop stress and no axial stress, whereas in the latter case, the bell is axially stressed throughout.

So, for those two reasons (the bell only carries half the thrust, and the loadcase is different), the nozzle would need beefing up, and worse, after staging you do not shed this extra structural mass.

A final problem is that the interstage has more functions than carrying the weight of the accelerating upper stage. In addition to strength, it also provides stiffness against the rocket 'bending' like a twig. Bending stiffness grows quadratically with diameter (for constant wall thickness), so it makes sense to make to create this stiffness on the outer perimeter rather than at the rocket's throat or gimbal mechanism.


There is a misunderstanding in your question

"The engine bell(s) already support the entire compressional stress generated by the weight of the stages above it when the engine is firing..."

No, the engine bells do not.

enter image description here

(Sutton, 7th edition, Chapter 2.2)

The bells mainly withstand the differential pressure forces from the gases flowing through them. Note that these forces are largely in the transverse direction, so that that "hoop strength" is the primary structural consideration for nozzles. (Of course a certain amount of longitudinal strength is required to keep the nozzles from falling off and to withstand the small components of longitudinal pressure force acting on them.)

The top of the combustion chamber is where the bulk of the force is transmitted to the vehicle, typically through a gimbal fixture.

enter image description here

(image source)

So, the interstage is needed to support the structural loads because the engine nozzles cannot. Nozzles that are beefy enough to handle the longitudinal loads would have severe heat transfer issues and complicate the design of the thrust vector control system.

  • $\begingroup$ Thank you! That makes a lot more sense. If you inserted a flared rod through the nozzle & into the chamber, where it would rest on the entire injector face (not great for the injectors), would it support the weight of the stages above it without issue? $\endgroup$ Commented Jun 22, 2020 at 17:58
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    $\begingroup$ I think that's pretty much what the SpaceX stage separation pusher thing does except it pushes on the throat. $\endgroup$ Commented Jun 22, 2020 at 18:03
  • $\begingroup$ Another follow-up would be: what if we seal the bell and pressurise it with helium... $\endgroup$ Commented Jun 24, 2020 at 19:05

It is important at stage separation to remove as much as possible weight from the upper stage. The interstage weight does not count after separation, but any enhancement of the upper stage engine nozzle does.

The interstage weight is small compared to the weight of the upper stages, but it is tiny compared to the weight of the lower stages.

Of course the lower end of the nozzle supports only a very small amount of the stages weight, as the other answers wrote.So a lot of additional weight would be added to the nozzle. The weight added to the nozzle would be dead weight just after separation.


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