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A rocket engine is basically a device that generates a high pressure inside the chamber and the pressure difference creates a force.

A nozzle helps in effectively accelerating the flow and increases the thrust.

But where exactly would the thrust force act? Is it on the nozzle, or top of the combustion chamber, or all over the body, or by any other place?

Also, the answer might vary based on fuel type, as liquid engine and solid motors have a different construction.

Finally, how is the force transmitted to the entire rocket structure? A structure capable of withstanding such concentrated load has to be really strong and well designed. What materials are generally used for this and what is the generally adopted design?

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  • $\begingroup$ related (where does the thrust force act): space.stackexchange.com/questions/18904/… $\endgroup$
    – Hobbes
    Jan 23, 2018 at 6:57
  • $\begingroup$ The thrust is usually transferred through the thrust structure $\endgroup$
    – user20636
    Jan 23, 2018 at 7:05

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The thrust acts on the nozzle and combustion chamber walls by virtue of the pressure differential they contain. Using the RS-25 (SSME) as an example, with illustrations from this pdf, I can highlight a few of the components.

Page 11 (pdf page 17) shows the gimbal bearing assembly, a ball-and-socket joint assembly made from a titanium forging. That is where more or less all of the thrust load is transferred to the vehicles thrust structure.

Page 23 (pdf page 29) shows the Block IIA powerhead, which is the combustion chamber and turbopump assembly. At the top center of the combustion chamber, you can see a flower-shaped flange that is bolted to the gimbal bearing assembly and is where load is transferred from the combustion chamber/nozzle assembly. You can also see this on Page 26 (pdf page 32) and in closer detail on Page 42 (pdf page 48) -- note the term "Thrust Cone".

Pages 45 and 46 (pdf pages 51 and 52) show detail of the combustion chamber. Load from the nozzle is sent up mostly through the throat ring, except not really, because it's also being reacted by the actual exhaust gas present in the combustion chamber. In all likelihood, the throat ring is probably under tension when the engine is firing.

The nozzle detail is seen on Pages 49 and 51 (pdf pages 55 and 57), you can see the flange through which it attaches to the combustion chamber at the top of the illustration. The Hatbands react the hoop stresses generated by the pressure inside the nozzle and prevent it from just blowing apart, much like the iron bands on a whiskey barrel. The conical(ish) shape of the nozzle means that the net result of the pressure is directed upward.

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  • $\begingroup$ Any idea what fraction of the force that accelerates the rocket is actually transmitted via the nozzle, compared to that of the combustion and expansion chamber(s)? More than a few percent? $\endgroup$
    – uhoh
    Jan 24, 2018 at 17:35
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    $\begingroup$ I don't know offhand, but you could get a reasonable approximation by integrating the axial component of the pressure distribution over the nozzle area $\endgroup$
    – Tristan
    Jan 24, 2018 at 18:40
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The force from the rocket engine is transmitted to the rocket structure by the Thrust Frame Adapter. This is a framework rated to handle the newtons of force created by the engine.

The spacecraft's load-bearing skeleton is built on top of the thrust frame adapter, and the spacecraft components are attached to the skeleton. Thrust Frame Adapter

(image source)

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