Message from @Laucivol
Discord ID: 638099328564723712
When metal heats up it expands, so the bolt holes are not in the same place they used to be
Yet the nozzle must point true
typically that is why they have staged rockets; different nozzle configurations for different pressures
I am gayn't
Rocket engineering is not simple
aero-spike program attempted to design a varaible nozzle
aero-spike wasnt that great in the end tho
limited success
again
They actually did
is the efficiency for different pressure levels
just a nozzle configuration issue?
It was just too expensive because it needed fancy and expensive new materials
Hrmm.. debating on which game to play on the flight.. KSP is calling me again...
mainly; but the shape of the nozzle effects the fuel deliver method
if you go back into KSP, you'll get bored from having nothing to do... again
Exactly what I was sayin'..
Except I enjoy the rocketry of it..
And getting to the Mars-analog.
The benefit of this wedgy boi nozzle was that it had much easier time being cooled
PV = nRT
Classic
Also because of venturi effect it could be thrust-vectored without any moving parts
Musk said aerospike wasn't effective in the end
yup, that was another added benefit
It had issues, yes
It is more fuel-hungry compared to normal engine
```“So you have your combustion efficiency and what percentage of max theoretical combustion you are and then what your nozzle efficiency is, which is really are you straightening the flow, shooting the molecules out in a straight line, so you go into the other direction.
“With a traditional combustion chamber, you can get to very high combustion efficiency, cause the molecules are bouncing around have got time to combine and do their thing.
“Then when you sort of choke it through the throat, it gives them more opportunity to combine.”```
aerospike could get a craft to orbit but not cost effectively
apparently
aerospike has low combustion efficiency
well, it's a trade-off; efficency at what pressure?
@Coolitic it could have been solved with pre-combustion chambers, but the project was axed before they could try that
you can optimize seperate nozzles for different stages of ascent but a single nozzle will always be less efficient over the entire range
Unless it is a flexy nozzle like they make them on the planes