On Fri, 25 Aug 2017 20:21:07 -0400, MFUwjB?? ?????? ? ??????? ??CDrOqN
wrote:

wrote on 8/25/2017 8:11 PM:
On Fri, 25 Aug 2017 16:02:18 -0700 (PDT), "
wrote:

On Friday, August 25, 2017 at 5:49:32 PM UTC-4, jebAuD?? ?????? ? ??????? ?t

Of course there is 'vectored thrust', but rockets are 'single-use'. It
is easier and simpler to use a computer program to control the power of
the three individual nozzles to get the rocket to point to the direction
you want it to go. Controlling the power is as easy as controlling the
rate of flow of air-fuel mixture through a valve.

https://en.wikipedia.org/wiki/Space_Shuttle_main_engine#/media/File:SSME1.jpg

Wrong again. It is a bunch more complicated to have three nozzles on each stage than to have one nozzle per stage. Can you tell me of a current production rocket that uses three or more nozzles per stage?

Dan
Dan,
It is obvious that the person who keeps posting about how easy it is
to make rocket engines is full of it. This person obviously doesn't
know what they are talking about and is just trying to get someone's
goat. C'mon, whoever it is won't post their real name and changes
their nym with every post in an attempt to avoid filters. Why bother
responding? I'm sick of all the crap posted by babies. Let them eat
**** while we just ignore them and get back to metalworking. I'm
serious Dan, don't bother responding to any of their crap. Let them
dig in their diapers for tasty morsels, RCM is not for **** eating
babies and they shouldn't be encouraged.
Eric


Maybe you can watch the two embedded YouTube videos on this page to
confirm how many nozzles they actually have (hint: 4).
https://www.rt.com/news/340588-hypersonic-warhead-sarmat-tested/


Well, a couple of things. You have been talking about rocket fuel
being essentially oxygen and hydrogen.... but the missile you are now
referring to uses asymmetrical dimethylhidrazine and nitrogen
tetraoxide.

Another minor detail, you have been repeatedly referring to a missile
having 3 exhaust nozzles but the one you use in your current argument
has four... in the first stage. while the second stage has a
closed-cycle single chambered sustainer and a four chambered open
cycle control motor with four rotating nozzles.

No mention at all about oxygen, hydrogen or three nozzles.

Another thing, the guidance system is referred to as: "The missile
employed an inertial guidance system that was is estimated by some
Western sources to have an operational CEP of 0.3 nm in 1975 with a
potential CEP of 0.25 nm by 1980."

Or, to put it another way, you simply don't know what you are talking
about.

Wait up a second. I now realize that while you were talking about
"three" in your earlier missives you have how shown us a 4 nozzle
missile.... obviously you are short of fingers.

Was this some sort of accident? Or a birth defect?
--
Cheers,

Schweik