Weatherlawyer <
weathe...@gmail.com> wrote in news:2ed89826-1170-4a9b-
b189-f62...@9g2000vbq.googlegroups.com:
> I believe he is attempting irony.
Irony, yes. Attempting, no.
> At take-off the air pressure diminishes immediately. Of course air
> pressure becomes a problem as soon as 60 mph. Battleships manage half
> that through a much stickier medium.
Maximum aerodynamic pressure (Max Q) on the Space Shuttle is about
60 seconds after liftoff. Before reaching this point, the SSME's
(Space Shuttle Main Engines) are throttled down to 72% to reduce
the pressures on the orbiter and prevent it from 'overspeeding', in
the aerodynamic sense. At about 72 seconds, the engines are then
brought back to their full cruise power of 104%. This moment is
marked in the communications you hear during launch as the call "Go
at throttle up" indicating that all systems are nominal at this point.
So no, the air pressure does not diminish immediately. Well, yes,
the static air pressure, but due to the acceleration of the craft
the dynamic pressures rise until max Q at which point they then
begin to diminish. This occurs with all rockets.
> (The Apollos used up a considerable quantity of fuel as coolant.)
No fuel is "used up". It circulates through and around the engine
to act as coolant before being used by the engine.
In the SSME's, the temperature in the combustion chamber is about
6,000蚌 (about 3,300蚓). This is higher than the boiling point of
both iron and titanium, and just shy of the melting point of
tungsten, the element with the highest melting temperature.
In the Apollo F-1 engines, kerosene was used as the fuel which
burns a couple hundred degrees cooler than the liquid hydrogen
of the SSME's. In both cases liquid oxygen is the oxidizer.
No material can withstand both the pressures and temperatures that
are required for this task, so obviously some form of cooling is
necessary.
In the case of the F-1, the 'relatively' cool exhaust from the
gas generator which powered the turbopumps was injected into the
exhaust nozzle to create a 'cool' layer between the walls of the
nozzle and the hotter main exhaust gasses. The gas generators
use some of the fuel to power the turbopumps which supply the
engine with it's fuel and oxidizer. The exhaust is then used
for the cooling process as a beneficial by-product. Hardly wasted.
In the case of the SSME's, which are much more complex than the
F-1, the cooling is done solely by circulating the hydrogen in
and around the parts. Any exhaust from the 'pre-burners' which
drive the turbopumps is used in the main combustion chamber as
part of the combustion process.
http://en.wikipedia.org/wiki/SSME
http://en.wikipedia.org/wiki/F-1_%28rocket_engine%29
Oh, here's a cool video of a new engine being tested. Icicles
form on the nozzle!
http://www.youtube.com/watch?v=4eM1mNNdguA
> Titanium is produced in a very elaborate chemistry laboratory -as
> opposed to iron which is produced in smelters
Granted, producing titanium from it's ore involves more effort
in it's production than iron/steel, known as the Kroll process.
http://en.wikipedia.org/wiki/Kroll_process
However, it's still a large scale industrial process, hardly invocative
of the typical image of a 'laboratory'.
Here's an excellent video all about it:
http://www.youtube.com/watch?v=XsdRo5jvnXo
Reduction of iron ore is also a large scale industrial process
that involves complex chemistry. It's just much easier to do
since you don't need to use expensive magnesium, don't need to
do the process under vacuum, and doesn't use dangerous chlorine.
BTW, there is a recently developed process which promises to
make titanium production cheap.
http://en.wikipedia.org/wiki/FFC_Cambridge_process
> requiring no more than fire-brick replacement every few weeks.
More like years. Think about it. Are you really going to shut
down that expensive blast furnace every few weeks for maintenance?
Instead, you design the thing to keep running as long as possible.
Time = money. (except for you liberal commucrats)
> All a spaceship has to do is reach escape velocity.
If you want to leave the Earth altogether, yes. If you want to
simply orbit, you can go quite a bit slower. Orbital velocity is
less than escape velocity.
> Its rate of acceleration is immaterial.
Well, not really. Other factors are involved which dictate the
rate of acceleration. It's pretty complex.
In fact, it _really_ is rocket science!
> Stream lining need not be. In fact the larger the
> fuselage, the exponentially larger the payload.
In space, aerodynamics usually don't matter. But not always. Even
in the typical low Earth orbit, there is still some air. That's why
the ISS needs periodic boosts of it's orbit. Atmospheric drag.
But getting payloads up from the ground you still have to travel
through the atmosphere to get there. Aerodynamics still plays a
roll. It's still very important. If it wasn't, then why are all
launch vehicles aerodynamic?
Think about it, the more aerodynamic the vehicle is at launch,
even though it's only important for a few minutes, the less
fuel needed to launch a given payload.
Surely you're not telling us that you are smarter than all them
thar rocket scientists?