I have recently been doing the math for SSTO using
H2O2 and other similar Isp combinations. To attain
the correct DeltaV you either need a very high Isp or
a very low mass ratio, am I correct?
Anyone here an advocate for using H2O2 on a SSTO
craft? I continue to calculate very high G
Hi,
Kirill Levin developed a good software for modelling
orbital rocket launches. It's in the form of Excel
spreadsheet, has many existing major rockets as
samples, and there is a nice documentation page.
http://www.geocities.com/levinkirill/SpaceModel/eng/
Alex
I gave an example
based on 300 or so Isp, which is a reasonable
approximation for
Peroxide/RP1. (warning - I did not do the actual
math, I am known to
make errors when just grabbing numbers off the top
of my head, but I'm
pretty sure I remembered it right.)
Dave
I was calculating
On Fri, 26 Sep 2003 06:23:57 -0700 (PDT), Thomas McNeill
[EMAIL PROTECTED] wrote:
I was calculating around 230 for an ISP. I have seen
300 and up to 320 on Astronautix.com but wasn't sure
how easy that was to attain with H2O2.
It isn't easy at all. It may be achievable.
Anyone know where to
There's a couple old DOS program called PROPEP and
CET that will tell
you all sorts of interesting things about propellant
combinations.
PROPEP has a GUI front end called GUIPEP. I got the
pair off the
ARocket sever.
I have that somewhere. I had once found a study from
a university on
On Fri, 26 Sep 2003, Thomas McNeill wrote:
...the correct DeltaV you either need a very high Isp or
a very [high] mass ratio, am I correct?
Correct... or some reasonable combination thereof. You need an excellent
mass ratio unless your Isp is most unreasonably high.
Anyone here an
On Fri, 26 Sep 2003 08:44:18 -0700 (PDT), Thomas McNeill
[EMAIL PROTECTED] wrote:
I have that somewhere. I had once found a study from
a university on a NOP (Nitrous Oxide/Propane) engine.
I was hoping to find out if more research had been
done on combinations of N2O with other fuels.
We use
