Re: The Cold Equations

SRB + H2O2/C3H40 Isp kicks microsatellite rocket ***, as well as
offering a real boost for any spaceplane:

In spite of what the likes of most any other Usenet infomercial spooks
(aka Art Deco, Bookman and countless others) have to say, which usually
is of absolutely no honest worth to the given topic, whereas here's
some interesting info of what the likes of perhaps yourself, Rusty,
Henry Spencer and so many other supposedly smart folks must already
have known about using 98%-H2O2 along with a little something else,
plus some of what's apparently been need-to-know and/or Usenet taboo
that's delivering a whole lot better Isp than plain old H2O2/RP-1.

RP-1 = C12H24 (H2O2/RP-1 is thereby not quite as good as for using H2O2
along with plain old Kerosene/hexadecane C12H26), and it seems that
each of those are seriously dragging rocket *** when it comes down to
using H2O2/C3H4O.

PROPARGYL ALCOHOL / Acrolein = C3H40
2-Propyn-1-ol as C3H4O / CH CCH2OH having the molecular mass: 56.1
http://www.emsdiasum.com/microscopy/technical/msds/10100.pdf
PRODUCT NAME: ? propargyl alcohol
CAS NO. 107-02-8
MOLECULAR FORMULA: C3H40
VAPOR DENSITY: 1.94
SPECIFIC GRAVITY: 0.839
http://www.atsdr.cdc.gov/MHMI/mmg124.html

http://www.dunnspace.com/alternate_ssto_propellants.htm
H2O2/propargyl alcohol yields roughly 40% more payload than H2O2/RP-1

H2O2/C3H40 is perhaps where my latest SWAG has shifted, as per
suggesting where the most serious rocket thrust or Isp/kg is to being
found (short of going first stage SRB or something thermal nuclear), as
well as per volume as being the best push comes to shove argument.
Short of what modern SRBs should still outperform as on behalf of the
first stage, it looks as though H2O2/C3H40 is a viable formulation of
keen interest, of a final do-everything solution that could make for a
two stage delivery to the moon as good as 25:1, meaning 25 tonnes worth
of rocket and payload liftoff mass (including the first stage SRB) per
tonne of the actual payload is about as good as it gets.

Taking the fullest advantage of the modern SRB for the initial thrust
to nearly if not a bit better than half LEO escape velocity, plus a
mostly composite upper stage that simply isn't going to represent all
that much inert/dry mass, especially since either H2O2 or C3H40 need be
pressurized nor sub-frozen like LH2/LO2. Therefore little if any
insulation demands, and of storage tanks of a composite basalt fiber
and microballoons which can't weigh 50% of what traditional tankage
involves.
-
Brad Guth

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