From: Robert Clark on
On Dec 20, 8:34 pm, BradGuth <bradg...(a)gmail.com> wrote:
> Why not stick with H2O2 and propargyl alcohol, or H2O2 and
> cyclopropane?
>
>  ~ BG

I had a debate with you a few months ago about which should be the
propellant to use for a single stage to orbit vehicle. I argued it
should be hydrogen/LOX because that gave the highest Isp and therefore
the lowest propellant mass. I also argued that both the DC-X
demonstrator and the proposed VentureStar vehicles used hydrogen fuel.
However, I now realize Isp is not the only key variable. There are
other variables that can overwhelm the Isp advantage of hydrogen/LOX.
Then propellant combinations with dense fuels and/or oxidizers,
including H2O2, may indeed be better suited for a SSTO vehicle.
Here's one report that discusses using H2O2 as the oxidizer for a
SSTO:

A Single Stage to Orbit Rocket with Non-Cryogenic Propellants.
Abstract
"Different propellant combinations for single-stage-to-orbit-rocket
applications were compared to oxygen/hydrogen, including nitrogen
tetroxide/hydrazine, oxygen/methane, oxygen/propane, oxygen/RP-1,
solid core nuclear/hydrogen, and hydrogen peroxide/JP-5. Results show
that hydrogen peroxide and JP-5, which have a specific impulse of 328
s in vacuum and a density of 1,330 kg/cu m. This high-density jet fuel
offers 1.79 times the payload specific energy of oxygen and hydrogen.
By catalytically decomposing the hydrogen peroxide to steam and oxygen
before injection into the thrust chamber, the JP-5 can be injected as
a liquid into a high-temperature gas flow. This would yield superior
combustion stability and permit easy throttling of the engine by
adjusting the amount of JP-5 in the mixture. It is concluded that
development of modern hydrogen peroxide/JP-5 engines, combined with
modern structural technology, could lead to a simple, robust, and
versatile single-stage-to-orbit capability."
http://www.erps.org/docs/SSTORwNCP.pdf [full text]


Bob Clark