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Static Test of Hydrogen Peroxide Kerosene Motor
Robert Compton
http://www.ad6uy.com/sac-l5/motor-test.html
"Our present plan for the coming year is to develop an 8'' diameter 500 lb/sec throttleable regeneratively cooled motor. The performance of the H2O2/kerosene motors is not trivial producing the highest density impulse of any usable oxidizer/fuel combination. We hope this report will encourage further development among amateur rocket designers."
Hydrogen delta-V
SSTO delta-V and dense fuels
Henry Spencer
http://yarchive.net/space/rocket/fuels/hydrogen_deltav.html
"A steeper mass line means that at any time after liftoff, the H2O2/kerosene SSTO has lower mass than the LOX/LH2 one, and since they have the same thrust... the H2O2/kerosene SSTO is accelerating faster. If they have the same total delta-V requirement, that last assumption must be wrong: the H2O2/kerosene burn time is shorter.
"But... the biggest penalty on top of the theoretical delta-V is gravity losses, and gravity losses are a function of burn time! The H2O2/kerosene SSTO is accelerating faster, so it has lower gravity losses, and needs less total delta-V. Moreover, that makes its burn time still shorter, and its mass line still steeper, so the difference in acceleration is even larger than it first seems...
"The H2O2/kerosene SSTO is operating in a very steep part of the mass-ratio curve. A 6% saving in delta-V is *not* trivial. For engines with a vacuum Isp of 320, the required mass ratio drops from 20 to 16. Given the aforementioned sophisticated scaling models, at this mass ratio, the H2O2/kerosene SSTO's payload at the same GLOM is now equal to that of the LOX/LH2 design."
Black Brants are available for a modest cost. Very fine sounding rockets, and sometimes exciting.
