DubaiAmateurRocketry - 25-7-2013 at 11:29
Lithium, Ammonium (EUTECTIC) Perchlorate Composite propellant –
This test include dissolved perchlorates in a solvent that can dissolve up to over 10 times the perchlorate its own that, that contain active
functioning groups to cure with diisocyanate groups. And that it remains dissolved even when cured.
The eutectic propellant has many advantages over traditional composite propellants NASA uses. It is denser, more efficient, burns at higher
temperature, more safe, slower burn rate, higher specific impulse, easier to construct, and so on. Lithium perchlorate also donate over 200% the
amount of oxygen Ammonium perchlorate donates.
As you can see in this photo, the combustion extremely complete and clean even with 15% Aluminum.
See more on
https://www.facebook.com/photo.php?fbid=593044000740658
[Edited on 25-7-2013 by DubaiAmateurRocketry]
DubaiAmateurRocketry - 25-7-2013 at 11:32
Sorry for the size of the engine though, we couldnt really afford a lot of Lithium perchlorate anhydrous...
franklyn - 25-7-2013 at 13:31
Little regarding composition of this propellant is conveyed in the given
description.
It's understood as a molecular blending of Lithium Perchlorate dissolved in an
unspecified solvent in which Perchlorate has extreme solubility under unspecified
conditions of temperature pressure etc. Would this be ethylene diamine ? The
resulting dry resin is then lit and burns without risk of detonating. The concept is
quite old , the cost of lithium makes this prohibitive.
www.google.com.br/patents/download/3094444_SOLID_COMPOSITE_P...
.
Bert - 25-7-2013 at 14:09
Not having the time to read all the links, can someone cut to the chase: Isp, density range possible for the system and cost/volume or weight.
(Edit: Around 250 seconds ISP... Decent density and mechanical properties. Kind of expensive, though)
[Edited on 14-2-2016 by Bert]