24-08-2017 дата публикации
Номер: US20170240484A1
Solid-fuel rocket propellants comprising an oxidizer, an oxophilic metal-halophilic metal formulation, and a binder are described herein. Further described are processes for preparing such propellants and methods of reducing hydrogen chloride production via the combustion of such propellants. Non-limiting examples of such formulations include aluminum-lithium alloys. 1. A solid-rocket propellant comprising an aluminum-lithium alloy wherein the ratio of lithium to aluminum is between about 14% and about 34% by weight , an oxidizer , and a binder.2. The solid-rocket propellant of claim 2 , wherein the alloy is crystalline.3. The solid-rocket propellant of wherein the crystalline phase of the alloy is simple cubic.4. The solid-rocket propellant of claim 1 , wherein the amount aluminum-lithium alloy in the propellant is between about 5% and about 40% by weight claim 1 , the amount of oxidizer is between about 55% and about 79% by weight claim 1 , and the amount of binder is between about 5% and about 25% by weight.5. The solid-rocket propellant of claim 4 , wherein the amount aluminum-lithium alloy in the propellant is between about 20% and about 40% by weight claim 4 , the amount of oxidizer is between about 55% and about 65% by weight claim 4 , and the amount of binder is about 8% claim 4 , 9% claim 4 , 10% claim 4 , 11% claim 4 , 12% claim 4 , 13% claim 4 , 14% claim 4 , or 15%.6. The solid-rocket propellant of claim 1 , further comprising an additive.7. The solid-rocket propellant of claim 6 , wherein the additive is a high explosive claim 6 , a catalyst claim 6 , a burn-rate modifier claim 6 , or a combination thereof.8. The solid-rocket propellant of claim 1 , wherein the oxidizer is ammonium perchlorate claim 1 , and the binder is hydroxyl-terminated polybutadiene claim 1 , carboxyl terminated polybutadiene claim 1 , Polybutadiene acrylonitrile claim 1 , dicyclopentadiene claim 1 , Polyurethane claim 1 , Plasticized nitrocellulose claim 1 , Glycidyl Azide ...
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