High performance large launch vehicle solid propellants

A high energy, large launch vehicle, plasticizer-free, solid propellant comprising an isocyanate cured polyglycidyl nitrate binder and from about 60 to about 75% by weight high energy particulate solids comprising ammonium nitrate oxidizer and particulates and fuel particulates selected from aluminum and magnesium, wherein the polyglycidyl nitrate is an isocyanate curable polyglycidyl nitrate polymer having a functionality of nearly 2.0 or more and a hydroxyl equivalent weight of from about 1000 to about 1700 and has less than about 2 to 5% by weight cyclic oligomer present in the polyglycidyl nitrate and said solid propellant upon combustion producing less than about 1.25% weight condensables and less than about 7 mol % by weight HCl.

A high energy, large launch vehicle, solid propellant having a theoretical specific impulse, at a pressure ratio of 1,000 psi to 14.7 psi, of at least 250 lb-sec/lb and comprising about 15 to about 40% by weight of an isocyanate cured polyglycidyl nitrate binder and from about 60 to about 85% by weight of particulate solids and wherein the particulate solids comprise ammonium nitrate oxidizer particulates and fuel particulates selected from aluminum or magnesium and wherein the polyglycidyl nitrate is an isocyanate curable polyglycidyl nitrate polymer having a functionality of nearly 2.0 or more and a hydroxyl equivalent weight of from about 1000 to about 1700 and has less than about 2 to 5% by weight cyclic oligomer present in the polyglycidyl nitrate.