Combustion inhibitor for composite frontal-combustion propellants useful in rocket motors comprises room-temperature-crosslinkable polyurethane binder and gasifiable oxygenated filler

摘要

A combustion inhibitor (I) for composite frontal-combustion propellants is produced from an injectable composition comprising: (a) 100 parts by weight (pbw) of a room-temperature-crosslinkable polyurethane binder formed from an aliphatic polyol and a polyisocyanate in an isocyanate:hydroxy group (NCO:OH) ratio of 1.05-1.2:1; (b) 30-120 pbw of a gasifiable oxygenated filler with a melting point equal to or above that of the binder; and (c) 0-40 pbw of an aliphatic plasticizer. An Independent claim is also included for a composite propellant block coated with (I).