High-performance propellant combinations for a rocket engine

摘要

A solid high-performance propellant for a rocket engine is described. The propellant is constituted by a combination of polyglycidylazide (GAP) ([C₃H₅N₃O]_n) or poly-3,3-­bis(azidomethyl)oxetane (BAMO) ([C₄H₆N₆O]_n) with boron, aluminium, or aluminium hydride (AlH₃) and a compound selected from the group consisting of hydrazinium nitroformate (N₂H₅C(NO₂)₃), nitronium perchlorate (NO₂ClO₄), or ammonium perchlorate (NH₄ClO₄), together with other conventional additives.