Highly soluble, non-hazardous hydroxylammonium salt solutions for use in hybrid rocket motors

Claim 1

A process for increasing the thrust of a rocket motor comprising a primary combustion chamber, a solid propellant grain within said primary chamber which generates combustion gas when ignited, a secondary combustion chamber aft of said primary chamber, and a passage connecting said primary and secondary chambers for conducting said combustion gas from said primary chamber to said secondary chamber, said process comprising the steps of: (a) providing a supply of an aqueous solution comprising from 50% to 90% by weight of a hydroxylammonium salt selected from the group consisting of hydroxylammonium nitrate and hydroxylammonium perchlorate; and (b) contacting said combustion gas with said solution substantially within one of said passage and said secondary chamber at selected times, thereby reacting said combustion gas and said solution in said secondary chamber to increase thrust during said selected times.