Monopropellant system

Abstract

The invention is directed to a monopropellant composition for propulsion and/or gas generation, comprising a solution of hydrazinium nitroformate (HNF) and/or ammonium dinitramide (ADN) in water and/or an alkanol.

1 . Monopropellant composition for propulsion and/or gas generation, comprising a solution of hydrazinium nitroformate (HNF) and/or ammonium dinitramide (ADN) in water and/or an alkanol.  
     
     
         2 . Monopropellant composition according to  claim 1 , wherein the amount of HNF and/or ADN is from 25 to 95 wt. % of the composition.  
     
     
         3 . Monopropellant composition according to  claim 1  or  2 , comprising water and an amount of a solvent, preferably a lower (C1 to C4) alkanol.  
     
     
         4 . Monopropellant composition according to  claim 3 , wherein the alkanol is methanol and/or ethanol.  
     
     
         5 . Monopropellant composition according to  claim 3  or  4 , wherein the amount of alkanol is between 5 and 70 wt. %.  
     
     
         6 . Monopropellant composition according to claim  1 - 5 , consisting of 25 to 75 wt. % of hydrazinium nitroformate, 5 to 50 wt. % of water and 0 to 25 wt. % of lower alkanol.  
     
     
         7 . Monopropellant composition according to claim  1 - 6 , further comprising solubilisers, vapour pressure decreasing agents and/or performance improving agents.  
     
     
         8 . Use of a composition of hydrazinium nitroformate and/or ammonium dinitramide according to claim  1 - 7  as propellant in spacecraft propulsion.  
     
     
         9 . Use of a composition of hydrazinium nitroformate and/or ammonium dinitramide according to claim  1 - 7  as emergency propellant in jet fighters.  
     
     
         10 . Use of a composition of hydrazine nitroformate and/or ammonium dinitramide according to claim  1 - 9  in an emergency gas generation system for submarines.  
     
     
         11 . Process for orienting and positioning of spacecraft after delivery into the normal orbit by a launch vehicle by the use of spacecraft propulsion system based on monopropellant thrusters, wherein the monopropellant according to claim  1 - 7  is used for propulsion.