Insensitive propellant composition

Abstract

The present invention relates to a propellant composition which comprises hydroxy-terminated polyether (HTPE), N-butyl-(2-nitratoethyl)nitramine (BuNENA) and ammonium perchlorate (AP) and is insensitive to impact and thermal reactions and thus suitably used for a solid rocket propulsion unit.

1 . An insensitive solid propellant composition comprising: 5-10 wt % of at least one selected from hydroxy-terminated polyether (HTPE) and hydroxy-terminated polycaprolactone ether (HTPC) as a binder; 5-15 wt % of N-butyl-N-(2-nitratorethyl)nitramine (BuNENA) as a plasticizer; 10-70 wt % of ammonium perchlorate (AP) as a main oxidizer; 1-30 wt % of ammonium nitrate (AN) as an auxiliary oxidizer; and 1-30 wt % of at least one selected from Al compounds, Zr compounds, B compounds and Fe compounds. 
     
     
         2 . The insensitive solid propellant composition according to  claim 1 , which comprises both of hydroxyl-terminated polyether and hydroxyl-terminated polycaprolactone ether as a binder. 
     
     
         3 . The insensitive solid propellant composition according to  claim 1 , which further comprises at least one of trimethylol ethane trinitrate and butanetriol trinitrate as a plasticizer. 
     
     
         4 . The insensitive solid propellant composition according to  claim 1 , which further comprises at least one isophorone diisocyanate and polyfunctional aliphatic isocyanate as a curing agent. 
     
     
         5 . The insensitive solid propellant composition according to  claim 1 , which further comprises N-methyl-p-nitroaniline or 2-nitrodiphenylamine.