High energy solid propellant

Abstract

The present invention provides a high energy solid propellant containing an oxidizer, binder and fuel, wherein the fuel and/or the propellant as a whole is encapsulated or microencapsulated so as prevent premature reaction while still maintaining the energetic properties thereof. The oxidizer is preferably ammonium perchlorate, ammonium nitrate or ammonium dinitramide. The binder is preferably polymeric hydrocarbons or polymers. The fuel is preferably lithium hexahydridoborane or lithium hexahydridoalane.

1 . A high energy solid propellant comprising: 
 (a) an oxidizer comprised of ammonium perchlorate, ammonium nitrate or ammonium dinitramide;    (b) a binder comprised of polymeric hydrocarbons or polymers; and    (c) a fuel comprised of lithium hexahydridoborane or lithium hexahydridoalane,    wherein the fuel is encapsulated or microencapsulated such that the propellant grain is fabricated without diminution of its energetic properties.    
     
     
         2 . The high energy solid propellant according to  claim 1 , wherein the binder is PDCPD (polydicyclopentadiene), polyethylene, polystyrene, or low molecular weight polyethylene.  
     
     
         3 . The high energy solid propellant according to  claim 1 , wherein the fuel is comprised of lithium hexahydridoborane and aluminum, or LHA (lithium hexahydridoalane) and aluminum.  
     
     
         4 . The high energy solid propellant according to  claim 2 , wherein fuel is comprised of lithium hexahydridoborane and aluminum, or LHA (lithium hexahydridoalane) and aluminum.  
     
     
         5 . The high energy solid propellant of  claim 1 , wherein the propellant comprises 60-80 wt % oxidizer, 5-30 wt % fuel, and 5-15 wt % binder.  
     
     
         6 . The high energy solid propellant of  claim 1 , wherein the propellant comprises 65-75 wt % oxidizer, 10-25 wt % fuel, and 10-15 wt % binder.  
     
     
         7 . The high energy solid propellant of  claim 1 , wherein the propellant comprises 70-75 wt % oxidizer, 15-25 wt % fuel, and 12 wt % binder.  
     
     
         8 . The high energy solid propellant of  claim 1 , wherein the entire propellant is encapsulated or microencapsulated such that the propellant grain is fabricated without diminution of its energetic properties.