Reduced toxicity hypergolic propellants

Abstract

The disclosure described herein is a reduced toxicity rocket propellant comprising a liquid fuel and a liquid oxidizer that ignites spontaneously upon contact with each other. The rocket propellant includes a metal hydride catalyst. Multiple embodiments of the propellant include multiple compositions of liquid fuel.

1 . A propellant comprising:
 a liquid oxidizer, wherein the liquid oxidizer is at least approximately 70% hydrogen peroxide by weight, and   a liquid fuel comprising:
 kerosene, 
 sodium borohydride, and 
 an amount of triethylene glycol dimethyl ether sufficient to dissolve the sodium borohydride. 
   
     
     
         2 . The propellant of  claim 1 , wherein the hydrogen peroxide is high test hydrogen peroxide. 
     
     
         3 . The propellant of  claim 1 , wherein the liquid fuel includes an amount of kerosene within the range of twenty percent (20%) to seventy-five percent (75%) by weight. 
     
     
         4 . The propellant of  claim 1 , wherein the liquid fuel comprises at least twenty percent (20%) triethylene glycol dimethyl ether by weight. 
     
     
         5 . The propellant of  claim 4 , wherein the liquid fuel includes an amount of triethylene glycol dimethyl ether within the range of twenty percent (20%) to eighty percent (80%) by weight. 
     
     
         6 . The propellant of  claim 1 , wherein the metal hydride is sodium borohydride. 
     
     
         7 . The propellant of  claim 6 , wherein the liquid fuel includes an amount of sodium borohydride within the range of five percent (5%) to fifteen percent (15%) by weight. 
     
     
         8 . The propellant of  claim 1 , wherein the liquid fuel includes a cobalt compound. 
     
     
         9 . A propellant comprising:
 a liquid oxidizer, wherein the liquid oxidizer is at least approximately 70% hydrogen peroxide by weight, and   a liquid fuel comprising:
 dimethylformamide, and 
 at least one percent (1%) metal hydride by weight. 
   
     
     
         10 . The propellant of  claim 9 , wherein the liquid fuel includes an amount of metal hydride within the range of one percent (1%) to eighteen percent (18%) by weight. 
     
     
         11 . The propellant of  claim 9 , wherein the metal hydride is sodium borohydride. 
     
     
         12 . The propellant of  claim 11 , wherein the liquid fuel includes an amount of sodium borohydride within the range of five percent (5%) to eighteen percent (18%) by weight, and an amount of dimethylformamide within the range of eighty-two percent (82%) to ninety-five percent (95%) by weight. 
     
     
         13 . The propellant of  claim 9 , wherein the liquid fuel includes a cobalt compound. 
     
     
         14 . A propellant comprising:
 a liquid oxidizer, wherein the liquid oxidizer is at least approximately 70% hydrogen peroxide by weight, and   a liquid fuel comprising:
 dimethyl sulfoxide, and 
 at least one percent (1%) metal hydride by weight. 
   
     
     
         15 . The propellant of  claim 14 , wherein the liquid fuel includes an amount of metal hydride within the range of one percent (1%) to fifteen percent (15%) by weight. 
     
     
         16 . The propellant of  claim 14 , wherein the metal hydride is sodium borohydride. 
     
     
         17 . The propellant of  claim 16 , wherein the liquid fuel includes an amount of sodium borohydride within the range of five percent (5%) to fifteen percent (15%) by weight, and an amount of dimethyl sulfoxide within the range of eighty-five percent (85%) to ninety-five percent (95%) by weight. 
     
     
         18 . The propellant of  claim 16 , wherein the liquid fuel is approximately 10% sodium borohydride. 
     
     
         19 . The propellant of  claim 14 , wherein the liquid fuel includes a cobalt compound. 
     
     
         20 . A propellant comprising:
 a liquid oxidizer, wherein the liquid oxidizer is at least approximately 70% hydrogen peroxide by weight,   a liquid fuel comprising:
 tetraethyl glycol, and 
 at least one percent (1%) metal hydride by weight. 
   
     
     
         21 . The propellant of  claim 20 , wherein the metal hydride is sodium borohydride. 
     
     
         22 . The propellant of  claim 21 , wherein the liquid fuel includes an amount of sodium borohydride within the range of five percent (5%) to fifteen percent (15%) by weight, and an amount of tetraethyl glycol within the range of eighty-five percent (85%) to ninety-five percent (95%) by weight. 
     
     
         23 . The propellant of  claim 20 , wherein the liquid fuel includes a cobalt compound.