Propellant Compositions and Methods of Making and Using the Same

Abstract

Formulated propellants and methods of forming the same are described herein including a method of manufacturing a rocket propellant comprising combining at least two hydrocarbon fluids.

1 . A method of manufacturing a rocket propellant comprising combining at least two hydrocarbon fluids. 
     
     
         2 . The method of  claim 1  wherein the rocket propellant meets RP-1 specifications. 
     
     
         3 . The method of  claim 1  wherein the hydrocarbon fluids have a specific gravity at 60° C. of between 0.760 and 0.825, as measured by ASTM D-1298. 
     
     
         4 . The method of  claim 1 , wherein the hydrocarbon fluids have a specific gravity at 60° C. of between 0.790 and 0.81, as measured by ASTM D-1298. 
     
     
         5 . The method of  claim 1 , wherein the hydrocarbon fluids have a sulfur concentration of less than 3 ppm as measured by ASTM D-5623. 
     
     
         6 . The method of  claim 1 , wherein the hydrocarbon fluids have an aromatics content of less than 1% by volume, as measured by ASTM D-1319. 
     
     
         7 . The method of  claim 6 , wherein the hydrocarbon fluids have an aromatics content of less than 0.01% by volume, as measured by ASTM-1319. 
     
     
         8 . The method of  claim 1 , wherein the hydrocarbon fluids have an olefins content of less than 0.1% by volume, as measured by ASTM-1319. 
     
     
         9 . The method of  claim 1 , wherein the hydrocarbon fluids have a hydrogen content of from between 13 and 15 wt. %, as measured by ASTM D-3343. 
     
     
         10 . The method of  claim 1 , wherein the hydrocarbon fluids have a flash point of between 130 and 225° F., as measured by ASTM D-93. 
     
     
         11 . The method of  claim 1 , wherein the rocket propellant has a hydrogen content of from between 14.25 to 15 wt. %, as measured by ASTM D-3343. 
     
     
         12 . The method of  claim 11 , wherein the rocket propellant has a hydrogen content of from between 14.8 to 15 wt. %, as measured by ASTM D-3343. 
     
     
         13 . The method of  claim 1 , wherein the rocket propellant has a net heat of combustion greater than 18,500 BTU/pound, as measured by ASTM D-240. 
     
     
         14 . The method of  claim 13 , wherein the rocket propellant has a net heat of combustion between 18,500 and 19,000 BTU/pound, as measured by ASTM D-240. 
     
     
         15 . The method of  claim 1 , wherein the density of the rocket propellant at 15° C. is from 0.799-0.815, as measured by ASTM D-1298. 
     
     
         16 . The method of  claim 15 , wherein the density of the rocket propellant at 15° C. is from 0.799-0.815, as measured by ASTM D-1298. 
     
     
         17 . The method of  claim 1 , wherein at least one of the hydrocarbon fluids comprises an isoparrafin. 
     
     
         18 . The method of  claim 1 , wherein at least one of the hydrocarbon fluids comprises a normal paraffin. 
     
     
         19 . The method of  claim 1 , wherein the rocket propellant has an aromatics content of less than 0.01% by volume, as measured by ASTM-1319. 
     
     
         20 . The method of  claim 1 , wherein none of the hydrocarbon fluids meet the RP-1 specification. 
     
     
         21 . The method of  claim 1 , wherein the rocket propellant further comprises a powdered metal. 
     
     
         22 . The method of  claim 21 , wherein the powdered metal is aluminum.