Compositions and methods of producing rocket propellants with enhanced cryogenic cooling, thermal stability, and thrust efficiency performance

Abstract

The present disclosure relates to a rocket propellant composition comprising (a) a liquid oxygen; and (b) a hydrocarbon mixture comprising: (i) a hydrogen content from about 14.0 mass % to about 16.0 mass %, by mass of the hydrocarbon mixture; (ii) a kinematic viscosity of from about 5 mm 2 /s to about 8 mm 2 /s at a temperature ranging from about −35° C. to about −33° C.; and (iii) a sulfur content of from about 0 ppm to about 0.1 ppm, by mass of 0 the hydrocarbon mixture.

What is claimed is: 
     
         1 . A rocket propellant composition comprising:
 (a) a liquid oxygen; and   (b) a hydrocarbon mixture comprising:
 (i) a hydrogen content from about 14.0 mass % to about 16.0 mass %, by mass of the hydrocarbon mixture; 
 (ii) a kinematic viscosity of from about 5 mm 2 /s to about 8 mm 2 /s at a temperature ranging from about −35° C. to about −33° C.; and 
 (iii) a sulfur content of from about 0 01 ppm to about 0.1 ppm, by mass of the hydrocarbon mixture. 
   
     
     
         2 . The rocket propellant composition according to  claim 1 , wherein a mixture ratio of the liquid oxygen to the hydrocarbon mixture ranges from about 1.8 to about 3.2. 
     
     
         3 . The rocket propellant composition according to  claim 1 , wherein a mixture ratio of the liquid oxygen to the hydrocarbon mixture ranges from about 1 to about 4. 
     
     
         4 . The rocket propellant composition according to  claim 1 , wherein the hydrogen content ranges from about 15.3 mass % to about 15.9 mass %, by mass of the hydrocarbon mixture. 
     
     
         5 . The rocket propellant composition according to  claim 1 , wherein the hydrocarbon mixture further comprises one or more of a branched paraffin, a straight chain paraffin, a cyclo-paraffin, and combinations thereof. 
     
     
         6 . The rocket propellant composition according to  claim 1 , wherein the hydrocarbon further comprises a flash point according to ASTM D93 of at least about 60° C. at 1 ATM. 
     
     
         7 . The rocket propellant composition according to  claim 1 , wherein the hydrocarbon mixture further has a distillation initial boiling point of at least about 180° C. 
     
     
         8 . The rocket propellant composition according to  claim 1 , wherein the hydrocarbon mixture further has a density ranging from about 0.7 kg/m3 to about 0.9 kg/m3 at a temperature of about 15° C. 
     
     
         9 . The rocket propellant composition according to  claim 1 , wherein the hydrocarbon mixture further comprises a freezing point that is lower than about −45° C. 
     
     
         10 . The rocket propellant composition according to  claim 1 , wherein the hydrocarbon mixture is a Fischer-Tropsch product. 
     
     
         11 . The rocket propellant composition according to  claim 1 , wherein the rocket propellant composition comprises a c* value of at least about 1% gain versus RP-1/RP-2 under set operating conditions. 
     
     
         12 . A method for producing a rocket propellant composition, the method comprising:
 (a) providing a liquid oxygen; and   (b) providing a hydrocarbon mixture comprising:
 (i) a hydrogen content from about 15.0 mass % to about 16.0 mass %, by mass of the hydrocarbon mixture; 
 (ii) a kinematic viscosity of from about 5 mm 2 /s to about 7 mm 2 /s at a temperature ranging from about −35° C. to about −33° C.; and 
 (iii) a sulfur content of from about 0.01 ppm to about 0.1 mass %, by mass of the hydrocarbon mixture. 
   
     
     
         13 . The method according to  claim 12 , wherein a mixture ratio of the liquid oxygen to the hydrocarbon mixture ranges from about 1 to about 4. 
     
     
         14 . The method according to  claim 12 , wherein a mixture ratio of the liquid oxygen to the hydrocarbon mixture ranges from about 1.8 to about 3.2. 
     
     
         15 . The method according to  claim 12 , further comprising combining the liquid oxygen and the hydrocarbon mixture at a burner plate. 
     
     
         16 . The method according to  claim 12 , wherein the hydrogen content ranges from about 15.3 mass % to about 15.9 mass %, by mass of the hydrocarbon mixture. 
     
     
         17 . The method according to  claim 12 , wherein the hydrocarbon further comprises a flash point according to ASTM D93 of at least about 60° C. at 1 ATM. 
     
     
         18 . The method according to  claim 12 , wherein the hydrocarbon mixture further comprises a distillation initial boiling point of at least about 190° C. 
     
     
         19 . The method according to  claim 12 , wherein the rocket fuel composition further comprises a density ranging from about 0.7 kg/m3 to about 0.8 kg/m3 at a temperature of about 15° C. 
     
     
         20 . The method according to  claim 12 , wherein the hydrocarbon mixture is a Fischer-Tropsch product. 
     
     
         21 . The method according to  claim 12 , wherein the rocket propellant composition comprises a c* value of at least about 1% gain versus RP-1/RP-2 under set operating conditions.