Compositions and methods of producing rocket propellants with enhanced cryogenic cooling, thermal stability, and thrust efficiency performance
AssigneeShell Oil Company
InventorsAnton HUNT, Cynthia Natalie GINESTRA, Joanna Margaret BAULDREAY, Paul Franciscus BOGERS, Elise Marie MINER
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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 mm2/s to about 8 mm2/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.
Claims21
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 mm2/s to about 8 mm2/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.
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 mm2/s to about 7 mm2/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.
Dependencies are inferred from the claim text.