Cryogenically compatible rocket propellant

Abstract

Propellants for rockets, space transportation vehicles, launch vehicles and systems, crew escape vehicles and systems, launch escape towers, and space vehicle systems are disclosed. Some embodiments provide a rocket propellant comprising a mixture of a small chain alkane from 1 to 4 carbons and a small chain alkene from 3 to 4 carbons. The mixture of the small chain alkane and small chain alkene is in a proportion that lowers the melting of the mixture below the melting point of both the small chain alkane and small chain alkene.

1 . A reduced-temperature propellant mixture for improving performance of a rocket stage, rockets, and the like, said reduced-temperature propellant mixture comprising:
 propane; and   propylene, wherein said propylene and said propane are placed in thermal communication in a rocket stage for reduced cost and a smaller rocket stage.   
     
     
         2 . The reduced-temperature propellant mixture according to  claim 1 , wherein said reduced-temperature propellant mixture is a mixture of about 50% propane/50% propylene that exhibits a melting point below that of a melting point of pure propane or pure propylene and compatible with a liquid oxidizer. 
     
     
         3 . The reduced-temperature propellant mixture according to  claim 2 , wherein said reduced-temperature propellant mixture is any mixture of propylene and propane for freezing point supression. 
     
     
         4 . The reduced-temperature propellant mixture according to  claim 1 , wherein said reduced-temperature propellant mixture is cooled with liquid nitrogen to between 75 Kelvin and 88 Kelvin to improve performance. 
     
     
         5 . A reduced-temperature propellant mixture for improving performance of a rocket stage, rockets, and the like, said reduced-temperature propellant mixture comprising:
 propane;   propylene; and   liquid oxidizer, wherein a mixture of said propane and said propylene is maintained in thermal communication with said liquid oxidizer for the purposes of improving a rocket stage.   
     
     
         6 . The reduced-temperature propellant mixture according to  claim 5 , wherein a mixture of said propane and said propylene is a mixture of about 50% propane/50% propylene, and wherein said mixture of about 50% propane/50% propylene and said liquid oxidizer are cooled below a normal boiling point to improve performance. 
     
     
         7 . The reduced-temperature propellant mixture according to  claim 5 , wherein a eutectic mixture of said propane and polypropylene is cooled to the melting point is the best choice of a propane/propylene fuel combusted with said liquid oxygen subcooled to that same temperature is the superior operating combination for a rocket propellant.