received by the International Bureau on 03 MAR 2017 (03.03.2017)

1. A rocket propellant comprising:

a hydrocarbon blend having an aromatic compounds content less than 0.5 mass percent, a specific energy of 18.4 KBtu/lb or greater, and a mass density of 0.830 grams per cubic centimeter or greater.

2. The rocket propellant of claim 1 having a total cycloparaffin content of 60 mass percent or higher.

3. The rocket propellant of claim 1 having a sulfur content less than 1 ppm by mass.

4. The rocket propellant of claim 1 which comprises a blend of a refined kerosene and at least one isoparaffm.

5. The rocket propellant of claim 4, in which the isoparaffin is at least one of the group consisting of isododecane and isoeicosane.

6. The rocket propellant of claim 1 , in which the hydrocarbon blend comprises a refined kerosene, and at least one cycloparaffin.

7. The rocket propellant of claim 6, in which the cycloparaffin is at least one of the group consisting of decalin, diethyl cyclohexane, and exo-tetrahydrodicyclopentadiene.

8. The rocket propellant of claim 1 , in which the hydrocarbon blend comprises a refined kerosene, at least one isoparaffm, and at least one cycloparaffin.

9. The rocket propellant of claim 8, in which the isoparaffin is at least one of the group consisting of isododecane and isoeicosane.

10. The rocket propellant of claim 8, in which the cycloparaffin is at least one of the group consisting of decalin, diethyl cyclohexane, and exo-tetrahydrodicyclopentadiene.