Rocket motor propellants, systems and/or methods

1. A rocket motor propellant comprising:

a low molecular weight hydroxyl-terminated polybutadiene (HTPB) polymer

and,

the low molecular weight of the low molecular weight HTPB polymer being less than about 1500; and,

a high molecular weight diisocyanate,

D(NCO) 2 ,

the molecular weight of the high molecular weight diisocyanate being greater than about 500;

the low molecular weight HTPB polymer and the high molecular weight diisocyanate being selected for their respective structures to provide for generating a resultant compound combination having a sufficiently low viscosity providing the properties of being

a liquid submix at room temperature, and,

low viscosity, the low viscosity being defined as sufficiently low to achieve the compound combination being:

mixed, cast and cured without the addition of heat.

2. A rocket motor propellant according to claim 1 :

the low molecular weight HTPB polymer being R20LM polymer; and,

the high molecular weight diisocyanate being dimeryl diisocyanate 2-heptyl-3,4-bis(9-isocyanatononyl)-1-pentylcyclohexane.

3. A rocket motor propellant according to claim 1 further including one or more of:

a cure catalyst;

a urethane cure catalyst; and,

a urethane cure catalyst of dibutlytin dilaurate.

4. A rocket motor propellant according to claim 1 having on the order of about 70% to about 30% binder to curative.

5. A rocket motor propellant according to claim 1 further comprising in combination, one or both:

zero or more various oxidizers and

zero or more metal fuels.

6. A rocket motor propellant according to claim 1 without the need of inert plasticizing agents.

7. A rocket comprising:

a propellant housing having a fore end and an aft end; the propellant housing having:

a rocket motor propellant according to claim 1 ;

a nozzle operably connected to the aft end of the propellant housing; and,

a fore nose section operably connected to the fore end of the propellant housing.

8. A rocket motor propellant comprising:

a liquid submix at room temperature of:

a low molecular weight hydroxyl-terminated polybutadiene (HTPB) polymer, the low molecular weight of the low molecular weight HTPB polymer being less than about 1500; and,

a high molecular weight diisocyanate, the molecular weight of the high molecular weight diisocyanate being greater than about 500;

the low molecular weight HTPB polymer is

or chemical equivalent; and,

the high molecular weight diisocyanate is

D(NCO) 2

the low molecular weight HTPB polymer and the high molecular weight diisocyanate being selected for their respective structures to provide for generating a resultant compound combination producing a low viscosity solid propellant formulation that the low viscosity is disposed sufficiently low to achieve the compound combination being configured to result from being and having the properties of:

mixed,

cast and

cured

without addition of heat.

9. A rocket motor propellant according to claim 8 further including one or more of:

a cure catalyst;

a urethane cure catalyst; and,

a urethane cure catalyst of dibutyltin dilaurate.

10. A rocket motor propellant according to claim 8 having on the order of about 70% to about 30% binder to curative.

11. A rocket motor propellant according to claim 8 further comprising in combination, one or both:

zero or more various oxidizers and

zero or more metal fuels.

12. A rocket motor propellant according to claim 8 without the need of inert plasticizing agents.

13. A rocket comprising:

a propellant housing having a fore end and an aft end; the propellant housing having:

a rocket motor propellant according to claim 8 ;

a nozzle operably connected to the aft end of the propellant housing; and,

a fore nose section operably connected to the fore end of the propellant housing.