Claims
- 1. A solid propellant formulation comprising:
about 5.0 to about 10.0 weight % of at least one energetic binder; about 20.0 to about 35.0 weight % of an energetic plasticizer; about 25.0 to about 45.0 weight % of ammonium dinitramide as a primary oxidizer; 0 to about 20.0 weight % of a metal fuel, wherein said metal fuel comprises particulate aluminum having a particle size of about 1 μm to about 60 μm and ultrafine aluminum having a particle size of less than 1 μm.
- 2. The solid propellant formulation of claim 1, wherein said energetic plasticizer is selected from the group consisting of butanetriol trinitrate, triethylene glycol dinitrate, nitroglycerine glycidyl azide polymer terminated with azide, bis-(2,2-dinitropropyl) acetal/formal and butyl nitratoethylnitramine.
- 3. The solid propellant formulation of claim 1, wherein said energetic plasticizer is butanetriol trinitrate.
- 4. The solid propellant formulation of claim 1, wherein said energetic binder is selected from the group consisting of glycidyl azide polymer, a copolymer of (bis-azidoethyl) oxetane with (3-nitratomethyl-3-methyl) oxetane, 3-azidomethyl-3-methyl oxetane, bis-(nitratomethyl) oxetane, polyglycidyl nitrate, polypropylene glycol, hydroxy-terminated polycaprolactones, hydroxy-terminated polyesters, hydroxy-terminated polyethers, hydroxy-terminated polycaprolactone ether and hydroxy-terminated polyalkylene oxide.
- 5. The solid propellant formulation of claim 1, wherein said energetic binder is a hydroxy-terminated polyalkylene oxide having a molecular weight of about 24,000 daltons.
- 6. The solid propellant formulation of claim 1, wherein said metal fuel comprises
about 10 weight % of said particulate aluminum having a particle size of about 1 μm to about 60 μm; and about 10 weight % of said ultrafine aluminum having a particle size of less than 1 μm.
- 7. The solid propellant formulation of claim 1, further comprising at least one member selected from a curative, a crosslinker, a stabilizer, a cure catalyst, a burn rate catalyst, a burn rate modifier, an opacifier and a bonding agent.
- 8. The solid propellant formulation of claim 6, wherein said crosslinker is selected from the group consisting of hexamethylene diisocyanate, isophorone diisocyanate, toluene diisocyanate and polymeric hexamethylene diisocyanate.
- 9. The solid propellant formulation of claim 6, wherein said burn rate catalyst is aluminum oxide.
- 10. The solid propellant formulation of claim 6, wherein said cure catalyst is selected from the group consisting of triphenyl bismuth, triphenyltin chloride, dibutyltin diacetate and dibutyltin dilaurate.
- 11. The solid propellant formulation of claim 6, wherein said curative is selected from the group consisting of hexamethylene diisocyanate, isophorone diisocyanate, toluene diisocyanate and the polymeric hexamethylene diisocyanate.
- 12. A solid propellant formulation comprising:
about 5.0 to about 10.0 weight % of at least one energetic binder; about 20.0 to about 35.0 weight % of an energetic plasticizer; about 25.0 to about 45.0 weight % of ammonium dinitramide as a primary oxidizer; about 10.0 weight % of particulate aluminum having a particle size in the range of about 1 μm to about 60 μm; and about 10.0 weight % of ultrafine aluminum having a particle size of less than 1 μm.
- 13. The solid propellant formulation of claim 12, wherein said energetic plasticizer is selected from the group consisting of butanetriol trinitrate, triethylene glycol dinitrate, nitroglycerine glycidyl azide polymer terminated with azide, bis-(2,2-dinitropropyl) acetal/formal and butyl nitratoethylnitramine.
- 14. The solid propellant formulation of claim 12, wherein said energetic plasticizer is butanetriol trinitrate.
- 15. The solid propellant formulation of claim 12, wherein said energetic binder is selected from the group consisting of glycidyl azide polymer, a copolymer of (bis-azidoethyl) oxetane with (3-nitratomethyl-3-methyl) oxetane, 3-azidomethyl-3-methyl oxetane, bis-(nitratomethyl) oxetane, polyglycidyl nitrate, hydroxy-terminated polycaprolactones, hydroxy-terminated polyesters, hydroxy-terminated polyethers, hydroxy-terminated polycaprolactone ether and a hydroxy-terminated polyalkylene oxide.
- 16. The solid propellant formulation of claim 12, wherein said energetic binder is a tetrahydroxy-terminated polyalkylene oxide having a molecular weight of about 24,000 daltons
- 17. The solid propellant formulation of claim 12, further comprising at least one member selected from a curative, a crosslinker, a stabilizer, a cure catalyst, a burn rate catalyst, a burn rate modifier, an opacifier and a bonding agent
- 18. The solid propellant formulation of claim 17, wherein said crosslinker is selected from the group consisting of hexamethylene diisocyanate, isophorone diisocyanate, toluene diisocyanate and polymeric hexamethylene diisocyanate.
- 19. The solid propellant formulation of claim 17, wherein said burn rate catalyst is aluminum oxide.
- 20. The solid propellant formulation of claim 17, wherein said cure catalyst is selected from the group consisting of triphenyl bismuth, triphenyltin chloride, dibutyltin diacetate and dibutyltin dilaurate.
- 21. The solid propellant formulation of claim 17, wherein said curative is selected from the group consisting of hexamethylene diisocyanate, isophorone diisocyanate, toluene diisocyanate and the polymeric hexamethylene diisocyanate.
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT
[0001] The invention described herein may be manufactured and used by or for the government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.