Claims
- 1. A solid propellant formulation comprising:about 5 to about 10 weight % of at least one energetic binder; about 20 to about 35 weight % of an energetic plasticizer; about 25 to about 45 weight % of ammonium dinitramide as a primary oxidizer; about 10 to about 20 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; andabout 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 bum rate catalyst, a bum 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 bum 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 hexmethylene diisocyanate.
CROSS-REFERENCE TO RELATED APPLICATIONS
This is a divisional of application Ser. No. 09/872,427 filed on May 29, 2001, now U.S. Pat. No. 6,613,168 which the entire disclosure of which is incorporated hereby reference.
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