Claims
- 1. A solid propellant formulation having a pressure slope break occurring higher than about 2500 psi to 3500 psi comprising:
about 6.0 to about 6.5 weight % of at least one energetic polymeric binder; about 18 to about 24 weight % ammonium perchlorate having a particle size of about 80 μm to about 100 μm as a primary oxidizer; about 10 to about 15 weight % of CL-20 having a particle size less than about 3.0 μm as a secondary oxidizer; about 25 to about 32 weight % of ammonium nitrate having a particle size of about 40 μm to about 60 μm as a co-oxidizer; about 19 to about 24 weight % of a metal fuel; and about 0.3 to about 0.6 weight % of a burn rate catalyst; wherein said solid propellant formulation has a burn rate of about 0.5 in/s at about 1000 psi and shows no pressure slope break up to about 8000 psi.
- 2. The solid propellant formulation of claim 1, wherein said secondary oxidizer has a particle size of about 90 μm.
- 3. The solid propellant formulation of claim 1, wherein said polymer binder consists essentially of a hydroxyl-terminated polycaprolactone polyether block polymer.
- 4. The solid propellant formulation of claim 1, wherein said polymer binder is selected from the group consisting of 2-oxepanone, polymer with alpha-hydro-omega-hydroxypoly (oxy-1,4-butanediol)and 2-Oxepanone, polymer with 2,2-bis(hydroxymethyl)-1,3-propanediol.
- 5. The solid propellant formulation of claim 1, wherein said metal fuel is aluminum fuel.
- 6. The solid propellant formulation of claim 5, wherein said aluminum fuel has a particle size of about 30 μm to about 95 μm.
- 7. The solid propellant formulation of claim 1, further comprising at least one member selected from a plasticizer, a curative, a stabilizer, a cure catalyst, a crosslinker and a bonding agent.
- 8. The solid propellant formulation of claim 7, wherein said plasicizer is selected from the group consisting of triethyleneglycol dinitrate, or n-butyl-2-nitratoethyl-nitramine diethyleneglycol dinitrate, trimethylolethane trinitrate, butanetriol trinitrate and any combination thereof.
- 9. The solid propellant formulation of claim 7, wherein said plasticizer is a combination of n-butyl-2-nitratoethyl-nitramine and triethyleneglycol dinitrate.
- 10. The solid propellant formulation of claim 7, wherein said curative is selected from the group consisting of hexamethylene diisocyanate, m-tetramethylxylene diisocyanate, dimeryl diisocyanate, toluene diisocyanate, polymeric hexamethylene diisocyanate, isophorone diisocyanate, biuret triisocyanate and any combination thereof.
- 11. The solid propellant formulation of claim 7, wherein said cure catalyst is selected from the group consisting of triphenyl bismuth triphenyltin chloride, dibutyltin diacetate and dibutyltin dilaurate.
- 12. The solid propellant formulation of claim 7, wherein said stabilizer is selected from the group consisting of N-methyl-p-nitroaniline and 2-NDPA (2-nitrodiphenylamine).
- 13. The solid propellant formulation of claim 1, wherein said burn rate catalyst is aluminum oxide having a surface of about 85 to about 115 m2/g.
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] This application is being filed as a Divisional Application in accordance with 37 C.F.R. 1.53(b). The Parent Application of this Divisional Application is application Ser. No. 09/798,013 filed Feb. 27, 2001.
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT
[0002] 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.
Divisions (1)
|
Number |
Date |
Country |
Parent |
09798013 |
Feb 2001 |
US |
Child |
10356022 |
Feb 2003 |
US |