초록 ▼

The addition of silicon (Si) powder from about 0.40 to 6.00 weight percent to ammonium nitrate (AN) propellant formulations as a fuel source results in a substantial increase in performance specific impulse (Isp). Theoretical Isp of AN propellant can be enhanced to levels approaching conventional in

The addition of silicon (Si) powder from about 0.40 to 6.00 weight percent to ammonium nitrate (AN) propellant formulations as a fuel source results in a substantial increase in performance specific impulse (Isp). Theoretical Isp of AN propellant can be enhanced to levels approaching conventional in-service propellant formulations containing much more hazardous ingredients. Using inert or energetic polymer binders, AN propellant formulations are possible that will meet the performance requirements of most tactical missile systems when silicon is used as a fuel additive. Silicon powder when used to replace elemental carbon in most formulations has two major advantages: (1) an increase in theoretical Isp and (2) an improved propellant combustion efficiency by increasing propellant burning temperature. An improvement in propellant burning properties are also expected. The adjustment of weight percent ammonium nitrate in the AN propellant formulation is made as the silicon powder is adjusted over the range of 0.40 weight percent to 6.00 to achieve the preferred results. Formulations are mixed, cast and cured by techniques and methods that are commonly used in the industry and that are known by personnel skilled in the art of propellant formulating.

대표청구항 ▼

An ammonium nitrate propellant composition selected from an ammonium nitrate propellant composition containing an inert polymer binder as defined under composition (A) hereinbelow or an ammonium nitrate propellant composition containing an energetic polymer binder as defined under composition (B) an

An ammonium nitrate propellant composition selected from an ammonium nitrate propellant composition containing an inert polymer binder as defined under composition (A) hereinbelow or an ammonium nitrate propellant composition containing an energetic polymer binder as defined under composition (B) and composition (C) hereinbelow, said compositions (A), (B), and (C), consisting in weight percents of the ingredients with functions specified as follows: ________________________________ -Composition A: Inert polymer binder, polyglycoladipate 6.47 Butanetriol trinitrate - plasticizer 18.79 Trimethylolethane trinitrate - plasticizer 12.59 Ammonium nitrate - oxidizer 60.00-54.40 N-methyl para nitroaniline - stabilizer 0.50 Hexamethylene diisocyanate - curing agent 1.22, Composition B: Energetic nitramine polymer binder 8.00 Butanediol trinitrate - plasticizer 17.86 Trimethylolethane trinitrate - plasticizer 11.90 Ammonium nitrate - oxidizer 59.60-54.00 N-methyl para nitroaniline - stabilizer 0.50 Triphenylbismuth - cure agent 0.03 Triisocyanate curing agent 1.71, and Composition C: Energetic glycidyl azide polymer binder 8.00 Butanetriol trinitrate - plasticizer 18.42 Trimethylolethane trinitrate - plasticizer 12.28 Ammonium nitrate - oxidizer 59.60-54.00 N-methyl para nitroaniline - stabilizer 0.50 hexamethylene diisocyanate - curing agent 0.77 Triphenylbismuth - cure catalyst 0.30, ________________________________ said compositions (A), (B), and (C) additionally consisting of a silicon powder additive to achieve an improvement in propellant performance Isp, combustion temperature, and combustion efficiency, said silicon powder additive incorporated into said ammonium nitrate propellant composition during propellant mixing in an amount from about 0.40 to about 6.00 weight percent of said silicon powder having a particle size of less than 5 microns average particle size, said improvement based on comparisons of measured specific impulses, density specific impulse, propellant burn temperatures in (degK.), and percent transmittances as determined in signature analysis of exhaust plumes of said ammonium nitrate composition containing said silicon powder as compared with said ammonium nitrate composition containing carbon black additive but no silicon powder, said composition (A) having burn temperatures of 2593 degK. and 2790 degK. with the incorporation of said silicon powder in weight percent of 1 and 6 weight percent, respectively, as compared with 2553 degK. with 0% silicon powder, said composition (B) having burn temperatures of 2660 degK. and 2850 degK. with the incorporation of said silicon powder in weight percent of 1 and 6 weight percent, respectively, as compared with 2620 degK. with 0% silicon powder, and said composition (C) having burn temperatures of 2744 degK. and 2921 degK. with the incorporation of said silicon powder in weight percent of 1 and 6 weight percent, respectively, as compared with 2706 degK. with 0% silicon powder.