SOLID ROCKET PROPELLANT WITH BLENDED TRIAZOLE PLASTICZER
A solid rocket propellant includes a blended plasticizer of at least two chemically different 3-nitro 1,2,4-triazoles.
1 . A solid rocket propellant comprising a blended plasticizer of at least two chemically different 3-nitro 1,2,4-triazoles.
2 . The solid rocket propellant as recited in claim 1 , wherein the blended plasticizer has a molar ratio from about 1.1:0.9 to about 0.9:1.1 of the two chemically different 3-nitro 1,2,4-triazoles.
3 . The solid rocket propellant as recited in claim 1 , wherein the two chemically different 3-nitro 1,2,4-triazoles are independently selected from the group consisting of azidoethyl nitro-triazole, azidopropyl nitro-triazole, nitradoethyl nitro-triazole, and nitradopropyl nitro-triazole.
4 . The solid rocket propellant as recited in claim 1 , wherein the two chemically different 3-nitro 1,2,4-triazoles are azidopropyl nitro-triazole and azidoethyl nitro-triazole.
5 . The solid rocket propellant as recited in claim 1 , wherein the two chemically different 3-nitro 1,2,4-triazoles are 1-azidoethyl 3-nitro 1,2,4-triazole and 1-azidopropyl 3-nitro 1,2,4-triazole.
6 . The solid rocket propellant as recited in claim 1 , wherein the blended plasticizer has a density from 1.51 grams per cubic centimeter to 1.63 grams per cubic centimeter.
7 . The solid rocket propellant as recited in claim 6 , wherein the blended plasticizer has a glass transition temperature of −62° C. to −75° C.
8 . The solid rocket propellant as recited in claim 1 , wherein the blended plasticizer has a thermal stability characterized by no weight loss up to 125° C. and 0.4% weight loss or less after 16 hours at 70° C.
9 . The solid rocket propellant as recited in claim 1 , further comprising a polymeric binder, wherein the polymeric binder and blended plasticizer have a total combined weight, and from 25% to 75% of the total combined weight is the blended plasticizer.
10 . A solid rocket motor comprising:
a motor case;
a nozzle attached with the motor case; and
a solid rocket propellant disposed in the motor case, the solid rocket propellant including a blended plasticizer of at least two chemically different 3-nitro 1,2,4-triazoles.
11 . The solid rocket motor as recited in claim 10 , wherein the blended plasticizer has a molar ratio from about 1.1:0.9 to about 0.9:1.1 of the two chemically different 3-nitro 1,2,4-triazoles.
12 . The solid rocket motor as recited in claim 10 , wherein the two chemically different 3-nitro 1,2,4-triazoles are independently selected from the group consisting of azidoethyl nitro-triazole, azidopropyl nitro-triazole, nitradoethyl nitro-triazole, and nitradopropyl nitro-triazole.
13 . The solid rocket motor as recited in claim 10 , wherein the two chemically different 3-nitro 1,2,4-triazoles are azidopropyl nitro-triazole and azidoethyl nitro-triazole.
14 . The solid rocket motor as recited in claim 10 , wherein the two chemically different 3-nitro 1,2,4 triazoles are 1-azidoethyl 3-nitro 1,2,4-triazole and 1-azidopropyl 3-nitro 1,2,4-triazole.
15 . The solid rocket motor as recited in claim 10 , wherein the blended plasticizer has a density from 1.51 grams per cubic centimeter to 1.63 grams per cubic centimeter, a glass transition temperature of −62° C. to −75° C., and a thermal stability characterized by no weight loss up to 125° C. and 0.4% weight loss or less after 16 hours at 70° C.
16 . The solid rocket motor as recited in claim 10 , further comprising a polymeric binder, wherein the polymeric binder and blended plasticizer have a total combined weight, and from 25% to 75% of the total combined weight is the blended plasticizer.
17 . A solid rocket propellant comprising a blended triazole plasticizer with a density from 1.51 grams per cubic centimeter to 1.63 grams per cubic centimeter, and a glass transition temperature of −62° C. to −75° C.
18 . The solid rocket motor as recited in claim 17 , wherein the blended triazole plasticizer includes azidopropyl nitro-triazole and azidoethyl nitro-triazole in a molar ratio from about 1.1:0.9 to about 0.9:1.1.