Solid rocket propellant with low glass transition
A solid rocket propellant includes a binder that has hydroxyl-terminated polybudadiene (HTPB) with a curative that is selected from isocyanate-terminated polyether, isocyanate-terminated polysiloxane, or combinations thereof.
1. A solid rocket propellant comprising a binder having hydroxyl-terminated polybudadiene (HTPB) with a curative that includes isocyanate-terminated polyether that is hexamethylene diisocyanate-terminated polytetrahydrofuran (pTHF).
2. The solid rocket propellant as recited in claim 1 , wherein the curative additionally includes isocyanate-terminated polysiloxane.
3. The solid rocket propellant as recited in claim 2 , wherein the isocyanate-terminated polysiloxane is diisocyanate-terminated polysiloxane.
4. The solid rocket propellant as recited in claim 1 , wherein the binder has a ratio of the curative to the HTPB, by weight, of about 5:95 to about 40:60.
5. The solid rocket propellant as recited in claim 1 , wherein the curative additionally includes diisocyanate-terminated polysiloxane, and the binder has a ratio of the curative to the HTPB, by weight, of about 5:95 to about 40:60.
6. 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 hydroxyl-terminated polybudadiene (HTPB) with a curative that includes isocyanate-terminated polyether that is hexamethylene diisocyanate-terminated polytetrahydrofuran (pTHF).
7. The solid rocket motor as recited in claim 6 , wherein the curative additionally includes diisocyanate-terminated polysiloxane.
8. The solid rocket motor as recited in claim 6 , wherein the binder has a ratio of the curative to the HTPB, by weight, of about 5:95 to about 40:60.
9. A polymer composition comprising a hydroxyl-terminated polybudadiene (HTPB) with a curative that includes isocyanate-terminated polyether that is hexamethylene diisocyanate-terminated polytetrahydrofuran (pTHF).
10. The polymer composition as recited in claim 9 , wherein the binder has a ratio of the curative to the HTPB, by weight, of about 5:95 to about 40:60.
11. The solid rocket motor as recited in claim 6 , wherein the curative additionally includes diisocyanate-terminated polysiloxane, and the binder has a ratio of the curative to the HTPB, by weight, of about 5:95 to about 40:60.
12. The polymer composition as recited in claim 9 , wherein the curative additionally includes diisocyanate-terminated polysiloxane, and the binder has a ratio of the curative to the HTPB, by weight, of about 5:95 to about 40:60.
13. The solid rocket propellant as recited in claim 1 , wherein the binder has a glass transition temperature (T g ) of lower than −80° C..