Solid rocket propellant with low glass transition

Patent metadata

Field	Value
Publication number	US-11312814-B2
Application number	US-201615762745-A
Country	US
Kind code	B2
Filing date	Sep 30, 2016
Priority date	Oct 19, 2015
Publication date	Apr 26, 2022
Grant date	Apr 26, 2022

Abstract

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.

First claim

What is claimed is:

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..

Assignees

• Aerojet Rocketdyne Inc

Inventors

• Doll Daniel
• Dawley Scott

Classifications

• C06B45/10 Primary

  the organic component containing a resin · CPC title

• C08G18/48

  Polyethers · CPC title

• C06B23/00

  Compositions characterised by non-explosive or non-thermic constituents {(in combination with specific explosives C06B25/20, C06B25/26, C06B29/04, C06B29/08, C06B31/06, C06B31/40, C06B33/02)} · CPC title

• F02K9/97

  Rocket nozzles (thrust or thrust vector control F02K9/80) · CPC title

• C08G18/4854

  Polyethers containing oxyalkylene groups having four carbon atoms in the alkylene group · CPC title