Solid propellant with non-crystalline polyether/inert plasticizer binder

• US 5,348,596 A
• Filed: 08/25/1989
• Issued: 09/20/1994
• Est. Priority Date: 08/25/1989
• Status: Expired due to Term

• Current Assignee: Alliant Techsystems Incorporated (Northrop Grumman Corporation)
• Original Assignee: Hercules Incorporated (Ashland Global Holdings, Inc.)
• Inventors: Roberts, James A., Goleniewski, John R.
• Primary Examiner(s): Miller, Edward A.
• Application Number:
  US07/398,210
• Time in Patent Office: 1,852 Days
• Field of Search: 149/19.4, 149/19.6
• US Class Current: 149/19.6
• CPC Class Codes: C06B 45/10 the organic component containing a resin

Abstract

A solid propellant composition comprising an oxidizer, a fuel and a binder, wherein the binder comprises, based on the weight of the total propellant composition:

(a) from about 3 to about 12% of a non-crystalline polyether having a molecular weight of from about 1000 to about 9,000, and

(b) from about 1 to about 12% of an inert plasticizer. Propellants of this invention can be used, for example, in ground-launched interceptors, air launched tactical motors, and space boosters.

Claims

1. A solid propellant composition comprising an oxidizer, a fuel, a binder, wherein the binder comprises, based on the weight of the total propellant composition:

(a) 3-12% of a non-crystalline polyether having a molecular weight of 1000-9000, and

(b) 1-12% of an inert plasticizer.

2. The solid propellant composition of claim 1 wherein the binder has a negative heat of explosion.

3. The solid propellant composition of claim 1, the propellant further comprising at least one additive selected from a bonding agent, burning rate additive, scavenger and catalyst.

4. The solid propellant composition of claim 1 wherein the non-crystalline polyether is selected from random copolymer of ethylene oxide and tetrahydrofuran.

5. The composition of claim 4 wherein the random copolymer has an ethylene oxide moiety content of 15-40% and a molecular weight of 1000-3000.

6. The solid propellant composition of claim 1 wherein the inert plasticizer is selected from triacetin, acetyl tri-n-butyl titrate, acetyl triethyl citrate, triethylene glycol bis-2-ethylbutyrate and tetraethylene glycol bis-2-ethylhexoate.

7. The solid propellant composition of claim 2 wherein the inert plasticizer is selected from triacetin, acetyl tri-n-butyl citrate, acetyl triethyl citrate, triethylene glycol bis-2-ethylbutyrate and tetraethylene glycol bis-2-ethylhexoate.

8. The solid propellant composition of claim 5 wherein the inert plasticizer is selected from triacetin, acetyl tri-n-butyl citrate, acetyl triethyl citrate, triethylene glycol bis-2-ethylbutyrate and tetraethylene glycol bis-2-ethylhexoate.

9. The composition of claim 1 wherein the fuel is selected from aluminum, magnesium, and zirconium powders, and mixtures thereof.

10. The composition of claim 2 wherein the fuel is selected from aluminum, magnesium, and zirconium powders, and mixtures thereof.

11. The composition of claim 5 wherein the fuel is selected from aluminum, magnesium, and zirconium powders, and mixtures thereof.

12. The composition of claim 8 wherein the fuel is selected from aluminum, magnesium, and zirconium powders, and mixtures thereof.

13. The composition of claim 1 wherein the inert plasticizer has a solubility parameter (δ

) greater than or equal to 9.

14. The composition of claim 2 wherein the inert plasticizer has a solubility parameter (δ

) greater than or equal to 9.

15. The composition of claim 5 wherein the inert plasticizer has a solubility parameter (δ

) greater than or equal to 9.

16. The composition of claim 8 wherein the inert plasticizer has a solubility parameter (δ

) greater than or equal to 9.

17. The composition of claim 9 wherein the inert plasticizer has a solubility parameter (δ

) greater than or equal to 9.

18. The composition of claim 12 wherein the inert plasticizer has a solubility parameter (δ

) greater than or equal to 9.