Double-base rocket propellants, and rocket assemblies comprising the same

• US 6,607,617 B1
• Filed: 06/01/2001
• Issued: 08/19/2003
• Est. Priority Date: 08/16/2000
• Status: Expired due to Fees

• Current Assignee: Northrop Grumman Innovation Systems, Inc. (Northrop Grumman Corporation)
• Original Assignee: Alliant Techsystems Incorporated (Northrop Grumman Corporation)
• Inventors: Blau, Reed J., Hughes, Craig D.
• Primary Examiner(s): HARDEE, JOHN R
• Application Number:
  US09/872,284
• Time in Patent Office: 809 Days
• Field of Search: 602/55, 149/19.8
• US Class Current: 149/19.8
• CPC Class Codes: C06B 23/001 Fillers, gelling and thickening agents (e.g. fibres) , absorbents for nitroglycerine binders, plasticisers for propellants C06B45/10; crosslinking or curing agents C06B45/10
• CPC Class Codes: C06B 25/24 with nitroglycerine

Abstract

This rocket motor propellant includes a combustible double-base propellant and non-carbonized, non-graphitized polymeric fibers dispersed in the double-base propellant. The double-base propellant is formed from a composition comprising nitrocellulose and at least one nitrate ester. Representative polymeric fibers include polyethylene, polypropylene, polyesters, polyamides, polyacrylonitriles and combinations thereof.

Claims

1. A rocket motor propellant comprising:

a combustible double-base propellant formed from a composition comprising nitrocellulose and at least one nitrate ester; and

non-carbonized, non-graphitized polymeric fibers dispersed in the double-base propellant.

2. A rocket motor propellant according to claim 1, wherein the polymeric fibers comprise at least one member selected from the group consisting of polyethylene, polypropylene, polyester, polyamide, and polyacrylonitrile fibers.

3. A rocket motor propellant according to claim 1, wherein the polymeric fibers comprise polyethylene.

4. A rocket motor propellant according to claim 1, wherein the polymeric fibers have an average length in the range of from about 0.05 mm to about 3 mm and average diameters in the range of from about 2 μ

m to about 40 μ

m.

5. A rocket motor propellant according to claim 1, wherein the polymeric fibers are present in the propellant in a range of about 0.02 weight percent to about 5 weight percent, based on the total weight of the propellant.

6. A rocket motor propellant according to claim 1, wherein the polymeric fibers are present in the propellant in a range of about 0.1 weight percent to about 2 weight percent, based on the total weight of the propellant.

7. A rocket motor propellant according to claim 1, wherein the nitrate ester comprises at least one member selected from the group consisting of nitroglycerin, butanetriol trinitrate, trimethyol ethane trinitrate, diethyleneglycol dinitrate, and triethyleneglycol dinitrate.

8. A rocket motor propellant according to claim 1, wherein the nitrate ester comprises butanetriol trinitrate.

9. A rocket motor assembly comprising a rocket motor case, a solid propellant grain contained in the rocket motor case, and a nozzle in operative association with the rocket motor case to receive and discharge combustion products generated upon ignition of the solid propellant grain, the solid propellant grain comprising:

a combustible double-base propellant formed from a composition comprising nitrocellulose and at least one nitrate ester; and

non-carbonized, non-graphitized polymeric fibers dispersed in the double-base propellant.

10. A rocket motor assembly according to claim 9, wherein the polymeric fibers comprise at least one member selected from the group consisting of polyethylene, polypropylene, polyester, polyamide, and polyacrylonitrile fibers.

11. A rocket motor assembly according to claim 9, wherein the polymeric fibers comprise polyethylene.

12. A rocket motor assembly according to claim 9, wherein the polymeric fibers have an average length in the range of from about 0.05 mm to about 3 mm and average diameters in the range of from about 2 μ

m to about 40 μ

m.

13. A rocket motor assembly according to claim 9, wherein the polymeric fibers are present in the solid propellant grain in a range of about 0.02 weight percent to about 5 weight percent, based on the total weight of the solid propellant grain.

14. A rocket motor assembly according to claim 9, wherein the polymeric fibers are present in the solid propellant grain in a range of about 0.1 weight percent to about 2 weight percent, based on the total weight of the solid propellant grain.

15. A rocket motor assembly according to claim 9, wherein the nitrate ester comprises at least one member selected from the group consisting of nitroglycerin, butanetriol trinitrate, trimethyol ethane trinitrate, diethyleneglycol dinitrate, and triethyleneglycol dinitrate.

16. A rocket motor assembly according to claim 9, wherein the nitrate ester comprises butanetriol trinitrate.