Low pressure exponent propellants containing boron

• US 5,074,938 A
• Filed: 05/25/1990
• Issued: 12/24/1991
• Est. Priority Date: 05/25/1990
• Status: Expired due to Fees

• Current Assignee: Alliant Techsystems Incorporated (Northrop Grumman Corporation)
• Original Assignee: Thiokol Corporation (Howmet Aerospace, Inc.)
• Inventors: Chi, Minn-Shong
• Primary Examiner(s): Lechert, Jr., Stephen J.
• Application Number:
  US07/528,938
• Time in Patent Office: 578 Days
• Field of Search: 149/2, 149/21, 149/22, 149/19.4, 149/19.5, 149/43, 149/44, 149/60, 149/88, 149/114, 149/109.6, 102/285, 102/291, 102/292
• US Class Current: 149/21
• CPC Class Codes: C06B 45/10 the organic component containing a resin
• CPC Class Codes: Y10S 149/114 Inorganic fuel

Abstract

Propellant grain consisting essentially of:

A. from about 50% to about 75% by weight of an oxidizer consisting essentially of ammonium nitrate;

B. from about 1% to about 20% by weight of a cured polymeric binder;

C. from 0% to about 30% by weight of a nitrate ester plasticizer;

D. from about 3.5% to about 8% by weight of boron in free elemental form; and

E. from 0% to about 3% by weight of aluminum metal.

The grain has a pressure exponent not exceeding about 0.30 at a combustion pressure between about 2500 and about 7000 pounds per square inch (between about 1700 and about 4800 N/cm²). Also, an uncured pourable slurry having the formula stated above, except that the binder is uncured. Also, a method for forming a propellant grain having the formula stated above, comprising the steps of providing the uncured pourable slurry defined above, pouring the slurry into a casing, and curing the slurry in situ to form a cured propellant grain having a pressure exponent not exceeding about 0.30 in the pressure range defined above.

Claims

1. A cured composite propellant grain consisting essentially of:

A. from about 50% to about 75% by weight of an oxidizer consisting essentially of ammonium nitrate;

B. from about 1% to about 20% by weight of a cured polymeric binder;

C. from 0% to about 30% by weight of a nitrate ester plasticizer;

D. from about 3.5% by weight to about 8% by weight of boron in free elemental form; and

E. from 0% to about 3% by weight aluminum metal;

said propellant having a pressure exponent not exceeding about 0.30 at a combustion pressure between about 2500 and about 7000 pounds per square inch (between about 1700 and about 4800 N/cm²).

2. The grain of claim 1, consisting essentially of from about 60% to about 75% by weight of said oxidizer.

3. The grain of claim 1, consisting essentially of from about 66% to about 71% by weight of said oxidizer.

4. The grain of claim 1, wherein said ammonium nitrate is phase-stabilized ammonium nitrate.

5. The grain of claim 1, wherein said ammonium nitrate is nickel oxide phase-stabilized ammonium nitrate.

6. The grain of claim 1, wherein said binder is a polyglycol adipate.

7. The grain of claim 1, consisting essentially of from about 5% to about 10% by weight of said binder.

8. The grain of claim 1, wherein said nitrate ester plasticizer is selected from the group consisting of triethylene glycol dinitrate, trimethylolethane trinitrate, and mixtures thereof.

9. The grain of claim 1, consisting essentially of from about 10% to about 25% by weight of said plasticizer.

10. The grain of claim 1, consisting essentially of from about 15% to about 20% by weight of said plasticizer.

11. The grain of claim 1, consisting essentially of from about 4% to about 5% by weight elemental boron.

12. The grain of claim 1, wherein said elemental boron has a particle size of about one micron.

13. The grain of claim 1, wherein said boron consists essentially of crystalline elemental boron.

14. The grain of claim 1, wherein substantially all said aluminum metal is flaked aluminum.

15. The grain of claim 1, wherein said propellant contains between 0% and about 1% by weight aluminum metal.

16. The grain of claim 1, wherein said propellant is substantially free of aluminum metal.

17. An uncured propellant composition in the form of a pourable slurry which is curable at ambient pressure to form a solid propellant grain, said slurry consisting essentially of:

A. from about 50% to about 75% by weight of an oxidizer consisting essentially of ammonium nitrate;

B. from about 1% to about 20% by weight of an uncured polymeric binder;

C. from 0% to about 30% by weight of a nitrate ester plasticizer;

D. from about 3.5% to about 8% by weight of boron in free elemental form; and

E. from 0% to about 3% by weight of aluminum metal;

said propellant being curable to form a grain having a pressure exponent not exceeding about 0.30 at a combustion pressure between about 2500 and about 7000 pounds per square inch (between about 1700 and about 4800 N/cm²).

18. A method of making a rocket motor, comprising the steps of:

A. providing a pourable slurry of uncured propellant having the composition of claim 17;

B. providing a casing having walls defining a propellant cavity;

C. pouring said slurry into said cavity, thereby forming an uncured propellant grain in said cavity conforming to the shape of said walls; and

D. curing said uncured grain in situ under conditions effective to provide a cured grain having a specific impulse not exceeding about 0.30 at a combustion pressure between about 2500 and about 7000 pounds per square inch (between about 1700 and about 4800 N/cm²).