Propellant formulations based on dinitramide salts and energetic binders

• US 5,498,303 A
• Filed: 04/21/1993
• Issued: 03/12/1996
• Est. Priority Date: 04/21/1993
• Status: Expired due to Fees

• Current Assignee: Alliant Techsystems Incorporated (Northrop Grumman Corporation)
• Original Assignee: Thiokol Corporation (Howmet Aerospace, Inc.)
• Inventors: Wardle, Robert B., Highsmith, Tom K., Hinshaw, Carol J.
• Primary Examiner(s): Miller, Edward A.
• Application Number:
  US08/052,035
• Time in Patent Office: 1,056 Days
• Field of Search: 149/19.1, 149/19.4, 149/19.6
• US Class Current: 149/19.6
• CPC Class Codes: C06B 25/34 the compound being a nitrated acyclic, alicyclic or heterocyclic amine
• CPC Class Codes: C06B 31/00 Compositions containing an inorganic nitrogen-oxygen salt
• CPC Class Codes: C06B 45/105 The resin being a polymer bearing energetic groups or containing a soluble organic explosive

Abstract

Composite propellant formulations are disclosed having a dinitramide salt oxidizer, such as ammonium dinitramide, an energetic binder, such as poly(glycidyl nitrate), a reactive metal, such as aluminum, and other typical propellant ingredients such as curatives and stabilizers. The disclosed propellant formulations are able to combust aluminum efficiently, possess high burn rates, and produce little or no HCl exhaust gases.

Claims

1. A composite propellant formulation which does not contain chlorine comprising:

poly(glycidyl nitrate) binder having a concentration in the propellant formulation in the range from about 10% to about 35% by weight;

a dinitramide salt oxidizer in the range from about 50% to about 70% by weight;

a reactive metal selected from aluminum, magnesium aluminum-magnesium alloys, and boron, said reactive metal having a concentration in the propellant formulation in the range from about 2% to about 25% by weight; and

a polyfunctional curative.

2. A composite propellant formulation as defined in claim 1, wherein the dinitramide salt oxidizer is ammonium dinitramide (ADN).

3. A composite propellant formulation as defined in claim 1, wherein the dinitramide salt oxidizer is tetrazolium dinitramide.

4. A composite propellant formulation as defined in claim 1, wherein the dinitramide salt oxidizer is ammoniumtetrazole dinitramide.

5. A composite propellant formulation as defined in claim 1, wherein the dinitramide salt oxidizer is aminoammoniumfurazan dinitramide.

6. A composite propellant formulation as defined in claim 1, wherein the energetic binder is poly(glycidyl nitrate), the dinitramide salt oxidizer is ammonium dinitramide (ADN), and the reactive metal is aluminum.

7. A composite propellant formulation as defined in claim 1, wherein the reactive metal has a concentration in the propellant formulation in the range from about 2% to about 5% by weight.

8. A composite propellant formulation which does not contain chlorine comprising:

a poly(glycidyl nitrate) binder having a concentration in the propellant formulation in the range from about 10% to about 35% by weight;

ammonium dinitramide oxidizer in the range from about 50% to about 70% by weight;

a reactive metal selected from aluminum, magnesium aluminum-magnesium alloys, and boron, said reactive metal having a concentration in the propellant formulation in the range from about 2% to about 25% by weight; and

a polyfunctional curative, wherein the composite propellant formulation has an uncatalyzed burn rate of at least 0.76 ips at 1000 psi.

9. A composite propellant formulation as defined in claim 8, further comprising from about 0% to about 20% by weight ammonium nitrate, wherein the combined amount of ammonium nitrate and the dinitramide salt oxidizer in the composite propellant formulation does not exceed about 70% by weight.