Use of graphite fibers to augment propellant burning rate

• US 4,072,546 A
• Filed: 11/05/1975
• Issued: 02/07/1978
• Est. Priority Date: 12/22/1971
• Status: Expired due to Term

• Current Assignee: Hercules Incorporated (Ashland Global Holdings, Inc.)
• Original Assignee: Hercules Incorporated (Ashland Global Holdings, Inc.)
• Inventors: Winer, Richard
• Primary Examiner(s): Miller, Edward A.
• Application Number:
  US05/628,863
• Time in Patent Office: 825 Days
• Field of Search: 149/2, 149/19.8, 149/19.9, 149/20, 149/21, 149/96, 149/100, 149/108.2, 102/102, 264/3 B, 264/3 C
• 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 45/00 Compositions or products which are defined by structure or arrangement of component of product explosive charges of particular form or shape F42B1/00, F42B3/00

Abstract

Solid propellant compositions having graphite fibers dispersed throughout the propellant are provided. The graphite fibers augment the burning rate of the solid propellant.

Claims

1. A solid propellant composition for use as a solid propellant in rocket motors, said composition being selected from the group consisting of single base, double base, triple base composite and composite modified double base composition types, said solid propellant composition containing a multiplicity of graphite fibers having diameters of from about 4 microns to about 10 microns substantially uniformly distributed throughout said solid propellant composition said graphite fibers comprising from about 0.03% to about 10% by weight based on the weight of the solid propellant composition.

2. The solid propellant composition of claim 1 in which the graphite fibers comprise from about 0.5% to about 6% by weight based on the weight of the solid propellant composition.

3. The solid propellant composition of claim 1 in which the propellant composition is of the single base type.

4. The solid propellant composition of claim 1 in which the propellant composition is of the double base type.

5. The solid propellant composition of claim 1 in which the propellant composition is of the triple base type.

6. The solid propellant composition of claim 1 in which the propellant composition is of the composite type.

7. The solid propellant composition of claim 6 in which the composite propellant comprises an inorganic oxidizing agent and a binder prepared from carboxyterminated polybutadiene.

8. The solid propellant composition of claim 7 in which the oxidizing agent is ammonium perchlorate.

9. The solid propellant composition of claim 7 in which the oxidizing agent is an organic type oxidizing agent selected from the group consisting of cyclotrimethylene trinitramine, cyclotetramethylene tetranitramine, pentaerythritol tetranitrate, ethylene dinitramine, and mixtures thereof.

10. The solid propellant composition of claim 1 in which the composition is in the shape of a propellant granule having a longitudinal axis and a substantial proportion of the graphite fibers are oriented parallel to said longitudinal axis.

11. In a rocket motor utilizing a solid propellant composition selected from the group consisting of single base, double base, triple base, composite and composite modified double base composition types as the source of propulsion, the improvement comprising said solid propellant composition having incorporated therein a multiplicity of graphite fibers having diameters of from about 4 microns to about 10 microns, said fibers being substantially uniformly distributed throughout said solid propellant composition, said graphite fibers comprising from about 0.03% to about 10% by weight based on the weight of the propellant composition, whereby the burning rate of said solid propellant composition is increased.

12. The rocket motor of claim 11 in which said graphite fibers comprise from about 0.5% to about 6% by weight based on the weight of the propellant composition.