Rapid burning propellent charge for automobile air bag inflators, rocket motors, and igniters therefor

• US 5,062,365 A
• Filed: 10/01/1990
• Issued: 11/05/1991
• Est. Priority Date: 08/18/1986
• Status: Expired due to Fees

• Current Assignee: Alliant Techsystems Incorporated (Northrop Grumman Corporation)
• Original Assignee: Thiokol Corporation (Howmet Aerospace, Inc.)
• Inventors: Canterberry, J. B.
• Primary Examiner(s): Nelson, Peter A.
• Application Number:
  US07/591,406
• Time in Patent Office: 400 Days
• Field of Search: 102/374, 102/380, 102/322, 102/290
• US Class Current: 102/322
• CPC Class Codes: B60R 21/2644 using only solid reacting substances, e.g. pellets, powder
• CPC Class Codes: C06B 21/0083 Treatment of solid structures, e.g. for coating or impregnating with a modifier compositions therefor C06B23/00
• 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
• CPC Class Codes: C06D 5/00 Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets explosive compositions containing an oxidizer, fuels for rocket engines intended for reaction with an oxidant other than air C06B
• CPC Class Codes: F42B 3/04 for producing gas under pressure generators of inflation fluid especially adapted for vehicle air bags B60R21/26
• CPC Class Codes: F42B 5/16 characterised by composition or physical dimensions or form of propellant charge, with or without projectile, or powder chemical composition C06B; F42B5/24 takes precedence

Abstract

A rapid burning propellant charge for applications including igniters, launch eject motors, and gas generators for automobile air bags. The propellant charge comprises a reticulated substrate having a quantity of interconnected ligaments and a coating of solid propellant material on the ligaments. In order to provide a large amount of surface area for a fast burn time, interstices are between coated ligaments to define propellant surface area for combustion. In applications where minimum smoke is desired, the reticulated substrate is preferably composed of carbon, graphite, or a non-combustible material, and the solid propellant material is preferably a minimum smoke type.

Claims

1. An igniter comprises a gas generant charge including a reticulated substrate having a network of interconnected ligaments and a coating of solid gas generant composition on said ligaments, said solid gas generant composition being interconnected in the form of a network, said coating has a thickness such that interstices are between coated ligaments which interstices define open gas generant surface area for supporting combustion, said interconnected ligaments defining voids which are open to each other so that the gas generant may constitute a single mass.

2. An igniter according to claim 1 wherein said reticulated substrate is composed of a material selected from the group consisting of a minimum smoke material and a non-combustible material, and said solid propellant material is a minimum smoke propellant.

3. An igniter according to claim 1 wherein said reticulated substrate is composed of a material selected from the group consisting of carbon and graphite.

10. An igniter to claim 1 wherein said reticulated substrate comprises less than about 6 percent of the volume of said gas generant charge and wherein said gas generant composition comprises at least about 90 percent of the volume of said gas generant charge.

4. A canister fired missile comprises a launch motor, a flight motor, and means for separating the launch motor from the flight motor, and said launch motor includes a case, a propellant charge within said case, a nozzle, and means for igniting said propellant charge, said propellant charge includes a reticulated substrate having a network of interconnected ligaments and a coating of solid propellant material on said ligaments, said solid propellant material being interconnected in the form of a network, said coating has a thickness such that interstices are between coated ligaments which interstices define open propellant surface area for supporting combustion, said interconnected ligaments defining voids which are open to each other so that the propellant may constitute a single mass.

5. A canister fired missile according to claim 4 wherein said reticulated substrate is composed of a material selected from the group consisting of a minimum smoke material and a non-combustible material, and said solid propellant material is a minimum smoke propellant.

6. A canister fired missile according to claim 4 wherein said reticulated substrate is composed of a material selected from the group consisting of carbon and graphite.

7. A canister fired missile according to claim 4 wherein said flight motor comprises a case, a propellant grain within said case, a nozzle, and an igniter for igniting said propellant grain, said igniter comprises a second reticulated substrate having a network of interconnected ligaments and a coating of solid propellant on said second reticulated substrate ligaments, said solid propellant material on said second reticulated substrate being interconnected in the form of a network, said coating on said second reticulated substrate has a thickness such that interstices are between said second reticulated substrate coated ligaments, said interconnected ligaments of said second reticulated substrate defining voids which are open to each other so that the propellant on said second reticulated substrate may constitute a single mass.

8. A canister fired missile according to claim 7 wherein said second reticulated substrate is composed of a material selected from the group consisting of a minimum smoke material and a non-combustible material, and said solid propellant material for said second reticulated substrate is a minimum smoke propellant.

9. A canister fired missile according to claim 7 wherein said second reticulated substrate is composed of a material selected from the group consisting of carbon and graphite.

11. A canister fired missile according to claim 4 wherein said reticulated substrate comprises less than about 6 percent of the volume of said propellant charge and wherein said propellant material comprises at least about 90 percent of the volume of said propellant charge.