Regenerative monopropellant airbag inflator

• US 5,851,030 A
• Filed: 12/03/1996
• Issued: 12/22/1998
• Est. Priority Date: 12/03/1996
• Status: Expired due to Fees

• Current Assignee: Morton International Incorporated (Autoliv Incorporated)
• Original Assignee: Autoliv ASP Incorporated (Autoliv Incorporated)
• Inventors: Johnson, Darrin L., Harris, Bradley D., Lauritzen, Donald R.
• Primary Examiner(s): Jordan, Charles T.
• Assistant Examiner(s): Wesson, Theresa M.
• Application Number:
  US08/759,995
• Time in Patent Office: 749 Days
• Field of Search: 280/741, 280/742, 280/736, 102/530, 102/531
• US Class Current: 280/741
• CPC Class Codes: B60R 21/264 using instantaneous generation of gas, e.g. pyrotechnic B60R21/268 takes precedence
• 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

Abstract

A regenerative monopropellant inflator having improved initiation of the regenerative cycle and improve operating efficiency. The inflator may direct the flow of the monopropellant into a localized volume to create a "hot spot" to increase combustion. This serves to ensure that the regenerative cycle is initiated. Various arrangements are provided to increase the residence time of the combusting monopropellant within the inflator, to ensure complete combustion of the monopropellant, and thus increased efficiency. These arrangements include inducing a helical gas flow to increase the length of the path traveled by the gas. Various barriers may also be placed within the gas flow to force direction changes, which reduce the velocity of the gas.

Claims

1. A regenerative monopropellant airbag inflator, comprising:

a housing having a longitudinal axis and defining an interior, said interior including at least one exit port extending through said housing;

an piston within said interior, said piston dividing said interior into a fuel supply chamber and a combustion chamber, said exit port communicating with said combustion chamber, and said piston being mounted for movement along said longitudinal axis;

a quantity of fluid monopropellant housed within said fuel supply chamber;

an initiator operatively associated with said combustion chamber;

a plurality of injection ports extending through said piston for flow of said fluid monopropellant from said fuel supply chamber to said combustion chamber, said injection ports being oriented to focus said fluid monopropellant to a localized area within said combustion chamber; and

an isolation cup mounted within said combustion chamber, said isolation cup including a concavity facing said piston, and wherein said localized area is located within said concavity.

2. An inflator as in claim 1, further including an isolation cup mounted within said combustion chamber, said isolation cup including a cavity facing said piston, and wherein said localized area is located within said concavity.

3. An inflator as in claim 2, further including a swirl chamber mounted within said combustion chamber, said swirl chamber having a peripheral wall and first and second ends, and a plurality of entrance ports extending through said peripheral wall, said second end communicating with said at least one exit port.

4. An inflator as in claim 3, wherein said entrance ports are angled to direct flow therethrough to said first end of said swirl chamber.

5. An inflator as in claim 3, wherein said entrance ports are angled with respect to radial to direct flow therethrough in a circular swirl within said swirl chamber.

6. An inflator as in claim 5, wherein said entrance ports are further angled to direct flow therethrough to said first end of said swirl chamber.

7. An inflator as in claim 6, wherein said first end of said swirl chamber has a hemisphere shape to smoothly turn gas flow toward said second end.

8. An inflator as in claim 7, wherein said at least one exit port comprises a single exit port, centered within said second end, and wherein said second end has a truncated annulus shape, with said exit port within said annulus shape.

9. A regenerative monopropellant airbag inflator, comprising:

a housing having a longitudinal axis and defining an interior, said interior including at least one exit port extending through said housing;

an piston within said interior, said piston dividing said interior into a fuel supply chamber and a combustion chamber, said exit port communicating with said combustion chamber, and said piston being mounted for movement along said longitudinal axis;

a quantity of fluid monopropellant housed within said fuel supply chamber;

an initiator operatively associated with said combustion chamber; and

a plurality of injection ports extending through said piston for flow of said fluid monopropellant from said fuel supply chamber to said combustion chamber, said injection ports being oriented to focus said fluid monopropellant to a localized area within said combustion chamber wherein said injection ports each include an inlet and an outlet, and said inlets are angularly offset, about said longitudinal axis, with respect to said outlets, to cause a helical flow within said combustion chamber.

10. An inflator as in claim 9, further including an isolation cup mounted within said combustion chamber, said isolation cup including a cavity facing said piston, and wherein said localized area is located within said concavity.

11. An inflator as in claim 9, wherein at least a portion of said inlets of said injection ports are located on a peripheral edge of said piston.

12. A regenerative monopropellant airbag inflator, comprising:

a housing having a longitudinal axis an defining an interior, said interior including at least one exit port extending through said housing;

a piston within said interior, said piston dividing said interior into a fuel supply chamber and a combustion chamber, said exit port communicating with said combustion chamber, and said piston being mounted for movement along said longitudinal axis;

a quantity of fluid monopropellant housed within said fuel supply chamber;

an initiator operatively associated with said combustion chamber; and

a plurality of injection ports extending through said piston for flow of said fluid monopropellant fuel from said fuel supply chamber to said combustion chamber, each of said injection ports having an inlet and an outlet, said inlets being angularly offset, about said longitudinal axis, with respect to said outlets, to cause a helical flow within said combustion chamber.

13. An inflator as in claim 12, wherein at least a portion of said inlets are located on a peripheral edge of said piston.

14. An inflator as in claim 12, further including an isolation cup mounted within said combustion chamber, said isolation cup including a cavity facing said piston, and wherein at least a portion of said flow is directed to a localized volume within said concavity.

15. An inflator as in claim 14, wherein at least a portion of said inlets of said injection ports are located on a peripheral edge of said piston.