The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Feb. 12, 1985

Filed:

Feb. 02, 1983
Applicant:
Inventor:

C Max White, Brigham City, UT (US);

Assignee:

Thiokol Corporation, Chicago, IL (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F02K / ;
U.S. Cl.
CPC ...
60256 ; 60 39821 ; 60 39823 ; 102202 ;
Abstract

A consumable wafer-like igniter for high-performance rocket motors having a full, head-end web of propellant in the forward end of the motor includes a hat-shaped urethane housing. The housing comprises a flat disk attached to one end of a short cylinder, a flange being attached to the other end for attachment of the igniter directly to the rocket motor propellant. A disk of solid propellant attached to the inside of the housing disk has holes formed therein and has radial grooves in the surface facing the rocket motor propellant for directing gases from the burning propellant through holes that are provided in the peripheral surface of the cylinder. A liner on the inside surface of the cylinder has holes that are in alignment with the holes in the cylinder but which, normally, are smaller. An igniter initiator having a tubular urethane housing is positioned adjacent the solid propellant disk. Upon ignition of the solid propellant disk, as the internal pressure within the igniter becomes greater, the holes in the liner expand, releasing the hot gases in a smoothly increasing volume thereby to provide rapid and reliable ignition of the rocket motor propellant before the igniter is consumed by combustion or becomes detached from the rocket motor propellant due to erosion of the latter.


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