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.
Patent No.:
Date of Patent:
Apr. 16, 1991
Filed:
Oct. 26, 1987
Robert I Myers, New Hope, AL (US);
Bryce D Brubaker, Huntsville, AL (US);
Robert E Overall, Huntsville, AL (US);
Morton Thiokol, Inc., Chicago, IL (US);
Abstract
An igniter which is removably insertable in a rocket motor nozzle throat. The igniter includes a sleeve which has a body portion and a plurality of flexible and frangible tab members extending axially from one end of the body portion and spaced circumferentially thereabout and which have first portions which in combination define a diameter which is greater than the nozzle throat diameter. The frangible portions of the tab members in combination define an outer diameter which is substantially equal to the throat diameter. The body portion of the sleeve has a diameter which is greater than the throat diameter. The sleeve is insertable in the nozzle throat by flexing the tab members so that the first portions clear the throat and so that the frangible portions of the tab members are disposed in the throat. The tab members, in combination, have an inner diameter which is substantially equal to the inner diameter of the body portion of the sleeve. After the sleeve has been inserted in the throat, an igniter tube having a diameter substantially equal to the inner diameter of the sleeve is inserted into the sleeve and secured thereto thereby forcing the tab members into their original positions to lock the igniter into position during the ignition process. When the pressure in the rocket motor chamber reaches a predetermined pressure, the frangible portions of the tab members break so that the igniter is ejected from the nozzle.