US 4,391,196 AGranted

Add-on igniter for pyrogen type igniter

AssigneeThe United States of America as represented by the Secretary of the Army

InventorRobert E. Betts

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Abstract

Disclosed is an add-on pyrotechnic package to a pyrogen igniter for a solid ropellant rocket motor which employs a perforated solid propellant grain. The pyrotechnic package is comprised of a container fabricated out of a material selected from pressed paper, plastic, or metal and contains pyrotechnic pellets selected from boron-potassium nitrate (B/KNO.sub.3), aluminum-potassium perchlorate (Al/KClO.sub.4), titanium-aluminium-potassium perchlorate (Ti-Al/KClO.sub.4), and large granules of black powder. The combination of the pyrogen igniter and the add-on pyrotechnic package when fired performs the functions of sweeping away any propellant components that have migrated to the propellant surfaces or that have formed on the propellant surfaces from chemical reactions, igniting the propellant perforated grain, and maintaining the pressure in the solid propellant rocket motor chamber to achieve more efficient ignition and performance of the rocket motor.

Claims2

Dependent claims

In a solid propellant rocket motor having a solid propellant perforated grain contained in a case, an exhaust nozzle at the aft end of said case and a pyrogen igniter at the forward end of said case, said pyrogen igniter including:

(i) an exhaust nozzle for exhausting hot gases;
(ii) an add-on pyrotechnic package secured to said pyrogen exhaust nozzle, said add-on pyrotechnic package comprising a suitable container for containing pyrotechnic pellets;
and,
(iii) pyrotechnic pellets contained in said container which are ignitable by hot pyrogen exhaust gases when said hot pyrogen exhaust gases impinge upon said pellets and produces rapid burning of said pellets that are subsequently discharged in the form of hot gases and hot particles along with said hot pyrogen exhaust gases to perform the functions of rapidly sweeping away any undesirable solid propellant perforated grain constituents that have migrated to the surface of said solid propellant perforated grain or reaction products that have formed on said surface from chemical reactions, rapidly igniting said solid propellant, perforated grain, and maintaining a high pressure rate rise in said solid propellant rocket motor which achieves improved ignition and performance of said propellant rocket motor.

1 more element

Dependencies are inferred from the claim text.