PhaCTIV - Phase Change Thermally Initialted Venting System

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: HQ0006-07-C-7782
Agency Tracking Number: B063-036-1135
Amount: $99,950.00
Phase: Phase I
Program: SBIR
Awards Year: 2007
Solicitation Year: 2006
Solicitation Topic Code: MDA06-036
Solicitation Number: 2006.3
Small Business Information
ZATORSKI COATING CO., INC.
77 Wopowog Road, East Hampton, CT, 06424
DUNS: 016537610
HUBZone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: N
Principal Investigator
 Ray Zatorski
 VP Engineering
 (860) 267-9889
 Zatorskico@comcast.net
Business Contact
 Ray Zatorski
Title: VP Engineering
Phone: (860) 267-9889
Email: Zatorskico@comcast.net
Research Institution
N/A
Abstract
PhaCTIV - Phase Change Thermally Initiated Venting System The Phase Change Thermally Initiated Venting System (PhaCTIV) consists of the following: 1) A structual plate (external) - low melt alloy - structual plate - thermal barrier (internal). 2) Structural plates are joined together with low-melt alloy having an operating range of 230°C to greater than 480°C, depending on requirements. 3) Thermal barrier materials (TBC) on the internal surface. The PhaCTIV is installed into sections of the motor case with the thermal barrier layer toward the interior. The thermal barrier preserves the integrity of the low-melt alloy during the firing of the motor. However an external fire will melt the alloy resulting in the structural plates falling away from the case venting the rocket motor resulting in thrust termination. This system has the following features: No pyrotechnics No energetics No sensors to activate the system No electronics No power required No maintenance The proposed thermal barrier system (TBS) also acts as an adhesive enhancement system for the propellant material. A version of the system was demonstrated in a test firing for an Army’s rocket case with a diameter of 225 mm. Both laboratory and commercial applications demonstrate that the TBC effectively insulates the low-melt alloy. This TBS is a version of the same system used in flight and land-based gas turbine engines with operating combustion temperatures in excess of 1150°F for thousands of hours. Utilizing the joining and metallurgical properties of the low-melt alloy with the structural plate system will provide strength equal to the bulk of the case. Tests are required to demonstrate that the bond strength of the plates to the low-melt alloy are stable over the anticipated temperature range of the motor during firing.

* information listed above is at the time of submission.

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