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Thermal Isolation of Solid Rocket Motor Exit Cone and Nozzle

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: HQ0147-14-C-7031
Agency Tracking Number: B2-1980
Amount: $973,887.00
Phase: Phase II
Program: SBIR
Solicitation Topic Code: MDA12-027
Solicitation Number: 2012.2
Timeline
Solicitation Year: 2012
Award Year: 2014
Award Start Date (Proposal Award Date): 2014-09-26
Award End Date (Contract End Date): 2016-09-24
Small Business Information
4914 Moores Mill Road
Huntsville, AL 35811-1558
United States
DUNS: 799114574
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Daniel Butts
 Senior Materials Engineer
 (256) 851-7653
 dbutts@plasmapros.com
Business Contact
 Timothy McKechnie
Title: President
Phone: (256) 851-7653
Email: timmck@plasmapros.com
Research Institution
 Stub
Abstract

Primary missile structures, ancillary mechanical and electrical sub-components of missile propulsion systems must be thermally isolated from hot propulsion gases. Silica-cloth phenolic and carbon-cloth phenolic are the go-to legacy insulator materials of choice. However, these materials have limited temperature use; mechanical degradation with decomposition of the matrix; and high thermal conductivity in the charred state. At present, burn durations, flame temperatures and inter-pulse delays are constrained to avoid overheating. The objective a Phase II investigation is to develop and evaluate a low cost, high payoff ceramic-based laminar composite. Results of material property studies will provide input for trade studies to investigate the benefits and payoff of this technology in multiple propulsion systems. Favorable insulator designs will be evaluated in sub-scale test motors. Approved for Public Release 14-MDA-7739 (18 March 14).

* Information listed above is at the time of submission. *

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