Thermal Isolation of Nozzle Exit Cone Insulators

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: HQ0147-13-C-7341
Agency Tracking Number: B122-027-0523
Amount: $99,068.00
Phase: Phase I
Program: SBIR
Awards Year: 2013
Solicitation Year: 2012
Solicitation Topic Code: MDA12-027
Solicitation Number: 2012.2
Small Business Information
150 Dow Street, Tower Two, Manchester, NH, -
DUNS: 00-925-45
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Patrick McDermott
 Senior Scientist
 (703) 577-6362
Business Contact
 John Dignam
Title: President
Phone: (603) 624-9197
Research Institution
To address the issue of heat transfer from the rocket motor nozzle exit cone into the metal support housing MSI proposes to apply a well-developed, highly insulating interlayer material, quartz polysiloxane Qz/Ps, between the exit cone surface and the metal substructure surface to maintain that surface below 150 degrees F. MSI has tested this material for fabrication of a number of high performance radomes and nosecones for USG customers where surface temperatures exceed the>1500F requirement in the solicitation. The material can incorporate glass micro balloons to significantly decrease weigh and thermal conductivity and can be braided onto to an existing exit cone outer diameter shapes using well-developed manufacturing procedures. A thermal model of the heat transfer will be developed during Phase I to guide the composition of the Qz/Ps insulating interface material as regards thickness, density, micro balloons content and distribution, and thermal conductivity. Proof of principal experiments will be conducted to validate the strength of the material, as well as thermal conductivity and other measurements.

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

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