Thermal Isolation of Nozzle Exit Cone Insulators

Period of Performance: 01/28/2013 - 07/30/2013

$99.1K

Phase 1 SBIR

Recipient Firm

Mentis Sciences, Inc.
215 Canal Street
Manchester, NH 03101
Principal Investigator

Abstract

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.