NASA STTR 2019-I Solicitation

Proposal Summary


PROPOSAL NUMBER:
 19-1- T12.05-3201
SUBTOPIC TITLE:
 In-situ Curing of Thermoset Resin Mixtures
PROPOSAL TITLE:
 In-Situ Application of Multi-Layer Thermal Protection System
SMALL BUSINESS CONCERN (SBC):
RESEARCH INSTITUTION (RI):
Name:  Cornerstone Research Group, Inc.
Name:  The University of Texas at Austin
Street:  510 Earl Boulevard
Street:  3925 West Braker Lane, Suite 3.340
City:  Miamisburg
City:  Austin
State/Zip:  OH 45342-6411
State/Zip:  TX 78759-5316
PHONE:  (937) 320-1877
PHONE:  (512) 232-1419

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Richard Hreha
E-mail:
hrehard@crgrp.com
Address:
510 Earl Boulevard Miamisburg, OH 45342 - 6411
Phone:
(937) 320-1877

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ms. Chrysa Theodore
E-mail:
theodorecm@crgrp.com
Address:
510 Earl Boulevard Miamisburg, OH 45342 - 6411
Phone:
(937) 320-1877
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Cornerstone Research Group Inc. (CRG) proposes to advance the state-of-the-art in space vehicle Thermal Protection Systems (TPS) through in-situ application and curing of a proprietary new resin technology called MG Resin, a family of thermoset formulations. The resins are being explored with DARPA, MDA, NASA, and the Army for a range of applications including C/C hot structures, TPS, syntactic insulation, and elastomeric rocket motor insulation among others. The materials have demonstrated high char yield, low erosion, and good mechanical performance, and are compatible with a wide variety of fillers and substrates. The overall material system is tunable to meet application, processing, and curing needs. Coupled with fillers, the resins allow a heat shield to be fabricated directly onto the vehicle and built up layer-by-layer for optimal performance to meet mission objectives. Inner layers can be filled with microballoons for insulation, outer layers filled with chopped fiber for strength, and the surface carbonized for improved ablation resistance. The hybrid materials are suitable for automated processing and the combined value is quicker and lower cost production of TPS for space exploration vehicles.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Thermal Protection Systems (TPS)

  • Aeroshells
  • Hypersonics
Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Foundry Refractory Materials

  • Furnace liners
  • Ladle liners

Fire Smoke and Toxicity Compliant Materials

  • Aircraft and marine interiors

Industrial Insulation

  • Furnaces and boilers
  • Reactors and piping
Duration: 13

Form Generated on 06/16/2019 22:59:47