Integrated MLI: Advanced Thermal Insulation Using Micro-Molding Technology

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNC08CA13C
Agency Tracking Number: 067039
Amount: $579,770.00
Phase: Phase II
Program: SBIR
Awards Year: 2008
Solicitation Year: 2006
Solicitation Topic Code: X9.01
Solicitation Number: N/A
Small Business Information
Quest Product Development Corporation
4900 Iris Street, Wheat Ridge, CO, 80033-2215
DUNS: 958218406
HUBZone Owned: Y
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Scott Dye
 Principal Investigator
 (303) 670-5088
 sdye@quest-corp.com
Business Contact
 Alan Kopelove
Title: Business Official
Phone: (303) 670-5088
Email: alank@quest-corp.com
Research Institution
N/A
Abstract
Lightweight, high performance thermal insulation is critical to NASA's next generation Exploration spacecraft. Zero or low cryogenic propellant boiloff is required during extended missions and lengthy on-orbit times. Multilayer insulation (MLI) is currently the insulation of choice for cryotank insulation. MLI's high vacuum performance exceeds alternative insulations by a factor of ten. However, heat flow through MLI is usually the largest heat leak in cryogenic systems, so improvements in thermal performance are desirable. Integrated Multi-Layer Insulation (IMLI) is an innovative new technology using a micro-molded polymer substructure integrated with radiation barriers to provide an ultra-high performance thermal insulation system. IMLI was proven a viable concept in Phase I work, reaching TRL4 with component validation in the laboratory. Prototypes were built and tested, demonstrating equal to lower thermal conductivity than MLI, and layers attached to each other in a snap-together assembly with controlled layer spacing. The Phase I IMLI prototype had a thermal conductivity of 1.8 W/m2, with the Celcon polymer used for these prototypes still outgassing. The IMLI thermal conductivity was calculated to be 63% that of MLI, which would provide improved long term cryogenic propellant storage. This improved insulation can provide lower thermal conductivity, vacuum compatibility, layers inherently attached to each other that support themselves, and efficient assembly. IMLI may also provide inherent structural benefits, including improved strength and integrity over current MLI. This proposal is to further develop IMLI toward commercialization. Tasks proposed include a next generation design improving on what was learned in Phase I, for material selection, fabrication methods for seams and corners including interleaving and layer thermal matching, and building and testing prototypes in realistic environments such as a 500 liter cryotank.

* information listed above is at the time of submission.

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