NASA SBIR 2006 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER:06 X9.01-8488
SUBTOPIC TITLE:Long Term Cryogenic Propellant Storage, Management, and Acquisition
PROPOSAL TITLE:Integrated MLI: Advanced Thermal Insulation using Micro-molding Technology

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Quest Product Development Corporation
4975 Miller Street
Wheat Ridge, CO 80033-2215
(303) 670-5088

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Scott   Dye
sdye@quest-corp.com
4975 Miller Street
Wheat Ridge, CO  80033-2215
(303) 670-5088

TECHNICAL ABSTRACT ( Limit 2000 characters, approximately 200 words)
Current Multilayer Insulation (MLI) technology is over 50 years old, and is typically comprised of 10 to 120 layers of metalized polymer films separated by polyester netting. MLI is the best thermal insulation in a vacuum, and is the insulation of choice for spacecraft and cryogenic system insulation, but has problems relating to density control and performance, application labor, and difficulty covering small and large scales.

An innovative concept for improved cryogenic insulation, Integrated MLI, is proposed based on a micro-machined or micro-molded substructure. Thermal conductivity will be lower than conventional MLI, layers would be inherently attached to each other and support one another, construction would be easier, and the vacuum shell could be supported by the IMLI, greatly reducing the mass of the insulation system with vacuum shells used to insulate cryogenic dewars or tanks.

An improved insulation should provide lower thermal conductivity, lower specific thermal conductivity, vacuum compatibility, layers inherently attached to each other that support themselves, efficient assembly and provide structural reliability.

Recent advances in injection molding has resulted in the ability to mold structures with very small features, comprised of materials with low thermal conductivity and low outgassing. Integrated MLI will consist of small micro-machined or micro-molded structures that support radiation barrier layers, and will offer significant advantages. Preliminary analysis of several potential designs indicates IMLI has a theoretical thermal conductivity less than half that of MLI, allowing improved long term cryogenic propellant storage and spacecraft thermal performance. It may provide improved structural assembly, strength and integrity over current MLI.

This proposal is to work on the design, material selection, assembly processes and preliminary physical property testing of a prototype of this innovative new thermal insulation.

POTENTIAL NASA COMMERCIAL APPLICATIONS ( Limit 1500 characters, approximately 150 words)
Integrated MLI might provide improved thermal performance and have improved structural integrity for spacecraft cryogenic propellant storage and thermal insulation. Other standard spacecraft insulation uses, such as insulating instruments, or insulating and preserving liquid hydrogen or liquid oxygen cryogenic systems and dewars, might also be well served by IMLI.

IMLI could provide the cryogenic insulation and vacuum shell used to insulation and maintain cryogenics on space instruments, satellites, CEV/CLV spacecraft cabins and lunar surface habitats. It may be able to provide substantially longer term cryogenic storage, helping enable longer term manned space flights. Low mass, low thermal conductance cryotank structural systems are of interest to NASA.

IMLI may have excellent properties required for spacecraft use; low thermal conductance, vacuum compatibility of materials, inherent control of layer dimensions and density, self-supporting layers with a post-and-beam substructure, ease of assembly for small and large areas, potential for both tight seams and material flexibility.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS ( Limit 1500 characters, approximately 150 words)
Extremely efficient thermal insulation, easily assembled and applied to cover various surfaces, would have utility in commercial cryogenic applications such as cryogenic vessels and pipes in scientific and industrial applications. A major use would be insulating dewars for liquid nitrogen, liquid helium, liquid oxygen, etc., which are widely found in research and industrial uses.

Other potential applications include large commercial tanks, industrial boilers and industrial hot and cold process equipment, refrigerated trucks and trailers, insulated tank, container and rail cars, liquid hydrogen fueled aircraft or fuel cells, appliances such as refrigerators and freezers, hot water heaters, Thermos type liquid containers, picnic and mobile containers to keep foods hot or cold, marine refrigeration, potentially even house structures.

NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.

TECHNOLOGY TAXONOMY MAPPING
Fluid Storage and Handling
Propellant Storage
Thermal Insulating Materials


Form Printed on 09-08-06 18:19