The Conductive Thermal Control Material Systems for Space Applications

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX12CA43C
Agency Tracking Number: 104054
Amount: $750,000.00
Phase: Phase II
Program: SBIR
Awards Year: 2012
Solicitation Year: 2010
Solicitation Topic Code: S3.02
Solicitation Number: N/A
Small Business Information
IL, Schaumburg, IL, 60194-3884
DUNS: 113703859
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: Y
Principal Investigator
 Mukund Deshpande
 Principal Investigator
 (630) 372-9650
 m.deshpande@amseng.net
Business Contact
 Mukund (Mike) Deshpande
Title: Chief Technical Officer/CEO
Phone: (630) 372-9650
Email: m.deshpande@amseng.net
Research Institution
 Stub
Abstract
This Phase II proposal is submitted to further develop and Validate materials and process engineering of the space environment stable, multifunctional conductive thermal control material system (TCMS) that can be applied to space hardware and can enables the hardware to carry higher leakage current through engineering the high electrical conductivity. An innovative space environmental stable TCMS concepts suggested through phase I research & development work for the multifunctional, low (¿S/¿T) material systems that can meet these aggressive goals in cost effective, reliable manner have emerged as validation candidates. The suggested efforts emphasize developments in two material science areas: the first one considers the development of born nitride nano structure that includes nanotubes and nano mesh along with ZnS nano whiskers concept and the second area proposes the synthesis and processing of atmospheric plasma deposition of the various doped ZnO and Zn-Ga-Al-O compounds that are recently identified as the high conductivity compounds. The material system that integratesthese two technologies can allow higher leakage currents that may also help to defend against the natural solar storm events. The suggested TCMS have been derived from the available mathematical models for space craft charging that pay attention to the individual charge dissipation mechanisms and the molecular dynamics of the material systems as well as its thermodynamics. Thus the envisioned derived material systems can provide the needed reliable & validated TCMS in typical space environments in (LEO), (GEO) & beyond. The reliability goal for the multifunctional conductive TCMS is to have a design life of>10 years in LEO and>15 years in GEO, and we anticipate the phase II developments to mature enough by end of first year to suggest a phase II E program with investments from primes specifically ready for the hardware demonstration.

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

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