Robust Engineered Thermal Control Material Systems for Crew Exploration Vehicle (CEV) and Prometheus Needs

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$599,999.00
Award Year:
2007
Program:
SBIR
Phase:
Phase II
Contract:
NNC07CA16C
Award Id:
77641
Agency Tracking Number:
053332
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
2309 Pennsbury Ct., Schaumburg, IL, 60194
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
113703859
Principal Investigator:
Mukund Deshpande
Principal Investigator
(630) 372-9650
m.deshpande@amseng.net
Business Contact:
Mukund Deshpande
CTO
(630) 372-9650
m.deshpande@amseng.net
Research Institution:
n/a
Abstract
This innovative SBIR Phase II proposal plans to develop new multifunctional high temperature capable TCMS technologies based on the identified needs for the thermal control and ESD functions of the exploration mission hardware and also for the heat rejection system. These efforts can also serve uniquely the Crew Exploration Vehicle radiator systems needs. The TCMS for the radiators of the both CEV and exploration missions need to operate at higher elevated temperatures and provide the space environment stable low ratio of (solar absorptance/emittance) performance in high radiation orbits involving intense UV, electrons and protons along with stable charge mitigation. The CEV application also needs it to withstand typical launch environments. According to the phase I findings, none of the state-of-an-art material systems that are currently in use are designed for the needs of the space environment stable operation at elevated temperatures, and hence, can not meet the same. The Phase I efforts proved the feasibility and identified the next generation solid state chemistries and processing requirements that can provide the multifunctional space stable performance at higher temperatures and also provided the unique guidance for tailoring the ESD performance when these very large thermal control areas get exposed to very low temperatures. The proposed phase II efforts will continue R&D and scale up the synthesis of the identified candidate engineered passivated pigments and validate its space environment stability with use of recently developed next generation negative CTE passivated additives with abilities to tailor CTE, thermal shock and thermal cycling performance. Thus, these Phase II efforts can provide the next generation "Robust" validated TCMS products that can be exposed to the elevated temperatures (500C) and conducting tasks geared towards putting together plasma spray technology and experience base as applied to TCMS for various exploration missions.

* information listed above is at the time of submission.

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