|PROPOSAL NUMBER:||03-II F3.01-9769|
|PHASE-I CONTRACT NUMBER:||NNJ04JC23C|
|SUBTOPIC TITLE:||Thermal Control Systems for Human Space Missions|
|PROPOSAL TITLE:||Integral Radiators for Next Generation Thermal Control Systems|
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Paragon Space Development Corp.
2700 E. Executive Dr., Ste. 100
Tucson ,AZ 85706 - 7151
(520) 903 - 1000
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Grant A. Anderson
2700 E. Executive Dr., Suite 100
Tucson ,AZ 85706 -7151
(520) 903 - 1000
U.S. Citizen or Legal Resident: Yes
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Integral radiators integrate the primary structural system and the thermal rejection system into a dual function subsystem allowing for reduced weight. The design of these systems require a careful trade-off of thermal fluids, structural materials, thermal coatings and structural shape. The Paragon Crescent panels are a family of solutions that allow a highly efficient stressed skin, semi-monocoque structure to also be a radiator on the external surface of a Apollo-like Service Module as envisioned for the CEV. The resulting design optimizes the structural/thermal trade-off while allowing for practical considerations of manufacturability, ground handling, testing, and access. The baseline materials and fluids chosen address cost, safety and robust design. Some coating development is still needed to meet the handling requirements. The structural concept will need to be tested to validate modeling predictions and gain experience in structural behavior. Finally, full up radiator panels need to be manufactured and tested to validate the manufacturing methods, thermal analysis, and overall radiator/thermal fluid choices.
POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The technology developed herein is directly applicable to the emerging CEV design and has the potential to be an enabler for maintaining the CEV as a small, agile but sophisticated vehicle. The potential prime contractors for CEV and other Exploration Initiative systems can all benefit from this innovation. A point design of the innovation shows that the structural/thermal radiator mass savings to a candidate Apollo Service Module-like CEV spacecraft could be as high as 40%, or 800-1000 lbs.
POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The application of this innovation is not limited to manned systems. Commercial and military satellites with commensurate heat dissipation/spacecraft size ratios also benefit from the innovations developed during the course of this SBIR. Structurally integrated radiators are also ideal configurations for high temperature radiator concepts still in the conceptual stage for use in nuclear or high-powered satellites.