Earth Observing-1 Technology Validation: Carbon-Carbon Radiator Panel Swales Aerospace

Format:

Conference/Event

Author/Creator:

Teti, Nicholas M., author.

Conference Name:

International Conference On Environmental Systems (2003-07-07 : Vancouver, Canada)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 2003

Summary:

The Earth Observing-1 spacecraft, built by Swales Aerospace for NASA's Goddard Space Flight Center (GSFC), was successfully launched on a Boeing Delta-II ELV on November 21, 2000. The EO-1 spacecraft thermal design is a cold bias design using passive radiators, regulated conductive paths, thermal coatings, louvers, thermostatically controlled heaters and multi-layer insulating (MLI) blankets. Five of the six passive radiators were aluminum honeycomb panels. The sixth panel was a technology demonstration referred to as the Carbon Carbon Radiator (CCR) panel. Carbon-Carbon (C-C) is a special class of composite materials in which both the reinforcing fibers and matrix materials are made of pure carbon. The use of high conductivity fibers in C-C fabrication yields composite materials that have high stiffness and high thermal conductivity. The primary thermal function of the EO-1 CCR is to readiatoe the 27.8 watts generated by the EO-1 Power Supply Electronics (PSE) and the 16.3 watts (peak power) generated by the Linear Etalon Imaging Spectral Array/Atmospheric Corrector (LEISA/AC) electronics boxes. The panel is also a structural member and must support the combined weight of the PSE (22.7 kg) and the LEISA/AC (4.5 kg) boxes and the dynamic an static loads during EO-1 integration, launch and orbit induced stresses. This paper presents the current on-orbit status of the CCR, the pre and post flight thermal model correlation results, lessons learned, and the current and future used of Carbon-Carbon materials

Notes:

Vendor supplied data

Publisher Number:

2003-01-2345

Access Restriction:

Restricted for use by site license