NASA Scientific and Technical Aerospace Reports

vapor line and liquid line are made of 1.6mm stainless steel tubing. The evaporator and the CC are connected on the outer
surface by a copper strap and a thermoelectric (TEC) is installed on the strap. The TEC is used to control the CC temperature
by applying an electrical current for heating or cooling. Tests performed in ambient included start-up, power cycle, sink
temperature cycle, and CC temperature control using TEC. The LHP demonstrated very robust operation in all tests where the
heat load varied between 0.5W and 1OOW, and the sink temperature varied between 243K and 293K. The heat leak from the
evaporator to the CC was extremely small. The TEC was able to control the CC temperature within +/-0.3K under all test
conditions, and the required control heater power was less than 1W.
Author
Thermoelectricity; Heat Pipes; Loads (Forces); Miniaturization; Temperature Control; Cooling
35
INSTRUMENTATION AND PHOTOGRAPHY
Includes remote sensors; measuring instruments and gages; detectors; cameras and photographic supplies; and holography. For aerial
photography see 43 Earth Resources and Remote Sensing. For related information see also 06 Avionics and Aircraft Instrumentation;
and 19 Spacecraft Instrumentation and Astrionics.
20040068186 NASA Goddard Space Flight Center, Greenbelt, MD, USA
International Thermal Detectors Workshop (TDW 2003)
Lakew, Brook, Editor; Brasunas, John, Editor; Aslam, Shahid, Editor; Fettig, Rainer, Editor; Boyle, Robert, Editor; February
2004; 159 pp.; In English; International Thermal Detectors Workshop, 19-20 Jun. 2003, Adelphi, MD, USA; See also
20040068187 - 20040068229; Original contains color and black and white illustrations
Report No.(s): NASA/CP-2004-212748; Rept-2004-00980-0; No Copyright; Avail: CASI; A08, Hardcopy
NASA’s future planetary and Earth Science missions will require ever more sensitive thermal detectors operating between
2K and 300 K. It is in response to this need that the International Workshop on thermal detectors (TDW03) was held. It put
together space borne IR/Sub-mm and heterodyne instrument scientists and astronomers, thermal detector developers,
cryocooling technologists as well as bandpass and blocking filter experts. Their varied expertise and backgrounds allowed for
a fertile discussion on outstanding issues and future detector developments. In this regard TDW03 was a great success.
Author
Measuring Instruments; Infrared Instruments
20040068187 Leicester Univ., UK
The IR Detector System for the GERB Instrument
Nelms, Nick; Butcher, Gillian; Blake, Oliver; Cole, Richard; Whitford, Chris; Holland, Andrew; International Thermal
Detectors Workshop (TDW 2003); February 2004, pp. 2-21 - 2-24; In English; See also 20040068186; No Copyright; Avail:
CASI; A01, Hardcopy
The Geostationary Earth Radiation Budget (GERB) instrument is an Earth observing scientific payload launched on-board
the European Space Agency Meteosat Second Generation (MSG) satellite in September 2002. The instrument measures
reflected and emitted radiation in two wavebands, 0.3 - 4 microns and4-30microns. The detector system comprises the focal
plane and supporting front-end electronics. The focal plane consists of a 256-element thermoelectric linear array operating at
approx. 300 K and four application specific integrated circuits (ASIC) providing parallel amplification, filtering and
digitisation. The front-end electronics are built around a digital signal processor, which performs integration and additional
filtering of the ASIC product. This paper describes in detail the design, operation and performance of the GERB detector
system.
Author
Infrared Detectors; Signal Processing; Signal Analyzers; Reflected Waves; Radiation Measurement
20040068188 Raytheon Co., Santa Barbara, CA, USA
Thermal Emission Imaging System (THEMIS)
Schueler, Carl F.; Silverman, Steven H.; Christensen, Philip R.; International Thermal Detectors Workshop (TDW 2003);
February 2004, pp. 2-29 - 2-32; In English; See also 20040068186; No Copyright; Avail: CASI; A01, Hardcopy
The Thermal Emission Imaging System (THEMIS) is based on bolt-together pushbroom optics and uncooled silicon
microbolometer focal plane array (FPA) technology. Sometimes dubbed "Mars Landsat," THEMIS was launched
in 2001 on Mars Odyssey, and provides guidance for future lander missions now in preparation for launch. Advanced materials
97