@prefix skos: <http://www.w3.org/2004/02/skos/core#> .
@prefix ns0: <http://gcmd.gsfc.nasa.gov/kms#> .

<https://gcmd.earthdata.nasa.gov/kms/concept/e8baa3a4-ef5a-455a-bf25-d61e59fc9bb3>
  skos:prefLabel "NOAA POES (Polar Orbiting Environmental Satellites)"@en ;
  a skos:Concept ;
  skos:narrower <https://gcmd.earthdata.nasa.gov/kms/concept/3e1c1312-4559-4318-a64f-d7aafd08550b> .

<https://gcmd.earthdata.nasa.gov/kms/concept/3e1c1312-4559-4318-a64f-d7aafd08550b>
  ns0:altLabel [ ] ;
  skos:definition """NOAA-4 was launched in November 1974 and was one in a series of
reconfigured ITOS satellites launched with new meteorological sensors
onboard to expand the operational capability of the ITOS system.  The
primary objective was to provide global daytime and nighttime direct
readout real-time cloudcover data on a daily basis. The
sun-synchronous spacecraft was also capable of supplying global
atmospheric temperature soundings and very high resolution infrared
cloudcover data for selected areas in either a direct readout or a
tape-recorder mode. A secondary objective was to obtain global
solar-proton flux data on a real-time daily basis. The sensors were
mounted on the satellite baseplate with their optical axes directed
vertically earthward. The nearly cubical spacecraft measured 1 by 1 by
1.2 m. The satellite was equipped with three curved solar panels that
were folded during launch and deployed after orbit was achieved. Each
panel measured over 4.2 m in length when unfolded and was covered with
approximately 3500 solar cells measuring 2 by 2 cm. The dynamics and
attitude control system maintained desired spacecraft orientation
through gyroscopic principles incorporated into the satellite
design. Earth orientation of the satellite body was maintained by
taking advantage of the precession induced from a momentum flywheel so
that the satellite body precession rate of one revolution per orbit
provided the desired 'earth-looking' attitude. Minor adjustments in
attitude and orientation were made by means of magnetic coils and by
varying the speed of the momentum flywheel.
The primary sensors consisted of a Very High Resolution Radiometer
(VHRR), Vertical Temperature Profile Radiometer (VTPR), and a Scanning
Radiometer (SR).
__________
Taken from the NSSDC System for Information Retrieval and Storage (SIRS). For
more information contact the NSSDC Coordinated Request and User Support Office,
301-286-6695 (NASA Goddard Space Flight Center, Code 933.4, Greenbelt, Maryland
20771, USA, "http://nssdc.gsfc.nasa.gov/)."""@en ;
  skos:prefLabel "NOAA-4"@en ;
  skos:inScheme <https://gcmd.earthdata.nasa.gov/kms/concepts/concept_scheme/platforms> ;
  skos:broader <https://gcmd.earthdata.nasa.gov/kms/concept/e8baa3a4-ef5a-455a-bf25-d61e59fc9bb3> ;
  a skos:Concept .

