@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/75b34f33-a790-4164-9cc0-02a997279e61>
  skos:prefLabel "TIROS"@en ;
  a skos:Concept ;
  skos:narrower <https://gcmd.earthdata.nasa.gov/kms/concept/292335bb-5733-4f54-bb1f-84ab20f838f3> .

<https://gcmd.earthdata.nasa.gov/kms/concept/292335bb-5733-4f54-bb1f-84ab20f838f3>
  ns0:resource [ ] ;
  ns0:altLabel [ ] ;
  skos:definition """The ITOS (Improved Tiros Operational Satellite) series (TIROS-M
was the prototype spacecraft) were the second generation of
operational sun-synchronous meteorological
spacecraft. Operational satellites were renamed NOAA.

The primary objective of ITOS was to provide improved
operational infrared and visual observations of earth cloud
cover for use in weather analysis and forecasting. Secondary
objectives included providing both solar proton and global heat
balance data on a regular daily basis. To accomplish these
tasks, the spacecraft carried:

-two television cameras for Automatic Picture Transmission (APT) and
-two Advanced Vidicon Camera System (AVCS) cameras. It also carried
-a low-resolution Flat Plate Radiometer (FPR),
-a Solar Proton Monitor (SPM), and
-two scanning radiometers that not only measured emitted infrared
radiation, but also served as a backup system for the APT and AVCS
cameras.

The nearly cubical spacecraft measured 1 by 1 by 1.2 m. The TV
cameras and infrared sensors were mounted on the satellite
baseplate with their optical axes directed verticially
earthward. 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 3420 solar cells, each measuring 2
by 2 cm. The ITOS 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.

Additional information available at
"http://www.skyrocket.de/space/doc_sdat/noaa_itos-a.htm"


Group: Platform_Details
   Entry_ID: TIROS-M
   Group: Platform_Identification
      Platform_Category: Earth Observation Satellites
      Platform_Series_or_Entity: TIROS
      Short_Name: TIROS-M
      Long_Name: Television Infrared Observation Satellite-M
   End_Group
   Group: Synonymous_Platform_Names
      Short_Name: ITOS
   End_Group
   Group: Platform_Associated_Instruments
      Short_Name: HRIR
   End_Group
   Creation_Date: 2007-11-14
   Online_Resource: http://www.skyrocket.de/space/doc_sdat/noaa_itos-a.htm
   Sample_Image: http://www.photolib.noaa.gov/700s/spac0170.jpg
   Group: Platform_Logistics
      Launch_Date: 1970-01-23
      Primary_Sponsor: NASA
   End_Group
End_Group"""@en ;
  skos:prefLabel "TIROS-M"@en ;
  skos:inScheme <https://gcmd.earthdata.nasa.gov/kms/concepts/concept_scheme/platforms> ;
  skos:broader <https://gcmd.earthdata.nasa.gov/kms/concept/75b34f33-a790-4164-9cc0-02a997279e61> ;
  a skos:Concept .

