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NOAA 2, 3, 4, 5 / ITOS D, E, E2, F, G, H


These were a series of reconfigured ITOS (Improved TIROS Operational Satellite) satellites launched with new meteorological sensors onboard to expand the operational capability of the ITOS system. NOAA was not equipped with conventional TV cameras. It was the first operational weather satellite to rely solely upon radiometric imaging to obtain cloudcover data. The primary objective of NOAA 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 primary sensors consisted of:

  • Very High Resolution Radiometer (VHRR),
  • Vertical Temperature Profile Radiometer (VTPR), and
  • Scanning Radiometer (SR).

The VHRR, VTPR, and SR 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 NOAA 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.

Nation: USA
Type / Application: Meteorology
Operator: NOAA
Contractors: RCA Astro
Equipment: VHRR, VTPR, SR
Configuration: TIROS-M Bus
Propulsion: ?
Power: 3 deployable fixed solar arrays, batteries
Mass: 309 kg (#D), ? kg (#E), 340 kg (#F), 345 kg (#G), 340 kg (#H)
Orbit: 1450 km 1456 km, 101.77 (#D), 1501 km 1512 km, 102.07 (#F), 1445 km 1460 km, 101.74 (#G), 1506 km 1521 km, 101.98 kg (#H)
Satellite COSPAR Date LS Launch Vehicle Remarks
NOAA 2 (ITOS D) 1972-082A 15.10.1972 Va SLC-2W Delta-300 with AMSAT P2A
ITOS E 1973-F06 16.07.1973 Va SLC-2W F Delta-300
NOAA 3 (ITOS F) 1973-086A 06.11.1973 Va SLC-2W Delta-300
NOAA 4 (ITOS G) 1974-089A 15.11.1974 Va SLC-2W Delta-2310 with AMSAT P2B, Intasat
NOAA 5 (ITOS H) (ex ITOS E2 ex ITOS C) 1976-077A 29.07.1976 Va SLC-2W Delta-2310

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