|Mission duration||2 years (planned)|
339 days (achieved)
|Manufacturer||RCA Astro Electronics |
|Launch mass||1,418 kg (3,126 lb) |
|Dry mass||735 kg (1,620 lb)|
|Start of mission|
|Launch date||29 May 1980, 10:53:00 UTC |
(Atlas S/N 19F) 
|Launch site||Vandenberg, SLC-3W|
|End of mission|
|Decay date||3 May 1981 |
|Reference system||Geocentric orbit |
|Perigee altitude||273 km (170 mi)|
|Apogee altitude||1,453 km (903 mi)|
NOAA B was an American operational weather satellite for use in the National Operational Environmental Satellite System (NOESS) and for the support of the Global Atmospheric Research Program (GARP) during 1978-1984. The satellite design provided an economical and stable Sun-synchronous platform for advanced operational instruments to measure the atmosphere of Earth, its surface and cloud cover, and the near-space environment.
NOAA-B was launched by NASA on 29 May 1980 at 10:53 UTC. Intended for a Sun-synchronous orbit, the spacecraft entered a lower, elliptical orbit due to a launch vehicle malfunction resulting in a failed mission. Had the launch been successful it would have been designated NOAA-7.
Following launch, a fuel leak between the turbopump and gearbox caused the main engine to lose 20–25% of its thrust. This caused the guidance system of the Atlas launch vehicle to increase the length of the first stage burn to compensate.
Due to requirements specific to TIROS missions, there was no interface between the satellite and the launch vehicle guidance systems. This resulted in the satellite attempting to separate from the launch vehicle at approximately 370 seconds after launch. The separation failed due to recontact between the Atlas - which was still under thrust - and the satellite, which only separated when the solid-fuel rocket motor intended to place NOAA-B into a circular 830 km (520 mi) Sun-synchronous orbit fired.
The satellite was based upon the DMSP Block 5D satellite bus developed for the U.S. Air Force, and it was capable of maintaining an Earth-pointing accuracy of better than ± 0.1° with a motion rate of less than 0.035 degrees/second.
Primary sensors included the Advanced Very High Resolution Radiometer (AVHRR/1) for global cloud cover observations, and the TIROS Operational Vertical Sounder (TOVS) suite for atmospheric temperature and water profiling. Secondary experiments consisted of a Space Environment Monitor (SEM) measuring proton and electron fluxes, and the Data Collection and Platform Location System (DCPLS) for relaying data from balloons and ocean buoys for the Argos system. The TOVS suite consists of three subsystems: the High Resolution Infrared Radiation Sounder 2 (HIRS/2), the Stratospheric Sounding Unit (SSU), and the Microwave Sounding Unit (MSU).
The NOAA 6 Advanced Very High Resolution Radiometer (AVHRR/1) was a four-channel scanning radiometer capable of providing global daytime and nighttime sea-surface temperature and information about ice, snow, and clouds. These data were obtained on a daily basis for use in weather analysis and forecasting. The multispectral radiometer operated in the scanning mode and measured emitted and reflected radiation in the following spectral intervals: channel 1 (visible), 0.55 to 0.90 micrometer (µm); channel 2 (near infrared), 0.725 µm to detector cutoff around 1.1 µm; channel 3 (IR window), 3.55 to 3.93 µm; and channel 4 (IR window), 10.5 to 11.5 µm. All four channels had a spatial resolution of 1.1 km, and the two IR-window channels had a thermal resolution of 0.12 Kelvin at 300 Kelvin. The AVHRR was capable of operating in both real-time or recorded modes. Real-time or direct readout data were transmitted to ground stations both at low (4 km) resolution via automatic picture transmission (APT) and at high (1 km) resolution via high-resolution picture transmission (HRPT). Data recorded on board were available for processing in the NOAA central computer facility. They included global area coverage (GAC) data, with a resolution of 4 km, and local area coverage (LAC), that contained data from selected portions of each orbit with a 1-km resolution. Identical experiments were flown on other spacecraft in the TIROS-N/NOAA series.
The TIROS Operational Vertical Sounder (TOVS) consisted of three instruments: the High-resolution Infrared Radiation Sounder modification 2 (HIRS/2), the Stratospheric Sounding Unit (SSU), and the Microwave Sounding Unit (MSU). All three instruments were designed to determine radiances needed to calculate temperature and humidity profiles of the atmosphere from the surface to the stratosphere (approximately 1 mb). The HIRS/2 instrument had 20 channels in the following spectral intervals: channels 1 through 5 , the 15-micrometer (µm) CO2 bands (15.0, 14.7, 14.5, 14.2, and 14.0 µm); channels 6 and 7, the 13.7- and 13.4-µm CO2/H2O bands; channel 8, the 11.1-µm window region; channel 9, the 9.7-µm ozone band; channels 10, 11, and 12, the 6-µm water vapor bands (8.3, 7.3, and 6.7 µm); channels 13 and 14, the 4.57- and 4.52-µm N2O bands; channels 15 and 16, the 4.46- and 4.40-µm CO2/N2O bands; channel 17, the 4.24-µm CO2 band; channels 18 and 19, the 4.0- and 3.7-µm window bands; and channel 20, the 0.70-µm visible region. The SSU instrument was provided by the British Meteorological Office (United Kingdom). It was similar to the Pressure-Modulated Radiometer (PMR) flown on Nimbus 6. The SSU operated at three 15.0-µm channels using selective absorption, passing the incoming radiation through three pressure-modulated cells containing CO2. The MSU instrument was similar to the Scanning Microwave Spectrometer (SCAMS) flown on Nimbus 6. The MSU had one channel in the 50.31-GHz window region and three channels in the 55-GHz oxygen band (53.73, 54.96, and 57.95 GHz) to obtain temperature profiles which were free of cloud interference. The HIRS/2 had a field of view (FOV) 30 km in diameter at nadir, whereas the MSU had a FOV of 110 km in diameter. The HIRS/2 sampled 56 FOVs in each scan line about 2250 km wide, and the MSU sampled 11 FOVs along the swath with the same width. Each SSU scan line had 8 FOVs with a width of 1500 km. This experiment was also flown on other TIROS-N/NOAA series spacecraft.
The Data Collection and Platform Location System (DCPLS) on NOAA-B, also known as Argos, was designed and built in France to meet the meteorological data needs of the United States and to support the Global Atmospheric Research Program (GARP). The system received low-duty-cycle transmissions of meteorological observations from free-floating balloons, ocean buoys, other satellites, and fixed ground-based sensor platforms distributed around the globe. These observations were organized on board the spacecraft and retransmitted when the spacecraft came within range of a Command and Data Acquisition (CDA) station. For free-moving balloons, the Doppler frequency shift of the transmitted signal was observed to calculate the location of the balloons. The DCPLS was expected, for a moving sensor platform, to have a location accuracy of 3 to 5 km, and a velocity accuracy of 1.0 to 1.6 m/s. This system had the capability of acquiring data from up to 4000 platforms per day. Identical experiments were flown on other spacecraft in the TIROS-N/NOAA series. Processing and dissemination of data were handled by CNES in Toulouse, France.
The Space Environmental Monitor (SEM) was an extension of the solar proton monitoring experiment flown on the ITOS spacecraft series. The object was to measure proton flux, electron flux density, and energy spectrum in the upper atmosphere. The experiment package consisted of three detector systems and a data processing unit. The Medium Energy Proton and Electron Detector (MEPED) measured protons in five energy ranges from 30 keV to >2.5 MeV; electrons above 30, 100, and 300 keV; protons and electrons (inseparable) above 6 MeV; and omni-directional protons above 16, 36, and 80 MeV. The High-Energy Proton Alpha Telescope (HEPAT), which had a 48° viewing cone, viewed in the anti-Earth direction and measured protons in four energy ranges above 370 MeV and alpha particles in two energy ranges above 850 MeV/nucleon. The Total Energy Detector (TED) measured electrons and protons between 300 eV and 20 keV.
Because the satellite had been unable to perform the pitch-down maneuver necessary to reach its intended orbit the spacecraft ended up in a highly elliptical orbit that was unsuitable for the intended mission. Following unsuccessful attempts to correct the orbit using the satellite's attitude control thrusters, NASA pronounced the mission a failure.
Unlike the earlier Nimbus 1, which was also launched into an unplanned elliptical orbit following a launch vehicle malfunction, no attempt appears to have been made to operate the spacecraft instrumentation during its remaining lifetime in orbit.