NOAA-9 in space
|Mission duration||2 years (planned)|
13 years (achieved)
|Launch mass||1,420 kg (3,130 lb) |
|Dry mass||740 kg (1,630 lb)|
|Start of mission|
|Launch date||12 December 1984,|
(Atlas S/N 39E)
|Launch site||Vandenberg, SLC-3W|
|End of mission|
|Last contact||13 February 1998 |
|Reference system||Geocentric orbit |
|Perigee altitude||841 km (523 mi)|
|Apogee altitude||862 km (536 mi)|
NOAA-9, known as NOAA-F before launch, was an American weather satellite operated by the National Oceanic and Atmospheric Administration (NOAA) for use in the National Environmental Satellite Data and Information Service (NESDIS). It was the second of the Advanced TIROS-N series of satellites. 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.
The NOAA-9 satellite had a mass of 1,420 kg (3,130 lb). 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: 1) an Advanced very-high-resolution radiometer (AVHRR/2) for global cloud cover observations, 2) a TIROS Operational Vertical Sounder (TOVS) suite for atmospheric temperature and water profiling. 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). 3) an Earth radiation budget experiment (ERBE), and 4) a Solar Backscattered UltraViolet radiometer (SBUV/2). The secondary experiment was a Data Collection and Platform Location System (DCPLS). A Search and Rescue Satellite-Aided Tracking System (SARSAT) system was also carried on NOAA-9. A Space Environment Monitor (SEM) measuring proton and electron fluxes.
The AVHRR/2 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 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). 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 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 DCPLS on NOAA-9, 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 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.
The Earth Radiation Budget Experiment (ERBE) was designed to measure the energy exchange between the Earth-atmosphere system and space. The measurements of global, zonal, and regional radiation budgets on monthly time scales helped in climate prediction and in the development of statistical relationships between regional weather and radiation budget anomalies. The ERBE consisted of two instrument packages: the Non-Scanner (ERBE-NS) instrument and the Scanner (ERBS-S) instrument. The ERBE-NS instrument had five sensors, each using cavity radiometer detectors. Four of them were primarily Earth-viewing: two wide field of view (FOV) sensors viewed the entire disk of the Earth from limb to limb, approximately 135°; two medium FOV sensors viewed a 10° region. The fifth sensor was a solar monitor that measured the total radiation from the Sun. Of the four Earth-viewing sensors, one wide and one medium FOV sensors made total radiation measurements; the other two measured reflected solar radiation in the shortwave spectral band between 0.2 and 5 micrometers by using Suprasil-W filters. The Earth-emitted longwave radiation component was determined by subtracting the shortwave measurement from the total measurement. The ERBE-S instrument was a scanning radiometer which contained three narrow FOV channels. One channel measured reflected solar radiation in the shortwave spectral interval between 0.2 and 5 micrometers (µm). Another channel measured Earth-emitted radiation in the longwave spectral region from 5 to 50 µm. The third channel measured total radiation with wavelength between 0.2 and 50 µm. All three channels were located within a continuously rotating scan drum which scaned the FOV across track sequentially from horizon to horizon. Each channel made 74 radiometric measurements during each scan, and the FOV of each channel was 3 by 4.5° that covered about 40 km at the surface of Earth. The ERBE-S also viewed the Sun for calibration.
The Search and Rescue Satellite Aided Tracking (SARSAT) instruments had the capability of detecting and locating existing emergency transmitters in a manner independent of the environmental data. Data from the 121.5-MHz Emergency Locator Transmitters (ELT), the 243-MHz Emergency Position Indicating Radio Beacons (EPIRB), and experimental 406-MHz ELTs/EPIRBs were received by the Search and Rescue Repeater (SARR) and broadcast in real time on an L-band frequency (1544.5 MHz). Real-time data were monitored by local user terminals operated in the United States, Canada, and France. The 406-MHz data were also processed by the Search and Rescue Processor (SARP) and retransmitted in real time and stored on the spacecraft for later transmittal to the CDA stations in Alaska and Virginia, thus providing full global coverage. The distress signals were forwarded to Mission Control Centers located in each country for subsequent relay to the appropriate Rescue Coordination Center.
The SBUV/2 was designed to map total ozone concentrations on a global scale, and to provide the vertical distribution of ozone in the atmosphere of Earth. The instrument design was based upon the technology developed for the SBUV/TOMS flown on Nimbus 7. The SBUV/2 instrument measured backscattered solar radiation in an 11.3° field of view in the nadir direction at 12 discrete, 1.1-nm wide, wavelength bands between 252.0 and 339.8 nm. The solar irradiance was determined at the same 12 wavelength bands by deploying a diffuser which reflected sunlight into the instrument's field of view. The SBUV/2 also measured the solar irradiance or the atmospheric radiance with a continuous spectral scan from 160 to 400 nm in increments of 0.148 nm. The SBUV/2 had another narrowband filter photometer channel, called the Cloud Cover Radiometer (CCR), which continuously measured the surface of Earth brightness at 380 nm. The CCR field of view was 11.3°.
The scanner instrument malfunctioned on 20 January 1987 after an operational life of 2.1 years. The nonscanner instrument was powered off on 3 April 1997. Receipt of both telemetary and ephemeris data was discontinued. The last contact occurred on 13 February 1998. In late 1999, a transmitter on 137.5 MHz started working again, sending an unmodulated carrier. It seems to transmit while the satellite is in sunlight.