NOAA-14

The AVHRR/2 was a five-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-IR), 0.725 µm to detector cutoff around 1.100 µm; channel 3 (IR window), 10.5 to 11.5 µm; channel 4 (IR window), 3.55 to 3.93 µm; and channel 5, 11.5 to 12.5 µm. All five 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/2 was made up of five modules: scanner modules, electronics modules, radiant cooler, optical system, and baseplate. The scanner module included an 80-pole hysteresis synchronous motor housing and a scan mirror. The scan motor continuously rotated the mirror at 360 rpm for cross-track scanning. The electronic module included systems for data processing, temperature control, telemetry, scan and motor logic. The radiant cooler consisted of four components. Its primary function was to shade the radiator surface and to operate the heater to maintain temperature control. The optical system consisted of a 20.3 cm aperature telescope and secondary optics which separated the radiant energy into spectral bands. The AVHRR/2 operated in either 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 products included "global area coverage" (GAC) data at a resolution of 4 km, and "local area coverage" (LAC) data, which contained data from selected portions of each orbit at a 1 km resolution. Identical experiments were flown on other spacecraft in the TIROS-N/NOAA series.[6]

The TOVS on NOAA-14 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).[7]

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-µm and 4.52-µm N₂O bands; channels 15 and 16, the 4.46-µm and 4.40-µm CO₂/N₂O bands; channel 17, the 4.24-µm CO₂ band; channels 18 and 19, the 4.0-µm and 3.7-µm window bands; and channel 20, the 0.70-µm visible region. For NOAA-I AND NOAA-J, channel 10 and 17 operate at 12.25 and 4.13 µm, respectively. Resolution for all channels is 17.4 km at nadir. The HIRS/2 instrument provides data for calculations of temperature profiles from the surface to 10 mb, water vapor content at three levels of the atmosphere, and total ozone content. HIRS/2 was made up of a scan system, optics, radiant cooler and detectors, electronics and data handling, and mechanical systems. The HIRS/2 scan mirror was stepped in synchrone with the spacecraft clock. The mirror was stepped in 1.8° steps acquiring data at 56 data points. The optical system consisted of two field stops: one for longwave and another for shortwave radiation. The instrument bandpass was defined by filters located on a filter wheel behind each field stop. A relay lens system focused the radiation on the detectors. The radiant cooler maintained temperature control for the thermal channels.[7]

The second instrument, the SSU, is provided by United Kingdom. The SSU measured temperature profiles in the upper atmosphere from 25 to 50 km in altitude. It had three channels that operated at 669.99, 669.63, and 669.36 per cm using three pressure-modulated cells containing CO₂ (at 100, 35 and 10 mb) to accomplish selective bandpass filtration of the sampled radiance. The SSU consisted of a single telescope with a 10° IFOV that was step scanned perpendicular to the subpoint track. Each scan line was composed of 8 individual 4-second steps. The SSU used uncooled pyroelectric detectors that integrated the radiance in each channel for 3.6 seconds during each step. A single 8-cm scan mirror was used for all three channels. The SSU detector was a flake of tri-glycine sulphate attached to the end of a conical gold-plated nickel pipe. The exit aperature of the pipe defined the illuminated area on the flake, and the input end of the pipe defined the field of view (FOV). The three detectors were mounted on a common block. The SSU was calibrated in synchronism with HIRS/2 once every 8 scans.[7]

The third instrument, the MSU, had four channels operating in the 50- to 60-GHz oxygen band (50.31, 53.73, 54.96 and 57.95 GHz) which obtained vertical temperature profiles free of cloud interference to an altitude of about 20 km. The MSU, developed by Jet Propulsion Laboratory (JPL), was a 4-channel Dicke radiometer and consisted of two scanning reflector antenna systems, orthomode transducers, four Dicke receivers, data programmer, and power supplies. The antennas scanned 47.4° on either side in 11 steps. Microwave energy received by each antenna was separated into vertical and horizontal polarization components by an orthomode transducer and each of the four signals was fed into one of the radiometer channels. The MSU was used along with HIRS/2 to remove data ambiguities caused by clouds. The same experiments are flown on other spacecraft in the TIROS-N/NOAA series.[7]

The Argos Data Collection and Location System (DCS) on NOAA-14 was designed to obtain 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 DCS consisted of three components: terrestrial platforms, on-board instruments, and the processing center. On-board receivers obtain transmitted signals at 401.65 MHz. Four processing channels, Data Recovery Units (DRU), operated in parallel. Each DRU consisted of a phase lock loop, bit synchronizer, doppler counter, and a data formatter. After measurement of the doppler frequency, sensor data were formatted with other instrument data, and the output data transferred to a buffer interface with the spacecraft data processor. Data from the DCS was included with the low bit rate instruments on NOAA-14. Data was processed at the Argos Data Processing Center of CNES in Toulouse, France. The DCS was expected to have a location accuracy of 5 to 8 km, and a velocity accuracy of 1.0 to 1.6 m/s. This system had the capability of acquiring data from up to 2000 platforms per day. Identical experiments are flown on other spacecraft in the TIROS-N / NOAA series.[8]

The Search and Rescue Satellite Aided Tracking system (SARSAT-COSPAS) was an international communications system for relaying search and rescue messages from ships and aircraft in distress. Cooperating organizations included NOAA, the Russian Merchant Marine, Canada Department of Defense and communications industries, and CNES/France. SARSAT equipment was provided by Canada and France to be flown on NOAA POES and on Russian polar orbiting satellites (COSPAS or "System for Search of Vessels in Distress"). The SARSAT-COSPAS system consisted of both space and ground components. The SARSAT system elements were: 1) a space-based receiver, frequency translation repeater (provided by the Department of Communications, Canada) for both existing and experimental Emergency Locator Transmitter (ELT)/Emergency Position Indicating Radio Beacons (EPIRB) bands; 2) a Local User Terminal (LUT) which received the ELT/EPIRB signals and processed the doppler data to Earth locate the transmitting platform; 3) operational and experimental ELT and EPIRB systems; 4) a space-based receiver and processor for the experimental (406 MHz) ELT/EPIRB transmissions (provided by CNES, France); and 5) the Mission Control Centers for coordinating activities, processing global data and coordinating search activities. Data from the 121.5-MHz ELTs, the 243-MHz EPIRBs, 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 (LUTs) operating in many countries (including United States, Canada, France, and Russia). The 406-MHz data were also processed by the Search and Rescue Processor (SARP), 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.[9]

The (SEM) experiment was an extension of the solar-proton monitoring experiment (SPM) flown on the ITOS spacecraft series. The objective was to measure proton flux, electron flux density, and energy spectrum in the upper atmosphere. The experiment package consisted of two detector systems and a data processing unit. The two components were: the Total Energy Detector (TED) and the Medium Energy Proton and Electron Detector (MEPED). The medium energy proton and electron detector (MEPED) measured protons in five energy ranges from 30 keV to >60 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 MEPED consisted of four directional, solid-state detector telescopes and an omni-directional sensor. The output from the detectors were connected to a signal analyzer which sensed and logically selected events above threshold values. The total energy detector (TED) measured the intensity of protons and electrons between 300 eV and 20 keV. The instrument consisted of a curved plate analyzer and a channeltron detector. Four curved plate analyzers measured incoming protons and electrons.[10]

The RAIDS was a U.S. Air Force (DoD) and NOAA test program instrument to make simultaneous measurements of the neutral and ion composition during the day and night. RAIDS used 8 ultraviolet telescopes from the extreme ultraviolet to near infrared spectral region.[11]