|Adeos - |
Credit: NASDA. 11,030 bytes. 299 x 224 pixels.
The polar orbiting ADEOS spacecraft was to perform Earth, atmospheric, and oceanographic remote sensing. ADEOS 1 and 2 used the same bus design to fly different instrument suites. These were the largest satellites Japan had ever developed. Several of the instruments on ADEOS were provided by NASA, NOAA, and CNES. The launch of ADEOS 2 was planned initially for early 1999. Spacecraft: 3-Axis stabilised, zero momentum biased control system with 0.3 deg control and 0.003 deg/sec stability using reaction wheels. Single solar array generates 4.5 kW for a 34 to 52 volt floating bus with 5x35 AHr NiCd batteries. Hydrazine propulsion system (135 kg fuel) for orbit maintenance. S-Band TT&C (S-Band, Uplink: 500 bps, Downlink: 4 Mbps). Ka-Band data crosslink at 120 Mbps to COMETS. X-Band direct downlink (40W and 8W, QPSK). System reliability is 0.7 at 3 years. Payload: ADEOS-1 Payload Description: AVNIR (Advanced Visible and Near-Infrared Radiometer): five visible/near-infrared bands (0.42 to 0.89 Ám); 16- or 8-m resolution; 80 km swath; +/- 40 deg cross-track pointing; stereo capability (from NASDA). ILAS (Infrared Limb Atmospheric Spectrometer): infrared occultation device (from Japan's Environmental Agency). IMG: nadir-looking Fourier transform infrared spectrometer (from MITI). NSCAT: active Ku-band scatterometer (from NASA). OCTS: Ocean Colour Temperature Scanner (from NASDA). POLDER: (from CNES). RIS: (from Japan's Environmental agency). TOMS: Total Ozone Mapping Spectrometer (from NASA). ADEOS-2 Payload Description: AMSR (Advanced Microwave Scanning Radiometer), GLI (Global Imager), Sea Winds, POLDER (Polarisation and Directionality of the Earth's Reflectances), ILAS-II (Improved Limb Atmospheric Spectrometer-II)
Initially put on August 20 1996 into wrong orbit - acceptable orbit achieved in September 1996. Spacecraft failed June 30 1997. $ 986 million total - $ 808 million for the satellite and $ 178 million for the launch.
Design Life: 3 years. Total Length: 5.0 m. Maximum Diameter: 4.0 m. Total Propellants: 135 kg. Electric system: 4.50 total average kW. Electrical System: Single solar array.
The polar orbiting ADEOS spacecraft performed Earth, atmospheric, and oceanographic remote sensing. Initially put on August 20 1996 into a wrong orbit, it achieved an acceptable orbit in September 1996.