AKA: Advanced Earth Observation Satellite;Midori. Status: Operational 1996. First Launch: 1996-08-17. Last Launch: 2002-12-14. Number: 2 . Gross mass: 135 kg (297 lb). Height: 5.00 m (16.40 ft). Span: 26.00 m (85.00 ft).
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. The spacecraft used a 3-Axis stabilized, zero momentum biased control system with 0.3 deg control and 0.003 deg/sec stability using reaction wheels. A single solar array generated 4.5 kW for a 34 to 52 volt floating bus with 5x35 AHr NiCd batteries. A hydrazine propulsion system with 135 kg fuel provided 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 was 0.7 at 3 years.
Initially put on 20 August 1996 into the wrong orbit - an acceptable orbit was achieved in September 1996. The spacecraft failed on 30 June 1997. Cost was $ 986 million total - $ 808 million for the satellite and $ 178 million for the launch. Electric System: 4.50 average kW.
NASA NSSDC Master Catalog Description
The Japanese Advanced Earth Observing Satellite (ADEOS) was developed to establish platform technology for Earth Observing System (EOS) spacecraft and inter-orbit communication technology for the transmission of Earth observation data. In addition, ADEOS contributed global observation of environmental change to the international community during the pre-EOS era. NASA's Mission to Planet Earth (MTPE) program contributed two instruments for the ADEOS mission.
ADEOS was a sun-synchronous, morning equator-crossing (in descending node at about 10:30 a.m.), polar orbiting spacecraft. It had a modular type shape with a deployable one wing solar paddle. The body measured 4 x 4 x 5 m and the solar paddle was 3 x 13 m in size.
ADEOS was three-axis stabilized by a zero momentum strap-down attitude-control system. Attitude was maintained by four reaction wheels, two magnetometers, an inertial reference unit, and two hydrazine thrusters. Power was provided by a single gallium arsenide flexible solar paddle and five 35 A-hr NiCd batteries. Data was transmitted via direct transmission and inter-orbit communication through ETS-6. A Mission Data Recorder system on-board ADEOS stored high data rate and low data rate data on separate tape recorders.
Eight experiments on ADEOS included: (1) Ocean Color and Temperature Scanner (OCTS), a NASDA core instrument; (2) Advanced Visible and Near-Infrared Radiometer (AVNIR), a NASDA core instrument; (3) NASA Scatterometer (NSCAT), a NASA/MTPE-provided instrument; (4) Total Ozone Mapping Spectrometer (TOMS), a NASA/MTPE provided instrument; (5) Polarization and Directionality of the Earth's Reflectances (POLDER), provided by CNES of France; (6) Interferometric Monitor for Greenhouse Gases (IMG), provided by MITI of Japan; (7) Improved Limb Atmospheric Spectrometer (ILAS), provided by Environmental Agency of Japan; and, (8) Retroreflector in Space (RIS), provided by the Environmental Agency of Japan.
The design lifetime for this mission was three years, but the spacecraft ceased operating on 30 June 1997 for as yet unknown reasons. Subsequent flights of ADEOS are planned during the EOS era.
Credit: Manufacturer Image
Credit: Manufacturer Image