Adeos Credit - NASDA

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. 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.

Payloads:

ADEOS-1:

• AVNIR (Advanced Visible and Near-Infrared Radiometer): five visible/near-infrared bands (0.42 to 0.89 µm); 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 Color Temperature Scanner (from NASDA).
• POLDER: (from CNES).
• RIS: (from Japan's Environmental agency).
• TOMS: Total Ozone Mapping Spectrometer (from NASA).

ADEOS-2 Payload

ADEOS-1:

• AMSR (Advanced Microwave Scanning Radiometer)
• GLI (Global Imager)
• Sea Winds
• POLDER (Polarization and Directionality of the Earth's Reflectance)
• ILAS-II (Improved Limb Atmospheric Spectrometer-II)

Financial/Operational:
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.

Design Life: 3 years. Typical orbit: LEO, 797 km, sun-synchronous with 10:30 equa cross. Length: 5.00 m (16.40 ft). Maximum Diameter: 4.00 m (13.10 ft). Span: 26.00 m (85.00 ft). Main Engine Propellants: 135 kg (297 lb). Electrical System: Single solar array. Electric System: 4.50 average kW. Associated Launch Vehicle: Ariane 44L, H-2.

• 1996 August 17 - ADEOS - Launch Site: Tanegashima. Launch Vehicle: H-2. Perigee: 799 km (496 mi). Apogee: 800 km (490 mi). Inclination: 98.60 deg. Period: 100.90 min.

• 1997 June 30 - ADEOS spacecraft fails -

  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.

• 2002 December 14 - Adeos 2 - Launch Site: Tanegashima. Launch Vehicle: H-2A. Mass: 3,730 kg (8,220 lb). Perigee: 804 km (499 mi). Apogee: 806 km (500 mi). Inclination: 98.70 deg. Period: 101.00 min.

  Environment Monitoring, Aeronomy.

• McDowell, Jonathan, Jonathan's Space Report (Internet Newsletter), Harvard University, Weekly, 1989 to Present. Essential internet newsletter recording worldwide weekly space events. Accessed at: http://www.planet4589.org/jsr.html.

• NASA/GSFC Orbital Information Group Website, . Accessed at: http://oig1.gsfc.nasa.gov/.

• Space-Launcher.com, Orbital Report News Agency. Accessed at: http://www.orbireport.com/Log.html.

• NASA Report, SeaWinds on Adeos 2 Launch Press Kit, . Accessed at: http://www.jpl.nasa.gov/news/press_kits/seawinds-adeos2.pdf. -right click to download pdfs!