Encyclopedia Astronautica
ADEOS



adeos.jpg
Adeos
Credit: NASDA
Japanese earth atmosphere satellite. 2 launches, 1996.08.17 (ADEOS) and 2002.12.14 (Adeos 2). 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 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 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.

Characteristics

Electric System: 4.50 average kW.

AKA: Advanced Earth Observation Satellite.
Gross mass: 135 kg (297 lb).
Height: 5.00 m (16.40 ft).
Span: 26.00 m (85.00 ft).
First Launch: 1996.08.17.
Last Launch: 2002.12.14.
Number: 2 .

More... - Chronology...


Associated Countries
See also
  • H-2 Heavy lift Japanese indigenous launch vehicle. The original H-2 version was cancelled due to high costs and poor reliability and replaced by the substantially redesigned H-2A.

    3 stage vehicle consisted of 2 x H-II SRB + 1 x H-II stage 1 + 1 x H-II stage 2 More...


Associated Launch Vehicles
  • Ariane 44L French orbital launch vehicle. Ariane 4 with 4 liquid rocket strap-ons. More...
  • H-II Japanese orbital launch vehicle. 3 stage vehicle consisted of 2 x H-II SRB boosters + core vehicle. More...
  • H-2 Heavy lift Japanese indigenous launch vehicle. The original H-2 version was cancelled due to high costs and poor reliability and replaced by the substantially redesigned H-2A. More...
  • H-IIA 202 Japanese orbital launch vehicle. Three stage version of H-IIA consisting of 2 x H-II SRB-A + two-stage core vehicle. More...

Associated Manufacturers and Agencies
  • NASDA Japanese agency overseeing development of rockets, spacecraft, and rocket engines. National Space Development Agency, Japan. More...
  • Mitsubishi Japanese manufacturer of rockets, spacecraft, and rocket engines. Mitsubishi Electric Corp, Japan. More...

Bibliography
  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: here.
  • McDowell, Jonathan, Jonathan's Space Report (Internet Newsletter), Harvard University, Weekly, 1989 to Present. Web Address when accessed: here.
  • NASA/GSFC Orbital Information Group Website, Web Address when accessed: here.
  • Space-Launcher.com, Orbital Report News Agency. Web Address when accessed: here.
  • NASA Report, SeaWinds on Adeos 2 Launch Press Kit, Web Address when accessed: here.

Associated Launch Sites
  • Tanegashima Japan's main launch site for he larger N and H launch vehicles. In use for sounding rockets from 1967 and orbital launches from 1975. As of 2007 over 140 major launches had been made from the site. More...

ADEOS Chronology


1996 August 17 - . 01:53 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II. LV Configuration: H-II H-II-4F.
  • ADEOS - . Nation: Japan. Agency: NASDA. Class: Earth. Type: Atmosphere satellite. Spacecraft: ADEOS. USAF Sat Cat: 24277 . COSPAR: 1996-046A. Apogee: 800 km (490 mi). Perigee: 799 km (496 mi). Inclination: 98.6000 deg. Period: 100.90 min.

1997 June 30 - .
  • ADEOS spacecraft fails - . Nation: Japan. Spacecraft: ADEOS. Summary: 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 - . 23:04 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202. LV Configuration: H-IIA 202 H-IIA-4F.
  • Adeos 2 - . Payload: Midori 2. Mass: 3,730 kg (8,220 lb). Nation: Japan. Agency: NASDA. Manufacturer: Mitsubishi. Class: Earth. Type: Earth resources satellite. Spacecraft: Adeos. USAF Sat Cat: 27597 . COSPAR: 2002-056A. Apogee: 806 km (500 mi). Perigee: 804 km (499 mi). Inclination: 98.7000 deg. Period: 101.00 min. Summary: Environment Monitoring, Aeronomy..

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