Adeos 1

Japan

International Sat. nº:

Japanese satellite nº: 78

Enginering name: Mitori
Advanced Earth Observing Satellite, also called Midori (means "green")

Launch data:

Designation	24277 / 96046A
Launch date	17 Aug 1996
Launch site	Tanegashima
Launch vehicle	H2 (#4)
Mission	Remote sensing, Earth Observation
Perigee/Apogee	800/830 km
Inclination	98.6°
Period	101 min
Cycle	41 days

To acquire global observation data corresponding to enviromental changes, such as global warming, depletion of the ozone layer, decrease of tropical rain forests, occurrence of unusual weather, etc. it will also help develop the platform bus interorbit data relay technologies necessary for next-generation Earth Observation Systems.

The satellite encountered several problems after launch: first a thruster problem which required to use the 20 N adjusters to reach final orbit; then on 24th September 1996 the satellite shutdown all nonessential systems. At the same time a scanning mirror used by the Interferomic Monitor for Greenhouse Gases became stuck on 20 September. Also, it was found that cosmic radiations affected the on-board computer. In late 1996 it was also found that the OCTS instrument has a mirror blocked.

Specifications

Prime contractor	Mitsubishi Electric
Operator	NASDA
Platform
Mass at launch	3560 kg
Mass in orbit
Dimension	4 x 4 x 5 m
Solar array	3 x 26 m
Stabilization	3-axis
DC power	4500 W
Design lifetime	3 years

Telemetry/data at: 2220, 8150, 8250, 8350 MHz perhaps also 467.7 MHz?
Ka-band inter orbit links to Comets

Line drawing of the ADEOS spacecraft (image credit: JAXA)

End of life

Out of service	30 Jun 1997
Cause	electrical failure caused by the solar array paddle break itself caused by improper maneuver

Initially put on August 20 1996 into wrong orbit - acceptable orbit achieved in September 1996. Spacecraft failed June 30 1997.

Payloads

Ocean Color and Temperature Scanner (OCTS)
Advanced Visible and NearInfrared Radiometer (AVNIR)
NASA Scatterometer (NSCAT)
Total Ozone Mapping Spectrometer (TOMS)
Polarization and Directionality of the Earth's reflectances (POLDER)
Interferometric Monitor for Greenhouse Gases (IMG)
Improved Limb Atmospheric Spectrometer (ILAS)
Retroreflector in Space (RIS)

Mission details:

Primary applications of ADEOS (Advanced Earth Observation Satellite), which has been renamed Midori after reaching orbit, include monitoring global environmental changes such as maritime meteorological conditions, atmospheric ozone, and gases that promote global warming. ADEOS was also expected to play a vital role in developing more sophisticated inter-orbit communications and platform technology for the satellite of tomorrow. ADEOS was launched by H-2 Launch Vehicle No.4 on August 1996 and provided a large volume of data containing valuable information about our environment atmosphere, ocean and land for about 10 months until it suddenly got out of control on June 30, 1997 because of the structural damage in its solar array paddle.
AEDOS includes the following instrumentation for consolidated continuous measurement of land, sea and air:
- AVNIR (Advanced Visible 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).
- OCTS (Ocean Color and Temperature Scanner), developed by NASDA.
In addition, there are six kinds of AO sensors:
- NSCAT: active Ku-band scatterometer (from NASA).
- TOMS (Total Ozone Mapping Spectrometer), both from NASA,
- POLDER (Polarization and Directionality of the Earth's Reflectances), a geosurface reflection measuring device from CNES,
- IMG (Interferometric Monitor for Greenhouse Gases) a sensor for measuring the greenhouse effect from the Ministry of International Trade and Industry (MITI),
- ILAS (Improved Limb Atmospheric Spectrometer), an improved spectrometer for measuring infrared radiation on the edge of the atmosphere (from Japan's Environmental Agency).
- RIS (Retroreflector In-Space), a retroreflector for measuring laser long light-path absorption between the earth and satellites (from Japan's Environmental agency).
The polar orbiting ADEOS spacecraft will perform Earth, atmospheric, and oceanographic remote sensing. ADEOS 1 and 2 use the same bus design to fly different instrument suites. These are the largest satellites Japan has ever developed. Several of the instruments on ADEOS were provided by NASA, NOAA, and CNES. The launch of ADEOS 2 is planned 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.

External links:

EOportal.org Satellite description

Ref.: #8, #14, #242 - update: 06.01.15

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