Satellites and Spacecraft Advanced Earth Observation Satellite-II "Midori II" (ADEOS-II)

Operation Finished

About Advanced Earth Observation Satellite-II "Midori II" (ADEOS-II)

The Advanced Earth Observing Satellite-II "Midori II"(ADEOS-II), the successor of the Advanced Earth Observing Satellite "Midori"(ADEOS) launched in 1996, is also known as Midori II.
Midori II was launched by the H-IIA launch vehicle in December 14, 2002.
Midori II has been engaged in various observation missions to understand the realities and causes of global environmental changes, such as abnormal weather conditions and the expansion of the ozone hole.?The combination of various sensor technologies allow the satellite to detect different electromagnetic waves reflected or emitted from plants, water and the atmosphere, enabling more precise observation of the Earth. Midori II is equipped with two sensors: the Advanced Microwave Scanning Radiometer (AMSR), which, day and night, can observe geographical parameters related to water; and the Global Imager (GLI), which can extensively and accurately observe oceans, land and clouds. The Global Imager is said to have attained the world’s highest standards in this field, in that it can observe the reflected solar radiation from the Earth’s surface, in order to understand the distribution of sea-surface temperature, snow, ice, cloud cover, aerosol, forest, sea phytoplankton, etc. Other devices on Midori II include the Improved Limb Atmospheric Spectrometer-II (ILAS-II), Sea Winds, the Polarization and Directionality of the Earth’s Reflectance (POLDER), and the Data Collection System (DCS).

Observation operation results

After an anomaly was detected in the "Midori-II" satellite on October 25, 2003, JAXA found that the possibility of restoring operations of the Midori-II was extremely slim as a result of its investigation, analysis, and inability to re-establish any communication with the satellite as of Oct. 31, 2003.

Major Characteristics

International Designation Code 2002-056A
Launch Date 10:31, December 14, 2002 (JST)
Launch Vehicle H-IIA Launch Vehicle No.4
Location Tanegashima Space Center
Shape Approx. 4m x 4m x 6m
A box shape with a deployable solar array paddles
Weight Approx. 3,700kg
Orbiter Sun-Synchronous Subrecurrent
Altitude Approx.803km
Inclination Approx. 99 degrees
Period Approx. 101 minutes / Recurrent Perid: Approx. 4day
Attitude Control Three-axis stabilization