The ERG  satellite was developed as a science satellite by Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA). Table 1 summarizes the specifications of the ERG  satellite.

  • The satellite was launched during the declining phase of solar cycle 24 on 20 December 2016. The nominal mission life is planned to be longer than 1 year.
  • The apogee altitude will be 5.0 Re (L~6.0 at the equatorial plane), where the average peak flux L shell of the outer belt during the declining phase is located [Miyoshi and Kataoka, 2011].
  • The orbital inclination will be 31°, so the satellite will not always stay at the magnetic equator. However, the satellite will have many chances to observe, for example, the phase space density, generation of plasma waves, and accelerations of relativistic electrons near the equator. Off-equatorial observations are also essential to discuss the propagation of plasma waves from the equator, so it is important to compare with observations by other satellites near the equator.

Table 1: Specifications of the ERG  Satellite
LaunchDate20 December 2016
LocationUchinoura Space Center (USC)
Launch VehicleEpsilon
Nominal Mission Life>1 yr
OrbitAltitudePerigee: about 460 km, Apogee: about 32,110 km
Type of OrbitElliptical orbit
Periodabout 565 min
Spin DirectionSun-oriented
Spin Rate7.5 rpm (8 s)
Satellite BusSPRINT bus
ConfigurationWeight350 kg

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