CurrentREIMEI

Innovate Technology Demonstration Experiment ”REIMEI” aims to demonstrate of next-generation advanced satellite technologies in orbit, realization of small-scale, frequent scientific observation missions.

HINODE GEOTAIL
Name (pre-launch in parentheses) REIMEI (INDEX)
International Designation Code 2005-031B
Objectives Demonstration of next-generation advanced satellite technologies in orbit
Realization of small-scale, frequent scientific observation missions
Lunch Date 06:10, August 24, 2005 (JST)
Launch Location Republic of Kazakhstan
Launch Vehicle Dnepr (launched together with OICETS satellite)
Weight Approx. 72 kg
Dimensions Approx. 62 × 62 × 72 cm
Orbit Altitude Perigee 610 km, Apogee 654 km
Inclination
Orbit Inclination 97.8°
Type of Orbit Near-circular orbit
Orbital Period 97 min
Attitude Control Method Bias Momentum Three Axis Stabilized Attitude Control
Scientific Instruments 1. Star tracker
2. Spin/non-spin type solar sensors (SSAS/NSAS)
3. Geomagnetic Aspect sensor (GAS)
4. Three-axis optical fiber gyro (FOG)
5. Reaction wheel (RW) and magnetic torquer (MTQ) as actuators
6. Multi-spectral Auroral Camera (MAC)
7. Aurora particle observation instrument (Electron/Ion Spectrum Analyzer: ESA/ISA)
Operation All the onboard instruments are operational in orbit. We succeeded in demonstrating advanced onboard satellite instrument technologies in orbit, including a solar-concentrated paddle using thin-film reflector and ultra-small GPS receiver as engineering missions.
Results We successfully obtained scientific results in terms of both satellite engineering and space science, and were able to demonstrate the effectiveness of small satellite.