Satellite Bus System Design
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We were selected as a competent authority to develop KOMPSAT 3A’s BUS platform by KARI
(Korea Aerospace Research Institute) in March 2010. Subsequently, we obtained the system design technology of LEO utility grade satellite.
Our expertise about the practical satellite production has been upgraded from this technology since we participated in the Korean space project with KARI.
Specifications of the commercial grade satellite applied the system design technology, we obtained from KARI, are as follows.
| Mission | LEO Earth Observation Satellite with PAN/MS/I |
|---|---|
| Orbit | 530km Sun-synchronous orbit |
| Mass | 1,000kg |
| Power | 1.4kW |
| Mission lifetime | 4 years |
| Components | Structure, EPS (Electric Power Subsystem), TCTM (Telecommand & Telemetry Subsystem), AOCS (Attitude & Orbit Control Subsystem), TCS (Thermal Control Subsystem), Propulsion Subsystem, Flight software, Payloads |
