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KOMPSAT-2 Overview

Mission Background

KOMPSAT-2 (Korea Multi-Purpose Satellite-2) was developed by KARI (Korea Aerospace Research Institute) to continue the observation programme of the KOMPSAT-1 mission.

Satellite Design

The KOMPSAT-2 spacecraft design is based on the KOMPSAT-1 heritage making extensive use of existing hardware, software, tools, and facilities; it allows parallel integration of the payload, equipment, and propulsion modules. The KOMPSAT-2 bus structure consists of the five modules: SMS (Structure and Mechanisms Subsystem), TCS (Thermal ConTrol Subsystem), AOCS (Attitude and Orbit Control Subsystem), TC&R (Telemetry Command and Ranging) subsystem, EPS (Electrical Power Subsystem), PS (Propulsion Subsystem), and the FSW (Flight Software) element.

The AOCS provides three-axis stabilisation (three-axis control with zero momentum bias system) with high accuracy for roll, pitch and yaw pointing. Star trackers, gyro reference assemblies, three-axis magnetometers, magnetic torquers and reaction wheels are used for attitude sensing and control. The propulsion subsystem makes use of re-used components (hydrazine monopropellant thrusters with blowdown pressure-feed system, 73 kg propellant).

Technical Specifications
Mass800 kg
Dimensions1.85 m x 2.6 m x 6.8 m
Design Lifetime3 years

Mission Operations

With a Sun-synchronous circular orbit with an altitude of 685 km, the KOMPSAT-2 orbit is identical to that of KOMPSAT-1 but with a different phase (180° apart).

Mission operations are performed at KMOC (Korea Mission Operation Centre). The KGS (KOMPSAT Ground Station) is located at KARI, Daejeon, South Korea. In addition, there is a second ground station at ETRI (Electronics and Telecommunications Research Institute) in South Korea.



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