Synonymous Platform Names:
Platform-based Instruments:
Orbit
Orbit Altitude:
685
Orbit Inclination:
98.13
Period:
98.46
Repeat Cycle:
~14
Perigee:
682.0
Apogee:
708.0
Orbit Type:
LEO > LOW EARTH ORBIT > POLAR SUN-SYNCHRONOUS
Related Data Sets
Description
KOMPSAT-2 (also referred to as Arirang-2 by South Korea) was developed by KARI (Korea Aerospace Research Institute) to continue the observation program of the KOMPSAT-1 mission. The main mission
... objectives of the KOMPSAT-2 are to provide a surveillance capability for large-scale disasters by acquiring high-resolution imagery for GIS (Geographic Information Systems) applications.
The 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 stabilization (3-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 pointing accuracy is < 0.025º in roll and pitch, and 0.08º in yaw. The pointing knowledge is 0.020º in roll and pitch, and 0.045º in yaw. The spacecraft platform offers a cross-track body-pointing capability through roll maneuvers (up to ±45º). The propulsion subsystem makes use of re-used components (hydrazine monopropellant thrusters with blowdown pressure-feed system, 73 kg propellant).
The spacecraft mass is 800 kg (including propellant), the S/C size is hexagonal: 1.85 m diameter x 2.6 m in height (6.8 m length in deployed configuration), the power is 955 W (EOL) provided by two solar arrays (GaAs cell technology). A super NiCd battery has a capacity of 30 Ah for eclipse phase support. The S/C design life is three years. EADS Astrium has been selected by KARI to support the platform development and manufacture of KOMPSAT-2.
Launch: A launch of the KOMPSAT-2 spacecraft took place on July 28, 2006 with a Rockot-KM launch vehicle of Eurockot Launch Services from Plesetsk, Russia.
Orbit: Sun-synchronous circular orbit, altitude = 685 km, inclination = 98.13º, period = 98.46 min, the mean local time of the ascending node is at 10:50 hours. The KOMPSAT-2 orbit is identical to that of KOMPSAT-1 but with a different phase (180º apart).
RF communications: Onboard storage capacity of 96 Gbit (BOL) and 64 Gbit (EOL) for image data. S-band (TT&C) and X-band (payload data at 8.205 GHz downlink frequency) communications are provided for all data transmission to the ground (real-time and playback), the downlink data rate is 320 Mbit/s (QPSK modulation). Encryption of image data. The CCSDS communication protocols are implemented. The S-band data rates are: 2 kbit/s uplink and 1.5 Mbit/s downlink.
Mission status: The KOMPSAT-2 spacecraft and its payload are operating nominally as of 2008.
• KOMPSAT-2 completed its commissioning phase in late September 2006 and started its nominal operations phase in October 2006.
• In August, 2006, KOMPSAT-2 had provided its first images.
• On Oct. 24, 2005, KARI has made Spot Image (France) exclusive distributor of imagery from the KOMPSAT-2 Earth observation satellite - except for customers from Korea, the United States, and the Middle East, which are being serviced by KAI Image Inc. of Korea.
Information obtained from http://www.eoportal.org/
KOMPSAT-2 Specifications
Imaging mode: Panchromatic Multispectral
Spatial Resolution: 1m 4m
Swatch Width: 15km 15km
Duty Cycle: >20% per Orbit
Off-Nadir Imaging: Up to 45 degree
Orbital Altitude: 685km, Sun-synchromous orbit
Operation Life: Minimum 5 years ( Design Life :3years)
Revisit Time: Less than 3 days
Data Transmission: 320 Mbps
Data Storage: 90 Gbits
Dynamic Range: 10 bits per pixel 
Online Resource:
Platform Logistics:
Design Life:
Minimum 5 years ( Design Life :3years)
Launch Date:
2006-07-28
Launch Site:
PLESETSK COSMODROME, RUSSIA
Primary Sponsors:
Korea Aerospace Research Institute (KARI), South Korea
