@prefix skos: . @prefix ns0: . skos:prefLabel "KOMPSAT"@en ; a skos:Concept ; skos:narrower . skos:changeNote """2018-06-12 12:36:10.0 [mmorahan] Move Concepts delete broader relation (null); add broader relation (KOMPSAT-2 [88d9cd91-a26e-467a-9554-c5d927540421,345347] - KOMPSAT [9abdb7c0-7b8e-426b-8bc7-57ea4a30d82c,367679]); """, """2019-02-21 05:40:39.0 [mmorahan] insert WeightedRelation (id: null related concept uuid: bf3e5771-7ca2-4083-a5e2-9be6a28fe588 relationship type: null relationship value: null generated by: null); """, """2020-10-06 09:31:52.0 [mmorahan] insert AltLabel (id: null category: primary text: Korea Multi-Purpose Satellite - 2 language code: en); """ ; ns0:altLabel [ ] ; skos:definition """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 Group: Platform_Details Entry_ID: KOMPSAT-2 Group: Platform_Identification Platform_Category: Earth Observation Satellites Short_Name: KOMPSAT-2 End_Group Group: Synonymous_Platform_Names Short_Name: Arirang-2 End_Group Group: Platform_Associated_Instruments Short_Name: CAMERA Short_Name: MS End_Group Group: 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 End_Group Creation_Date: 2008-07-09 Online_Resource: http://directory.eoportal.org/get_announce.php?an_id=7483 Online_Resource: http://www.kaiimage.co.kr/eng/kompsat_b01.asp Group: Platform_Logistics Launch_Date: 2006-07-28 Launch_Site: PLESETSK COSMODROME, RUSSIA Design_Life: Minimum 5 years ( Design Life :3years) Primary_Sponsor: Korea Aerospace Research Institute (KARI), South Korea End_Group End_Group"""@en ; skos:prefLabel "KOMPSAT-2"@en ; skos:inScheme ; skos:broader ; a skos:Concept .