Korea Multi-Purpose Satellite (KOMPSAT)
type: Concept

KOMPSAT-2
type: Concept
change note: 2020-10-06 09:31:52.0 [mmorahan] insert AltLabel (id: null category: primary text: Korea Multi-Purpose Satellite - 2 language code: en);
change note: 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);
change note: 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]);
in scheme: platforms
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 su…