- Comments and corrections to this article are always welcome for further updates. The contract also included the delivery of stiffening mechanism for each of the solar arrays, to achieve a high eigenfrequency of the solar array wings in order to allow agile satellite operation/pointing.

12). Decenter Figure 4: Schematic view of the payloads in the H-IIA launch vehicle (image credit: Mitsubishi) 11) 12). The FPA design features a modular and scalable architecture; it has a total of six independent FPMs (Focal Plane Modules) in a stacking configuration, 2 are dedicated for the Pan bands and 4 are used for the MS bands. - F number = f/12, - 0.7 m for Pan band at nadir

1) 2) 3), SI (Satrec Initiative) of Daejeon participation in the KOMPSAT-3 development of KARI: 4) 5). 15) 16). The CEUP and CC modules are actually part of the spacecraft bus, while the FPA is integrated with OM to constitute EOS. The CC (Camera Control) unit of CEU communicates with the spacecraft OBC via a MIL-STD-1553B interface. AEISS (Advanced Earth Imaging Sensor System), AEISS is a high-resolution pushbroom imager (Pan and MS) for land applications of cartography and disaster monitoring. A check-up of the condition, attitude control systems, and on-board equipment has confirmed that the KOMPSAT-3 is functioning normally.

20), Figure 9: Comparison of an image scene observed by AEISS on KOMPSAT-3 (right) and observed by MSC on KOMPSAT-2 (left), image credit: KARI. 28), 1 m (Pan) / 15 km The spacecraft is 3-axis stabilized. 17), • In January 2013, KOMPSAT-3 is still in the commissioning phase and should be operational soon. KOMPSAT 3 is an Earth observation mission of Korea Aerospace Research Institute (KARI), funded by Ministry of Education, Science and Technology (MEST) within the Korean government space development program. Legend to Figure 9: The image scene is of Jeodong Port on Ulleungdo Island, Korea. - SI provided the DM (Development Model) of power controller, and on-board computer processor module as well as six FM coarse sun sensors to KARI. The UIS is to process ‘Product Order’ of the External User.

The CEU architecture is shown in Figure 13.

Tilt, Table 4: In-orbit stability requirements of HSTS. CEU (Camera Electronics Unit): The CEU manages the overall operation of EOS; hence, it defines the functionality and operational capabilities of EOS which implies also the performance of the FPA. The MCE provides the S-band command and telemetry communications interface to the satellite and the necessary functions to operate the satellite. Figure 2: System architecture of the KOMPSAT-3 mission (image credit: KARI), Figure 3: Photo of the KARI KOMPSAT-3/Arirang-3 spacecraft at TNSC on May 1, 2012 (image credit: The Korea Herald), Launch: The KOMPSAT-3 (Arirang-3) spacecraft was launched as a “co-payload” on May 17, 2012 (16:39 UTC) from the Tanegashima Space Center of JAXA, Japan on the H-IIA launch system.