Kompsat 3/3A

Archive: since 2012


The imagery, acquired by KOMPSAT 3/3A can be obtained from SIIS (SI Imaging Services), which is an exclusive representative of the KOMPSAT constellation. Each product is provided as a specific set of data: pan + four multispectral or as four pansharpened bands. Image data processing levels:

  • Level 1R (Corrected for radiometric and sensor distortions)
  • Level 1O (Ortho-ready)
  • Level 1G (Geometric distortion correction by using SRTM DEM)
  • Kompsat 3/3A Image Hamadan Province, Iran
    Corgar, Garadice ED, Municipal District, Ireland 54.06121°N 7.76733°W
  • Kompsat 3/3A Image Hamadan Province, Iran
    Jeolla Namdo Kohyn, South Korea 34.54440°N 127.15233°E
  • Kompsat 3/3A Image Hamadan Province, Iran
    Tibau do Sul, Microrregião do Litoral Sul, Brazil 6.20262°S 35.09857°W


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. The project started in 2004 to continue KOMPSAT-1 and KOMPSAT-2 missions and provide high-res satellite imagery for Geographical Information Systems (GIS) and the following applied fields: agriculture, environment, oceanography and natural disasters.


KOMPSAT-3 (Arirang-3) satellite was launched on the H-IIA system on May 17, 2012 from Tanegashima Space Center in Japan. KOMPSAT 3A (Arirang-3A) joined the mission on March 25, 2015. It was launched on a Dnepr-1 vehicle (RS-20) from the Jasny Dombarovsky launch site, Russia, to the lower than KOMPSAT 3 sun-synchronous orbit.


To meet the demand for high-resolution imagery from government, both satellites are equipped with a pushbroom imager, AEISS (Advanced Earth Imaging Sensor System), developed by KARI in cooperation with EADS Astrium GmbH, Friedrichshafen. It is delivering the highest resolution data among the cameras installed on domestic satellites and is capable of acquiring images with maximum spatial resolution of 50-70 cm.


Band configuration
  • PAN: 450-900 µm
  • MS1 (Blue): 450-520 µm
  • MS2 (Green): 520-600 µm
  • MS3 (Red): 630-690 µm
  • MS4 (NIR): 760-900 µm
  • Korsch-type telescope
  • 80 cm diameter of primary light weight mirror aperture
  • Five mirrors of Zerodur design
  • Focal length = 8.6 m
  • F number = f/12
GSD (Ground Sample Distance)
  • 0.5-0.7 m (Pan band, nadir)
  • 2.2-2.8 m (MS bands, nadir)
Swath width
1 km (at nadir)
Tilt angle
Roll: ±45º, pitch: ±30º
Location accuracy
< 48.5 m CE90
Pan CCD detector module
  • Line array of 24,000 pixels. 2 stacks of 12 k pixels each
  • TDI (Time Delay Integration), < 64 TDI in 4 stages
  • Pixel pitch = 8.75 µm
  • Source data rate = 16 x 15 Mpixel/s (or 3.84 Gbit/s)
MS CCD detector module
  • Line array of 6,000 pixels, provision of 8 stacks, TDI capability
  • Pixel pitch = 2 x 17.5 µm
  • Binning of MS pixels
  • Source data rate = 4 x 240 Mbit/s
PRNU (Photo Response Non-Uniformity)
DSNU (Dark Signal Non-Uniformity)
SNR (Signal-to-Noise Ratio)
> 100 for Pan and MS
Radiometric resolution
14 bit
Data compression
CCSDS 120.1-G-1E
Payload data memory
512 Gbit
Data rate
1 GB/s

Notwithstanding KOMPSAT 3’s capacity to deliver panchromatic optical images at a nominal ground sampling distance (GSD) of 70 cm, the next satellite was enhanced with thermal infrared sensor, therefore KOMPSAT-3A became a unique example of space technologies commercialization. It appeared to be the first satellite, equipped with two imaging systems where the AEISS was complemented with IIS (Infrared Imaging System). It operates within the MWIR (Mid-Wavelength Infrared) region of 3 – 5 µm at high spatial and thermal resolution. These temperature-sensitive IR sensors (IRS) can assist in monitoring of wildfires, volcanic and seismic activities as well as water currents and natural disasters.

Let’s make a graphic comparison of two satellites

Launch date May 17, 2012 March 25, 2015
Designed lifetime 4 years
Payload EO EO, IR
Altitude 625 km 528 km
Inclination 98.13º 97.513º
Mean LTAN (Local Time on Ascending Node) 13:30 hours 13:30 hours
Orbital period 98.5 minutes 95.2 minutes
No of revolutions 14.6 revolutions/day 15.1 revolutions/day
Orbit velocity 7.51 km/second 7.60 km/second
Ground speed 6.78 km/second 7.02 km/second
Repeated ground track 28 days /423 revolutions 28 days /409 revolutions
Revisit time 1.4 days
Coverage per cycle Global coverage in one month
Maximum image dimensions (Across track x along track, km) Strip mode (mono): 16 x 4000
Wide Area (mono): 48 x 100
Single Pass (stereo): 16 x 200