MIMAN is a CubeSat for monitoring fine dust on the Korean Peninsula. Fine dust, a type of aerosol, is one of the factors of climate change, and has been designated as a group 1 carcinogen by the WHO. Accordingly, research on the generation and flow of the fine dust is being actively conducted around the world. To study the spatiotemporal distribution of fine dust, observation over a wide area using satellites is required. Satellites of South Korea that provides fine dust observation data include GEO-KOMPSAT 2B (GK-2B), a geostationary satellite launched in 2020. When observing fine dust in geostationary orbits, although the temporal resolution is high, only a specific area can be observed, and it has the disadvantage of securing relatively low spatial resolution compared to low orbits. If a low-orbit fine dust observation system that can capture high spatial resolution is established, observation data for the entire world can be provided. In addition, data with high spatial resolution can be utilized to remove clouds from data with relatively low spatial resolution. Currently, Korea does not have a low-orbit satellite system capable of observing the East Asian region with high spatial resolution. If this is built as a CubeSat-based platform, it will be possible to increase the accessibility to observation data. With this goal in mind, the Cubeset Yonsei team at Yonsei University developed the CubeSat MIMAN.
    MIMAN is a 3U cube satellite with dimensions of 10 cm X 10 cm X 34 cm. It is equipped with an optical camera for CubeSat and antennas for communication, and transmits images with a resolution of 200 m or less in the area of ​​400 km X 400 km above the West Sea once every two days to the ground. The image sent down to the ground is provided to the fine dust research team after appropriate correction so that it can be used as research data.


  • Satellite Constellation

    Satellite constellation with small or microsatellites is a rising concept in the recent space industry. Unlike the traditional single satellite mission, satellite constellation can achieve rapid revisit time as well as enhanced coverage ability, which makes the scope of satellite mission goes further. Designing orbital patterns for satellite constellation has been studied to obtain efficient configuration for mission-specific objectives. Also, constellation deployment and maintenance strategy are one of the essential parts for effective mission operation.


  • Scanning the EARTH SAR & OPTICS

    As the miniaturization of satellites progresses, Earth observation using microsatellites is emerging worldwide.
    The cost of producing the micro-satellites has been greatly reduced compared to the existing satellites, and efficient mass production is possible through platform development.
    In addition to the sale of mass-produced platforms for satellites, the satellite market is becoming active with the provision of Earth observation service.
    This study aims to lay the groundwork for platform development for satellite mass production by designing the micro-optical satellite and micro SAR satellite system according to global satellite development trend.
    Micro-optical satellites are expected to build a low-cost Eart observation system.
    Micro SAR satellites are expected to be able to build all-weather observation systems that are not affected by the observation environment.

  • Vision-based Autonomous Rendezvous and Docking

    • Development of control algorithm for spacecraft rendezvous and docking
    • Development of spacecraft relative pose estimation algorithm based on vision sensor
    • Development of GNC system for autonomous rendezvous and docking
    • Verification of GNC system using Formation Flying Testbed

  • SAR Satellite Constellation Control Center

    • Functionality analysis of Synthetic Aperture Radar (SAR) satellite control center
    • Conceptual design of SAR satellite control center
    • Develop precise orbit determination module for SAR satellite constellation
  • Multiple Satellite System Orbit Determination

    • Satellite Laser Ranging(SLR) Based Satellite Orbit Determination
    • Inter-satellite Link(ISL) Based Satellite Orbit Determination
    • Real-time On-board Orbit Determination using Kalman Filter
    • Navigation System Hardware Simulator Development/Applications
  • Lunar Exploration


    Space Flight Dynamics Software Development for Korean Lunar Exploration 
    – Build FDS for the Korean Lunar exploration program
    – Develop of data simulation module for processing/generating DSN data & error corrections
    – Develop of DSN-based orbit determination module
    – Achieve 1km-level orbit determination precision
    – Develop event prediction module for predicting various celestial phenomena 

    Lunar Mission Design and Analysis using CubeSat and Smartphone-sat 
    – Preliminary Lunar CubeSat/phonesat mission design

    Development of GMAT components III 
    – General Mission Analysis Tool (GMAT)
    – Visualization of launch trajectory
    – Accurate celestial event location capability through SPICE kernel
    – High-fidelity low-thrust trajectory optimization capability based on Gauss-Legendre-Radau collocation method

    CANYVAL-C mission is aimed at scientific validation of photographing the sun’s corona.
    This mission is the application of Virtual Telescope technology that uses several discrete satellites as a space telescope.
    The mission requires development of inertial alignment hold technology, spacecraft formation flying GNC technology and inter-satellite link technology.
    CANYVAL-C is a subsequent mission of CANYVAL-X, technical experiment mission of virtual telescope, and expects further projects of solar science and X-ray objective science mission.

    The CANYVAL-C system consists of two CubeSats, ‘PUMBAA’ and ‘TIMON’. PUMBAA, the occulter, is a 2U CubeSat that covers the sun for corona imaging.

    TIMON, the detector, is an 1U CubeSat that takes a coronagraph with an optical camera.
    The CubeSats are planned to be launched in July, 2019.

  • Asteroid Deflection

    • Design interplanetary trajectory to target asteroid
    • Develop techniques to deflect a potentially hazardous asteroid
  • On-board Ephemeris Generator

    • Supporting Korea Lunar Pathfinder Mission
    • Develop algorithm of Ephemeris data compression.
    • Verify the algorithm through simulations.
    • Develop on-board ephemeris generation algorithm for Korean Lunar Exploration.
    • Develop software for compressed ephemeris data that will be used on Ground station.
    • Implement the algorithm to GMAT
  • Satellite Orbit Determination using Optical Observation

    • Develop of initial orbit determination software using elevation/azimuth angle
    • Develop of precise orbit determination software using batch least-square algorithm and optical observation model
    • Performance analysis of precise orbit determination using Optical Wide-field Patrol (OWL) observation data

    OWL-Net Mongol site