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The project aims to develop a 100kg-grade next-generation small satellite to conduct scientific missions, verify core space technologies and develop new space technologies. It will be the first in the small satellite series developed under the objectives of miniaturization, modularization and standardization. Together with the talent development program aimed at training professionals to implement the Medium-term Space Development Plan, the project plays a central role in national space development.

- To develop the next-generation small satellite series and new technologies by creating a standardized platform for
   small satellites based on miniaturization, modularization and standardization.
- To conduct in-orbit verification of core space technologies that will enhance domestic space capabilities and enhance
   technological competitiveness for import substitution.
- To develop space technologies and enhance independent space development capabilities through geo-environmental
   monitoring and astronomical observation
- Hands-on and customized development of researchers and scientists through field experience in space technologies
   and science
Objective Plan
MIniaturization • Maximization of payload capacity through miniaturization of the satellite structure
- Payload percentage in satellite weight : 40%~50%
- Satellite weight : Approximately 100kg
• Development of eco-friendly propulsion system which can be deployed selectively according to mission requirements
Standardization • Standardization of electrical and mechanical connection conditions to support various missions
• Set development standards for performance requirements such as lifespan, attitude pointing precision etc that vary between missions and develop as optional specifications
Modularization Design modular payloads for the stable operation of the main body
Low Power Designl Implement low power design by considering the power requirements of the respective technology verification payloads
Key Specifications
Item Development Parameters Note
Operation Orbit (km) 650 ~ 800 Sun-synchronous Orbit (SSO)
Weight (kg) Approx. 100
Volume (mm) 578 × 598 × 923 Not including adaptor height
Mission Length (Years) 2
Attitude Control Method 3-axis stabilization
Power (W) 250 As of mission completion
Bus Votage (V) +24 ~ +32 Primary source+28V supply
Communication Bus CAN Bus SOH
Bus-Payload Communication Serializer/Deserializer LVDS < 100 Mbps
Satellite Control Frequency S-band Satellite status information
Observation Data Frequency X-band Payload
Type Payload
Scientific Mission Instrument for the Study of Space Storms(ISSS)
Near-Infrared Spectrometer for Star Formation History(NISS)
Core Space Technology
Next-generation High Speed Data Storage(SDR-10)
5 mNm-grade Reaction Wheel Assembly(RWA)
3 Dimensional Mass Memory적(3DMM)
S-band TCTM Digital Transponder(SDT)
Standardized On-board Satellite Computer Module (OBC)
Space-grade Fiber Optic Gyro (FOG)
FM-grade high speed/high precision Star Tracker (STR)