SPACECRAFT PLATFORM


1) AOCS (Attitude and Orbit Control Subsystem)
The attitude and orbit control subsystem (AOCS) provides attitude information and maintains the required spacecraft attitude during all phases of the mission throughout its operational lifetime. The AOCS determines the attitude of the spacecraft while in orbit, based on the information from star tracker and Sun Sensor.


2) CDHS (Command and data handling system)
Command and data handling system (CDHS) is an on-board computer that controls the operation of the satellite during normal conditions. mission and housekeeping data from all subsystems is stored and prepared for downlink via Communication Subsystem (COMS). CDHS has reliable communication between On-board computer (OBC) and payload with CAN BUS (controller Area Network) protocol. CDHS also support time sync between OBC and payloads.


3) EPS (Electrical Power System)
The Electrical Power System (EPS) provides power regulation for satellite sub-systems using battery and solar array interfaces to power the satellite while in orbit. The EPS consists of a solar panel that produces electricity from solar energy, a battery that stores the generated power, and a power board that serves to charge the battery and supply power to the system at various voltage levels. EPS has high efficiency solar cells and high capacity batteries.


4) COMS (Communication Subsystem)
The Communication Subsystem (COMS) is composed of the telemetry and command sub-systems, which send and receive data, respectively. Analog and digital data collected by the sensors and payload of the satellite must be relayed to the ground station via the telemetry sub-system. COMS provides reliable communication links between SNIPE spacecraft and ground station as follows: Command reception (UHF, S-band), Telemetry transmission (UHF), and Payload mission data transmission (S-band)


5) PROPULSION
The propulsion subsystem provides the means for attitude and orbit control (AOC) and orbital maneuvering. Korea Astronomy and Space Science Institute satellite-1 (KASISat-1) utilizes cold gas system to achieve highly reliable propulsion while serving as a space weather station.


Figure 3. The design of the Langmuir Probe (LP) [Left: cross section, Center: mechanical design, Right: Position of the LP]













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