Electrical Power System (EPS)

This sub-system deals with the generation, storage and distribution of electrical power to all the components in the satellite. It consists of a power generation unit (solar panels), a power storage unit (battery and charger) and a power distribution unit.

SPEED (Space-based Proton Electron Energy Detector)

This sub-system will carry out the scientific experiment on-board the satellite. It is measuring the instrument that counts the number of charged particles incident on it and measures their energies. The detector consists of the following modules: Physical Instrument: A transducer system which absorbs the energy of the incident particle and converts it to an electrical signal. Detector Electronics: Analog pulse processing electronics and a Digital processing unit to process the signal.

Attitude Control System (ACS)

This sub-system deals with determining and controlling the satellite’s orientation and rotation rate. It compensates for disturbance torques that cause the satellite to change its orientation. It consists of sensors, an attitude determination algorithm, a control algorithm and actuators for exerting control torques on the satellite body.

Single Board Computer (SBC)

The on-board software is implemented on two micro-controllers - BAE and CDMS. The software running on BAE is responsible for acquisition of the attitude information of the satellite. The software written in the CDMS micro-controller is responsible for decoding the tele-commands received from the ground station and also generates the required telemetry.

Communication System (COM)

This sub-system performs the function of reception and transmission of data and commands between the satellite and ground station. The communication system consists of two segments, On-board segment and the Ground segment. On-board Segment (COM-OS): The On-board Segment receives the tele-commands from the Ground Segment and transmits payload data to the Ground Segment of the satellite. Ground Segment (COM-GS): The Ground Segment caters to tele-command uplink and payload data reception.

Mechanical Structure (STR)

This sub-system consists of the satellite’s physical load-bearing structure, the fasteners that hold components in place, launch vehicle interface and the extended structures such as the antenna

Thermal Control System (TCS)

This sub-system determines the temperature at various parts of the satellite and maintains the temperature within ranges that are safe for the components to operate. It consists of temperature sensors at various parts of the satellite, and active and passive elements for controlling the temperature.

Mission Control System (MCS)

The Mission Control System sends telecommands to the satellite and receives telemetry data. They deal with the software aspect post launch

Ground Station (GS)

The ground station receives the data from the satellite and sends back necessary commands to the satellite. They are responsible for maintaining the IITMSAT Ground Station, taking care of various components in the uplink and downlink chain such as Low Noise Amplifiers (LNA), Power Amplifier (PA) and Antennas.

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