The Command and Data Handling Subsystem controls and handles data between different subsystems of satellites.
The C&DH system consists of an Onboard Computer (OBC), which controls the operation of the Satellite.
The OBC has software installed that manages the programs written to handle various tasks.
The primary components of the OBC are micro-controllers with RAM, ROM, and other I/O peripherals.
Electronic Power System
The Electronic Power System (EPS) is designed to generate, store and distribute power to the satellite.
Power Generation: The power is generated through solar panels Placed onto the outer walls of the satellite.
Power storage: The power from the solar panels is regulated and converted to an appropriate charging voltage for the batteries.
The EPS supplies a constant voltage bus to the satellites subsystem. The bus is voltage regulated, with current limiting sensors to protect the batteries from draining the charge by the subsystems.
Design a Structure with deployment mechanisms which occupies 30x30x30 cm3 volume in stowed configuration and also mass less then 10kg.
Design a structure which can withstand the launch loads and maintain its structural integrity.
Design and develop Solar panel deployment, Antenna deployment, Drag sail mechanism for de-orbiting and Separation mechanism.
To have minimum centre of gravity deviation from geometric centre to provide better control.
To make sure the temperature of electronic packages/PCB's are maintained within the range 0 to 40◦C.
Communication system is composed of two parts, the space segment which contains onboard communication system on the satellite and the ground segment (ground station).The purpose of the system is to operate the satellite from the ground and transmit collected data from the satellite back to the ground station.
The onboard communication system is responsible for transmitting the telemetry data (health parameters of satellite) and payload data to ground station, Receive the commands sent from ground station.
The ground station is responsible for receiving the telemetry and payload data from satellite and process the same and command the satellite.
Attitude Determination & Control System
The purpose of the Attitude Determination and Control (ADCS) system is to determine the attitude (orientation) of the satellite and correct any deviation from the expected attitude.
As the name suggest, the subsystem is divided into two part, namely the attitude determination and attitude control. The satellite employs sensors to sense the attitude and actuators to correct/contol the same.
ADCS subsystem ensures that the satellite maintains its desired orientation in space. Besides sun sensor, gyro and magnetometer, the actuation system of STUDSAT-2 comprises of three orthogonally placed magnetic torquer coils and a tetrahedral reaction wheel.