Sun sensor detects the direction of the solar light.
Magnetorquer is the actuator to control the attitude satellites by magnetic force generated from coil.
Momentum wheel is the actuator on satellites, which stabilize the attirude of satellites.
Reaction wheel is the actuator to control the attitude of satellites, which changes its number of revolutions to change attitude.
Spin stabilization is the method to control attitude of satellite by spining.
Bias momentum is one of the type of attitude control methods. bias momentum uses momentum wheel and effect of gyro stabilization.
Electrical Power Subsystem (EPS) manages the power of satellites. Satellites have solar panels to generate electricity, and battery to store the energy. EPS should design the circuit to control and distribute power.
Depth of discharge (DOD) is the ratio of power discharged to the capacity of the battery. Battery life depends on DOD, thus it is required to sizing battery considering mission lifetime.
Deployment switch detects the separation of satellites from rockets. Satellites are powered by this deployment switch when cold launch.
RBF Pin is the abbreviation of Remove Before Flight Pin, which turns on the power of the satellites by pulling out.