The Attitude Determination and Control Subsystem (ADCS) maintains spacecraft stabilisation and orients it to a desired direction when required. The spacecraft determines its attitude, using sensors, calculates the correction required to achieve the desired orientation and executes the maneuver using actuators.

Development of ADCS sensors, actuators, and Flight Control Software (FCS) has been performed by ATSB^®. Laboratory functional test of the ADCS components integrated with FCS is done with a three Degrees of Freedom (3-DOF) test bed, called an Air Bearing Trolley (ABT). It is used for a Hardware in the Loop (HIL) test to demonstrate satellite ADCS responses.