For a satellite to operate outer space, attitude control determination system (ACDS) is one of the important subsystems onboard beside the other subsystems. It divided into
3 major parts which are attitude actuators, attitude sensors and attitude controller. This is important to maintain the attitude pointing accuracy for a satellite. In addition, when a satellite having a gravity gradient effect at Low Earth Orbit (LEO) it also become a problem for it to maintain it attitude accuracy. Since it is an asymmetric body satellite, the tendency to have a large quantity of gravity gradient effect will be high.
Moreover, two actuators will be use. First is the passive attitude control which is gradient boom that will place on the asymmetric body satellite then magnetic torquer act as an active attitude control that will be placed in each axis of the asymmetric axis. Furthermore, a mathematical modelling of gravity gradient stabilized satellite will be developed based on Euler moment equation. This is to understand the satellite dynamic behaviour in space when the satellite is affected by gravity gradient near the earth. Then, it will be apply with the active control which consists of actuator and controller to the satellite to understand the behaviour and also the performance.
Attitude perfromance of gravity-gradient stabilized satellite with and without active control_Muhammad Norhafiz Arjunaiti_A2_2014_NI