Integrated attitude and orbit model of an earth orbiting satellite using three-axis control

Objective of this study is creating an integrated satellite orbital dynamics model with attitude control models. This research gives an insight to the mathematical modeling and simulation of satellite attitude and orbit dynamics. In the model pointing accuracy knowledge is assumed 100μrad and the target of control system is 500μrad as pointing accuracy. Based on these parameters control actuators and sensors are selected. Through an explanation and modeling of attitude and orbit dynamics models, a control strategy for the attitude is designed. An attitude observer based on linear Kalman filter (LKF) is developed and benchmarked and implemented in a simulator and this observer uses a linear, constant coefficient state matrix to provide a feedback control. The results show using reaction wheels and LKF in the integrated model aid to achieve the required pointing accuracy.