Attitude Estimation of Nano-satellite according to Navigation Sensors using of Combination Method

The purpose of this paper is attitude estimation of nano-satellite which requires navigation sensors data for reducing the cost function and movement effect of nano-satellite. The data of navigation sensors and methods are used to achieve the required attitude estimation. The navigation attitude sensors are gyroscope, magnetometer and sun sensor. Furthermore, the extended Kalman filter is used to combine the measured data of gyroscope, magnetometer and sun sensor. This paper presents the methods for accurate estimation of the attitude of nano-satellite missions according to the developed quaternion estimation and nonlinear analysis along with the extended Kalman filter. This work demonstrates the application of nano-satellite with navigation sensors. The methods are used, to achieve high accurate and fast starting attitude estimation. The methods are simulated by MATLAB software. The obtained results were analyzed and compared with other sets of data.