Attitude Determination using Kalman Filtering for Low Earth Orbit Microsatellites pp. 161-196
Authors: (Si Mohammed, Mohammed Arezki, Space Mechanic Division, Centre of Space Techniques, Arzew, Algeria)
Abstract: As part of the attitude determination and control system on board microsatellites, the kalman filter is implemented to generate an estimate attitude upon sensor observation. This chapter presents an overview and analysis of some attitude estimators based on Kalman filtering for application on low Earth orbit microsatellites. Various steps of the design and in orbit implementation of the estimators are described. These estimators are used during nominal attitude of the microsatellite. One type of attitude estimator is based on small Euler angles. For this mode two estimator versions have been used, the full estimator and its reduced version. This estimator is useful for on board computation where energy resources are very limited. Another type of attitude estimator is based on the quaternion parameter. The advantage of the quaternion parameter is the none singularity. For this mode two estimator versions have been used, the six state and the seven state estimators. Numerical analysis and in orbit test results clearly indicate that the reduced version is better than the full version for specifically attitude determination and control system configuration of a microsatellite. Also, the results prove that the six state estimator is better than the seven state estimator in terms of computational demand.