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Attitude determination of a near Earth small satellite by using magnetometer data only 
Plasma wave source location 
Magion 5 Atitude Determination
Query Interface for Magion 5  Magnetic field data The attitude solution for a spinstabilized satellite is evaluated from onboard 3axis magnetometer readings. The method is based on a theoretical approach of the satellite motion as well as on the behaviour of the geomagnetic field along the orbital trace. The initial conditions are estimated using a specific parameterization of the attitude at an initial epoch. A local reference system is defined with one axis parallel to the direction of the magnetic field vector. The attitude matrix could be then straightly derived in terms of the Euler angles up to an unknown initial phase. For a convenient definition of the local frame, the initial phase is geometrical described as the angle obtained by coning the main axis of the satellite along the magnetic field line until it crosses a rectangular plane to the ecliptic one. The evaluation of the unknown initial Euler angle originates from the properties of the Earth's magnetic field, when the satellite is crossing over regions with fast variations of the direction of the magnetic field line. The kinematic solutions of Euler equations could be established from gyro data measurements or from a theoretical approach of the satellite motion in respect with it's mass center. A batch numerical filter has been developed to search for the bestfit state parameters and to solve for the solutions of the dynamic and kinematic equations of motion. The environmental effects due to the solar pressure, gravity and magnetic disturbance torques as well as the internal passive stabilization torque have been related to the torquefree attitude solutions of a nutating spacecraft. Numerical integration methods based on ordinary differential equations techniques have been tested for the truncation errors and also for their stability in the attitude minimization algorithm. The accuracy of the method depends on the correct estimates of external and internal torques acting on the satellite, on the exactness of the geomagnetic field model and on the accuracy of the onboard measurements. The method was applied for a spinstabilized satellite. Magion5 as a small subsatellite with 65 degrees inclination orbit and a perigee of 20000 Km, was intended for carrying out simultaneously measurements with the Auroral Probe main satellite, in the framework of Interball project. Contact: Dr. Horia Comisel 
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