Abstract
Spacecraft may exhibit changes of its moments and products of inertia in-orbit due to several reasons. In this case, knowledge of spacecraft moments and products of inertia represents an utmost importance for the spacecraft attitude and orbit control system (AOCS). The contribution of the current research article is to estimate in-orbit spacecraft moments and products of inertia based on measurements of magnetometer, gyro, star sensor, and GPS through extended Kalman filter without test slews while being able to estimate attitude and orbital states at the same time. The proposed solution is also able to converge despite large initial estimation errors.
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