Concurrent Spacecraft Attitude and Orbit Estimation with Attitude Control Based on Magnetometer, Gyroscope, and GPS Measurements through Extended Kalman Filter

Abstract

The main objective of this research is to provide attitude estimation, orbit estimation, and attitude control algorithms suitable for application to the next Egyptian scientific satellite. Concurrent spacecraft orbit and attitude estimates must be suitable for usage by the attitude control algorithm. The developed estimation algorithms are able to deal with sever tumbling conditions characterized by large initial attitude, angular velocity and position estimation errors. The estimation algorithms could provide attitude estimates within 0.5 o (3-) and 60 m (3-) for the position estimation errors. The attitude control algorithm developed is able to bring the spacecraft from its initial tumbling conditions to nadir pointing within an error of only 0.5 o (3-).

A Review and a Quantitative Comparison among the Exact Solution and the Numerical Integration Methods with Fixed Time Step Commonly Used to Solve the Two-Body Problem

“…The main role of the research at hand is to answer simply the problem of finding a suitable numerical integration algorithm to be used for orbit propagation and estimation such as that found in [8]. This is done through a review of the commonly used numerical integration algorithms with fixed time step of the two-body problem.…”