Attitude determination algorithms for spinning satellites using single antenna GPS receiver and MEMS gyro

This paper proposes a new subsystem of attitude determination for spin-stabilized satellites, which makes use of information from single antenna GPS receiver and a MEMS gyro. The incremental carrier phase state equation and measure model for spinning satelliteʼs attitude motion are derived. The subsystem senses attitude by demodulation of periodic oscillations of the GPS carrier phase caused by satelliteʼs spinning motion with the aid of a MEMS gyro. Numerical examples for spin-stabilized satellites with and without nutation motion are carried out to validate the algorithm. Five key parameters which affect the attitude sensing accuracy are analyzed at last.