Single-Antenna GPS-Based Aircraft Attitude Determination

The principle and method of aircraft attitude determination with the information given by single-antenna GPS receiver are discussed in this paper. The attitude mentioned in the paper is also called as pseudo-attitude. It consists of flight path angle to the local horizontal plane and roll angle about the aircraft velocity vector axis.The research and development of the aircraft attitude determination with the information given by single-antenna GPS receiver past three phase: making the model of the system and realization by computer; the compilation and debug of the real-time software; the engineering realization of the system.There are three major sections in software developing: to achieve the velocity vector by analyzing the information given by the GPS receiver; to estimate acceleration vector using a Kalman filter model with the velocity vector information; the attitude synthesizing algorithm mode.Put the navigation information to the pedal screen and the administrator can find the attitude of the aircraft; it also can be saved as information used be automatic system.