Abstract: A twice rapid transfer alignment approach to missile GPS/SINS navigation systems on moving base in flight is put forward. In the first time transfer alignment it uses velocity matching plus attitude change matching and mainly performs azimuth alignment and primarily performs horizon alignment. In the second time transfer alignment, based on the first time transfer alignment, it uses velocity matching and performs horizon alignment once more. The first time transfer alignment can be finished in several seconds and therefore alignment time in captive flight is shortened. The second time transfer alignment gets rid of flexible influence and therefore enhances horizon alignment. Simulation shows it is efficient.

Key words: aerocraft control, navigation technology, transfer alignment, GPS/SINS, integrated navigation, moving base