MISSILE GUIDANCE SYSTEM

PROBLEM TO BE SOLVED: To obtain an information necessary for the guidance of a missile from a GPS signal. SOLUTION: GPS receiving antennas 11A-11D are arranged in an airframe head unit A, an airframe rear unit B and horizontal stabilizer ends C, D to receive the GPS signal by reception processing units 12A-12D. A position is obtained by effecting position measuring and operating process in a position operating unit 13 with respect to the receiving signal of the reception processing unit 12A and, further, a speed is operated from a change per unit time of a position in a speed operating unit 14. At the same time, the GPS signals from the same GPS satellite is taken out in respective reception processing units 12A-12D to obtain phase differences between A-B, C-D and B-D respectively through phase detecting units 161-163 while the phase differences are smoothed by Kalman filters 171-173 and, thereafter, the phase differences are converted into airframe coordinates at a receiving position through an airframe coordinate converting unit 18 to obtain the angle of attitude of the airframe. The change is divided by a time whereby an angular velocity is obtained.