Inertial guidance-based seeker and the corresponding seeker guidance system

Abstract

The present invention is a missile (202, 400, 500) developed specifically for defensive purposes, and a guidance method related to the missile. The missile comprises two gyroscopes (414a, 414b) or a gimbal at or near its center of mass, which are integrated into the explosive charge (306). The missile tip (501) has various sensors, from a camera (401) to a microphone (402), an IR camera (403) and an NFC antenna (405). In addition, GPS positioning (407) can be utilized. In the invention, the position and direction of the target (201) are continuously measured by sensors, and using the gyroscope(s) (414a, 414b) as a reference, the position of the missile's rocket motor (507) and the direction of the thrust can be controlled, i.e. turned, utilizing the precession phenomenon. The sensor data analysis is continuously repeated at desired short time intervals until the missile (202, 400, 500) is caused to collide with the target (201), whereby the target (201) is destroyed.