Abstract

The present invention is a missile (500) intended particularly for a defensive purpose, and a control method related to the missile. In its mass centre, or in the immediate vicinity thereof, the missile comprises two gyro­scopes or a gimbal integrated in an explosive charge. The head (501) of the missile is provided with various sensors, ranging from a cam­era to a microphone, an IR camera and an NFC antenna. GPS positioning can also be utilized. In the invention, the position and direction of a target are continuously measured by means of the sensors, and by using the gyroscoρe∕gyroscoρes as a reference, it is possible to control i.e turn the on/off state and direction of the rocket en­gine (507) of the missile, utilizing the precession phenomenon. Sensor data analysis is continuously repeated at desired short intervals until the missile (500) is brought to intercept the target, whereby the target is destroyed.

IPC Classes  ?

• F41G 7/22 - Homing guidance systems
• F41G 7/34 - Direction control systems for self-propelled missiles based on predetermined target position data
• F41G 7/36 - Direction control systems for self-propelled missiles based on predetermined target position data using inertial references
• F42B 10/60 - Steering arrangements
• F42B 15/01 - Arrangements thereon for guidance or control
• F42B 19/06 - Directional control
• F41H 11/02 - Anti-aircraft or anti-guided missile defence installations or systems
• F41G 7/00 - Direction control systems for self-propelled missiles
• F42B 10/26 - Stabilising arrangements using spin