System and method for guiding a cannon shell in flight

1. A method for controlling artillery projectile having a guiding device, comprising:

providing control commands to change an angle of attack of a pair of lift guiding fins by a first driving mechanism;

providing control commands to change an angle of attack of a pair of roll stabilizing fins by a second driving mechanism;

and

controlling the roll angle to provide a lift force to cause said guiding device to guide the projectile along a trajectory, wherein the projectile is configured to spin about its longitudinal axis during flight.

2. The method of claim 1 , further comprising:

receiving indication of a momentary location of the projectile with respect to a respective point on a desired trajectory;

calculating one or more periods of time, a future point which is on a line tangent to the desired trajectory; and

providing the control signals to direct the projectile to the future point.

3. The method of claim 1 , further comprising:

enabling activation of a detonation chain by a detonator coupled to a detonation control unit.

4. The method of claim 3 , further comprising:

disabling the detonation chain based on a first safety measure and a second safety measure, wherein the first safety measure is responsive to speed of rotation of the projectile and the second safety measure is responsive to revolutions of the projectile.

5. The method of claim 3 , further comprising:

activating, at a time preceding the expected time of hitting a target by the projectile, a detonator coupled to a detonation control unit, said detonation control unit being adapted to operate independently of the detonation chain.

6. The method of claim 5 , further comprising:

transferring to the detonation control unit, at a time preceding the expected time of hitting a target by said projectile, data for controlling the detonation chain.

7. The method of claim 1 , further comprising rotating the lift guiding fins in opposition to the roll stabilizing fins.

8. The method of claim 1 , wherein the projectile has a front portion and a rear portion coupled via a bearing arrangement that allows rotation of the front portion with respect to the rear portion.

9. The method of claim 2 , wherein the indication of the momentary location of the projectile is received from a global positioning system (GPS).