Missile guidance system and missile

Details Missile guidance system and missile Missile guidance system and missile

F - Mech Eng,Light,Heat,Weapons

42

B

F42B 10/02 (2006.01) B64C 15/14 (2006.01) B64D 17/80 (2006.01) F41G 7/22 (2006.01) F42B 10/66 (2006.01) F42B 15/00 (2006.01)

Patent

CA 2092441

A staged missile having a booster stage, sustainer stage, fuel source, steering electronics, warhead and homing head is used for striking a target, such as a helicopter, from above. The missile is braked after a ballistic flight before a target zone and is redirected to a direction substantially perpendicular to the ground surface over the target zone such that the homing head of the missile hanging from the brake parachute is directed downwardly. Once the homing head has locked in on the target, the brake parachute is jettisoned and the missile is directed to the target by the sustainer thruster. Near the time of deployment of the brake parachute, a transverse thruster is activated at the centre of gravity of the missile such that a force is produced which is added vectorially to the earth's gravitational force to firstly accelerate the tilting of the missile to the vertical direction, and during the homing phase associated with the redirection, to secondly counteract roll, pitch and yaw movements of the missile and for stabilization.

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